Aluminum Design Manual

Copyright © 2005, The Aluminum Association, Inc. All rights reservedNo part of this publication may be reproduced, stored in a retrieval system, or transmitted, in any form, or by any means,

electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission ofThe Aluminum Association, Inc.

Copyright © 2005, The Aluminum Association, Inc. All rights reservedNo part of this publication may be reproduced, stored in a retrieval system, or transmitted, in any form, or by any means,

electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission ofThe Aluminum Association, Inc.

TABLE OFCONTENTS

Aluminum Design Manual

Table of Contents

PART TITLE

IA Specification for Aluminum Structures – Allowable Stress Design

IB Specification for Aluminum Structures – Building Load and Resistance Factor Design

IIA Commentary on Specification for Aluminum Structures – Allowable Stress Design

IIB Commentary on Specification for Aluminum Structures – Building Load and Resistance Factor Design

III Design Guide

IV Materials

V Material Properties

VI Section Properties

VII Design Aids

VIII Illustrative Examples of Design

IX Guidelines for Aluminum Sheet Metal Work in Building Construction

Appendix 1 Metric Guide for Aluminum Structural Design

Index

FOREWORD

FOREWORD

The Aluminum Design Manual includes aluminum structural design specifications and accompanying commentary, a supplemental design guide, material properties, section properties, design aid tables and graphs, illustrative design examples and guidelines for aluminum sheet metal work in building construction.

This edition of the Aluminum Design Manual is the product of the efforts of the Aluminum Association Engineering and Design Task Force, whose members are listed below.

The Aluminum Association Engineering and Design Task Force

Steve Sunday, Alcoa Inc., chairFrank Armao, Lincoln Electric Co.Randy Killian, Conservatek Industries, Inc.Randy Kissell, The TGB PartnershipGreg McKenna, Kawneer Company, Inc.Craig C. Menzemer, University of AkronGeorge Olive, Larson Engineering of MissouriGerald Orrison, TemcorTeoman Peköz, Cornell UniversityFrank Shoup, Alcoa Inc.Mike Skillingberg, The Aluminum Association, Inc.


PART I-A

Specification for Aluminum Structures–

Allowable Stress Design

The Aluminum Association, Inc.900 19th Street, NW, Washington, DC 20006

Eighth Edition, January 2005

January 2005 I-A-3

FOREWORD

The first edition of the Specification for Aluminum Structures was published in November, 1967, followed by subsequent edi-tions in 1971, 1976, 1982, 1986, 1994, and 2000. This eighth edition of the allowable stress design Specification, developed as a consensus document, includes new or revised provisions concerning

• shear yield strengths• welded strengths• adding 6063-T52, 6351-T6, and 7005-T53 • materials for screws used to connect aluminum parts• factors on welded tensile ultimate strength and compressive yield strength• welded connections (groove, fillet, plug and slot, and stud welds)• screw pull-over• revision of Section 1.2, Materials• revision of Section 5, Mechanical Connections• revision of Section 6, Fabrication and Erection• a new Section 8, Castings• weighted average strengths• design stresses for wind loads• fatigue strength for welds with permanent backing• net effective areas for channels, I beams, zees, angles, and tees• single angles in flexure• tapered thickness element strength• web crippling of extrusions• compressive strength of complex cross sections• strength of elements in bending in their own plane• unbraced length in bending

These improvements and additions are the result of studies sponsored by the Aluminum Association and others. The Aluminum Association gratefully acknowledges the efforts of the Engineering and Design Task Force in drafting this Specification and the Engineering Advisory Committee in reviewing it.



The Aluminum Association Engineering Advisory Committee

Includes the members of the Engineering and Design Task force and the following persons:

Robert E. Abendroth, Iowa State UniversityFrancisco Castano, Geometrica, Inc.Terence Cavanagh, Terrapin Testing, Inc.Karen C. Chou, Minnesota State University, MankatoCynthia Ebert, Larson Engineering of Missouri

I-A-4 January 2005

Andrew J. Hinkle, S & K TechnologiesDimitris Kosteas, Technical University of MunichLeRoy Lutz, Computerized Structural DesignBrian Malloy, Alcoa Engineered ProductsRay Minor, Hapco American FlagCarl Wagus, American Architectural Manufacturers AssociationRobert W. Walton, Texas Wall Systems

Guidelines for the Preparation of Technical Inquiries on the Specification for Aluminum Structures

Technical inquiries to obtain an interpretation or request a revision to the Specification for Aluminum Structures should be directed to:

VP, TechnologyThe Aluminum Association900 19th Street, NWWashington, DC 20006Fax: 202-862-5164 email: [email protected]

Comments on other parts of the Aluminum Design Manual are also welcome.

Inquiries should be typewritten and include the inquirer’s name, affiliation, and address. Each inquiry should address a single section of the Specification unless the inquiry involves two or more interrelated sections. The section and edition of the Speci-fication should be identified.

Requests for interpretations should be phrased, where possible, to permit a “yes” or “no” answer and include the necessary background information, including sketches where appropriate.

Requests for revisions should include proposed wording for the revision and technical justification.

Inquiries are considered at the first meeting of the Engineering and Design Task Force following receipt of the inquiry.

January 2005 I-A-5

IASpecification for Aluminum Structures—Allowable Stress Design

TABLE OF CONTENTS

Section 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .91.1 Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.2 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.3 Safety Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1.3.1 Building Type Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.3.2 Bridge Type Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.3.3 Other Type Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Section 2. Design Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.1 Section Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.2 Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.3 Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Section 3. General Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.1 Material Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.2 Nomenclature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.3 Tables Relating to Mechanical Properties and Buckling Constants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 143.4 Allowable Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3.4.1 Tension, Axial . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.2 Tension in Extreme Fibers of Beams—Flat Elements In Uniform Tension . . . . . . . . . . . . . . . . . . . . . . . . 263.4.3 Tension in Extreme Fibers of Beams—Round or Oval Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.4 Tension in Extreme Fibers of Beams—Flat Elements In Bending in Their Own Plane . . . . . . . . . . . . . . . 263.4.5 Bearing on Rivets and Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.6 Bearing on Flat Surfaces and Pins and on Bolts in Slotted Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.7 Compression in Columns, Axial, Gross Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3.4.7.1 Sections Not Subject to Torsional or Torsional-Flexural Buckling . . . . . . . . . . . . . . . . . . . . . . . . 263.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or Torsional-Flexural Buckling . . . . 263.4.7.3 Nonsymmetric Sections Subject to Torsional or Torsional-Flexural Buckling . . . . . . . . . . . . . . . 27

3.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of Symmetry— Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 273.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is not an Axis of

Symmetry—Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 273.4.9 Uniform Compression in Elements of Columns—Flat Elements Supported on Both Edges . . . . . . . . . . . 28

3.4.9.1 Uniform Compression in Elements of Columns—Flat Elements Supported on One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

3.4.9.2 Uniform Compression in Elements of Columns—Flat Elements Supported on Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

3.4.10 Uniform Compression in Elements of Columns—Curved Elements Supported on Both Edges . . . . . . . . . 323.4.11 Compression in Beams, Extreme Fiber, Gross Section—Single Web Shapes . . . . . . . . . . . . . . . . . . . . . . 323.4.12 Compression in Beams, Extreme Fiber, Gross Section—Round or Oval Tubes . . . . . . . . . . . . . . . . . . . . . 323.4.13 Compression in Beams, Extreme Fiber, Gross Section—Solid Rectangular and Round Sections . . . . . . . 323.4.14 Compression in Beams, Extreme Fiber, Gross Section—Tubular Shapes . . . . . . . . . . . . . . . . . . . . . . . . . . 333.4.15 Uniform Compression in Elements of Beams—Flat Elements Supported on One Edge . . . . . . . . . . . . . . . 333.4.16 Uniform Compression in Elements of Beams—Flat Elements Supported on Both Edges . . . . . . . . . . . . . 34

3.4.16.1 Uniform Compression in Elements of Beams—Curved Elements Supported on Both Edges . . 343.4.16.2 Uniform Compression in Elements of Beams—Flat Elements Supported on

One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .343.4.16.3 Uniform Compression in Elements of Beams—Flat Elements Supported on

Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 343.4.17 Compression in Elements of Beams (Element in Bending in Own Plane)—Flat Elements Supported on

Tension Edge, Compression Edge Free . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

I-A-6 January 2005

3.4.18 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

3.4.19 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges and With a Longitudinal Stiffener . . . . . . . . . . . . . . . . . . . . . . . 35

3.4.20 Shear in Elements—Unstiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . 363.4.21 Shear in Elements—Stiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . 36

Section 4. Special Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .374.1 Combined Axial Load and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

4.1.1 Combined Compression and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 374.1.2 Combined Tension and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

4.2 Torsion and Shear in Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 374.3 Torsion and Bending in Open Shapes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 374.4 Combined Shear, Compression, and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 374.5 Longitudinal Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 384.6 Transverse Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

4.6.1 Stiffeners for Web Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 384.6.2 Bearing Stiffeners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

4.7 Effects of Local Buckling on Member Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394.7.1 Local Buckling Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394.7.2 Weighted Average Axial Compressive Stress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394.7.3 Weighted Average Bending Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394.7.4 Effect of Local Buckling on Column Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 404.7.5 Effect of Local Buckling on Beam Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 404.7.6 Effective Width for Calculation of Bending Deflection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 404.7.7 Web Crippling of Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.7.8 Combined Web Crippling and Bending for Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

4.8 Fatigue . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.8.1 Constant Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.8.2 Variable Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

4.9 Compression in Single Web Beams Including Single Web Beams With Tubular Portions . . . . . . . . . . . . . . . . . . . 474.9.1 Doubly Symmetric Sections and Sections Symmetric About the Bending Axis . . . . . . . . . . . . . . . . . . . . . 474.9.2 Singly Symmetric Sections Unsymmetric about the Bending Axis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 474.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis,

Doubly Symmetric Sections and Sections Without an Axis of Symmetry . . . . . . . . . . . . . . . . . . . . . . . . . . 474.9.4 Lateral Buckling Coefficients . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

4.9.4.1 Doubly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 484.9.4.2 Singly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 484.9.4.3 Special Cases—Doubly or Singly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 484.9.4.4 Cantilever Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

4.10 Compression in Elastically Supported Flanges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 494.11 Single Angles in Flexure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

4.11.1 Bending About Geometric Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 504.11.2 Bending About Principal Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

4.12 Tapered Thickness Elements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 514.13 Compressive Strength of Beam Elements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

4.13.1 Compressive Strength of Beam Elements—Flat Elements in Uniform Compression . . . . . . . . . . . . . . . . . 514.13.2 Compressive Strength of Beam Elements—Flat Elements in Bending In Their Own Plane . . . . . . . . . . . . 51

Section 5. Mechanical Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .525.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

5.1.1 Minimum Edge Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 525.1.2 Maximum Spacing of Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 525.1.3 Block Shear Rupture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 525.1.4 Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 525.1.5 Effective Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 525.1.6 Long Grips . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

January 2005 I-A-7

5.1.7 Strength and Arrangement of Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.1.8 Countersunk Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

5.2 Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.1 Bolt Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.2 Holes and Slots for Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.3 Bolt Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.4 Bolt Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.5 Bolt Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 535.2.6 Minimum Spacing of Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.7 Lockbolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8 Slip-Critical Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

5.2.8.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.2 Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.3 Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.4 Design for Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.5 Design for Slip Resistance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.6 Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 545.2.8.7 Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

5.3 Riveted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 555.3.1 Rivet Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 555.3.2 Holes for Cold-Driven Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 555.3.3 Rivet Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 555.3.4 Rivet Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 555.3.5 Rivet Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 565.3.6 Minimum Spacing of Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 565.3.7 Blind Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 565.3.8 Hollow-End (Semi-tubular) Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

5.4 Tapping Screw Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 565.4.1 Screw Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 575.4.2 Screw Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

5.4.2.1 Pull-Out . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 575.4.2.2 Pull-Over . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

5.4.3 Screw Shear and Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 575.4.4 Minimum Spacing of Screws . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

5.5 Building Sheathing Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.5.1 Endlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.5.2 Sidelaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.5.3 Fasteners in Laps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.5.4 Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

Section 6. Fabrication and Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .596.1 Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

6.1.1 Punch and Scribe Marks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.1.2 Temperature Correction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

6.2 Cutting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.2.1 Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.2.2 Edge Quality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.2.3 Re-entrant Corners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.2.4 Oxygen Cutting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

6.3 Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 596.4 Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

6.4.1 Fabrication Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.4.2 Hole Alignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

6.5 Riveting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.5.1 Driven Head . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

6.5.1.1 Flat Heads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.5.1.2 Cone-Point Heads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

I-A-8 January 2005

6.5.2 Hole Filling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.5.3 Defective Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

6.6 Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.6.1 Where Painting Is Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.6.2 Surface Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

6.7 Contact with Dissimilar Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.7.1 Steel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.7.2 Wood, Fiberboard, or Other Porous Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.7.3 Concrete or Masonry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606.7.4 Runoff From Heavy Metals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

6.8 Mechanical Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 616.9 Fabrication Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 616.10 Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 616.11 Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

6.11.1 Erection Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 616.11.2 Bolt Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

Section 7. Welded Construction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .627.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.2 Welded Members . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

7.2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.2.2 Members with Part of the Cross Section Weld-Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.2.3 Columns or Beams with Transverse Welds Away from Supports and Cantilevers with

Transverse Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.3 Welded Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

7.3.1 Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.3.1.1 Complete Penetration and Partial Penetration Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . 627.3.1.2 Effective Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 647.3.1.3 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

7.3.2 Fillet Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 647.3.2.1 Effective Throat and Effective Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 647.3.2.2 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

7.3.3 Plug and Slot Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 657.3.3.1 Effective Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 657.3.3.2 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

7.3.4 Stud Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 657.4 Post-Weld Heat Treating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

Section 8. Castings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .678.1 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 678.2 Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 678.3 Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 688.4 Welding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

Section 9. Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .709.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 709.2 Test Loading and Behavior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 709.3 Number of Tests and the Evaluation of Test Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

9.3.1 Tests for Determining Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 709.3.2 Tests for Determining Structural Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

9.4 Testing Roofing and Siding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 719.4.1 Test Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 719.4.2 Different Thicknesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 719.4.3 Allowable Loads from Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 719.4.4 Deflections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

January 2005 I-A-9

Section 1. General

1.1 Scope

This Specification shall apply to the design of aluminum alloy load-carrying members.

1.2 Materials

This Specification applies to the aluminum alloys listed in Tables 3.3-1, 5.2.3-1, and 5.3.4-1 and produced to the following ASTM specifications:

B 209 Aluminum and Aluminum-Alloy Sheet and PlateB 210 Aluminum and Aluminum-Alloy Drawn Seam-

less TubesB 211 Aluminum and Aluminum-Alloy Bar, Rod,

and WireB 221 Aluminum and Aluminum-Alloy Extruded Bars,

Rods, Wire, Profiles, and TubesB 241 Aluminum and Aluminum-Alloy Seamless Pipe

and Seamless Extruded TubeB 247 Aluminum and Aluminum-Alloy Die Forgings,

Hand Forgings, and Rolled Ring ForgingsB 308 Aluminum-Alloy 6061-T6 Standard Structural

ProfilesB 316 Aluminum and Aluminum-Alloy Rivet and

Cold-Heading Wire and RodsB 429 Aluminum Alloy Extruded Structural Pipe

and TubeB 632 Aluminum Alloy Rolled Tread PlateB 928 High Magnesium Aluminum-Alloy Sheet and

Plate for Marine ServiceF 468 Nonferrous Bolts, Hex Cap Screws, and Studs

for General Use

This Specification also applies to castings that meet the requirements of Section 8.1.

1.3 Safety Factors

1.3.1 Building Type Structures

Basic allowable tensile stresses for buildings, structural supports for highway signs, luminaires, traffic signals, and similar structures shall be the lesser of the minimum yield strength divided by a factor of safety of 1.65, or the mini-mum ultimate tensile strength divided by a factor of safety of 1.95. Other allowable stresses for buildings and similar structures shall be based upon the factors of safety shown in Table 3.4-1.

1.3.2 Bridge Type Structures

Basic allowable tensile stresses for bridge type structures shall be the lesser of the minimum yield strength divided by a factor of safety of 1.85, or the minimum ultimate tensile strength divided by a factor of safety of 2.2. Other allow-able stresses for bridge and similar structures shall be based upon the factors of safety shown in Table 3.4-1.

1.3.3 Other Type Structures

Where it is customary or standard practice to use factors of safety other than those given in Sections 1.3.1 or 1.3.2, the general formulas in Table 3.4-3 shall be permitted to be used with the desired factors of safety substituted for nu , ny , or na .

I-A-10 January 2005

Section 2. Design Procedure

2.1 Section Properties

Section properties such as cross-sectional area, moment of inertia, section modulus, radius of gyration, and torsion and warping constants shall be determined using nominal dimensions. Cross section dimensions shall not vary by more than the tolerances given in Aluminum Standards and Data.

2.2 Procedure

Computations of forces, moments, stresses, and deflec-tions shall be in accordance with accepted methods of elas-tic structural analysis and engineering design. The formu-las and methods for determining allowable stresses in this Specification have been simplified in many cases for ease of computation but are not intended to preclude the use of more rigorous analysis.

2.3 Loads

Building-type structures shall be designed for the nomi-nal loads given in the applicable building code or perfor-mance specification. Nominal loads shall be factored and combined in accordance with the applicable building code or performance specification. In the absence of a code or performance specification, ASCE 7-02, Minimum Design Loads for Buildings and Other Structures, shall be used.

Bridge-type structures shall be designed for the loads given in AASHTO’s Standard Specifications for Highway Bridges.

Other structures shall be designed for the loads given in the performance specification.

January 2005 I-A-11

Section 3. General Design Rules

3.1 Material Properties

Minimum mechanical properties used for non-welded material shall be as listed in Table 3.3-1.

Minimum mechanical properties used for welded material shall be as listed in Table 3.3-2.

The following properties shall be used unless more pre-cise values are specified:

Coefficient of thermal expansion

13 × 10-6/oF (23 × 10-6/oC)

Density 0.1 lb/in3 (2.7 × 103 kg/m3)

Poisson’s ratio 0.33

3.2 Nomenclature

A consistent set of units shall be used throughout this Specification.

a = detail dimension parallel to the direction of stress ae = equivalent width of rectangular panel al = shorter dimension of rectangular panel a2 = longer dimension of rectangular panel A = cross sectional area Ac = area of compression element (compression flange

plus 1/3 of area of web between compression flange and neutral axis)

Ah = gross area of cross section of longitudinal stiffener

As = area of the stiffener Asn = thread stripping area of internal thread per unit

length of engagement Aw = the portion of area of cross section A lying within

1.0 in. (25 mm) of a weld b = width of section or element be = effective width of flat element to be used in

deflection calculations bo = width of element with an intermediate stiffener

as shown in Fig. 3.4.9.2-1 b/t = width to thickness ratio of a flat element of a

cross section B = buckling formula intercept with the following

subscripts: c-compression in columns p-compression in flat elements t-compression in curved elements tb-bending in curved elements br-bending in flat elements s-shear in flat elements

c = distance from neutral axis to extreme fiber C = buckling formula intersection (see B for

subscripts) C = coefficient which depends on screw

location Cb = coefficient which depends on moment gradient

Cf = constant to be determined from Table 4.8.1-1 and Figure 4.8.1-1

Cm = 0.6 - 0.4(M1/M2) for members whose ends are prevented from sway

= 0.85 for members whose ends are not prevented from swaying

CP = correction factor Cw = torsional warping constant of the cross section Cwa = t2 sin θ (0.46Fcy + 0.02 √

____ EFcy )

Cwb = Cw3 + Ri (1– cosθ) Cw1 = 5.4 in. (140 mm) Cw2 = 1.3 in. (33 mm) Cw3 = 0.4 in. or 10 mm consistent with other units used C1 = coefficient defined in Section 4.9.4 C2 = coefficient defined in Section 4.9.4 d = depth of section or beam df = distance between flange centroids ds = flat width of lip stiffener shown in Fig. 3.4.9.1-1 d1 = clear distance from the neutral axis to the

compression flange D = buckling formula slope (see B for subscripts) D = diameter Dh = nominal hole diameter Dn = nominal dead load Ds = defined in Fig. 3.4.9.1-1 Dw = nominal washer diameter Dws = larger of the nominal washer diameter and the

screw head e = base for natural logarithms ≈2.72 E = compressive modulus of elasticity

(See Table 3.3-1) f = calculated stress fa = average stress on cross section produced by axial

load fb = maximum bending stress produced by transverse

loads and/or bending moment fs = shear stress caused by torsion or transverse shear

loads F = allowable stress Fa = allowable compressive stress for a member con-

sidered as an axially loaded column according to Sections 3.4.7 through 3.4.10

Fao = allowable compressive stress of axially loaded member considered as a short column according to Section 4.7.2.

Fb = allowable bending stress for members subjected to bending only

Fc = allowable compressive stress Fcr = local buckling stress for element from

Section 4.7.1 Fcy = compressive yield strength Fcyw = compressive yield strength across a groove weld

(0.2% offset in 2 in. (50 mm) gage length)

Fe = elastic buckling stress divided by nu = π2E _______ nu(kL/r)2

I-A-12 January 2005

Feb = elastic lateral buckling stress of beam calculated using Eq. 3.4.11-3 or Section 4.9 with ny = 1.0

Fec = elastic critical stress Fec = allowable elastic lateral buckling stress of beam

calculated assuming that the elements are not buckled

Fef = elastic torsional-flexural buckling stress Fet = elastic torsional buckling stress

Fet = 1 ____ Ar 2 O

( GJ + π2ECw ______ (KtLt)2 )

Fex = π2E ______ ( kxLb ____ rx

) 2

Fm = mean value of the fabrication factor Fn = allowable stress for cross section 1.0 in. (25 mm)

or more from weld Fpw = allowable stress on cross section, part of whose

area lies within 1.0 in. (25 mm) of a weld Frb = allowable stress for beam with buckled elements Frc = allowable stress for column with buckled

elements Fs = allowable shear stress for members

subjected only to torsion or shear FST = allowable stress according to Section 3.4.9.1 or

3.4.16.2 Fsu = shear ultimate strength Fsuw = shear ultimate strength within 1.0 in.

(25 mm) of a weld Ft = allowable te nsile stress for the member loaded

only axially according to Section 3.4.1 Ftu = tensile ultimate strength Ftuw = tensile ultimate strength across a groove weld Ftul = tensile ultimate strength of member in contact

with the screw head Ftu2 = tensile ultimate strength of member not in

contact with the screw head Fty = tensile yield strength Ftyw = tensile yield strength across a groove weld

(0.2% offset in 2 in. (50 mm) gage length) FUT = allowable stress according to Section 3.4.9.1

or 3.4.16.2 Fw = allowable stress on cross section if entire area

were to lie within 1.0 in. (25 mm) of a weld Fy = either Fty or Fcy, whichever is smaller g = spacing of rivet or bolt holes perpendicular to

direction of load go = distance from shear center to the point of

application of load G = shear modulus Gf = grip of rivet or bolt h = clear height of shear web I = moment of inertia Ib = required moment of inertia of bearing stiffener Icy = moment of inertia of compression flange

about web Ih = moment of inertia of longitudinal stiffener

Io = moment of inertia of the stiffener about the cen-troidal axis of the stiffener parallel to the flat element that is stiffened

Is = moment of inertia of transverse stiffener to resist shear buckling

Ix = moment of inertia of a beam about axis perpendicular to web

Iy = moment of inertia of a beam about axis parallel to web

Iyc = moment of inertia of compression element about axis parallel to vertical web

j = parameter defined by Eq. 4.9.3-5 or -6 J = torsion constant k = the effective length factor. k shall be taken larger

than or equal to unity unless rational analysis justifies a smaller value

kt = coefficient for tension members kx = effective length coefficient for buckling about the

x-axis ky = effective length coefficient for buckling about the

y-axis kl = coefficient for determining slenderness limit S2

for sections for which the allowable compressive stress is based on ultimate strength

k2 = coefficient for determining allowable compres-sive stress in sections with slenderness ratio above S2 for which the allowable compressive stress is based on ultimate strength

Ks = coefficient in Section 5.4.2.1 Kt = effective length coefficient for torsional buckling.

Kt shall be taken larger than or equal to unity unless rational analysis justifies a smaller value

L = unsupported length in the plane of bending Lb = unbraced length for bending Ln = nominal live load Ls = length of tube between circumferential stiffeners Lt = unbraced length for twisting m = constant to be determined from Table 4.8.1-1 M = bending moment applied to the member Ma = allowable bending moment for the member if

bending moment alone is applied to the member MA = absolute value of moment at quarter-point of the

unbraced beam segment MB = absolute value of moment at mid-point of the

unbraced beam segment MC = absolute value of moment at three-quarter point

of the unbraced beam segment Me = elastic critical moment Mi = bending strength of member with intermediate

thickness Mm = mean value of the material factor MMAX = absolute value of maximum moment in the

unbraced beam segment M1 = bending strength of member of thinnest material M2 = bending strength of member of thickest material

January 2005 I-A-13

M1/M2 = ratio of end moments where M2 is the larger of the two end moments and M1/M2 is positive when the member is bent in reverse curvature, negative when bent in single curvature

n = number of tests n = number of threads per unit length for a screw na = factor of safety on appearance of buckling ns = factor of safety for screw connections nu = factor of safety on ultimate strength ny = factor of safety on yield strength N = length of bearing at reaction or concentrated load N = number of cycles to failure Ns = number of stress ranges in the spectrum P = applied interior reaction or concentrated load per

web for flat webs Pas = allowable shear force per screw Pat = allowable tensile force per screw Pbs = concentrated load on bearing stiffener Pc = allowable reaction or concentrated load per web Pnot = nominal pull-out strength per screw Pnov = nominal pull-over strength per screw Pns = nominal shear strength per screw Pnt = nominal tensile strength per screw q = uniform design load r = radius of gyration

ro = √_______________

r 2 x + r 2 y + x 2 o + y 2 o rs = radius of gyration of the stiffener rx , ry = radii of gyration of the cross-section about the cen-

troidal principal axes (see Section 4.9.2 for rye of singly symmetric sections unsymmetric about the bending axis)

rye = effective radius of gyration R = transition radius, the radius of an attachment of

the weld detail Rb = mid-thickness radius of a round element or maxi-

mum mid-thickness radius of an oval element Ri = bend radius at juncture of flange and web

measured to inside surface of bend Rs = stress ratio, the ratio of minimum stress to

maximum stress s = spacing of transverse stiffeners (clear distance

between stiffeners for stiffeners consisting of a pair of members, one on each side of the web, center-to-center distance between stiffeners con-sisting of a member on one side of the web only); spacing of rivet or bolt holes parallel to direction of load

S = 1.28 √___

E ___ Fcy

Sc = section modulus of a beam, compression side

Sra = the applied stress range Srd = allowable stress range Sre = equivalent stress range Sri = the ith stress range in the spectrum St = section modulus of a beam, tension side

Sw = size of a weld Sx = standard deviation of the test results S1, S2 = slenderness limits t = thickness of element tavg = the average thickness of the element tc = depth of full thread engagement of screw into t2

not including tapping or drilling point ti = thickness of the intermediate thickness material

tested tmax = thickness of thickest material tested tmax = greater thickness of a tapered thickness element tmin = thickness of thinnest material tested tmin = lesser thickness of a tapered thickness element t1 = thickness of member in contact with the screw

head t2 = thickness of member not in contact with the

screw head U = parameter defined by Eq. 4.9.3-8 V = shear force on web at stiffener location VF = coefficient of variation of the fabrication factor VM = coefficient of variation of the material factor VP = coefficient of variation of the ratio of the observed

failure loads divided by the average value of all the observed failure loads

VQ = coefficient of variation of the loads xo = x - coordinate of the shear center Xa = strength at which 99% of the material is expected

to conform at a confidence level of 95% Xi = failure load of ith test Xm = mean of the test results yo = y - coordinate of the shear center α = Dn /Ln

αi = number of cycles in the spectrum of the ith stress range divided by the total number of cycles

αs = a factor equal to unity for a stiffener consisting of equal members on both sides of the web and equal to 3.5 for a stiffener consisting of a mem-ber on one side only

β = 1 – (xo /ro)2

βo = the target reliability index βs = spring constant (transverse force applied to the

compression flange of the member of unit length divided by the deflection due to the force)

δ = (tmax – tmin) _________ tmin

for tapered thickness elements

λs = equivalent slenderness ratio for an intermediate stiffener

ρst = ratio defined in Section 3.4.9.1 and 3.4.16.2 θ = angle between plane of web and plane of bearing

surface (θ ≤ 90°)

I-A-14 January 2005

3.3 Tables Relating to Mechanical Properties and Buckling Constants

This Section consists of the following tables concerning formulas for determining allowable stresses and constants and coefficients needed for these formulas:

3.3-1 Minimum Mechanical Properties for Alumi-num Alloys

3.3-1M Minimum Mechanical Properties for Alumi-num Alloys

3.3-2 Minimum Mechanical Properties for Welded Aluminum Alloys

3.3-2M Minimum Mechanical Properties for Welded Aluminum Alloys

3.3-3 Formulas for Buckling Constants for Prod-ucts Whose Temper Designation Begins With -O, -H, -T1, -T2, T3, or -T4

3.3-4 Formulas for Buckling Constants for Prod-ucts Whose Temper Designation Begins With -T5, -T6, -T7, -T8, or -T9

January 2005 I-A-15

Table 3.3-1 MINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS

ALLOY AND TEMPER PRODUCTTHICKNESS

RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi

COMPRESSIVE MODULUS OF ELASTICITY2

E (ksi)1100-H12

-H14Sheet, Plate, Drawn Tube, Rolled Rod & Bar

AllAll

1416

1114

1013

910

10,10010,100

2014-T6-T651-T6, T6510, T6511-T6, T651

SheetPlateExtrusionsCold Finished Rod & Bar, Drawn Tube

0.040 to 0.2490.250 to 2.000

AllAll

66676065

58595355

59585253

40403538

10,90010,90010,90010,900

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.025 to 0.0390.040 to 0.2490.250 to 0.499

636464

555757

565856

383939

10,80010,80010,800

3003-H12-H14-H16-H18-H12-H14-H16-H18

Sheet & PlateSheet & PlateSheet SheetDrawn TubeDrawn TubeDrawn TubeDrawn Tube

0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.128

AllAllAllAll

1720242717202427

1217212412172124

1014182011161921

1112141511121415

10,10010,10010,10010,10010,10010,10010,10010,100

Alclad3003-H12

-H14-H16-H18-H14-H18

Sheet & PlateSheet & PlateSheet SheetDrawn Tube Drawn Tube

0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.025 to 0.2590.010 to 0.500

161923261926

111620231623

91317191520

101214151215

10,10010,10010,10010,10010,10010,100

3004-H32-H34-H36-H38-H34-H36


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.018 to 0.4500.018 to 0.450

283235383235

212528312528

182225292427

171920211920

10,10010,10010,10010,10010,10010,100

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361

Sheet SheetSheet SheetSheet Sheet

0.017 to 0.2490.009 to 0.2490.006 to 0.1620.006 to 0.1280.024 to 0.0500.024 to 0.050

273134373134

202427302630

172124282228

161819211819

10,10010,10010,10010,10010,10010,100

3005-H25-H28

SheetSheet

0.013 to 0.0500.006 to 0.080

2631

2227

2025

1517

10,10010,100

3105-H25 Sheet 0.013 to 0.080 23 19 17 14 10,100

5005-H12-H14-H16-H32-H34-H36

Sheet & PlateSheet & PlateSheetSheet & PlateSheet & PlateSheet

0.017 to 2.0000.009 to 1.0000.006 to 0.1620.017 to 2.0000.009 to 1.0000.006 to 0.162

182124172023

141720121518

131518111416

111214111213

10,10010,10010,10010,10010,10010,100

5050-H32-H34-H32

-H34

SheetSheetCold Fin. Rod & BarDrawn TubeCold Fin. Rod & BarDrawn Tube

0.017 to 2.0000.009 to 0.249

All

All

222522

25

162016

20

141815

19

141513

15

10,10010,10010,100

10,100

For all footnotes, see last page of this Table.

( )

I-A-16 January 2005



RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi


E (ksi)5052-O

-H32-H34-H36

Sheet & PlateSheet & PlateCold Fin. Rod & BarDrawn TubeSheet

0.006 to 3.000AllAll

0.006 to 0.162

253134

37

9.52326

29

9.52124

26

161920

22

10,20010,20010,200

10,2005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321

ExtrusionsExtrusionsExtrusionsSheet & PlateSheet & PlateSheet & PlatePlatePlate

up thru 5.000up thru 0.5000.501 to 5.0000.051 to 1.5000.188 to 1.5000.188 to 1.5001.501 to 3.0001.501 to 3.000

3940404044444141

1624241831312929

1621211826262424

2424232526262424

10,40010,40010,40010,40010,40010,40010,40010,400

5086-O-H111-H111 -O-H112-H112-H112-H116-H112-H32

-H34

ExtrusionsExtrusionsExtrusionsSheet & PlatePlatePlatePlatePlateSheet & PlateSheet & PlateDrawn TubeSheet & PlateDrawn Tube


AllAll

All

35363635363535344040

44

14212114181614142828

34

14181814171615152626

32

21212121222121212424

26

10,40010,40010,40010,40010,40010,40010,40010,40010,40010,400

10,400

5154-H38 Sheet 0.006 to 0.128 45 35 33 24 10,3005454-O

-H111-H111-H112-O-H32-H34

ExtrusionsExtrusionsExtrusionsExtrusionsSheet & PlateSheet & PlateSheet & Plate

up thru 5.000up thru 0.5000.501 to 5.000up thru 5.0000.020 to 3.0000.020 to 2.0000.020 to 1.000

31333331313639

12191912122629

12161613122427

19201919192123

10,40010,40010,40010,40010,40010,40010,400

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321

Sheet & PlateSheet & PlateSheet & PlatePlatePlatePlatePlate

0.051 to 1.5000.188 to 1.2500.188 to 1.2501.251 to 1.5001.251 to 1.5001.501 to 3.0001.501 to 3.000

42464644444141

19333331312929

19272725252525

26272725252525

10,40010,40010,40010,40010,40010,40010,400

6005-T5 Extrusions up thru 1.000 38 35 35 24 10,1006061-T6, T651

-T6, T6510, T6511-T6, T651-T6-T6

Sheet & PlateExtrusionsCold Fin. Rod & BarDrawn TubePipe

0.010 to 4.000All

up thru 8.0000.025 to 0.500

All

4238424238

3535353535

3535353535

2724252724

10,10010,10010,10010,10010,100

6063-T5, -T52-T5-T6

ExtrusionsExtrusionsExtrusionsExtrusions & Pipe

up thru 0.500up thru 1.0000.500 to 1.000

All

22222130

16161525

16161525

13131219

10,10010,10010,10010,100

6066-T6, T6510, T6511 Extrusions All 50 45 45 27 10,1006070-T6, T62 Extrusions up thru 2.999 48 45 45 29 10,1006105-T5 Extrusions up thru 0.500 38 35 35 24 10,10063516351

-T5-T6

ExtrusionsExtrusions

up thru 1.000up thru 0.750

3842

3537

3537

2427

10,10010,100

6463-T6 Extrusions up thru 0.500 30 25 25 19 10,1007005-T53 Extrusions up thru 0.750 50 44 43 28 10,500

1. Ftu and Fty are minimum specified values (except Fty for 1100-H12, H14 Cold Finished Rod and Bar and Drawn Tube, Alclad 3003-H18 Sheet and 5050-H32, H34 Cold Finished Rod and Bar which are minimum expected values); other strength properties are corresponding minimum expected values.

2. Typical values. For deflection calculations an average modulus of elasticity is used; this is 100 ksi lower than values in this column.

( )

January 2005 I-A-17

Table 3.3-1MMINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS


RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)1100-H12


AllAll

95110

75 95

70 90

62 70

69,60069,600

2014-T6-T651-T6, T6510, T6511-T6, T651


1.00 to 6.306.30 to 50.00

AllAll

455460415450

400405365380

405400360365

275275240260

75,20075,20075,20075,200

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.63 to 1.001.00 to 6.30

6.30 to 12.50

435440440

380395395

385400385

260270270

74,50074,50074,500

3003-H12-H14-H16-H18-H12-H14-H16-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.20

AllAllAllAll

120140165185120140165185

85115145165 85115145165

70 95125140 75110130145

75 85 95105 75 85 95105

69,60069,60069,60069,60069,60069,60069,60069,600

Alclad3003-H12

-H14-H16-H18-H14-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.63 to 6.300.25 to 12.50

115135160180135180

80110140160110160

62 90115130105140

70 85 95105 85105

69,60069,60069,60069,60069,60069,600

3004-H32-H34-H36-H38-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.45 to 11.500.45 to 11.50

190220240260220240

145170190215170190

125150170200165185

115130140145130140

69,60069,60069,60069,60069,60069,600

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361


0.40 to 6.300.20 to 6.300.15 to 4.000.15 to 3.200.60 to 1.200.60 to 1.20

185215235255215235

140165185205180205

115145165195150195

110125130145125130

69,60069,60069,60069,60069,60069,600

3005-H25-H28

SheetSheet

0.32 to 1.200.15 to 2.00

180215

150185

140170

105115

69,60069,600

3105-H25 Sheet 0.32 to 2.00 160 130 115 95 69,600

5005-H12-H14-H16-H32-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.00

0.40 to 50.000.20 to 25.000.15 to 4.00

125145165120140160

95115135 85105125

90105125 75 95110

75 85 95 75 85 90

69,60069,60069,60069,60069,60069,600

5050-H32-H34-H32

-H34


0.40 to 6.300.20 to 6.30

All

All

150170150

170

110140110

140

95125105

130

95105 90

105

69,60069,60069,600

69,600


( )

I-A-18 January 2005



RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)5052-O

-H32-H34

-H36


0.15 to 80.00AllAll

0.15 to 4.00

170215235

255

65160180

200

66145165

180

110130140

150

70,30070,30070,300

70,3005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321



12.70 to 130.001.20 to 6.30

4.00 to 40.004.00 to 40.0040.00 to 80.0040.00 to 80.00

270275275275305305285285

110165165125215215200200

110145145125180180165165

165165160170180180165165

71,70071,70071,70071,70071,70071,70071,70071,700

5086-O-H111-H111 -O-H112-H112-H112-H116-H32

-H34

ExtrusionsExtrusionsExtrusionsSheet & PlateSheet & PlatePlatePlateSheet & PlateSheet & PlateDrawn TubeSheet & PlateDrawn Tube


12.70 to 130.000.50 to 50.004.00 to 12.5012.50 to 40.0040.00 to 80.001.60 to 50.00

All

All

240250250240250240235275275

300

95145145 95125105 95195195

235

95125125 95115110105180180

220

145145145145150145145165165

180

71,70071,70071,70071,70071,70071,70071,70071,70071,700

71,700

5154-H38 Sheet 0.15 to 3.20 310 240 230 165 71,7005454-O

-H111-H111-H112-O-H32-H34



12.70 to 130.00up thru 130.000.50 to 80.000.50 to 50.000.50 to 25.00

215230230215215250270

85130130 85 85180200

85110110 90 85165185

130140130130130145160

71,70071,70071,70071,70071,70071,70071,700

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321


1.20 to 6.304.00 to 12.504.00 to 12.5012.50 to 40.0012.50 to 40.0040.00 to 80.0040.00 to 80.00

290315315305305285285

130230230215215200200

130185185170170170170

180185185170170170170

71,70071,70071,70071,70071,70071,70071,700

6005-T5 Extrusions up thru 25 260 240 240 165 69,6006061-T6, T651

-T6, T6510, T6511-T6, T651-T6-T6


0.25 to 100.00All

up thru 2000.63 to 12.50

All

290260290290260

240240240240240

240240240240240

185165170185165

69,60069,60069,60069,60069,600

6063-T5, -T52-T5-T6


up thru 12.50up thru 25.0012.50 to 25.00

All

150150145205

110110105170

110110105170

90 90 85130

69,60069,60069,60069,600

6066-T6, T6510, T6511 Extrusions All 345 310 310 185 69,6006070-T6, T62 Extrusions up thru 80.00 330 310 310 200 69,6006105-T5 Extrusions up thru 12.50 260 240 240 165 69,6006351-T5 Extrusions up thru 25.00 260 240 240 165 69,6006351-T6 Extrusions up thru 20.00 290 255 255 185 69,6006463-T6 Extrusions up thru 12.50 205 170 170 130 69,6007005-T53 Extrusions up thru 20.00 345 305 295 195 72,400


2. Typical values. For deflection calculations an average modulus of elasticity is used; this is 700 MPa lower than values in this column.

( )

January 2005 I-A-19

Table 3.3-2MINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEin.

TENSION COMPRESSIONFcyw

2

ksi

SHEARFsuw ksi

Ftuw1

ksiFtyw

2 ksi

1100-H12, H14 All 11 3.5 3.5 8

3003-H12, H14, H16, H18 All 14 5 5 10

Alclad 3003-

H12, H14, H16, H18

All

13

4.5

4.510

3004-H32, H34, H36, H38 All 22 8.5 8.5 14

Alclad 3004-

H32, H34, H36, H38

All

21

8

8

13

3005-H25 Sheet 17 6.5 6.5 12

5005-H12, H14, H32, H34 All 15 5 5 9

5050-H32, H34 All 18 6 6 12

5052-O, H32, H34 All 25 9.5 9.5 16

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321

ExtrusionsSheet & PlatePlate

0.188-1.5001.501-3.000

394039

161817

151817

232424

5086-5086-5086-

O, H111H112O, H32, H34, H116

ExtrusionsPlateSheet & Plate

0.250-2.000353535

141414

131414

212121

5154-H38 Sheet 30 11 11 19

5454-5454-5454-

O, H111H112O, H32, H34

ExtrusionsExtrusionsSheet & Plate

313131

121212

111212

191919

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

0.188-1.5001.501-3.000

4241

1918

1817

2525

6005-T5 Extrusions up thru 0.250 24 13 13 15

6061-6061-

T6, T651, T6510, T65113

T6, T651, T6510, T65114

AllAll over 0.375

2424

1511

1511

1515

6063-T5, T52, T6 All 17 8 8 11

6351-6351-

T5, T63

T5, T64

ExtrusionsExtrusions over 0.375

2424

1511

1511

1515

6463-T6 Extrusions 0.125-0.500 17 8 8 11


1. Filler wires are listed in Table 7.1-1. Values of Ftuw are AWS D1.2 weld qualification values.

2. 0.2% offset in 2 in. gage length across a groove weld.

3. Values when welded with 5183, 5356, or 5556 alloy filler wire, regardless of thickness. Values also apply to thicknesses less than or equal to 0.375 in. when welded with 4043, 5554, or 5654 alloy filler wire.

4. Values when welded with 4043, 5554, or 5654 alloy filler wire.

I-A-20 January 2005

Table 3.3-2MMINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEmm


2

MPa

SHEARFsuw MPa

Ftuw1

MPaFtyw

2 MPa

1100-H12, H14 All 75 25 25 55

3003-H12, H14, H16, H18 All 95 35 35 70

Alclad 3003-

H12, H14, H16, H18

All

90

30

30

70

3004-H32, H34, H36, H38 All 150 60 60 95

Alclad 3004-

H32, H34, H36, H38

All

145

55

55

90

3005-H25 Sheet 115 45 45 85

5005-H12, H14, H32, H34 All 105 35 35 62

5050-H32, H34 All 125 40 40 85

5052-O, H32, H34 All 170 65 65 110

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321


6.30-38.0038.00-80.00

270270270

110115115

110115115

160165165

5086-5086-5086-

O, H111H112O, H32, H34, H116


6.30-50.00240240240

95 95 95

85 95 95

145145145

5154-H38 Sheet 205 75 75 130

5454-5454-5454-

O, H111H112O, H32, H34


215215215

85 85 85

85 85 85

130130130

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

6.30-38.0038.00-80.00

285285

125125

125120

170170


6061-6061-

T6, T651, T6510, T65113

T6, T651, T6510, T65114

AllAll over 9.50

165165

105 80

105 80

105105

6063-T5, T52, T6 All 115 55 55 75

6351-6351-

T5, T63

T5, T64


165165

105 80

105 80

105105

6463-T6 Extrusions 3.20-12.50 115 55 55 75



2. 0.2% offset in 50 mm gage length across a groove weld.

3. Values when welded with 5183, 5356, or 5556 alloy filler wire, regardless of thickness. Values also apply to thicknesses less than or equal to 9.5 mm when welded with 4043, 5554, or 5654 alloy filler wire.


January 2005 I-A-21

Table 3.3-3 FORMULAS FOR BUCKLING CONSTANTS FOR PRODUCTS WHOSE TEMPER

DESIGNATION BEGINS WITH -O, -H, -T1, -T2, -T3, OR -T4

Type of Member and StressIntercept

ksiIntercept

MPaSlope Intersection

Compression in Columns and Beam Flanges Bc = Fcy [ 1 + ( Fcy _____

1000 ) 1/2

] Bc = Fcy [ 1 + ( Fcy _____ 6900

) 1/2

] Dc = Bc ___ 20

( 6Bc ___ E

) 1/2

Cc = 2Bc ____ 3Dc

Axial Compression in Flat Elements Bp = Fcy [ 1 +

( Fcy ) 1/3

______ 7.6

] Bp = Fcy [ 1 + ( Fcy ) 1/3

______ 14.5

] Dp = Bp ___ 20

( 6Bp ___ E

) 1/2

Cp = 2Bp ____ 3Dp

Axial Compression in Curved Elements Bt = Fcy [ 1 +

( Fcy ) 1/5

______ 5.8

] Bt = Fcy [ 1 + ( Fcy ) 1/5

______ 8.5

] Dt = Bt ___ 3.7

( Bt __ E

) 1/3

Ct*

Bending Compression in Flat Elements Bbr = 1.3Fcy [ 1 +

( Fcy ) 1/3

______ 7

] Bbr = 1.3Fcy [ 1 + ( Fcy ) 1/3

_____ 13.3

] Dbr = Bbr ___ 20

( 6Bbr ____ E

) 1/2

Cbr = 2Bbr ____ 3Dbr

Bending Compression in Curved Elements Btb = 1.5Fy [ 1 +

( Fy ) 1/5

______ 5.8

] Btb = 1.5Fy [ 1 + ( Fy ) 1/5

_____ 8.5

] Dtb = Btb ___ 2.7

( Btb ___ E

) 1/3

Ctb = ( Btb – Bt _______ Dtb – Dt

) 2

Shear in Flat Elements Bs =

Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 6.2

] Bs = Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 11.8

] Ds = Bs ___ 20

( 6Bs ___ E

) 1/2

Cs = 2Bs ____ 3Ds

Ultimate Strength of Flat Elements in Compression or Bending

k1 = 0.50, k2 = 2.04

*Ct shall be determined using a plot of curves of limit state stress based on elastic and inelastic buckling or by trial and error solution.

I-A-22 January 2005


DESIGNATION BEGINS WITH -T5, -T6, -T7, -T8, OR -T9


ksiIntercept



2250 ) 1/2

] Bc = Fcy [ 1 + ( Fcy ______ 15510

) 1/2

] Dc = Bc ___ 10

( Bc __ E

) 1/2

Cc = 0.41 Bc ___ Dc


( Fcy ) 1/3

______ 11.4

] Bp = Fcy [ 1 + ( Fcy ) 1/3

______ 21.7

] Dp = Bp ___ 10

( Bp __ E

) 1/2

Cp = 0.41 Bp ___ Dp


( Fcy ) 1/5

______ 8.7

] Bt = Fcy [ 1 + ( Fcy ) 1/5

______ 12.8

] Dt = Bt ___ 4.5

( Bt __ E

) 1/3

Ct*


( Fcy ) 1/3

_____ 7 ] Bbr = 1.3Fcy [ 1 +

( Fcy ) 1/3

_____ 13.3

] Dbr = Bbr ___ 20

( 6Bbr ____ E

) 1/2



( Fy ) 1/5

_____ 8.7

] Btb = 1.5Fy [ 1 + ( Fy ) 1/5

_____ 12.8

] Dtb = Btb ___ 2.7

( Btb ___ E

) 1/3

Ctb = ( Btb – Bt _______ Dtb – Dt

) 2


Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 9.3

] Bs = Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 17.7

] Ds = Bs ___ 10

( Bs __ E

) 1/2

Cs = 0.41 Bs ___ Ds

Ultimate Strength of Flat Elements in Compression k1 = 0.35, k2 = 2.27

Ultimate Strength of Flat Elements in Bending k1 = 0.50, k2 = 2.04


January 2005 I-A-23

3.4 Allowable Stresses

Allowable stresses shall be determined in accordance with provisions of this Specification.

In the following subsections:• The factors nu, ny, and na shall be taken from Table 3.4-1.• Values of coefficient kt shall be taken from Table 3.4-2.

Table 3.4-1SAFETY FACTORS

Building and similar type structures

Bridge and similar type structures

nu 1.95 2.20

ny 1.65 1.85

na 1.20 1.35

Other safety factors are given throughout this Specification.

Table 3.4-2COEFFICIENT kt

Alloy and TemperNon-welded or Regions

Farther than 1.0 in. (25 mm) from a Weld

Regions Within 1.0 in. (25 mm) of a Weld

2014-T6, -T651, -T6510, -T6511Alclad 2014-T6, -T651

1.25 –

6066-T6, -T6510, -T6511 1.1 –

6070-T6, -T62 1.1 –

All Others Listed in Table 3.3-1 1.0 1.0

kt is used in Sections 3.4.1, 3.4.2, 3.4.3, and 3.4.4.

• Values of k1 and k2 shall be taken from Tables 3.3-3 and 3.3-4.

The formulas of this Section are also listed in Table 3.4-3.

I-A-24 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Allo

wab

le S

tres

s

Tab

le 3

.4-3

G

EN

ER

AL

FO

RM

UL

AS

FO

R

DE

TE

RM

ININ

G A

LLO

WA

BL

E S

TR

ES

S

FR

OM

SE

CT

ION

3.4

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

r

gros

s se

ctio

n

net s

ectio

n1

Fty

/ny

Ftu

/(k t

n u)

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

(flan

ges)

2

F =

Fty

___

n y o

r F

= F

tu

____

k t n

u

Rou

nd o

r ov

al tu

bes

3F

= 1.

17F

ty

______

n y

or

F =

1.24

Ftu

______

k t n

u

Fla

t ele

men

ts in

ben

ding

in

thei

r ow

n pl

ane

(web

s)4

for

sym

met

ric s

hape

s:

F =

1.3F

ty

____

_ n y

o

r F

= 1.

42F

tu

______

k t n

u

for

unsy

mm

etric

sha

pes

se

e S

ectio

n 3.

4.4

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, e

quat

ions

of S

ectio

ns 3

.4.1

0,

3.4.

12, a

nd 3

.4.1

6.1

appl

y fo

r R

b /t

≤ 2

0.

BE

AR

ING

On

rivet

s an

d bo

lts

52F

tu /n

u

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d

hole

s6

2Ftu

/(1.

5nu)

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Allo

wab

le

Str

ess

Sle

nd

ern

ess

≤ S

1

Sle

nd

ern

ess

L

imit

S1

Allo

wab

le S

tres

s S

1 <

Sle

nd

ern

ess

< S

2

Sle

nd

ern

ess

Lim

it S

2

Allo

wab

le S

tres

s S

len

der

nes

s ≥

S2

CO

MP

RE

SS

ION

IN

CO

LU

MN

S,

axia

l, gr

oss

se

ctio

n

All

colu

mns

7 F

cy

___

n y

kL

___ r

= B

c –

n uF

cy

____

_ n y

__

__

__

__

Dc

1

__

n u ( B

c –

Dc kL

__

_ r ) kL

__

_ r =

Cc

π2 E

____

__

n u ( kL

__

_ r ) 2

CO

MP

RE

SS

ION

IN

CO

LU

MN

E

LE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e—co

lum

ns

buck

ling

abou

t a s

ymm

etry

ax

is

8 F

cy

___

n y

b __

t = B

p –

n uF

cy

____

_ n y

__

__

__

__

5.1

Dp

1 __

n u

( Bp –

5.1D

p b

__ t )

b __

t =

k 1B

p __

___

5.1D

p k 2

√____

BpE

________

n u(5

.1b/

t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e—co

lum

ns

not b

uckl

ing

abou

t a

sym

met

ry a

xis

8.1

Fcy

___

n y

b __

t = B

p –

n uF

cy

____

_ n y

__

__

__

__

5.1D

p

1 __

n u ( B

p –

5.1D

p b

__ t )

b __

t = C

p __

_ 5.

1

π2 E

____

____

_ n u

(5.1

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

9 F

cy

___

n y

b __

t = B

p –

n uF

cy

____

_ n y

__

__

__

__

1.6D

p

1 __

n u ( B

p –

1.6D

p b

__ t )

b __

t =

k 1B

p __

___

1.6D

p k 2

√____

BpE

________

n u(1

.6b/

t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

See

Sec

tion

3.4.

9.1

Fla

t ele

men

ts

supp

orte

d on

bot

h

edge

s an

d w

ith a

n

inte

rmed

iate

stif

fene

r

9.2

See

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

su

ppor

ted

on b

oth

ed

ges

10 F

cy

___

n y

Rb

__

t =

( Bt –

n uF

cy

____

_ n y

____

____

_ D

t ) 2

1

__

n u

( B t –

Dt √__

_ R

b __

t ) R

b __

t =

Ct

π2 E

_________________

16n u

( Rb

__

t ) ( 1

+ √_

__

_

R

b/t

___

35 ) 2

b

b ob o

January 2005 I-A-25

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Allo

wab

le

Str

ess

Sle

nd

ern

ess

≤ S

1

Sle

nd

ern

ess

L

imit

S1

Allo

wab

le S

tres

s S

1 <

Sle

nd

ern

ess

< S

2

Sle

nd

ern

ess

Lim

it S

2

Allo

wab

le S

tres

s S

len

der

nes

s ≥

S2

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

11 F

cy

___

n y

L

b _

__

__

r y √ __

_ C

b = 1.

2(B

c –

Fcy

) _

__

__

__

__

_

Dc

1 __

n y

( Bc –

D

c L

b _________

1.2

r y √ __

_ C

b )

Lb

__

__

_

r y √ __

_ C

b = 1

.2C

c

π2 E

Cb

____

____

n y (

Lb

__

__

1.2r

y ) 2

Rou

nd o

r ov

al tu

bes

12 1.

17F

cy

______

n y

R

b __

_ t =

( Btb

– 1

.17F

cy

__

__

__

__

__

_

Dtb

) 2

1 __

n y ( B t

b –

Dtb

√ ___

Rb

___ t )

Rb

__

t =

[ ( n u

__

n y B t

b-B

t ) / ( n u

__

n y D t

b-D

t ) ] 2S

ame

as

Sec

ion

3.4.

10

Sol

id r

ecta

ngul

ar a

nd

roun

d se

ctio

ns

13 1.

3Fcy

_____

n y

d __

t √ ____

_ L

b __

__

Cbd

= B

br –

1.3

Fcy

____

____

__

2.3D

br

1 __

n y

[ Bbr

– 2

.3D

br d __

t √ ____

L

b __

__

Cbd

] d __

t √ ____

_ L

b __

__

Cbd

= C

br

___

2.3

π2 E

Cb

_____________

5.

29n y

( d __ t ) 2 Lb/

d

Tubu

lar

shap

es

14

Fcy

___

n y

L

bSc

__

__

__

__

_

0.5C

b √ ___

I yJ =

( Bc –

Fcy

____

___

1.6D

c ) 2

1

__

n y ( B

c –

1.6D

c √ __

__

__

__

_

LbS

c ________

0.5C

b √ ___

I yJ )

L

bSc

__

__

__

__

0.5C

b √ ___

I yJ =

( Cc

___

1.6 ) 2

π2 E

__

__

__

__

__

__

__

__

2.

56n y

( L

bSc

__

__

__

__

_

0.5C

b √ ___

I yJ )

CO

MP

RE

SS

ION

IN

BE

AM

E

LE

ME

NT

S,

(ele

men

t in

un

iform

co

mpr

essi

on),

gr

oss

sect

ion

Fla

t ele

men

ts

supp

orte

d on

one

edg

e 15

Fcy

___

n y

b __

t = B

p –

Fcy

____

___

5.1D

p 1 __

n y

[ B p –

5.1

Dp b

__

t ] b __

t =

k 1B

p __

___

5.1D

p k 2

√____

BpE

________

n y(5

.1b/

t)

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

16

Fcy

___

n y

b __

t = B

p –

Fcy

____

___

1.6D

p 1 __

n y

[ B p –

1.6

Dp b

__

t ] b __

t =

k 1B

p __

___

1.6D

p k 2

√____

BpE

________

n y(1

.6b/

t)

Cur

ved

elem

ents

sup

port

ed

on b

oth

edge

s 16

.1 1.

17F

cy

______

n y

R

b __

t =

( Bt –

1.1

7Fcy

__________

Dt

) 2

1 __

n y

( B t –

Dt √__

_ R

b __

t ) R

b __

t =

Ct

π2 E

__

__

__

__

__

__

__

__

16n y

( Rb

__

t ) ( 1 +

√__

__

Rb/

t __

___

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16

.2S

ee S

ectio

n 3.

4.16

.2

Fla

t ele

men

ts

supp

orte

d on

bot

h

edge

s an

d w

ith a

n

inte

rmed

iate

stif

fene

r

16.3

See

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LE

ME

NT

S,

(ele

men

t in

bend

ing

in o

wn

plan

e), g

ross

se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

te

nsio

n ed

ge, c

ompr

essi

on

edge

free

17

1.3F

cy

_____

n y

b __

t = B

br –

1.3

Fcy

____

____

__

3.5D

br

1 __

n y

[ Bbr

– 3

.5D

br b __

t ] b __

t =

Cbr

___

3.5

π2 E

____

____

_ n y

(3.5

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

18

1.3F

cy

_____

n y

h __

t = B

br –

1.3F

cy

____

____

_ m

Dbr

1 __

n y

[ Bbr

– m

Dbr

h __

t ] h

__ t =

k 1B

br

____

_ m

Dbr

k 2

√__

__

Bbr

E

____

___

n ym

h / t

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

and

with

a

long

itudi

nal s

tiffe

ner

19 1.

3Fcy

_____

n y

h __

t = B

br –

1.3

Fcy

____

____

__

0.29

Dbr

1 __

n y

[ Bbr

– 0

.29D

br h __

t ] h __

t = k 1

Bbr

____

_ 0.

29D

br

k 2

√_____

Bbr

E

_________

n y(0

.29h

/t)

SH

EA

R IN

E

LE

ME

NT

S,

gros

s se

ctio

n

Uns

tiffe

ned

flat e

lem

ents

su

ppor

ted

on b

oth

edge

s 20

Fty

____

√ __

3 n y

h

__ t =

Bs –

Fty

/ √__

3

__

____

____

1.25

Ds

1 __

n y

[ Bs –

1.25

Ds h

__ t ]

h __

t =

Cs

____

1.25

π2 E

____

____

__

n y ( 1

.25h

/t ) 2

Stif

fene

d fla

t ele

men

ts

supp

orte

d on

bot

h ed

ges

21 F

ty

____

√ __

3 n y

a e

__

t =

Bs –

n aF

ty / (

n y √__

3

)

__

__

__

__

__

__

__

1.25

Ds

1 __

n a

[ Bs –

1.25

Ds a e

__

t ]

a e

__

t =

Cs

____

1.25

π2 E

____

____

___

n a ( 1

.25a

e /t

) 2

b

b ob o

I-A-26 January 2005

3.4.1 Tension, Axial

Axial tensile stress shall not exceed

F = Fty/ny (Eq. 3.4.1-1)

on the gross area and

F = Ftu / ( kt ) ( nu ) (Eq. 3.4.1-2)

on the effective net area (see Section 5.1.5).Values of nu and ny are listed in Table 3.4-1. Values of kt

are listed in Table 3.4-2.Block shear rupture strength provisions for the end con-

nections of tension members are given in Section 5.1.3.

3.4.2 Tension in Extreme Fibers of Beams— Flat Elements In Uniform Tension

The allowable stress is the lesser of:

F = Fty ___ ny

and F = Ftu ___ ktnu

3.4.3 Tension in Extreme Fibers of Beams— Round or Oval Tubes

The allowable stress is the lesser of:

F = 1.17Fty ______ ny

(Eq. 3.4.3-1)

and

F = 1.24Ftu ______

kt nu (Eq. 3.4.3-2)

3.4.4 Tension in Extreme Fibers of Beams— Flat Elements In Bending in Their Own Plane

a. For elements symmetric about the bending axis, the allowable stress is the lesser of:

F = 1.3Fty _____ ny

(Eq. 3.4.4-1)

and

F = 1.42Ftu ______

kt nu (Eq. 3.4.4-2)

b. For elements unsymmetric about the bending axis, the extreme fiber stress of the element shall not exceed the limiting value from a. and the stress at midheight of the element shall not exceed the stress given in Sec-tion 3.4.2.

3.4.5 Bearing on Rivets and Bolts

F = 2Ftu /nu (Eq. 3.4.5-1)

This value shall be used for a ratio of edge distance to fas-tener diameter of 2 or greater. For smaller ratios this allow-able stress shall be multiplied by the ratio: (edge distance)/ (2 × fastener diameter). Edge distance is the distance from the center of the fastener to the edge of the material in the

direction of the applied load and shall not be less than 1.5 times the fastener diameter to extruded, sheared, sawed, rolled, or planed edges.

3.4.6 Bearing on Flat Surfaces and Pins and on Bolts in Slotted Holes

F = 2Ftu / ( 1.5nu ) (Eq. 3.4.6-1)

(See Section 5.2.2 for limits on slot lengths.)

3.4.7 Compression in Columns, Axial, Gross Section

For members in axial compression, the allowable stress is the lesser of that determined from this Section and Sec-tions 3.4.8 through 3.4.10.

a. Fc = Fcy ___ ny

(Eq. 3.4.7-1)

for kL ___ r ≤ S1

b. Fc = ( Bc –

Dc kL _____ r ) __________ nu

(Eq. 3.4.7-2)

for S1 < kL ___ r < S2

c. Fc = π2E _______ nu ( kL ___ r ) 2

(Eq. 3.4.7-3)

for kL ___ r ≥ S2

where

S1 = Bc –

nuFcy _____ ny ________

Dc (Eq. 3.4.7-4)

S2 = Cc (Eq. 3.4.7-5)

k = the effective length factor by rational analysis. k shall be taken larger than or equal to unity unless rational analysis justifies a smaller value.

L = the unsupported length

r = radius of gyration of the column about the axis of buckling

3.4.7.1 Sections Not Subject to Torsional or Torsional-Flexural Buckling

For closed sections and other sections that are not sub-ject to torsional or torsional-flexural buckling, kL ___ r shall be the largest slenderness ratio for flexural buckling of the column.

3.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or Torsional- Flexural Buckling

For doubly or singly symmetric sections subject to tor-sional or torsional-flexural buckling kL ___ r shall be the larger of the largest slenderness ratio for flexural buckling and the equivalent slenderness ratio determined for torsional-flexural buckling as follows:

January 2005 I-A-27

( kL ___ r ) e = π √

___

E __ Fe

(Eq. 3.4.7.2-1)

where Fe is the elastic critical stress determined as follows:

For torsional buckling:

Fe = Fet (Eq. 3.4.7.2-2)

For torsional-flexural buckling:

Fe = Fef = 1 ___ 2β

[ ( Fex + Fet ) – √__________________

( Fex + Fet ) 2 – 4βFexFet ] (Eq. 3.4.7.2-3)

Alternatively, for torsional-flexural buckling, a conservative estimate of Fe shall be permitted to be obtained as follows:

Fe = Fef = FexFet _______

Fex + Fet (Eq. 3.4.7.2-4)

In the above equations

x-axis is the centroidal symmetry axis

A = cross-sectional area

Cw = torsional warping constant of the cross-section

E = compressive modulus of elasticity (See Table 3.3-1)

Fex = π2E ______ ( kxLb ____ rx

) 2 (Eq. 3.4.7.2-5)

Fet = 1 ____ Ar 2 O

( GJ + π2ECw ______ (KtLt)2 ) (Eq. 3.4.7.2-6)

G = shear modulus = 3E/8 (Eq. 3.4.7.2-7)

J = torsion constant

kx = effective length coefficient for buckling about the x-axis

Kt = effective length coefficient for torsional buckling. Kt shall be taken larger than or equal to unity unless rational analysis justifies a smaller value.

Lt = unbraced length for twisting

Lb = unbraced length for bending about the x-axis

ro = √___________

r 2 x + r 2 y + x 2 o (Eq. 3.4.7.2-8) polar radius of gyration of the cross-section about the shear center.

rx, ry = radii of gyration of the cross-section about the centroidal principal axes

xo = x - coordinate of the shear center

β = 1 – ( xo /ro ) 2 (Eq. 3.4.7.2-9)

3.4.7.3 Nonsymmetric Sections Subject to Torsional or Torsional-Flexural Buckling

For nonsymmetric sections subject to torsional or torsional-flexural buckling kL ___ r shall be determined by rational analysis.

3.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of Symmetry—Flat Elements Supported On One Edge

a. Fc = Fcy ___ ny

(Eq. 3.4.8-1)

for b/t ≤ S1

b. Fc = 1 __ nu [ Bp – 5.1Dp b __ t ] (Eq. 3.4.8-2)

for S1 < b/t < S2

c. Fc = k2 √

____ BpE ________

nu ( 5.1b/t ) (Eq. 3.4.8-3)

for b/t ≥ S2

where

S1 = Bp –

nu __ ny Fcy

_________ 5.1Dp

(Eq. 3.4.8-4)

S2 = k1Bp _____

5.1Dp (Eq. 3.4.8-5)

b = distance from unsupported edge of element to toe of the fillet or bend, except if the inside corner radius exceeds 4 times the thickness; then the inside radius shall be assumed equal to 4 times the thickness in calculating b. Element width b is illustrated in Figure 3.4.8-1.

3.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is not an Axis of Symmetry—Flat Elements Supported On One Edge

a. Fc = Fcy ___ ny

(Eq. 3.4.8.1-1)

for b/t ≤ S1

b. Fc = 1 __ nu [ Bp – 5.1Dp b __ t ] (Eq. 3.4.8.1-2)

for S1 < b/t < S2

c. Fc = π2E _________ nu ( 5.1b/t ) 2

(Eq. 3.4.8.1-3)

for b/t ≥ S2

where

S1 = Bp –

nu __ ny Fcy

_________ 5.1Dp

(Eq. 3.4.8.1-4)

S2 = Cp ___ 5.1

(Eq. 3.4.8.1-5)


I-A-28 January 2005

3.4.9 Uniform Compression in Elements of Columns—Flat Elements Supported on Both Edges

a. Fc = Fcy ___ ny

(Eq. 3.4.9-1)

for b/t ≤ S1

b. Fc = 1 __ nu [ Bp – 1.6Dp b __ t ] (Eq. 3.4.9-2)

for S1 < b/t < S2

c. Fc = k2 √

____ BpE ________

nu ( 1.6b/t ) (Eq. 3.4.9-3)

for b/t ≥ S2

where

S1 = Bp –

nu __ ny Fcy

_________ 1.6Dp

(Eq. 3.4.9-4)

S2 = k1Bp _____

1.6Dp (Eq. 3.4.9-5)


3.4.9.1 Uniform Compression in Elements of Columns—Flat Elements Supported on One Edge and With Stiffener on Other Edge

The provisions of this Section apply when Ds /b ≤ 0.8. The allowable stress is the lesser of

Fc = Fcy ___ ny

(Eq. 3.4.9.1-1)

and

Fc = FUT + ( FST – FUT ) ρST ≤ FST (Eq. 3.4.9.1-2)

Figure 3.4.8-1FLAT ELEMENTS SUPPORTED ON ONE EDGE

If r > 4t, then use r = 4t to calculate b.

January 2005 I-A-29

For a simple straight lip edge stiffener of constant thick-ness, Fc shall not exceed the allowable stress for the stiffener according to Section 3.4.8.


Ds = defined in Figure 3.4.9.1-1 and -2

FUT = allowable stress according to Section 3.4.8 neglecting the stiffener

FST = allowable stress according to Section 3.4.9

ρST = ratio to be determined as follows:

ρST = 1.0 for b/t ≤ S/3 (Eq. 3.4.9.1-3)

ρST = rs _________

9t ( b/t ___ S – 1 __

3 ) ≤ 1.0 for S/3 < b/t ≤ S

(Eq. 3.4.9.1-4)

ρST = rs ___________

1.5t ( b/ t ___ S + 3 )

≤ 1.0 for 2S > b/t > S (Eq. 3.4.9.1-5)

rs = radius of gyration of the stiffener determined as follows:

- For simple straight lip stiffeners of con-stant thickness similar to that shown in Figure 3.4.9.1-1, rs shall be calculated as:

rs = ds sin θ ______

√__

3

- for other stiffeners, rs shall be calculated about the mid-thickness of the element being stiffened

ds = flat width of lip stiffener shown in Figure 3.4.9.1-1

S = 1.28 √___

E ___ Fcy

b = distance from unsupported edge of element to toe of fillet or bend, except if the inside corner radius exceeds 4 times the thickness; then the inside radius shall be assumed to equal 4 times the thickness in calculating b. Element width b is illustrated in Figures 3.4.9.1-1. and 3.4.9.1-2

Figure 3.4.9-1FLAT ELEMENTS SUPPORTED ON BOTH EDGES


I-A-30 January 2005

3.4.9.2 Uniform Compression in Elements of Columns—Flat Elements Supported on Both Edges and With an Intermediate Stiffener

a. Fc = Fcy ___ ny

(Eq. 3.4.9.2-1)

for λs ≤ S1

b. Fc = (Bc – Dcλs) _________ nu

(Eq. 3.4.9.2-2)

for S1 < λs < S2

c. Fc = π2E ____

nuλs2 (Eq. 3.4.9.2-3)

for λs ≥ S2

The allowable stress Fc obtained above shall not be more than the allowable stress according to Section 3.4.9 for the sub-elements of the intermediately stiffened element.

The allowable stress Fc obtained above shall not be less than that determined according to Section 3.4.9 ignoring the intermediate stiffener.

Figure 3.4.9.1-1EDGE STIFFENED ELEMENTS




January 2005 I-A-31

In the above equations:

As = area of the stiffener

Io = moment of inertia of a section comprising the stiff-ener and one half of the width of the adjacent sub-elements and the transition corners between them taken about the centroidal axis of the section parallel to the element that is stiffened (Figure 3.4.9.2-1).

S1 = Bc ‒ nuFcy _____ ny

_____

Dc

(Eq. 3.4.9.2-4)

S2 = Cc (Eq. 3.4.9.2-5)

λs = 4.62 ( b __ t ) √_______________

1 + As / bt

_______________ 1 + √

__________

1 + 10.67Io _______

bt3 (Eq. 3.4.9.2-6)

Figure 3.4.9.2-1FLAT ELEMENTS WITH AN INTERMEDIATE STIFFENER

Line o-o is the neutral axis of the stiffener and plate of width b/2 on each side of the stiffener. Io is the moment of inertia of the portion shown in the partial section.


I-A-32 January 2005

3.4.10 Uniform Compression in Elements of Columns—Curved Elements Supported on Both Edges

a. Fc = Fcy ___ ny

(Eq. 3.4.10-1)

for b/t ≤ S1

b. Fc = 1 __ nu [ Bt – Dt √

___

Rb __ t ] (Eq. 3.4.10-2)

for S1 < b/t < S2

c. Fc = π2E __________________

16nu ( Rb __ t ) ( 1 + √

____ Rb /t _____

35 ) 2

(Eq. 3.4.10-3)

for b/t ≥ S2

where

S1 = ( Bt – nu __ ny

Fcy

________ Dt

) 2 (Eq. 3.4.10-4)

S2 = Ct (Eq. 3.4.10-5)

For tubes with circumferential welds, the equations of this Section apply for Rb /t ≤ 20.

3.4.11 Compression in Beams, Extreme Fiber, Gross Section—Single Web Shapes

For single web shapes not subject to lateral buckling (bent about the strong axis with continuous lateral support or bent about the weak axis), determine the compressive allowable stress Fc from Sections 3.4.15 through 3.4.19 as applicable.

For single web shapes subject to lateral buckling (bent about the strong axis without continuous lateral support), the compressive allowable stress Fc is the lesser of that determined from Sections 3.4.15 through 3.4.19 as appli-cable and the following:

a. Fc = Fcy ___ ny

(Eq. 3.4.11-1)

for Lb _____

ry √___

Cb ≤ S1

b. Fc =

( Bc – DcLb ________

1.2ry √___

Cb ) ____________ ny

(Eq. 3.4.11-2)

for S1 < Lb _____

ry √___

Cb < S2

c. Fc = Cbπ2E

________ ny ( Lb ____

1.2ry

) 2 (Eq. 3.4.11-3)

for Lb _____

ry √___

Cb ≥ S2

where

S1 = 1.2 ( Bc – Fcy )

___________ Dc

(Eq. 3.4.11-4)

S2 = 1.2Cc (Eq. 3.4.11-5)

ry = radius of gyration of the shape (about an axis parallel to the web) (For beams that are unsym-metrical about the horizontal axis, ry shall be calculated as though both flanges were the same as the compression flange).

Lb = length of the beam between bracing points or between a brace point and the free end of a cantilever beam. Bracing points are the points at which the compression flange is restrained against lateral movement or the cross section is restrained against twisting.

Cb = coefficient that depends on moment variation over the unbraced length. Cb shall be as given in Section 4.9.4 or taken as 1.

Alternatively, Fc may be calculated by replacing ry by rye given in Section 4.9.

3.4.12 Compression in Beams, Extreme Fiber, Gross Section—Round or Oval Tubes

a. Fc = 1.17Fcy ______ ny

(Eq. 3.4.12-1)

for Rb /t ≤ S1

b. Fc = 1 __ ny ( Btb – Dtb √

___

Rb __ t ) (Eq. 3.4.12-2)

for S1 < Rb /t < S2

c. For Rb /t ≥ S2, the allowable bending stress shall be determined from the formulas for tubes in compres-sion in Section 3.4.10 using the formula that is appro-priate for the particular value of Rb /t.


Rb = mid-thickness radius of a round element or max-imum mid-thickness radius of an oval element

S1 = ( Btb – 1.17Fcy __________ Dtb

) 2 (Eq. 3.4.12-3)

S2 = ( nu __ ny

Btb – Bt

_________ nu __ ny

Dtb – Dt

) 2

(Eq. 3.4.12-4)


3.4.13 Compression in Beams, Extreme Fiber, Gross Section—Solid Rectangular and Round Sections

For rectangular sections bent about the weak axis, rod,

and square bar: Fc = 1.3Fcy _____ ny

For rectangular sections bent about the strong axis:

a. Fc = 1.3Fcy _____ ny

(Eq. 3.4.13-1)

for d __ t √____

Lb ____

Cb d ≤ S1

January 2005 I-A-33

b. Fc = 1 __ ny ( Bbr – 2.3Dbr

d __ t √____

Lb ____

Cb d ) (Eq. 3.4.13-2)

for S1 < d __ t √____

Lb ____

Cb d < S2

c. Fc = π2E ____________ 5.29ny ( d __ t )

2 Lb ____

Cb d (Eq. 3.4.13-3)

for d __ t √____

Lb ____

Cb d ≥ S2

where

S1 = Bbr – 1.3Fcy _________

2.3Dbr (Eq. 3.4.13-4)

S2 = Cbr ___ 2.3

(Eq. 3.4.13-5)

d = depth of section

Lb = length of the beam between bracing points or between a brace point and the free end of a cantilever beam. Bracing points are the points at which the compression flange is restrained against lateral movement or the cross section is restrained against twisting.


3.4.14 Compression in Beams, Extreme Fiber, Gross Section—Tubular Shapes

For the purposes of this Specification, tubular shapes are defined as closed sections.

For tubular shapes not subject to lateral buckling (bent about the strong axis with continuous lateral support or bent about the weak axis) and round, square, hexagonal, and octagonal tubes, determine the compressive allowable stress Fc from Sections 3.4.12 and 3.4.15 through 3.4.19 as applicable.

For tubular shapes subject to lateral buckling (bent about the strong axis without continuous lateral support), the compressive allowable stress Fc is the lesser of that deter-mined from Sections 3.4.12 and 3.4.15 through 3.4.19 as applicable and the following:

a. Fc = Fcy ___ ny

(Eq. 3.4.14-1)

for LbSc __________

Cb ( √___

Iy J / 2 ) ≤ S1

b. Fc = 1 __ ny ( Bc – 1.6Dc √

___________

LbSc ___________

Cb ( √___

Iy J / 2 ) ) (Eq. 3.4.14-2)

for S1 < LbSc ________

Cb √___

IyJ / 2 < S2

c. Fc = π2E _________________ 2.56ny ( LbSc __________

Cb ( √___

Iy J / 2 ) ) (Eq. 3.4.14-3)

for LbSc _________

Cb √___

IyJ / 2 ≥ S2

where

S1 = ( Bc – Fcy ______ 1.6Dc

) 2 (Eq. 3.4.14-4)

S2 = ( Cc ___ 1.6

) 2 (Eq. 3.4.14-5)

Iy = moment of inertia of the beam about the minor axis

J = torsion constant Lb = length of the beam between bracing points or

between a brace point and the free end of a cantilever beam. Bracing points are the points at which the compression flange is restrained against lateral movement or the cross section is restrained against twisting.


Alternatively, Fc may be calculated by using the equa-tions in Section 3.4.11 and replacing ry by rye given in Sec-tion 4.9.

For narrow rectangular tubes bent about the strong axis with a depth-to-width ratio greater than or equal to 6, the term √

___ Iy J /2 may be replaced by Iy

3.4.15 Uniform Compression in Elements of Beams—Flat Elements Supported on One Edge

a. Fc = Fcy ___ ny

(Eq. 3.4.15-1)

for b/t ≤ S1

b. Fc = 1 __ ny [ Bp – 5.1Dp b __ t ] (Eq. 3.4.15-2)

for S1 < b /t < S2

c. Fc = k2 √

____ BpE _________

ny ( 5.1b / t ) (Eq. 3.4.15-3)

for b/t ≥ S2

where

S1 = Bp – Fcy ______ 5.1Dp

(Eq. 3.4.15-4)

S2 = k1Bp _____

5.1Dp (Eq. 3.4.15-5)

b = distance from unsupported edge of element to toe of the fillet or bend, except if the inside cor-ner radius exceeds 4 times the thickness; then the inside radius shall be assumed equal to 4 times the thickness in calculating b. Element width b is illustrated in Figure 3.4.8-1.

I-A-34 January 2005

3.4.16 Uniform Compression in Elements of Beams—Flat Elements Supported on Both Edges

a. Fc = Fcy ___ ny

(Eq. 3.4.16-1)

for b/t ≤ S1

b. Fc = 1 __ ny [ Bp – 1.6Dp b __ t ] (Eq. 3.4.16-2)

for S1 < b/t < S2

c. Fc = k2 √

____ BpE _________

ny ( 1.6b / t ) (Eq. 3.4.16-3)

for b/t ≥ S2

where

S1 = Bp – Fcy _______ 1.6Dp

(Eq. 3.4.16-4)

S2 = k1Bp _____

1.6Dp (Eq. 3.4.16-5)

b = distance from unsupported edge of element to toe of the fillet or bend, except if the inside cor-ner radius exceeds 4 times the thickness; then the inside radius shall be assumed equal to 4 times the thickness in calculating b. Element width b is illustrated in Figure 3.4.9-1.

3.4.16.1 Uniform Compression in Elements of Beams—Curved Elements Supported on Both Edges

a. Fc = 1.17Fcy ______ ny

(Eq. 3.4.16.1-1)

for b/t ≤ S1

b. Fc = 1 __ ny [ Bt – Dt √

___

Rb __ t ] (Eq. 3.4.16.1-2)

for S1 < b/t < S2

c. Fc = π2E ___________________

16ny ( Rb __ t ) ( 1 + √

_____ Rb / t ______

35 ) 2

(Eq. 3.4.16.1-3)

for b/t ≥ S2

where

S1 = ( Bt – 1.17Fcy __________ Dt

) 2 (Eq. 3.4.16.1-4)

S2 = Ct (Eq. 3.4.16.1-5)

Ct shall be determined using a plot of the curves of allowable stress for values of Rb /t less than and greater than S2 or by a trial and error solution.


3.4.16.2 Uniform Compression in Elements of Beams—Flat Elements Supported on One Edge and With Stiffener on Other Edge

The provisions of this Section apply when Ds /b ≤ 0.8. The allowable stress is the lesser of

Fc = Fcy ___ ny

(Eq. 3.4.16.2-1)

and

Fc = FUT + ( FST -FUT ) ρST ≤ FST (Eq. 3.4.16.2-2)

For a straight stiffener of constant thickness, Fc shall not exceed the allowable stress for the stiffener according to Section 3.4.8.


Ds = defined in Figure 3.4.9.1-1 and -2 FUT = allowable stress according to Section 3.4.15

neglecting the stiffener FST = allowable stress according to Section 3.4.16 ρST = ratio to be determined as follows: ρST = 1.0 for b/t ≤ S/3

ρST = rs __________

9t ( b / t ____ S – 1 __

3 ) ≤ 1.0 for S/3 < b/t ≤ S

ρST = rs _____________

1.5t ( b / t ____ S + 3 )

≤ 1.0 for 2S > b/t > S


- For simple straight lip stiffeners of con-stant thickness similar to that shown in Figure 3.4.9.1-1, rs shall be calculated as:


√__

3

- for other type stiffeners, rs shall be calculated about the mid-thickness of the element being stiffened

ds = flat width of stiffener shown in Figure 3.4.9.1-1

S = 1.28 √___

E ___ Fcy

b = distance from unsupported edge of element to toe of fillet or bend, unless the inside corner radius exceeds 4t; then the inside radius shall be assumed to be 4t to calculate b. Element width b is illustrated in Figure 3.4.9.1-1.

3.4.16.3 Uniform Compression in Elements of Beams—Flat Elements Supported on Both Edges and With an Intermediate Stiffener

a. Fc = Fcy ___ ny

(Eq. 3.4.16.3-1)

for λs ≤ S1

b. Fc = ( Bc – Dcλs ) _________ ny

(Eq. 3.4.16.3-2)

for S1 < λs < S2

c. Fc = π2E ____

nyλs2 (Eq. 3.4.16.3-3)

for λs ≥ S2

π2E

January 2005 I-A-35

The allowable stress Fc obtained above shall not be more than the allowable stress according to Section 3.4.16 for the sub-elements of the intermediately stiffened element.

The allowable stress Fc obtained above shall not be less than that determined according to Section 3.4.16 ignoring the intermediate stiffener.


As = area of the stiffener

Io = moment of inertia of a section comprising the stiff-ener and one half of the width of the adjacent sub-elements and the transition corners between them taken about the centroidal axis of the section parallel to the element that is stiffened (Figure 3.4.9.2-1).

S1 = Bc – Fcy _______

Dc (Eq. 3.4.16.3-4)

S2 = Cc (Eq. 3.4.16.3-5)

λs = 4.62 ( b __ t ) √______________

1 + As / bt

______________ 1 + √

__________

1 + 10.67Io ______

bt3 (Eq. 3.4.16.3-6)

3.4.17 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Tension Edge, Compression Edge Free

a. Fc = 1.3Fcy _____ ny

(Eq. 3.4.17-1)

for b/t ≤ S1

b. Fc = 1 __ ny [ Bbr – 3.5Dbr

b __ t ] (Eq. 3.4.17-2)

for S1 < b/t < S2

c. Fc = π2E _________ ny ( 3.5b/t ) 2

(Eq. 3.4.17-3)

for b/t ≥ S2

where

S1 = Bbr – 1.3Fcy _________

3.5Dbr (Eq. 3.4.17-4)

S2 = Cbr ___ 3.5

(Eq. 3.4.17-5)

3.4.18 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges

a. Fc = 1.3Fcy _____ ny

(Eq. 3.4.18-1)

for h/t ≤ S1

b. Fc = 1 __ ny [ Bbr – mDbr

h __ t ] (Eq. 3.4.18-2)

for S1 < h/t < S2

c. Fc = k2 √

____ BbrE _________

ny ( mh / t ) (Eq. 3.4.18-3)

for h/t ≥ S2

where

S1 = Bbr−1.3Fcy _________

mDbr (Eq. 3.4.18-4)

S2 = k1Bbr _____ mDbr

(Eq. 3.4.18-5)

m = 1.15 + co /(2cc) for –1 < co /cc < 1

m = 1.3/(1 – co /cc) for co /cc ≤ –1

cc = distance from neutral axis to extreme fiber of the element with the greatest compressive stress

co = distance from neutral axis to other extreme fiber of the element

Distances to compressive fibers are negative and dis-tances to tensile fibers are positive.

h = clear height of web (illustrated in Figure 3.4.18-1)

3.4.19 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges and With a Longitudinal Stiffener

The provisions of this Section apply for stiffeners located at 0.4d1 from the flange as shown in Figure 3.4.19-1.

a. Fc = 1.3Fcy _____ ny

(Eq. 3.4.19-1)

for h/t < S1

Figure 3.4.18-1DIMENSIONAL NOTATION

Figure 3.4.19-1DIMENSIONS h AND d1

I-A-36 January 2005

b. Fc = 1 __ ny [ Bbr – 0.29Dbr

h __ t ] (Eq. 3.4.19-2)

for S1 < h/t < S2

c. Fc = k2 √

____ BbrE ___________

ny ( 0.29h / t ) (Eq. 3.4.19-3)

for h/t ≥ S2

where

S1 = Bbr – 1.3Fcy _________

0.29Dbr (Eq. 3.4.19-4)

S2 = k1Bbr _______

0.29Dbr (Eq. 3.4.19-5)

h = clear web height (see Figure 3.4.19-1)

d1 = clear distance from the neutral axis to the com-pression flange (see Figure 3.4.19-1)

3.4.20 Shear in Elements—Unstiffened Flat Elements Supported on Both Edges

a. Fs = Fty / √

__ 3 ______ ny

(Eq. 3.4.20-1)

for h/t ≤ S1

b. Fs = 1 __ ny [ Bs –1.25Ds

h __ t ] (Eq. 3.4.20-2)

for S1 < h/t < S2

c. Fs = π2E __________ ny ( 1.25h/t ) 2

(Eq. 3.4.20-3)

for h/t ≥ S2

where h = clear web height (see Figure 3.4.18-1)

S1 = Bs – Fty / √

__ 3 __________

1.25Ds (Eq. 3.4.20-4)

S2 = Cs ____

1.25 (Eq. 3.4.20-5)

3.4.21 Shear in Elements—Stiffened Flat Elements Supported on Both Edges

a. Fs = Fty / √

__ 3 ______ ny

(Eq. 3.4.21-1)

for ae /t ≤ S1

b. Fs = 1 __ na [ Bs – 1.25Ds

ae __ t ] (Eq. 3.4.21-2)

for S1 < ae /t < S2

c. Fs = π2E ___________ na ( 1.25ae / t ) 2

(Eq. 3.4.21-3)

for ae /t ≥ S2

whereae =

a1 ____________ √

___________

1 + 0.7 ( a1 __ a2 )

a1 = shorter dimension of rectangular panel

a2 = longer dimension of rectangular panel

S1 =

Bs – naFty _____ ny √

__ 3

_________ 1.25Ds

(Eq. 3.4.21-4)

S2 = Cs ____

1.25 (Eq. 3.4.21-5)

2

January 2005 I-A-37

4.1 Combined Axial Load and Bending

4.1.1 Combined Compression and Bending

A member subjected to axial compression and bending moment loads shall be proportioned in accordance with the following two formulas (both equations must be checked):

fa __ Fa

+ Cmx fbx ____________

Fbx ( 1 – fa /Fex ) +

Cmy fby ____________ Fby ( 1 – fa /Fey )

≤ 1.0

(Eq. 4.1.1-1)

fa ___

Fao +

fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.1-2)

When fa /Fa < 0.15, the following Equation 4.1.1-3 shall be permitted to be used in lieu of Equations 4.1.1-1 and 4.1.1-2:

fa __ Fa

+ fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.1-3)

In Equations 4.1.1-1, 4.1.1-2, and 4.1.1-3, the subscripts x and y, combined with subscripts b, m, and e indicate the axis of bending about which a particular stress or design parameter applies and

fa = average compressive stress on cross section produced by the compressive load

fb = maximum compressive bending stress produced by the transverse loads and/or end moments

Fa = allowable compressive stress for member con-sidered as axially loaded column according either to Sections 3.4.7 through 3.4.10 or 4.7.2

Fb = allowable compressive stress for member con-sidered as a beam according to either Sections 3.4.11 through 3.4.19 or 4.7.2

Cm = 0.6 – 0.4(M1/M2) for members whose ends are prevented from sway



Fao = allowable compressive stress of an axially loaded member considered as a short column according to Section 4.7.2 without consideration of Sec-tion 3.4.7

Fe = elastic buckling stress divided by nu

= π2E ________ nu ( kL /r ) 2

r = radius of gyration about the bending axis

L = unsupported length in the plane of bending

k = effective length factor in the plane of bending

4.1.2 Combined Tension and Bending

A member subjected to axial tension and bending shall be proportioned in accordance with the formula:

fa __ Ft

+ fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.2-1)

In Equation 4.1.2-1, the subscripts x and y, combined with the subscript b indicate the axis of bending about which a particular stress or design parameter applies and where

fa = average tensile stress on cross section produced by the tensile load

fb = maximum tensile bending stress produced by the transverse loads and/or end moments

Fb = allowable tensile stress for the member as a beam according to Section 3.4.2 through 3.4.4 and 4.7.3

Ft = allowable tensile stress for the member loaded only axially according to Section 3.4.1

4.2 Torsion and Shear in Tubes

Allowable shear stresses in round or oval tubes sub-jected to torsion or shear loads shall be determined from Section 3.4.20 with the ratio h/t given by

h __ t = 2.9 ( Rb __ t ) 5/8

( Ls __ Rb

) 1/4

(Eq. 4.2-1)

where Rb = mid-thickness radius of a round tube or maximum

mid-thickness radius of an oval tube

t = thickness of tube

Ls = length of tube between circumferential stiffeners, or overall length if no circumferential stiffeners are present

4.3 Torsion and Bending in Open Shapes

The stresses in open sections caused by torsion due to twisting moments applied directly or due to lateral loads or supports not in the plane of the shear center of open sections shall include shear, flexural and warping stresses. The stresses thus computed plus those due to bending shall not exceed the appropriate allowable stress for the type of stress in the element considered.

4.4 Combined Shear, Compression, and Bending

Allowable combinations of shear, compression, and bend-ing shall be determined from either of the following formulas:

a. For walls of curved surfaces or round tubular members:

fa __ Fa

+ fb __ Fb

+ ( fs __ Fs

) 2 ≤ 1.0 (Eq. 4.4-1)

Section 4. Special Design Rules

I-A-38 January 2005

b. For webs of rectilinear shapes, plates of built-up girders or similar members:

fa __ Fa

+ ( fb __ Fb

) 2 + ( fs __ Fs

) 2 ≤ 1.0 (Eq. 4.4-2)

wherefa = average compressive stress produced by axial com-

pressive load

Fa = allowable compressive stress for members sub-jected to compression only

fb = maximum bending stress (compression) produced by applied bending moment

Fb = allowable bending stress (compression) for mem-bers subjected to bending only

fs = shear stress caused by torsion or transverse shear loads

Fs = allowable shear stress for members subjected only to torsion or shear

4.5 Longitudinal Stiffeners for Webs

If a longitudinal stiffener is used on a beam web, it shall be located so that the distance from the toe of the compres-sion flange to the centroid of the stiffener is 0.4 of the dis-tance from the toe of the compression flange to the neutral axis of the beam. The longitudinal stiffener shall have a moment of inertia, about the web of the beam, not less than that given by the expression:

Ih = 0.02αs fth3

_________ E

[ ( 1 + 6Ah ___ ht

) ( s __ h ) 2 + 0.4 ] (Eq. 4.5-1)

whereAh = gross cross sectional area of longitudinal stiffenerf = compressive stress at toe of flange

h = clear height of web between flanges

Ih = moment of inertia of the longitudinal stiffener. For a stiffener consisting of equal members on both sides of the web, the moment of inertia Ih shall be the sum of the moments of inertia about the centerline of the web. For a stiffener consisting of a member on one side only, the moment of inertia shall be taken about the face of the web in contact with the stiffener.

s = distance between transverse stiffeners

t = thickness of the web

αs = 1, for stiffener consisting of equal members on both sides of web

αs = 3.5, for stiffener consisting of member on only one side of web

4.6 Transverse Stiffeners for Webs

When a stiffener is composed of a pair of members, one on each side of the web, the stiffener spacing s shall be the clear distance between the pairs of stiffeners. When a

stiffener is composed of a member on one side only of the web, the stiffener spacing s shall be the distance between rivet lines or other connecting lines.

For a stiffener composed of members of equal size on each side of the web, the moment of inertia of the stiffener shall be computed about the centerline of the web. For a stiff-ener composed of a member on one side only of the web, the moment of inertia of the stiffener shall be computed about the face of the web in contact with the stiffener.

In the determination of the required moment of inertia of stiffeners, the distance h shall be taken as the full clear height of the web regardless of whether or not a longitudi-nal stiffener is present.

Unless the outer edge of a stiffener is continuously stiff-ened, its thickness shall not be less than 1/12th the clear width of the outstanding leg.

4.6.1 Stiffeners for Web Shear

Stiffeners applied to beam webs to resist shear buckling shall have a moment of inertia not less than the value given by the following expression:

s __ h ≤ 0.4, Is =

0.46naVh2

_________ E

( s __ h ) (Eq. 4.6.1-1)

s __ h > 0.4, Is =

0.073naVh2

_________ E

( h __ s ) (Eq. 4.6.1-2)

whereh = clear height of web

Is = moment of inertia of stiffener

na = factor of safety on appearance of buckling from Table 3.4-1

s = stiffener spacing

V = shear force on web at stiffener location

Stiffeners shall extend from flange to flange but need not be connected to either flange.

4.6.2 Bearing Stiffeners

Bearing stiffeners at points of support of concentrated loads shall be connected to the web by enough rivets, or other means, to transmit the load. Such stiffeners shall be fitted to form a tight and uniform bearing against the loaded flanges, unless welds, designed to transmit the full reaction or load, are provided between flange and stiffener.

Only that part of a stiffener cross section which lies out-side the fillet of the flange angle shall be considered as effec-tive in bearing.

The moment of inertia of the bearing stiffener shall not be less than that given by the following expression:

Ib = Is + Pbsh2nu ______ π2E

(Eq. 4.6.2-1)

whereE = compressive modulus of elasticity

h = clear height of web between flanges

E

January 2005 I-A-39

Ib = required moment of inertia of bearing stiffener

Is = moment of inertia required to resist shear buckling

nu = factor of safety

Pbs = concentrated load on stiffener

4.7 Effects of Local Buckling on Member Performance

4.7.1 Local Buckling Stresses

Where local buckling stress values are required to be calculated, the critical stresses, Fcr, given in Table 4.7.1-1 shall be used. For cases not covered in Table 4.7.1-1, the value of Fcr shall be determined using the expression for Fc in the appropriate subsection of Section 3.4 for the case b/t > S2 with nu or ny taken as 1.0.

Table 4.7.1-1

Section Local Buckling Stress, Fcr

3.4.8 and 3.4.15 π2E _______ ( 5.1b/t ) 2

3.4.9 and 3.4.16 π2E _______ ( 1.6b/t ) 2

3.4.9.1 and 3.4.16.2 ( nyFc ) 2

______ Fcy

3.4.18 π2E ______ ( mh/t ) 2

π2E ________ ( 0.65h/t ) 2

for yNA = h/2

3.4.19 π2E ________ ( 0.29h/t ) 2

4.7.2 Weighted Average Axial Compressive Stress

As an alternative to using the least of the allowable com-pressive stresses of a section’s elements for the allowable axial compressive stress of the section, the weighted aver-age allowable axial compressive stress shall be determined in accordance with this Section.

The weighted average allowable axial compressive stress of a section is the average allowable stress of the section’s elements, where the allowable stress for each element is weighted by the ratio of the area of the element to the total area of the section.

The allowable stress in elements with stiffeners shall not exceed the allowable stress in an intermediate stiffener or an edge stiffener.

The allowable axial compressive stress of the section shall not exceed that given by Section 3.4.7.

4.7.3 Weighted Average Bending Strength

As an alternative to using the least of the strengths of a section’s elements for the bending strength of the section, the strength shall be determined in accordance with this Section.

The allowable stress in elements with stiffeners shall not exceed the allowable stress in an intermediate stiffener or an edge stiffener.

For shapes not subject to lateral buckling, the allowable bending moment Ma is the lesser of the allowable compressive bending moment and the allowable tensile bending moment.

The allowable compressive bending moment is

Mac = Fcf If /ccf + Fcw Iw /ccw (Eq. 4.7.3-1)

where Fcf = the allowable compressive stress for the flat elements

in uniform compression

Fcw = the allowable compressive stress for the flat ele-ments in bending in their own plane

If = the moment of inertia of the flange group about the neutral axis of the entire section. The flange group consists of the flat elements in uniform compres-sion and the flat elements in uniform tension and their edge or intermediate stiffeners.

Iw = the moment of inertia of the web group about the neutral axis of the entire section. The web group consists of the flat elements in bending in their own plane and their intermediate stiffeners.

ccf = the distance from the centerline of the compression flange to the neutral axis of the entire cross-section

ccw = the distance from the web group’s extreme com-pression fiber to the neutral axis of the entire cross-section

(See Figure 4.7.3-1).If there are stiffeners located farther than the compression

flange from the neutral axis of the entire cross-section, the allowable compressive bending moment shall not exceed

Fcy If /(ny ccs) + Fcw Iw /ccw (Eq. 4.7.3-2)

where ccs = the distance from the neutral axis of the entire cross-

section to the extreme fiber of compression flange stiffeners

The allowable tensile bending moment is

Mat = Ftf If /ctf + Ftw Iw/ctw (Eq. 4.7.3-3)

where Ftf = the allowable tensile stress for the flat elements

in uniform tension

Ftw = the allowable tensile stress for the flat elements in bending in their own plane

If , Iw = the same as above

ctf = the distance from the extreme tension fiber to the neutral axis of the entire cross-section

ctw = the distance from the web group’s extreme ten-sion fiber to the neutral axis of the entire cross-section

I-A-40 January 2005

For shapes subject to lateral buckling, the allowable bending moment Ma is the least of the allowable compres-sive bending moment Mac, the allowable tensile bending moment Mat, and Fb S where Fb = allowable compression bending stress given by

Section 3.4.11 or 3.4.14

S = section modulus of the entire cross-section

4.7.4 Effect of Local Buckling on Column Strength

An additional limitation shall be placed on the allow-able stress for columns in which local buckling of the cross section occurs at a stress that is less than the calculated flexural buckling stress of the column, assuming that the elements are not buckled. The allowable stress shall not exceed the value given by

Frc = Fec

1/3Fcr2/3

________ nu (Eq. 4.7.4-1)

For Fcr /nu < Fc (Eq. 4.7.4-2)

whereFc = allowable stress for column given in Section 3.4.7

Fcr = element local buckling stress given in Section 4.7.1

Fec = π2E ______

( kL /r ) 2 (Eq. 4.7.4-3)

Frc = allowable stress for column with buckled elements

The allowable stress also shall not exceed the allowable stress given in Section 4.7.2.

4.7.5 Effect of Local Buckling on Beam Strength

The allowable compressive bending stress shall be reduced for single web beams whose flanges consist of thin, flat ele-ments supported on one edge and in which local buckling

of the cross section occurs at a stress that is less than the lateral buckling stress of the beam, calculated assuming that the elements are not buckled. The allowable stress shall not exceed the value given by

Frb = Feb

1/3Fcr2/3

________ ny (Eq. 4.7.5-1)

For Fcr /ny < Fc (Eq. 4.7.5-2)

whereFc = allowable stress for beam given in Section 3.4.11

or Section 4.9

Fcr = element local buckling stress given in Section 4.7.1

Feb = elastic lateral buckling stress of beam calculated using Equation 3.4.11-3 and Section 4.9 with ny = 1.0

Frb = allowable stress for beam with buckled elements

The allowable stress also shall not exceed the allowable stress for the section given in Section 4.7.2.

4.7.6 Effective Width for Calculation of Bending Deflection

The effective width concept shall be used to determine an effective section for the moment of inertia used to cal-culate deflections.

For sections containing elements covered in Sections 3.4.15, 3.4.16, 3.4.18, or 3.4.19 with b/t or h/t values exceed-ing 1.65S2 and elements covered in Sections 3.4.16.2 or 3.4.16.3 with Fcr < fa, the effective width be of a thin element subjected to direct compression stresses is:

If fa ≤ Fcr , be = b (Eq. 4.7.6-1)

If fa > Fcr , be = b √_____

Fcr /fa (Eq. 4.7.6-2)

Figure 4.7.3-1

January 2005 I-A-41

wherebe = effective width of flat element to be used in deflec-

tion calculations

b = width of element as defined in Sections referred to above

Fcr = local buckling stress for element from Section 4.7.1

fa = compressive stress for element due to applied loads

The same expression is used to calculate the effective width on the compression side of a web in bending, with the max-imum compressive bending stress due to the applied loads, fb, replacing fa. In this case the effective web area is to be placed next to the compression flange.

4.7.7 Web Crippling of Flat Webs

For interior reactions and concentrated loads:

Pc = Cwa ( N + Cw1 ) ____________

nyCwb (Eq. 4.7.7-1)

For end reactions and concentrated loads:

Pc = 1.2Cwa ( N + Cw2 ) ______________

nyCwb (Eq. 4.7.7-2)

whereCwa = t2 sin θ ( 0.46Fcy + 0.02 √

____ EFcy ) (Eq. 4.7.7-3)

Cwb = Cw3 + Ri ( 1 – cos θ ) (Eq. 4.7.7-4)

Cw1 = 5.4 in. (140 mm)

Cw2 = 1.3 in. (33 mm)

Cw3 = 0.4 in. (10 mm)

E = compressive modulus of elasticity of the web

Fcy = compressive yield strength of the web

Pc = allowable transverse force per web for flat webs

N = length of bearing at the reaction or concentrated load

Ri : for shapes made by bending, Ri = bend radius at juncture of the flange and web measured to the inside of the bend; for extruded shapes, Ri = 0

t = web thickness

θ = angle between the plane of web and the plane of the bearing surface (θ ≤ 90 degrees)

4.7.8 Combined Web Crippling and Bending for Flat Webs

Allowable combinations of interior reactions and con-centrated loads and bending shall be determined from the following formula:

( M ___ Ma

) 1.5

+ ( P __ Pc

) 1.5

≤ 1.0 (Eq. 4.7.8-1)

whereM = bending moment applied to the member

Ma = allowable bending moment for the member if bend-ing moment alone is applied to the member

P = applied interior reaction or concentrated load per web for flat webs

Pc = allowable interior reaction or concentrated load per web for flat webs calculated according to Sec-tion 4.7.7.

4.8 Fatigue

Welded details, mechanically fastened joints and base material of aluminum alloys subjected to repeated fluctua-tions of stress shall meet all the static requirements of this Specification as well as the fatigue requirements of this Section. Fatigue design of castings and associated details shall be made by testing in accordance with Section 9.

Categories of details for fatigue design parameters shall be chosen from Figure 4.8-1 and Table 4.8-1.

The maximum and minimum stresses used to calculate the stress range are nominal stresses determined by standard elastic methods. Stresses perpendicular to the expected plane of cracking shall be used.

4.8.1 Constant Amplitude Loading

For constant amplitude loading

Sra ≤ Srd (Eq. 4.8.1-1)

whereSra = applied stress range, the algebraic difference between

the minimum and maximum calculated stress in the member or detail

Srd = the allowable stress range

Srd = Cf N–1/m (Eq. 4.8.1-2)

Cf , m = constants from Table 4.8.1-1 and shown in Figure 4.8.1-1

N = the number of cycles to failure

If the applied stress range, Sra, is less than the constant amplitude fatigue limit as given in Table 4.8.1-1, then no further fatigue consideration shall be needed. The allow-able stress range, Srd shall not be less than the value from Equation 4.8.1-2 when N = 5 × 106 cycles and shall not be greater than the value from Equation 4.8.1-2 when N = 105 cycles.

4.8.2 Variable Amplitude Loading

If the maximum stress range in the spectrum is less than the fatigue limit, then no further fatigue assessment shall be needed.

For variable amplitude loading:

Sre ≤ Srd (Eq. 4.8.2-1)

whereSre = equivalent stress range

Sre = ( ∑ i = 1

Ns

αi S m ri ) 1/m

(Eq. 4.8.2-2)

I-A-42 January 2005


Srd = Cf N–1/m (Eq. 4.8.2-3)


Sri = the ith stress range in the spectrum

Cf , m = constants from Table 4.8.1-1 and shown in Figure 4.8.1-1

NS = the number of stress ranges in the spectrum


The allowable stress range Srd shall not be greater than the value from Equation 4.8.2-3 when N = 105 cycles.

Table 4.8-1STRESS CATEGORY

General Condition Detail Detail Category(1)

Fatigue Design Details(2)

Plain Material Base metal with rolled, extruded, drawn, or cold finished surfaces; cut or sheared surfaces with ANSI/ASME B46.1 surface roughness of 1000μ in. (25μm) or less.

A 1, 2

Built Up Members Base metal and weld metal in members, without attachments, built-up of plates or shapes connected by continuous full- or partial-penetration groove welds or continuous fillet welds parallel to the direction of applied stress.

Calculated flexural stress, fb, in base metal at toe of welds on girder webs or flanges adjacent to welded transverse stiffeners. Base metal at end of partial-length welded cover plates having square or tapered ends, with or without welds across the ends.

B

C

E

3, 4, 5

6, 21

5

Mechanically Fastened Base metal at the gross section of slip-critical connections and at the net section of bearing connections, where the joint configuration does not result in out-of-plane bending in the connected material and the stress ratio (the ratio of minimum stress to maximum stress)3 Rs is Rs ≤ 0 0 < Rs < 0.5 0.5 ≤ Rs

Base metal at the gross section of slip-critical connections and at the net section of bearing connections, where the joint configuration results in out-of-plane bending in connected material.

BDE

E

777

8

Fillet Welds Base metal at intermittent fillet welds.

Base metal at junction of axially loaded members with fillet welded end connections. Welds shall be disposed about the axis of the members so as to balance weld stresses.

Weld metal of continuous or intermittent longitudinal or transverse fillet welds.

E

E

F

15, 17

5, 15,18

See last page of this table for footnotes.

January 2005 I-A-43


(Continued)

General Condition Detail Detail Category1

Fatigue Design Details2

Groove Welds Base metal and weld metal at full-penetration groove welded splices of parts of similar cross section ground flush, with grinding in the direction of applied stress and with weld soundness established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welded splices at transitions in width or thickness, with welds ground to slopes no steeper than 1 to 2.5, with grinding in the direction of applied stress, and with weld soundness established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welded splices, with or without transitions having slopes no greater than 1 to 2.5, when reinforcement is not removed and/or weld soundness is not established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welds with per-manent backing

B

B

C

E

9, 10

11, 12

9, 10, 11, 12

22

Attachments Base metal detail of any length attached by groove welds subject to transverse and/or longitudinal loading, when the detail embodies a transition radius, R, not less than 2 in. (50 mm) and with the weld termination ground smooth: R ≥ 24 in. (610 mm) 24 in. > R ≥ 6 in. (150 mm) 6 in. > R ≥ 2 in. (50 mm)

Base metal at a detail attached by groove welds or fillet welds, where the detail dimension parallel to the direction of stress, a, is less than 2 in. (50 mm)

Base metal at detail attached by groove welds or fillet welds subject to longitudinal loading, with transition radius, if any, less than 2 in. (50 mm): 2 in. (50 mm ) ≤ a ≤ 12b or 4 in. (100 mm) a > 12b or 4 in. (100 mm)where a = detail dimension parallel to the direction of stress b = detail dimension normal to the direction of stress and the sur-

face of the base metal

Base metal at a detail of any length attached by fillet welds or partial-penetration groove welds in the direction parallel to the stress, when the detail embodies a transition radius, R, not less than 2 in. (50 mm) and weld termination ground smooth: R ≥ 24 in. (610 mm) 24 in. (610 mm) > R ≥ 6 in. (150 mm) 6 in. (150 mm) > R ≥ 2 in. (50 mm)

BCD

C

DE

BCD

131313

19

1414, 19, 20

161616

1. See Table 4.8.1-1. All stresses are T and Rev., where “T” signifies range in tensile stress only; “Rev.” signifies a range involving reversal of

tensile or compressive stress; except Category F where stress range is in shear including shear stress reversal.

2. See Figure 4.8-1. These examples are provided as guidelines and are not intended to exclude other reasonably similar situations.

3. Tensile stresses are considered to be positive and compressive stresses are considered to be negative.

I-A-44 January 2005

Figure 4.8-1FATIGUE DESIGN DETAILS

January 2005 I-A-45


(Continued)

I-A-46 January 2005

Table 4.8.1-1CONSTANTS FOR S-N CURVES1

Detail Category3

Cf

mFatigue Limit2

ksi MPa ksi MPa

A 96.5 665 6.85 10.2 70

B 130 900 4.84 5.4 37

C 278 1920 3.64 4.0 28

D 157 1080 3.73 2.5 17

E 160 1100 3.45 1.8 13

F 174 1200 3.42 1.9 13

1. Different constants are to be used for calculations in ksi and MPa

2. Fatigue limit is based on N = 5x106

3. See Table 4.8-1

Figure 4.8.1-1SCHEMATIC FATIGUE CURVE

January 2005 I-A-47

4.9 Compression in Single Web Beams Including Single Web Beams With Tubular Portions

For compression in single web beams including single web beams with tubular portions, analysis shall be con-ducted using either the provisions of Section 3.4.11 or by replacing ry in Section 3.4.11 with rye determined in accor-dance with Sections 4.9.1 through 4.9.3. Sections with the tension flange partially or fully braced and with the com-pression flange laterally unbraced shall be designed using Section 4.9 without consideration of tensile flange restraint or another rational method of analysis.

4.9.1 Doubly Symmetric Sections and Sections Symmetric About the Bending Axis

For checking beam sections at brace or support points or between brace or support points of beam spans subjected to end moment only or to transverse loads applied at the neutral axis of the beam:

rye = 1 ___ 1.7

√____________________

Iy d ___ Sc

√________________

1 + 0.152 J __ Iy

( kyLb ____ d ) 2 (Eq. 4.9.1-1)

For checking beam spans between brace or support points of beams subjected to transverse loads applied on the top or bottom flange (where the load is free to move laterally with the beam if the beam buckles):

rye = 1 ___ 1.7

√_______________________________

Iyd

___ Sc

[ ± 0.5 + √__________________

1.25 + 0.152 J __ Iy

( kyLb ____ d ) 2 ]

(Eq. 4.9.1-2)

The minus sign in front of the term ‘0.5’ shall be used when the load is on a flange acting towards the shear cen-ter; the plus sign shall be used when the load is on a flange acting away from the shear center.


y-axis is the centroidal symmetry or principal axis such that the tension flange has a positive y coordinate and bending is about the x-axis

rye = effective radius of gyrationIy = moment of inertia of beam about axis parallel to webSc = section modulus of beam, compression sideJ = torsion constant of beam. For non-tubular open sec-

tions an approximate value of J shall be calculated by assuming the section to be composed of rectangles and letting J equal the sum of the terms bt3/3 for each rectangle where b is the larger dimension. The term for each rectangle whose b/t ratio is less than 10 shall be computed by the expression (1/3 – 0.2t/b) bt3.

For sections containing open parts and tubular por-tions, J shall be taken as the sum of J for the open parts and the tubular parts.

ky = effective length coefficient for compression flange about the y-axis. ky shall not be taken less than 1.

Lb = length of the beam between bracing points or between a brace point and the free end of a cantilever beam. Bracing points are the points at which the compres-sion flange is restrained against lateral movement or the cross section is restrained against twisting

d = depth of beam.

4.9.2 Singly Symmetric Sections Unsymmetric about the Bending Axis

For a beam that is unsymmetric about the bending axis, the rye in Section 4.9.1 is calculated by taking Iy, Sc, and J as though both flanges were the same as the compression flange with the overall depth remaining the same.

4.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis, Doubly Symmetric Sections and Sections Without an Axis of Symmetry

For a loading that does not cause torsion or lateral bend-ing a more accurate value of rye is determined according to this section. If the loading causes torsion and/or lateral bend-ing, warping stress and/or lateral bending flexural stress, the provisions of Section 4.3 shall apply.

rye = Lb ____

1.2π √____

Me ___ ESc

(Eq. 4.9.3-1)

whereMe = the elastic critical moment determined as follows:

Me = AFey [ U + √___________

U2 + r 2 o ( Fet ___ Fey

) ] (Eq. 4.9.3-2)

Me for cantilever beams shall be determined by rational analysis unless the free end is braced or if the beam load-ing is covered in Section 4.9.4. References for rational analysis are given in the Commentary.


y-axis is the centroidal symmetry or principal axis such that the tension flange has a positive y coordinate and bending is about the x-axis

A = cross-sectional area

C1 and C2 = coefficients to be taken from Section 4.9.4, or, for cases not covered in Section 4.9.4,deter-mined by rational analysis

Cw = torsional warping constant of the cross section

E = compressive modulus of elasticity (see Table 3.3-1)

Fey = π2E ______ ( kyLb ____ ry

) 2 (Eq. 4.9.3-3)

Fet = 1 ____ Ar 2 o

( GJ + π2ECw ______ ( Kt Lt ) 2

) (Eq. 4.9.3-4)

G = shear modulus = 3E/8

I-A-48 January 2005

g0 = distance from the shear center to the point of applica-tion of the load; taken as + when the load is applied directed away from the shear center and – when the load is directed towards the shear center. When there is no transverse load (pure moment cases) g0 = 0.

Iy = moment of inertia of the section about the y axis

J = torsion constant (See definition in Section 4.9.1)

j = 1 ___ 2Ix

( ∫ A

y3dA + ∫ A

yx2dA ) – yo (Eq. 4.9.3-5)

For doubly symmetric I sections, j = 0For singly symmetric I sections, as an alternative to equa-tion 4.9.3.-5,

j = 0.45df ( 2Icy ___ Iy

– 1 ) [ 1 – ( Iy __ Ix

) 2 ] (Eq. 4.9.3-6)

where Icy is the moment of inertia of the compression flange taken about the web, Ix and Iy are the moments of inertia of the entire section about the x- and y-axes and df is the distance between the flange centroids or for T-sections df is the distance between the flange centroid and the tip of the stem.

For singly symmetric I sections where the smaller flange is not less than 80 percent of the area of the larger flange j shall be permitted to be taken as – yo.

ky = effective length coefficient for compression flange about the y-axis. ky shall not be taken less than 1.0.

Lt = unbraced length for twisting.

ro = √________________

r 2 x + r 2 y + x 2 o + y 2 o (Eq. 4.9.3-7)

Polar radius of gyration of the cross-section about the shear center.

rx , ry = actual radii of gyration of the cross-section about the centroidal principal axes

Sc = section modulus for the extreme compression fiber for bending about the x-axis

U = C1g0 – C2j (Eq. 4.9.3-8)

xo = x - coordinate of the shear center

yo = y - coordinate of the shear center

The origin of the coordinate system is the intersection of the principal axes.

4.9.4 Lateral Buckling Coefficients

For cases not covered in Sections 4.9.4.3 and 4.9.4.4, coefficients Cb, C1 and C2 shall be determined as specified in Section 4.9.4.1 or 4.9.4.2.

4.9.4.1 Doubly Symmetric Sections

Cb: Cb = 12.5MMAX _________________________

2.5MMAX + 3MA + 4MB + 3MC

(Eq. 4.9.4.1-1)

whereMMAX = absolute value of maximum moment in the

unbraced beam segment

MA = absolute value of moment at quarter point of the unbraced beam segment

MB = absolute value of moment at mid-point of the unbraced beam segment

MC = absolute value of moment at three-quarter point of the unbraced beam segment

Cb values for doubly symmetric section cantilever beams unbraced at the free end are given in Section 4.9.4.4. Cb values for cantilever beams braced at the free end can be evaluated using Eq. 4.9.4.1-1.

C1: When the moments vary linearly between the ends of the unbraced segment C1 = 0. For some special cases the values of C1 are given in Section 4.9.4.3. For other variations, unless more accurate values are available, C1 shall be taken as 0.5.

C2: Since j = 0, a value of C2 is not needed.

4.9.4.2 Singly Symmetric Sections

Cb: For sections with Icy /Iy less than or equal to 0.1 or greater than or equal to 0.9, Cb = 1.0

For sections with Icy /Iy greater than 0.1 and less than 0.9, the value of Cb shall be determined according to Eq. 4.9.4.1-1.

When MMAX produces compression on the larger flange and the smaller flange is also subjected to compres-sion in the unbraced length, then the member shall be checked at the location of MMAX as well as at the location where the smaller flange is subjected to its maximum compression. Cb at the location of MMAX shall be calculated using Eq. 4.9.4.1-1. Cb for the location where the smaller flange is subjected to its maximum compression shall be taken as 1.67.

C1: When the moments vary linearly between the ends of the unbraced segment C1 = 0. For some special cases the values of C1 are given in Section 4.9.4.3. For other cases C1 shall be determined by rational analysis.


4.9.4.3 Special Cases—Doubly or Singly Symmetric Sections

For simply supported beams with loadings listed below, the following Cb, C1 and C2 values shall be used, except for sections with Icy /Iy less than or equal to 0.1 or greater than or equal to 0.9 where Cb shall be taken as 1.0:

January 2005 I-A-49

a. Uniformly distributed load over the entire span Cb = 1.13, C1 = 0.41Cb, C2 = 0.47Cb

b. One concentrated load placed at a distance aL from one of the ends of span

Cb = 1.75 – 1.6a ( 1 – a ) (Eq. 4.9.4.3-1)

C1 = Cb _______

a ( 1-a ) π2 sin2πa (Eq. 4.9.4.3-2)

C2 = Cb – C1 ______

2 (Eq. 4.9.4.3-3)

c. Two concentrated loads placed symmetrically at a dis-tance aL from each end of span

Cb = 1 + 2.8a3 (Eq. 4.9.4.3-4)

C1 = 2Cb ____ aπ2 sin2πa (Eq. 4.9.4.3-5)

C2 = ( 1 – a ) Cb – C1 ___ 2 (Eq. 4.9.4.3-6)

4.9.4.4 Cantilever Beams

For cantilever beams braced at the support and unbraced at the free end Cb shall be taken as follows:

Concentrated load at free end applied at the centroid Cb = 1.28, ky = 1.0

Uniform transverse load applied at the centroid Cb = 2.08, ky = 1.0

Uniform bending moment Cb = 0.50, ky = 2.1

4.10 Compression in Elastically Supported Flanges

Allowable compressive stresses in elastically supported flanges, such as the compression flange of a standing seam roof or of a hat-shaped beam loaded with the two flanges in compression, shall be determined from Section 3.4.11 with the following effective value of Lb /ry, substituted in the formulas for allowable stress.

Effective Lb __ ry

= 2.7 ( EA 2 c ____ βsIyc

) 1/4

(Eq. 4.10-1)

where Ac = area of compression element (compression flange

plus 1/3 of the area of the web between the com-pression flange and the neutral axis

E = compressive modulus of elasticity

Iyc = moment of inertia of compression element about an axis parallel to the vertical web

βs = spring constant (transverse force applied to the com-pression flange of the member of unit length divided by the deflection due to the force)

4.11 Single Angles in Flexure

The strength of a single angle in flexure (Mn) is given in this Section. The design strength is Mn /ny.

a. For local buckling:1) If a leg tip is a point of maximum compression

(Figure 4.11-1):

Figure 4.11-1

Mn = 1.3Fcy Sc (Eq. 4.11-1)for b/t ≤ S1

Mn = [Bbr – 4Dbr(b/t)]Sc (Eq. 4.11-2)for S1 < b/t < S2

Mn = π2ESc /(4(b/t))2 (Eq. 4.11-3)for b/t ≥ S2

where S1 = (Bbr – 1.3Fcy)/(4Dbr) (Eq. 4.11-4)

S2 = Cbr /4 (Eq. 4.11-5)

2) If a leg is in uniform compression (Figure 4.11-2)

Figure 4.11-2

Mn = Fcy Sc (Eq. 4.11-6)for b/t ≤ S1

Mn = [Bp – 5.1Dp(b/t)]Sc (Eq. 4.11-7)for S1 < b/t < S2

Mn = π2ESc /(5.1(b/t))2 (Eq. 4.11-8)for b/t ≥ S2

where:S1 = (Bp – Fcy)/(5.1Dp) (Eq. 4.11-9)

S2 = Cp /5.1 (Eq. 4.11-10)

b. For yielding (Figure 4.11-3):

Figure 4.11-3

Mn = 1.3My (Eq. 4.11-11)

where My = yield moment about the axis of bending.

c. For lateral-torsional buckling:

for Me ≤ My, Mn = (0.92 – 0.17Me /My)Me

(Eq. 4.11-12)

I-A-50 January 2005

for Me > My, Mn = ( 1.92 – 1.17 √______

My /Me ) My ≤ 1.3My (Eq. 4.11-13)

where Me = elastic lateral-torsional buckling moment from Section 4.11.1 or 4.11.2 as applicable.

Cb shall be determined in accordance with Section 4.9.4.1 but shall not exceed 1.5.

4.11.1 Bending About Geometric Axes

Bending about a geometric axis is shown in Figure 4.11.1-1.

Figure 4.11.1-1

a. Angles with continuous lateral-torsional restraint: Mn is the lesser of:1) local buckling strength determined by Section 4.11a.2) yield strength determined by Section 4.11b.

b. Equal leg angles with lateral-torsional restraint only at the point of maximum moment: Strengths shall be calcu-lated with Sc being the geometric section modulus. Mn is the least of:1) local buckling strength determined by Section 4.11a.2) yield strength determined by Section 4.11b. 3) If the leg tip is in compression, lateral-torsional buck-

ling strength determined by Section 4.11c with

Me = 0.82Eb4tCb _________

L 2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 – 1 ] (Eq. 4.11.1-1)

If the leg tip is in tension, lateral-torsional buckling strength determined by Section 4.11c with

Me = 0.82Eb4tCb _________

L2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 + 1 ] (Eq. 4.11.1-2)

c. Equal leg angles without lateral-torsional restraint: Strengths shall be calculated with Sc being 0.80 of the geometric section modulus.

If the leg tip is in compression, Mn is the lesser of:1) local buckling strength determined by Section 4.11a(1)2) lateral-torsional buckling determined by Section 4.11c

with

Me = 0.66Eb4tCb _________

L2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 – 1 ] (Eq. 4.11.1-3)

If the leg tip is in tension, Mn is the lesser of:1) yield strength determined by Section 4.11b2) lateral-torsional buckling determined by Section 4.11c

with

Me = 0.66Eb4tCb _________

L2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 + 1 ] (Eq. 4.11.1-4)

d. Unequal leg angles without lateral-torsional restraint: moments about the geometric axes shall be resolved into moments about the principal axes and the angle shall be designed as an angle bent about a principal axis (Section 4.11.2).

4.11.2 Bending About Principal Axes

Bending about principal axes is shown in Figure 4.11.2-1.

Figure 4.11.2-1

a. Equal leg angles, major axis bending: Mn is the lesser of:1) local buckling strength determined by Section 4.11a2) lateral-torsional buckling strength determined by

Section 4.11c, with

Me = Cb 0.46Eb2t2

________ Lb

(Eq. 4.11.2-1)

b. Unequal leg angles, major axis bending: Mn is the lesser of:1) local buckling strength determined by Section 4.11a

for the leg with its tip in compression2) lateral-torsional strength determined by Section 4.11c,

with

Me = 4.9E Iz __ L2

b

Cb [ √________________ βw

2 + 0.052 ( Lbt / rz ) 2 + βw ] (Eq. 4.11.2-2)

Iz = minor principal axis moment of inertia

rz = minor principal axis radius of gyration

βw = [ 1 __ Iw

∫z ( w2 + z2 ) dA ] – 2zo, (Eq. 4.11.2-3)

βw is a section property for unequal leg angles and is positive when the short leg is in compression and negative when the long leg is in compression. (See the Commentary for values for common angle sizes and equations for determining βw.) If the long leg is in compression anywhere along the unbraced length of the angle, βw is negative.

zo = coordinate along the z-axis of the shear center with respect to the centroid

Iw = major principal axis moment of inertia

c. Equal and unequal leg angles, minor axis bending:1) If the leg tips are in compression, Mn is the lesser

of the local buckling strength determined by Section 4.11a(1) and the yield strength determined by Sec-tion 4.11b.

Minor Axis Bending

Major Axis Bending

Subsections a. and b.

Subsection c.

January 2005 I-A-51

2) If the leg tips are in tension, Mn is the yield strength determined by Section 4.11b.

4.12 Tapered Thickness Elements

For uniform compression on elements with linearly vary-ing thickness where δ ≤ 2.0:

a. For tapered thickness elements with the thick edge sup-ported and the thin edge free, the slenderness ratio is

(1 – 0.12δ) ( b ___ tavg )

b. For tapered thickness elements with the thin edge sup-ported and the thick edge free, the slenderness ratio is

( b ___ tavg )

c. For tapered thickness elements supported on both edges,

the slenderness ratio is ( b ___ tavg )

where b = width of the element

tavg = tmax + tmin ________

2

= the average thickness of the element

tmin = lesser thickness

tmax = greater thickness

δ = (tmax – tmin) ________

tmin

Figure 4.12-1

4.13 Compressive Strength of Beam Elements

As an alternative to Section 3, the compressive strength of elements of beams composed entirely of flat elements addressed by Sections 3.4.15, 3.4.16, 3.4.16.2, 3.4.16.3, or 3.4.18 shall be determined as follows in Sections 4.13.1 and 4.13.2. The allowable stress for the shape shall then be determined using Section 4.7.3, except that the strength of any stiffened element need not be limited to the strength of the stiffener.

4.13.1 Compressive Strength of Beam Elements— Flat Elements in Uniform Compression

a. Fc = Fcy ___ ny

(Eq. 4.13.1-1)

for λeq ≤ S1

b. Fc = Bp –Dpλeq ________ ny

(Eq. 4.13.1-2)

for S1 < λeq < S2

c. Fc = k2 √

____ BpE ______

nyλeq (Eq. 4.13.1-3)

for λeq ≥ S2

where

S1 = Bp – Fcy ______

Dp (Eq. 4.13.1-4)

S2 = k1Bp ____ Dp

(Eq. 4.13.1-5)

λeq = π √___

E ___ Fcr

(Eq. 4.13.1-6)

Fcr = Mcr /Sc

where Mcr is the elastic buckling moment of the beam under pure bending with continuous lateral support deter-mined by linear elastic analysis and Sc is the compressive section modulus of the entire cross section.

4.13.2 Compressive Strength of Beam Elements— Flat Elements in Bending In Their Own Plane

a. Fc = 1.3Fcy _____ ny

(Eq. 4.13.2-1)

for λeq ≤ S1

b. Fc = Bbr – Dbrλeq _________ ny

(Eq. 4.13.2-2)

for S1 < λeq < S2

c. Fc = k2 √

____ Bbr E _______

nyλeq (Eq. 4.13.2-3)

for λeq ≥ S2

where

S1 = Bbr – 1.3Fcy _________

Dbr (Eq. 4.13.2-4)

S2 = k1Bbr ____ Dbr

(Eq. 4.13.2-5)

λeq = π √___

E ___ Fcr

(Eq. 4.13.2-6)

Fcr = Mcr /Sc

where Mcr is the elastic buckling moment of the beam under pure bending with continuous lateral support deter-mined by linear elastic analysis and Sc is the compressive section modulus of the entire cross section.

I-A-52 January 2005

5.1 General

5.1.1 Minimum Edge Distance

If the distance from the center of a fastener to the edge of the connected part in the direction of the force on the fas-tener is less than 2D, the allowable bearing strength of the connected part shall be factored by this distance divided by 2D, where D is the nominal diameter of the fastener. (See Sections 3.4.5 and 3.4.6).

The distance from the center of a fastener to an edge of a part shall not be less than 1.5D.

5.1.2 Maximum Spacing of Fasteners

The pitch and gage of fasteners joining components of tension members shall not exceed (3 + 20t) in. [(75 + 20t) mm] where t is the thickness of the outside component.

In outside components of compression members:

1) the pitch of fasteners in the direction of stress shall be based on the allowable stress from Section 3.4.7 with an effective length kL = s/2, where s is the pitch, and

2) the gage of fasteners perpendicular to the direction of stress shall be based on the allowable stress from Section 3.4.9 with a width b = 0.8g where g is the gage. If only one line of fasteners is used, the allow-able stress shall be based on Section 3.4.8.1 with a width b = the edge distance of the fastener.

5.1.3 Block Shear Rupture

The block shear rupture allowable force Psr of bolted connections on a failure path with shear on some segments and tension on the other segments is:

For Ftu Ant ≥ Fsu Anv

Psr = ( ( Fty / √__

3 ) Agv + Ftu Ant ) /nu (Eq. 5.1.3-1)

OtherwisePsr = ( FsuAnv + Fty Agt ) /nu (Eq. 5.1.3-2)

The block shear rupture allowable force Psr of welded connections on a failure path with shear on some segments and tension on the other segments is:

For Ftu Agt ≥ Fsu Agv

Psr = ( ( Fty / √__

3 ) Agv + Ftu Agt ) /nu (Eq. 5.1.3-3)

OtherwisePsr = ( FsuAgv + Fty Agt ) /nu (Eq. 5.1.3-4)

where Agv = gross area in shear

Agt = gross area in tension

Anv = net area in shear

Ant = net area in tension

5.1.4 Net Area

The net area An of a member is the sum of the products of the thickness and the least net width of each element computed as follows:

The width of holes shall be taken as the nominal hole diameter for drilled or reamed holes and the nominal hole diameter plus 1/32 in. (0.8 mm) for punched holes.

For a chain of holes extending across a part in any diagonal or zigzag line, the net width of the part shall be obtained by deducting from the gross width the sum of the hole widths of all holes in the chain, and adding, for each gage space in the chain, the quantity s2/4g where

s = longitudinal center-to-center spacing (pitch) of any two consecutive holes

g = transverse center-to-center spacing (gage) between fastener gage lines

For angles, the gage for holes in opposite legs shall be the sum of the gages from the back of the angles less the thickness.

Weld metal in plug or slot welds shall not be included in the net area.

5.1.5 Effective Net Area

The effective net area for angles, channels, tees, zees, and I-shaped sections shall be determined as follows:

1) If tension is transmitted directly to each of the cross-sectional elements of the member by fasteners or welds, the effective net area Ae is the net area.

2) If tension is transmitted by fasteners or welds through some but not all of the cross-sectional elements of the member, the effective net area Ae is:

Ae = An ( 1 – _ x __

L ) ( 1 –

_ y __

L ) (Eq. 5.1.5-1)

whereAn = net area of the member at the connection

L = length of the connection in the direction of load, mea-sured from the center of fasteners or the end of welds

_ x = eccentricity of the connection in the x axis direction

_ y = eccentricity of the connection in the y axis direction

If the length of the connection L is zero, the net effective area is the net area of the connected elements.

5.1.6 Long Grips

If the grip (total thickness of parts being fastened) of an aluminum fastener exceeds 4.5D, the fastener’s nominal shear strength shall be reduced by dividing by [½+Gf /(9D)] where Gf is the grip and D is the fastener’s nominal diameter.

Section 5. Mechanical Connections

January 2005 I-A-53

5.1.7 Strength and Arrangement of Connections

If the center of resistance of a connection does not coin-cide with the resultant line of action of the load, members and connections shall be proportioned to account for load eccentricities at the connection.

5.1.8 Countersunk Holes

The bearing length for countersunk holes shall be the part thickness less one-half the depth of the countersink.

5.2 Bolted Connections

5.2.1 Bolt Material

Bolt fastener material shall be one of the following:

a. Aluminum: Bolts shall meet ASTM F468 and be 2024-T4, 6061-T6, or 7075-T73. When 2024 bolts will be exposed to contact with liquid water or humidity near the dew point in the intended service, they shall have a minimum 0.0002 in. (0.005 mm) thick anodic coating. Nuts shall meet ASTM F467. Nuts for ¼ in. (M6) bolts and smaller shall be 2024-T4; larger nuts shall be 6061-T6 or 6262-T9. Flat washers shall be Alclad 2024-T4. Spring lock wash-ers shall be 7075-T6.

b. Carbon steel: Carbon steel bolts, nuts, and washers shall be hot-dip galvanized to ASTM A153 or electro- galvanized to ASTM B633. Galvanizing thickness shall be adequate to provide corrosion protection for the antici-pated service. Hot-dipped galvanized A490 bolts shall not be used. Galvanized steel fasteners shall be lubricated to eliminate galling and assure adequate preload. When other platings and/or coatings are used, evidence shall be submitted to substantiate their corrosion resistance when in contact in aluminum. Bolt hardness shall be less than Rockwell C35.

c. Stainless steel: Stainless steel bolts, nuts and wash-ers shall be 300 series stainless steel. Bolts shall meet ASTM F593. Nuts shall meet ASTM F594.

5.2.2 Holes and Slots for Bolts

The nominal diameter of holes for bolts shall not be more than 1/16 in. (2 mm) greater than the nominal diameter of the bolt unless slip-critical connections are used.

The nominal width of slots for bolts shall not be more than 1/16 in. (2 mm) greater than the nominal diameter of the bolt. If the nominal length of the slot exceeds 2.5D or the edge distance is less than 2D, where D is the nominal bolt diameter, the edge distance perpendicular to the slot length and slot length shall be sized to avoid overstress-ing the material along the slot. Unless slip-critical connec-tions are used, the length shall be normal to the direction of load.

5.2.3 Bolt Tension

The allowable tension load on an aluminum bolt is the root area of the bolt (π/4[D − 1.191/n]2) times its allowable tensile stress, which is Ftu /(1.2nu), where n = number of threads/in.. (See Table 5.2.3-1 or Table 5.2.3-1M).

5.2.4 Bolt Shear

The allowable shear load on an aluminum bolt is its effective shear area times its allowable shear stress, which is Fsu /(1.2nu). (See Table 5.2.3-1 or Table 5.2.3-1M). The effective shear area for bolts with no threads in the shear plane shall be based on the nominal diameter. The effective shear area for bolts with threads in the shear plane shall be based on the root diameter (D − 1.191/n).

5.2.5 Bolt Bearing

The allowable bearing load applied by a bolt to an alumi-num part is the part’s allowable bearing stress (see Sections 3.4.5 and 3.4.6) times the effective bearing area of the bolt. The bolt’s effective bearing area is its nominal diameter multi-plied by the bearing length (see Section 5.1.8 for countersunk holes). This applies to threaded and unthreaded surfaces.

Table 5.2.3-1DESIGN STRESSES FOR BOLTS

Alloy and Temper

Minimum Shear Ultimate

Strength1

Fsu

(ksi)

Minimum Tensile Ultimate

Strength1

Ftu

(ksi)

Building Type Structures Bridge Type Structures

Design Shear Stress on

Effective Area2

(ksi)

Design Tensile Stress on

Root Area 2

(ksi)


Effective Area3

(ksi)


Root Area 3

(ksi)

2024-T4 37 62 16 26 14 23

6061-T6 25 42 10.5 18 9.5 16

7075-T73 41 68 18 29 16 26

1. From ASTM B316/B316M and F4682. SF = 2.343. SF = 2.64

I-A-54 January 2005

Table 5.2.3-1MDESIGN STRESSES FOR BOLTS

Alloy and Temper

Minimum Shear Ultimate

Strength1

Fsu

(MPa)

Minimum Tensile Ultimate

Strength1

Ftu

(MPa)



Effective Area2

(MPa)


Root Area 2

(MPa)


Effective Area3

(MPa)


Root Area 3

(MPa)

2024-T4 255 425 110 180 95 160

6061-T6 170 290 75 125 65 110

7075-T73 280 470 120 200 105 180

1. From ASTM B316/B316M2. SF = 2.343. SF = 2.64

5.2.6 Minimum Spacing of Bolts

The minimum distance between bolt centers shall be 2.5 times the nominal bolt diameter.

5.2.7 Lockbolts

Lockbolts shall meet the requirements in this Specifica-tion for conventional bolts and be installed in conformance with the lockbolt manufacturer’s specifications. The bear-ing areas under the head and collar shall not be less than those of a conventional bolt and nut.

5.2.8 Slip-Critical Bolted Connections

5.2.8.1 General

Slip-critical connections between aluminum members or between aluminum and steel members shall comply with the Research Council on Structural Connections (RCSC) Speci-fication for Structural Joints Using ASTM A325 or A490 Bolts, Allowable Stress Design, except as modified here. The shear on a bolt in a slip-critical connection shall not exceed the allowable shear for the bolt (Section 5.2.8.4), the allow-able bearing for the connected members (Section 3.4.5), or the allowable slip load (Section 5.2.8.5).

5.2.8.2 Material

Aluminum used in slip-critical connections shall have a tensile yield strength of at least 15 ksi (105 MPa). Bolts shall comply with ASTM A325, nuts shall comply with ASTM A563 Grade DH or ASTM A194 Grade 2H, and washers shall comply with ASTM F436. Bolts, nuts, and washers shall be zinc coated by the hot-dip or mechanically deposited processes as specified in ASTM A325.

5.2.8.3 Holes

Holes shall be standard holes, oversize holes, short slot-ted holes, or long slotted holes. The nominal dimensions for

each hole type shall not exceed those shown in the RCSC Specification Table 1.

5.2.8.4 Design for Strength

The shear stress on a bolt shall not exceed 21 ksi (145 MPa) for bolts with threads in the shear plane and 30 ksi (205 MPa) for bolts without threads in the shear plane. Bolt shear stresses are based on the nominal cross sectional area (unthreaded body area) of a bolt. The bearing stress on the connected parts shall not exceed the allowable bearing stress specified in Section 3.4.5.

5.2.8.5 Design for Slip Resistance

Aluminum surfaces abrasion blasted with coal slag to SSPC SP-5 to an average substrate profile of 2.0 mils (0.05 mm) in contact with similar aluminum surfaces or zinc painted steel surfaces with a maximum dry film thickness of 4 mils (0.1 mm) are Class B surfaces. Slip coefficients for other surfaces shall be determined in accordance with the RCSC Specification Appendix A.

In addition to the requirements of Section 5.2.8.4, bolts shall be proportioned so that the allowable slip load per unit of bolt area determined from the following table is not exceeded. The nominal diameter of the bolt shall be used to calculate its area.

Bolts shall be installed to develop the minimum bolt tension specified in Section 5.2.8.7.

The effect on slip resistance of temperature changes from the installation temperature and the difference in coefficients of thermal expansion of aluminum and steel shall be addressed.

5.2.8.6 Washers

a. Washers shall be used under bolt heads and under nuts.b. At a long slotted hole in an outer ply, a galvanized steel

plate washer or bar at least 5/16 in. (8 mm) thick with

January 2005 I-A-55

standard holes, shall be used. The plate washer or bar shall completely cover the slot but need not be hardened.

c. Where the outer face of the bolted parts has a slope greater than 1:20 with respect to a plane normal to the bolt axis, a beveled washer shall be used.

5.2.8.7 Installation

Bolts shall be tightened in accordance with the RCSC Specification.

5.3 Riveted Connections

5.3.1 Rivet Material

Rivet material shall be one of the following:

a. Aluminum: Aluminum shall meet ASTM B 316.b. Carbon steel: Carbon steel shall not be used unless the

aluminum is joined to carbon steel (see Section 6.7.1), or corrosion resistance of the structure is not required, or the structure is protected against corrosion.

c. Stainless steel: Stainless steel shall be 300 series.

5.3.2 Holes for Cold-Driven Rivets

The finished diameter of holes for cold-driven rivets shall not be more than 4% greater than the nominal diameter of the rivet.

5.3.3 Rivet Tension

Rivets shall not be used to carry tensile loads.

5.3.4 Rivet Shear

The allowable shear load on an aluminum rivet is its effective shear area times its allowable shear stress, which is Fsu /(1.2nu). (See Table 5.3.4-1 or Table 5.3.4-1M). The effective shear area of solid rivets shall be based on the nominal hole diameter. (See Section 5.3.2 for hole size lim-its and Section 5.3.8 for hollow-end rivets).

Contact Surface of Bolted Parts

Hole Type and Direction of Load

Any Direction Transverse Parallel

StandardOversize & Short Slots

Long SlotsLong Slots

ksi MPa ksi MPa ksi MPa ksi MPa

Class B (Slip Coefficient 0.50)

28 195 24 165 20 140 17 115

Table 5.3.4-1DESIGN STRESSES FOR RIVETS

Designation Before Driving

Minimum Shear Ultimate Strength1

Fsu

(ksi)


Design Shear Stress on Effective Area2

(ksi)


(ksi)

2017-T4 33 14 12.5

2024-T42 37 16 14

2117-T4 26 11 10

2219-T6 30 13 11.5

6053-T61 20 8.5 7.5

6061-T6 25 10.5 9.5

7050-T7 39 17 15

7075-T6 42 18 16

7075-T73 41 18 16

7178-T6 46 20 17

1. From ASTM B316/B316M for heat treated alloys.2. SF = 2.343. SF = 2.64

I-A-56 January 2005

Table 5.3.4-1MDESIGN STRESSES FOR RIVETS



Fsu

(MPa)



(MPa)


(MPa)

2017-T4 225 95 85

2024-T42 255 110 95

2117-T4 180 75 70

2219-T6 205 90 80

6053-T61 135 60 50

6061-T6 170 75 65

7050-T7 270 115 100

7075-T6 290 125 110

7075-T73 280 120 105

7178-T6 315 135 120

1. From ASTM B316/B316M for heat treated alloys.2. SF = 2.343. SF = 2.64

5.3.5 Rivet Bearing

The allowable bearing load applied by a rivet to an alu-minum part is the part’s allowable bearing stress (see Sec-tion 3.4.5) times the effective bearing area of the rivet. The rivet’s effective bearing area is the nominal hole diameter multiplied by the bearing length (see Section 5.1.8 for coun-tersunk holes).

5.3.6 Minimum Spacing of Rivets

The minimum distance between rivet centers shall be 3 times the nominal rivet diameter.

5.3.7 Blind Rivets

Grip lengths and hole sizes for blind rivets shall comply with the rivet manufacturer’s specifications.

5.3.8 Hollow-End (Semi-tubular) Rivets

The shear strength of hollow-end rivets with solid cross sections for a portion of the length shall be taken equal to the strength of solid rivets of the same material if the bottom of the cavity is at least 25% of the rivet diameter from the plane of shear.

5.4 Tapping Screw Connections

This Section applies to tapping screws with a nominal

diameter from 0.164 in. (4.2 mm) through 0.25 in. (6.3 mm). Screws shall be thread-forming or thread-cutting, with or without a self-drilling point. As an alternate to Sections 5.4.1 and 5.4.2, strengths shall be based on tests according to Sec-tion 9.

Screws shall be installed and tightened in accordance with the manufacturer’s specifications.

The following nomenclature applies to this Section:Asn = thread stripping area of internal thread per unit

length of engagement

C = coefficient that depends on screw location

D = nominal screw diameter

Dh = nominal hole diameter

Dw = nominal washer diameter

Dws = larger of the nominal washer diameter and the screw head

Ftu1 = tensile ultimate strength of member in contact with the screw head

Ftu2 = tensile ultimate strength of member not in contact with the screw head

Fty1 = tensile yield strength of member in contact with the screw head

Fty2 = tensile yield strength of member not in contact with the screw head

Ks = coefficient that depends on member thickness

January 2005 I-A-57

n = number of threads per unit length for a screw

ns = safety factor = 3.0

Pnt = nominal tensile strength of a screw

Pnot = nominal pull-out strength of a screw

Pnov = nominal pull-over strength of a screw

Pns = nominal shear strength of a screw

t1 = thickness of member in contact with the screw head

t2 = thickness of member not in contact with the screw head

tc = depth of full thread engagement of screw into t2 not including tapping or drilling point

5.4.1 Screw Material

Screws shall be:a. aluminum,b. austenitic stainless steel, orc. if the screw will not be exposed to contact with liquid

water or humidity near the dew point in its intended ser-vice:1) non-austenitic stainless steel with a minimum nominal

composition of 16% chromium and a Rockwell hard-ness less than C35 in the load bearing portion of the shank, or

2) coated or plated carbon steel with a Rockwell hard-ness less than C35 in the load bearing portion of the shank. Screws shall be zinc coated per ASTM A123, A641, or B633 or nickel/chromium plated per ASTM B456, Type SC. When other platings and/or coatings are to be used, evidence shall be submitted to substan-tiate the corrosion resistance of these products.

5.4.2 Screw Tension

For screws that carry tensile loads, the head of the screw or washer, if a washer is provided, shall have a diameter Dw not less than 5/16 in. (8 mm). Washers shall be at least 0.050 in. (1.3 mm) thick.

The allowable tension force on a screw is the least of:

1) Pnot /ns (see Section 5.4.2.1)2) Pnov /ns (see Section 5.4.2.2)3) Pnt /(1.25ns)

5.4.2.1 Pull-Out

The nominal pull-out strength, Pnot, for pulling a screw out of a threaded part, is:

1) For UNC threads (screw thread types C, D, F, G, and T)a. for 0.060 in. ≤ tc ≤ 0.125 in. (1.5 mm ≤ tc ≤ 3 mm)

Pnot = Ks D tc Fty2 (Eq. 5.4.2.1-1)

whereKs = 1.01 for 0.060 in. ≤ tc < 0.080 in.

(1.5 mm ≤ tc < 2 mm)

Ks = 1.20 for 0.080 in. ≤ tc ≤ 0.125 in. (2 mm ≤ tc ≤ 3 mm)

b. for 0.125 in. < tc < 0.25 in. (3 mm < tc < 6.3 mm)

Pnot = 1.2DFty2(0.25 – tc) + 1.16AsnFtu2(tc – 0.125)(Eq. 5.4.2.1-2)

c. for 0.25 in. ≤ tc ≤ 0.375 in. (6.3 mm ≤ tc ≤ 10 mm)

Pnot = 0.58 Asn tc Ftu2 (Eq. 5.4.2.1-3)

2) For spaced threads (screw thread types AB, B, BP, BF, and BT)a. for 0.038 in. ≤ tc ≤ 2/n (1 mm < tc < 2/n)


whereKs = 1.01 for 0.038 in. ≤ tc < 0.080 in.

(1 mm ≤ tc < 2 mm)

Ks = 1.20 for 0.080 in. ≤ tc < 2/n (2 mm ≤ tc < 2/n)

b. for 2/n < tc < 4/n

Pnot = 1.2D Fty2 (4/n – tc) + 3.26D Ftu2 (tc – 2/n) (Eq. 5.4.2.1-5)

c. for 4/n ≤ tc ≤ 0.375 in. (4/n ≤ tc ≤ 8 mm)

Pnot = 1.63D tc Ftu2 (Eq. 5.4.2.1-6)

5.4.2.2 Pull-Over

The nominal pull-over strength, Pnov, for pulling con-nected material over the head of a screw or washer, if pres-ent, is:

Pnov = C t1 Ftu1 (Dws – Dh) (Eq. 5.4.2.2-1)

where C is a coefficient that depends on screw location (1.0 for valley fastening and 0.7 for crown fastening), and Dws is the larger of the screw head diameter or the washer diam-eter, but no greater than 5/8 in. (16 mm). (See Section 5.4.2 for the washer thickness requirement.) The nominal pull-over strength need not be less than the pull-over strength computed from equation 5.4.2.2-2 for countersunk screws.

For countersunk screws with an 82o nominal angle head, the nominal pull-over strength is:

Pnov = (0.27 + 1.45t1/D) D t1Fty1 (Eq. 5.4.2.2-2)

for 0.06 in. ≤ t1 < 0.19 in. (1.5 mm ≤ t1 < 5 mm) and t1/D ≤ 1.1. If t1/D > 1.1, use t1/D = 1.1

5.4.3 Screw Shear and Bearing

The shear force on a screw shall not exceed the least of:

1) 2 Ftu1 D t1/nu. (Eq. 5.4.3-1)

If the screw is countersunk, one-half the depth of the countersink shall be deducted from t1.

I-A-58 January 2005

2) Ftu2 D t2 /nu (Eq. 5.4.3-2)

3) 4.2(t23D)1/2 Ftu2 /ns , for t2 ≤ t1 (Eq. 5.4.3-3)

4) Pss /(1.25 ns) (Eq. 5.4.3-4)

5.4.4 Minimum Spacing of Screws

The minimum distance between screw centers shall be 2.5 times the nominal screw diameter.

5.5 Building Sheathing Connections

5.5.1 Endlaps

Minimum endlaps shall be those expressed in Table 5.5.1-1.

5.5.2 Sidelaps

For a sinusoidal corrugated sheet, the minimum sidelap for roofing shall have a width equal to the pitch of the cor-

rugations, and the minimum sidelap for siding shall have a width equal to half the pitch.

For a trapezoidal sheet of a depth greater than 1 in. (25 mm) the minimum sidelap for both roofing and siding shall have a developed width equal to the width of the narrowest flat plus 2 in. (50 mm). A trapezoidal sheet with a depth of 1 in. (25 mm) or less shall have an overlap of proven design including an anti-siphoning feature.

5.5.3 Fasteners in Laps

The minimum size of fasteners used in end laps and side laps shall be #12 (5.5 mm) for screws and 3/16 in. (5 mm) diameter for rivets. The maximum spacing for sidelap fas-teners shall be 12 in. (300 mm). Endlap fasteners shall be located no more than 2 in. (50 mm) from the end of the overlapping sheet.

5.5.4 Flashing

Flashing shall be formed from aluminum sheet.

Table 5.5.1-1MINIMUM END LAPS

Depth of sectionMinimum End Laps

Roofing, slope greater than 2 on 12, less than 3 on 12

Roofing, slope 3 on 12 or more

Siding

1 in. or less(25 mm or less)

– 6 in.(150 mm)

4 in.(100 mm)

Greater than 1 in., less than 2 in. (Greater than 25 mm, less than 50 mm)

9 in.(230 mm)

6 in.(150 mm)

4 in.(100 mm)

2 in. or more (50 mm or more) 9 in.(230 mm)

6 in.(150 mm)

6 in.(150 mm)

January 2005 I-A-59

6.1 Layout

6.1.1 Punch and Scribe Marks

Punched or scribed layout marks shall not remain on fabricated material designed for fatigue.

6.1.2 Temperature Correction

A temperature correction shall be applied where neces-sary in the layout of dimensions. The coefficient of expan-sion used shall be 13 × 10-6 per oF (23 × 10-6 per oC).

6.2 Cutting

6.2.1 Methods

Cutting shall be by shearing, sawing, nibbling, routing, arc cutting, laser or abrasive water jet. Edges which have been arc or laser cut shall be planed to remove edge cracks.

6.2.2 Edge Quality

Cut edges shall be true, smooth, and free from excessive burrs or ragged breaks.

6.2.3 Re-entrant Corners

Re-entrant corners shall be filleted.

6.2.4 Oxygen Cutting

Oxygen cutting is prohibited.

6.3 Heating

Aluminum heated above 150oF (66oC) during fabrication other than welding is subject to the following requirements:

a. Temperature controls and supervision shall be provided to ensure that time-temperature limits are met, and time and temperature exposure shall be documented.

b. When heating reduces metal strengths, design stresses shall be reduced consistent with the mechanical proper-ties of the aluminum after the heating process. Reduced design stresses need not be used for the alloys and tempers in Table 6.3-1 if the cumulative time at the elevated tem-perature does not exceed the limits given.

Table 6.3-1TEMPERATURE EXPOSURE LIMITS

FOR ARTIFICIALLY AGED TEMPERS OF 6005, 6061, AND 6063

Temperature1 Time

oF oC

450 230 5 min

425 220 15 min

400 205 30 min

375 190 2 hr

350 175 10 hr

325 165 100 hr

300 150 1,000 hr

212 100 100,000 hr

1) Interpolate time (t) for other temperatures (T) using

logt = logt2 + log ( T2 /T )

__________ log ( T2 /T1 )

( log t1/t2 )

whereT1 = next lower temperature in Table 6.3-1 than TT2 = next higher temperature in Table 6.3-1 than Tt1 = time corresponding to T1

t2 = time corresponding to T2

c. 5083, 5086, 5154, and 5456 shall not be held at tem-peratures from 150oF (66oC) to 450oF (230oC). To hot form such alloys, they shall be 1) rapidly heated to a temperature not to exceed 550oF

(290oC) 2) formed before the metal cools below 450oF (230oC),

and 3) rapidly cooled from 450oF (230oC) to 150oF (66oC).

Section 6. Fabrication and Erection

I-A-60 January 2005

6.4 Holes

6.4.1 Fabrication Methods

Holes shall be punched or drilled. Punching shall not be used for castings or if the metal thickness is greater than the diameter of the hole. The amount by which the diam-eter of a sub-punched hole is less than that of the finished hole shall be at least ¼ the thickness of the piece but not less than 1/32 in. (0.8 mm).

6.4.2 Hole Alignment

If holes must be enlarged to admit fasteners, they shall be reamed. Poor matching holes shall be rejected. Holes shall not be drifted in a manner that distorts the metal. All chips and foreign matter between contacting surfaces shall be removed before assembly.

6.5 Riveting

6.5.1 Driven Head

The driven head of aluminum rivets shall be flat or cone-point, with dimensions as follows:

6.5.1.1 Flat Heads

Flat heads shall have a diameter at least 1.4 times the nominal diameter of the rivet and a height at least 0.4 times the nominal diameter of the rivet.

6.5.1.2 Cone-Point Heads

Cone-point heads shall have a diameter at least 1.4 times the nominal diameter of the rivet and a height to the apex of the cone at least 0.65 times the nominal diameter of the rivet. The nominal included angle at the apex of the cone shall be 127o.

6.5.2 Hole Filling

Rivets shall fill holes completely. Rivet heads shall be concentric with the rivet holes and shall be in continuous contact with the surface of the part joined.

6.5.3 Defective Rivets

Defective rivets shall be removed by drilling. The drill bit diameter shall not exceed the diameter of the replace-ment rivet.

6.6 Finishes

6.6.1 Where Painting Is Required

Aluminum shall be painted where:a. 2014 is in the presence of moisture,

b. aluminum would otherwise be in contact with or fastened to dissimilar materials as described in Section 6.7,

c. aluminum is exposed to corrosive conditions.

6.6.2 Surface Preparation

Surfaces to be painted shall be prepared immediately before painting by:

a. a chemical cleaner (such as a solution of phosphoric acid and organic solvents)

b. abrasion blasting c. unsealed anodizing d. chemical conversion coating, or e. using the procedure specified by the coating supplier.

6.7 Contact with Dissimilar Materials

Where aluminum is in contact with or fastened to the materials specified in Sections 6.7.1 through 6.7.3, direct contact between the aluminum and the other material shall be prevented as specified in those sections or by placing a compatible, nonporous isolator between the aluminum and the other material.

6.7.1 Steel

Steel surfaces to be placed in contact with uncoated alu-minum shall be painted with a coating suitable for the ser-vice. Where very corrosive conditions are expected, addi-tional protection can be obtained by applying a sealant that excludes moisture from the joint during service. Aluminized, hot-dip galvanized or electro-galvanized steel in contact with aluminum need not be painted. Stainless steel (300 series) in contact with aluminum need not be painted except in high chloride environments.

6.7.2 Wood, Fiberboard, or Other Porous Materials

Aluminum surfaces to be placed in contact with wood, fiberboard, or other porous material that absorbs water shall be factory painted or given a heavy coat of alkali resistant bituminous paint or other coating providing the equivalent protection before installation.

6.7.3 Concrete or Masonry

Aluminum shall not be embedded in concrete with cor-rosive additives such as chlorides if the aluminum will be electrically connected to steel.

Unless the concrete or masonry will remain dry after curing and no corrosive additives such as chlorides are used, aluminum surfaces to be placed next to or embedded in concrete or masonry shall be:

a. given one coat of suitable paint, such as zinc molybdate primer conforming to Federal Specification TT-P-645B or equivalent, or

January 2005 I-A-61

b. given a heavy coating of alkali resistant bituminous paint, or

c. isolated with a suitable plastic tape or other isolation material.

6.7.4 Runoff From Heavy Metals

Aluminum shall not be exposed to water that has come in contact with a heavy metal such as copper. The heavy metal shall be painted or coated or the drainage from the metal diverted away from the aluminum or painted alumi-num shall be used.

6.8 Mechanical Finishes

Abrasion blasting shall not be used if it distorts, perfo-rates, or significantly reduces the thickness of the material blasted.

6.9 Fabrication Tolerances

A fabricated member shall not vary from straight or from its intended curvature by more than its length divided by 960.

6.10 Bending

Bend radii shall be large enough to avoid cracking.

6.11 Erection

6.11.1 Erection Tolerances

Tolerances on erected dimensions shall be suitable for the intended service.

6.11.2 Bolt Installation

Unless the joint is a slip-critical connection, bolts shall be installed snug tight, defined as the tightness that exists when all plies in a joint are in firm but not necessarily con-tinuous contact. Slip-critical connections shall be tightened in accordance with Section 5.2.8.7.

I-A-62 January 2005

7.1 General

Welding shall comply with the American Welding Soci-ety’s D1.2 Structural Welding Code—Aluminum. Filler alloys shall meet AWS A5.10 and be selected from Table 7.1-1.

7.2 Welded Members

7.2.1 General

The weld-affected zone shall be taken to extend 1 in. (25 mm) to each side of the centerline of a weld. Mechani-cal properties for weld-affected metal shall be taken from Table 3.3-2. The modulus of elasticity for weld-affected metal is the same as for non-welded metal.

Allowable stresses calculated in accordance with Sec-tion 7.2.1 apply to:

1) Members in axial tension with transverse welds affect-ing their entire cross section,

2) Bearing stresses at weld-affected metal,3) Columns or beams supported at both ends with trans-

verse welds affecting their entire cross-section and no farther than 0.05L from the ends,

4) Columns or beams of tubes or curved elements with transverse welds affecting their entire cross section, and

5) Flat elements of columns or beams with welds at the supported edges only.

Allowable stresses for these welded members shall be cal-culated from the same formulas as for non-welded mem-bers with the following adjustments.

1) Allowable stresses for axial or flexural tension (Sec-tions 3.4.1 through 3.4.4), bearing (Sections 3.4.5 and 3.4.6), and axial or flexural compression or shear (Sec-tions 3.4.7 through 3.4.21) with slenderness less than S1 shall be calculated using welded mechanical properties from Table 3.3-2.

2) Allowable stresses for tubes and curved elements in axial or flexural compression or shear (Section 3.4.10, 3.4.12, and 3.4.16.1) with slenderness greater than S1 shall be calculated using welded mechanical properties from Table 3.3-2 and buckling constants from Table 3.3-3 regardless of temper before welding.

3) Allowable stresses for all other members and elements in axial or flexural compression or shear (Sections 3.4.7 through 3.4.21) with slenderness greater than S1 shall be calculated using non-welded mechanical properties from Table 3.3-1 and buckling constants from Table 3.3-3 or 3.3-4 as appropriate for the temper before welding.

7.2.2 Members with Part of the Cross Section Weld-Affected

For members with part of the cross section weld-affected, the allowable stress is

Fpw = Fn – Aw ___ A

( Fn – Fw ) (Eq. 7.2.2-1)

where

Fpw = allowable stress on the cross section, part of which is weld-affected.

Fn = allowable stress if no part of the cross section were weld-affected. Use buckling constants for unwelded metal from Table 3.3-3 or 3.3-4 and mechanical properties from Table 3.3-1.

Fw = allowable stress if the entire cross sectional area were weld-affected. Use buckling constants for annealed material (Table 3.3-3) regardless of the temper before welding, and mechanical properties from Table 3.3-2.

A = net cross sectional area of a tension member or tension flange of a beam; gross cross sectional area of a column or compression flange of a beam. A beam flange shall consist of the portion of the section farther than 2c/3 from the neutral axis, where c is the distance from the neutral axis to the extreme fiber.

Aw = weld-affected cross sectional area. If Aw < 0.15A, Aw shall be taken as zero.

7.2.3 Columns or Beams with Transverse Welds Away from Supports and Cantilevers with Transverse Welds

For columns or beams supported at both ends with trans-verse welds farther than 0.05L from the member ends and cantilever beams with transverse welds, allowable stresses shall be calculated in accordance with Section 7.2.2 as if the entire cross sectional area were weld-affected.

7.3 Welded Connections

7.3.1 Groove Welds

7.3.1.1 Complete Penetration and Partial Penetration Groove Welds

The following types of groove welds are complete pen-etration welds:

1) Welds welded from both sides with the root of the first weld backgouged to sound metal before welding the second side.

2) Welds welded from one side using permanent or tem-porary backing.

3) Welds welded from one side using AC-GTAW root pass without backing

4) Welds welded from one side using PAW-VP in the key-hole mode.

All other groove welds are partial penetration welds.

Section 7. Welded Construction

January 2005 I-A-63

Tab

le 7

.1-1

WE

LD

FIL

LE

RS

FO

R W

RO

UG

HT

AL

LOY

S

Bas

e M

etal

Bas

e M

etal

1060

110

030

03A

lcla

d 3

003

2219

3004

A

lcla

d 3

004

5005

5050

5052

5083

5456

5086

5154

5454

6005

6061

6063

6105

6351

6463

7005

7005

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)55

56(5

183)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5556

(5

183,

535

6)

6005

, 606

1,

6063

, 610

5,

6351

, 646

3

4043

(404

7)41

4553

56(4

043,

404

7,

5183

, 555

6)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(404

3, 4

047,

51

83, 5

556)

5454

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6) 5

654

(518

3, 5

356,

5556

)

5554

(518

3, 5

356,

55

56)

5154

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)56

54

(518

3, 5

356,

5556

)

5086

5356

(518

3, 5

556)

DN

W53

56(5

183,

5556

)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)

5083

, 545

653

56(5

183,

555

6)D

NW

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5556

(518

3)

5052

5356

(5

183,

555

6)D

NW

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5005

, 505

040

43(1

100,

404

7)D

NW

5356

(404

3, 4

047,

51

83, 5

556)

5356

(404

3, 4

047,

51

83, 5

556)

3004

, A

lcla

d 3

004

4043

(40

47,

5183

,535

6,55

56)

DN

W53

56(5

183,

555

6)

2219

4145

2319

(414

5)

1060

, 110

0,

3003

, A

lcla

d 3

003

4043

(110

0, 4

047)

Not

es:

1) T

his

tabl

e is

for

stru

ctur

al a

pplic

atio

ns s

ubje

cted

to n

orm

al a

tmos

pher

ic c

ondi

tions

usi

ng G

TAW

or

GM

AW

.2)

DN

W =

Do

Not

Wel

d

I-A-64 January 2005

7.3.1.2 Effective Area

1) Size: The weld size of a complete joint penetration groove weld is the thickness of the thinner part joined. The weld size of a partial joint penetration groove weld is the depth of preparation Sw (see Figure 7.3-1) for all V and bevel groove welds with an included angle greater than 45o, and the depth of preparation of all J and U groove welds.

2) Length: The effective weld length for tension and com-pression is the length of the weld perpendicular to the direction of tensile or compressive stress. The effective weld length for shear is the length of the weld parallel to the direction of shear stress.

3) Area: The effective area of a groove weld is the effec-tive weld length times the weld size.

Figure 7.3-1PARTIAL JOINT PENETRATION GROOVE

WELD DEPTH OF PREPARATION Sw

7.3.1.3 Design Strength

The allowable tensile or compressive strength of a groove weld (Pgw) is

Pgw = Ftuw Awe ______ nu

(Eq. 7.3.1.3-1)

whereFtuw = least of the welded tensile ultimate strengths of

the base metals and the filler. Welded tensile ulti-mate strengths of base metals shall be taken from Table 3.3-2 and tensile ultimate strengths of fill-ers from Table 7.3-1.

Awe = weld effective area nu = 1.95

The allowable shear strength of a groove weld (Vgw) is

Vgw = Fsuw Awe ______ nu

(Eq. 7.3.1.3-2)

whereFsuw = least of the welded shear ultimate strengths of the base

metals and the filler. Welded shear ultimate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1

Awe = weld effective area.

7.3.2 Fillet Welds

7.3.2.1 Effective Throat and Effective Length

The effective throat is the shortest distance from the joint root to the face of the diagrammatic weld (see Figure 7.3-2).

Figure 7.3-2EFFECTIVE THROAT OF A FILLET WELD

Table 7.3-1FILLER STRENGTHS

Filler Minimum TensileUltimate Strength

(ksi)

Minimum ShearUltimate Strength

(ksi)1100 11 7.5

2319 35 16

4043 24 11.5

4047 – 13

4643 – 13.5

5183 40 21

5356 35 17

5554 31 17

5556 42 20

5654 30 12

Table 7.3-1MFILLER STRENGTHS


(MPa)


(MPa)1100 75 50

2319 240 110

4043 165 80

4047 – 90

4643 – 95

5183 275 145

5356 240 115

5554 215 115

5556 290 140

5654 205 85

January 2005 I-A-65

The weld effective length Lwe is the overall length of the weld, including boxing. If the effective length of a fillet weld is less than 4 times its nominal size Sw (see Figure 7.3-2) the effective weld size shall be considered to be 25% of its effec-tive length. The minimum length of segments of an inter-mittent fillet weld shall be 1½ in. (40 mm). The maximum effective length of a longitudinal fillet weld is 100 times its nominal size.


Stress on a fillet weld shall be considered to be shear for any direction of applied load. The allowable shear strength of a fillet weld (Vw) is

Vw = Fsw Lwe ______ nu

(Eq. 7.3.2.2-1)

whereFsw = least of:

1) the product of the filler’s shear ultimate strength and the effective throat.

2) for base metal in shear at the weld-base metal joint, the product of the base met-al’s welded shear ultimate strength and the fillet size Sw at the joint;

3) for base metal in tension at the weld-base metal joint, the product of the base met-al’s welded tensile ultimate strength and the fillet size Sw at the joint.

Welded shear and tensile ultimate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1.

Lwe = weld effective length

7.3.3 Plug and Slot Welds


The effective area of plug or slot welds is the nominal area of the hole or slot in the plane of the faying surface (see Figure 7.3-3). Slot lengths shall not exceed 10 times the slotted material’s thickness.

Figure 7.3-3SLOT WELD PLAN VIEW


The allowable shear strength of a plug or slot weld (Vw) is

Vw = Fsw Awe ______ nu

(Eq. 7.3.3.2-1)

whereFsw = lesser of the welded shear ultimate strengths

of the filler and the base metal under the weld. Welded shear ultimate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1.

Awe = weld effective area

7.3.4 Stud Welds

The allowable tensile strength of a stud weld (Tw) is

Tw = Tuw ___ nu

(Eq. 7.3.4-1)

whereTuw = minimum tensile strength of the stud in Table 7.3-2

Table 7.3-2MINIMUM TENSILE STRENGTHS FOR

5183, 5356, AND 5556 STUDS

Stud SizeArc(lb)

Capacitor Discharge(lb)

6-32 – 375

8-32 – 635

10-24 770 770

1/4-20 1360 1360

5/16-18 2300 2300

3/8-16 3250 –

7/16-14 4400 –

1/2-13 5950 –

I-A-66 January 2005

Table 7.3-2MMINIMUM TENSILE STRENGTHS FOR

5183, 5356, AND 5556 STUDS

Stud SizeArc(N)

Capacitor Discharge(N)

6-32 – 1670

8-32 – 2820

10-24 3420 3420

1/4-20 6050 6050

5/16-18 10,200 10,200

3/8-16 14,500 –

7/16-14 19,600 –

1/2-13 26,500 –

7.4 Post-Weld Heat Treating

For alloy 6005 lighting pole assemblies, up through 0.250 in. (6 mm) thick which are welded in the –T1 temper with filler alloy 4043 and precipitation heat treated (artifi-cially aged) to the –T5 temper by an approved method after welding, the allowable stresses within 1.0 in. (25 mm) of the weld shall be 85% of the values for non-welded alloy 6005-T5.

For alloy 6063 lighting pole assemblies, up through 0.375 in. (10 mm) thick which are welded in the –T4 temper with filler alloy 4043 and precipitation heat treated (artifi-cially aged) to the –T6 temper by an approved method after welding, the allowable stresses within 1.0 in. (25 mm) of the weld shall be 85% of the values for non-welded alloy 6063-T6.

January 2005 I-A-67

8.1 Materials

Section 8 of this Specification applies to castings listed in Table 8.2-1 and produced to the following ASTM Speci-fications:

B 26 Aluminum-Alloy Sand Castings B 108 Aluminum-Alloy Permanent Mold Castings

Dimensional tolerances shall conform to Standards for Aluminum Sand and Permanent Mold Castings.

The purchaser shall require the casting producer to report tensile yield strengths. For sand castings, the purchaser shall require that tensile ultimate and tensile yield strengths of specimens cut from castings shall be at least 75% of the val-ues specified in B 26.

Radiographic inspection to ASTM B 26 Grade C or B 108 Grade C criteria is required. The number of castings radio-graphed and the lot acceptance criteria shall be as follows:

Lot SizeNumber of Castings

Required to be Radiographed

Number of Castings Required to Meet

Grade C to Pass Lot

2 through 50 2 2

51 through 500 8 7

over 500 13 11

8.2 Mechanical Properties

Minimum strengths shall be taken from Table 8.2-1 or Table 8.2-1M.

Table 8.2-1MINIMUM STRENGTHS OF CASTINGS

Alloy-Temper Casting TypeMinimum TensileUltimate Strength

Ftu (ksi)

Minimum Tensile Yield Strength

Fty (ksi)Note

356.0-T6 sand 22.5 15

A356.0-T6 sand 25.5 18

354.0-T61 permanent mold364743

27.73633

(1)(2)(3)

C355.0-T61 permanent mold304037

22.53030

(1)(2)(3)

356.0-T6 permanent mold 33 22 (1)

A356.0-T61 permanent mold 28.5

3328

19.52626

(1)(2)(3)

A357.0-T61 permanent mold 33.7

4641

273631

(1)(2)(3)

359.0-T61 permanent mold 33.7

4540

25.53430

(1)(2)(3)

359.0-T62 permanent mold 35.2

4740

28.53830

(1)(2)(3)

535.0-F permanent mold 26.2 13.5 (1)

1) These strengths apply at any location in the casting if the purchaser does not specify test specimens be cut from castings.

2) These strengths apply in the locations specified by the purchaser if the purchaser specifies such locations. At other locations, the strengths in (1) apply.

3) These strengths apply anywhere in the casting if the purchaser specifies that these strengths shall be met in specimens cut from the cast-ing without designating a location.

Section 8. Castings

I-A-68 January 2005

The compressive yield strength Fcy of castings shall be taken as the tensile yield strength Fty.

The modulus of elasticity E of castings shall be taken as 10,000 ksi (70,000 MPa).

The tension coefficient kt for the alloy-tempers in Table 8.2-1 and Table 8.2-1M is 1.0.

Table 8.2-1MMINIMUM STRENGTHS OF CASTINGS

Alloy-Temper Casting TypeMinimum TensileUltimate Strength

Ftu (MPa)


Fty (MPa)Note

356.0-T6 sand 154 105

A356.0-T6 sand 176 124


191248228

(1)(2)(3)

C355.0-T61 permanent mold207276255

155207207

(1)(2)(3)


A356.0-T61 permanent mold196228193

134179179

(1)(2)(3)

A357.0-T61 permanent mold232317283

186248214

(1)(2)(3)


175234207

(1)(2)(3)


196262207

(1)(2)(3)

535.0-F permanent mold 180 93 (1)

Notes

1) These strengths apply at any location in the casting if the purchaser does not specify test specimens be cut from castings.2) These strengths apply in the locations specified by the purchaser if the purchaser specifies such locations. At other locations, the strengths

in (1) apply.3) These strengths apply anywhere in the casting if the purchaser specifies that these strengths shall be met in specimens cut from the cast-

ing without designating a location.

8.3 Design

Design shall be in accordance with all the provisions of this Specification.

8.4 Welding

Fillers shall be selected from Table 8.4-1. Minimum welded strengths shall be those established in the AWS D1.2 weld procedure qualification test.

January 2005 I-A-69

Table 8.4-1WELD FILLERS FOR CAST ALLOYS

BASE METAL TO BASE METAL 535.0

356.0A356.0A357.0359.0

354.0C355.0

1060, 1100, 3003, Alclad 3003 53564043

(4047)4145

2219 4043 4145 4145

3004, Alclad 3004 53564043

(4047)4145

(4043, 4047)

5005, 5050 53564043

(4047)4145

(4043, 4047)

5052 53564043

(4047)4145

(4043, 4047)

5083, 5456 5356 DNW DNW

5086 5356 DNW DNW

5154 5356 DNW DNW

5454 53564043

(4047)DNW

6005, 6061, 6063, 6105, 6351, 6463

53564043

(4047, 4145, 4643)4145

(4043, 4047)

7005 53564043

(4047)DNW

354.0C355.0

DNW 41454145

(note 1)

356.0, A356.0, A357.0, 359.0

4043(5356)

4043(note 1)

535.0 5356

Notes

1) To weld C355.0 to itself, 4009 may be used; to weld A356.0 to itself, 4010 may be used; and to weld A357.0 to itself, 4011 may be used.

2) DNW = Do not weld

I-A-70 January 2005

9.1 General

Testing shall be considered to be an acceptable method for substantiating the design of aluminum alloy load carry-ing members, assemblies or connections whose strengths cannot otherwise be determined in accordance with Sec-tions 1 through 8. Tests shall be conducted by an indepen-dent testing laboratory or by a manufacturer’s testing labo-ratory when certified by a qualified independent witness.

General provisions for testing are given in Sections 9.2 and 9.3. Specific provisions for building sheathing are given in Section 9.4.

9.2 Test Loading and Behavior

In order to test a structure or load carrying member adequately, the loading shall be applied in a fashion that is representative of the loading during service. Further, the structure or member shall be supported in a manner that is equivalent to the supports available when the structure is in service.

In tests that require measurement of deflection of a panel or beam, a preload, that is a minimum of 20% of the design load, shall be applied to set the specimen before testing, and deflections shall be measured at the supports as well as at the point of maximum critical deflection, so that the difference will indicate the specimen deflection. The preload shall only be taken as a zero load for deflection measurements when proper account of this is taken in reporting deflections.

As an alternative, the structural performance of exterior aluminum fenestration products such as windows, curtain walls, and doors shall be determined in accordance with ASTM E 330.

9.3 Number of Tests and the Evaluation of Test Results

9.3.1 Tests for Determining Mechanical Properties

In determining yield strength and ultimate strength of material or fasteners, sufficient tests shall be conducted to statistically establish the strength at which 99% of the material is expected to exceed with a confidence of 95%. This strength shall be calculated as follows:

Xa = Xm – KSx (Eq. 9.3.1-1)

whereXa = strength at which 99% of the material is expected

to exceed with a confidence of 95%Xm = mean of the test resultsSx = standard deviation of the test resultsK = statistical coefficient based on the number of tests

(n). K is a one-sided factor for 99% of the popula-tion exceeding Xa with a confidence of 95%. Val-ues of K for the following values of n are:

n K n K

3 10.55 18 3.370

4 7.042 19 3.331

5 5.741 20 3.295

6 5.062 21 3.262

7 4.641 22 3.233

8 4.353 23 3.206

9 4.143 24 3.181

10 3.981 25 3.158

11 3.852 30 3.064

12 3.747 35 2.994

13 3.659 40 2.941

14 3.585 45 2.897

15 3.520 50 2.863

16 3.463 100 2.684

17 3.415

9.3.2 Tests for Determining Structural Performance

Where practicable, in member and structural systems tests the evaluation of test results shall be made on the basis of not fewer than four identical specimens. If the deviation from the average value exceeds ±10%, at least three more tests of the same kind shall be made.

The allowable design value shall be taken as the average of all test results divided by the safety factor, SF, deter-mined as follows:

SF = 1.05α +1 ___________ MmFm ( α + 1 )

eβo √_____________

V M 2

+ V F 2

+ CP V P

2

+ V Q 2

(Eq. 9.3.2-1)

whereCp = correction factor = n

2 – 1 ______ n2 – 3n

Dn = nominal dead load

e = base for natural logarithms ≈ 2.72

Fm = mean value of the fabrication factor

Ln = nominal live load

Mm = mean value of the material factor

n = number of tests

Xi = failure load of ith test

Xm = average value of failure loads in all tests

= ∑

i = 1

n

X i _______ n

VF = coefficient of variation of the fabrication factor

VM = coefficient of variation of the material factor

Section 9. Testing

January 2005 I-A-71

Vp = coefficient of variation of the ratio of the observed failure loads divided by the average value of all the observed failure loads

= √___________________

∑

i = 1

n

( Xi ___ Xm

) 2

– ( ∑

i = 1

n

Xi ___ Xm

) 2

_________ n __________________

n – 1

VQ = coefficient of variation of the loads

= √

___________________ ( 0.105Dn ) 2 + ( 0.25Ln ) 2 ____________________

1.05Dn + Ln ; in lieu of calculation

by the above formula, VQ = 0.21

α = Dn /Ln ; in lieu of calculation by the above formula, α = 0.2

βo = the target reliability index, 2.5 for columns, beams and beam columns, 3.0 for tension members and 3.5 for connections.

The following values shall be used when documented statistical data established from sufficient number of results on material properties does not exist for the member or connection:

Mm = 1.10 for behavior governed by the yield stress

= 1.00 for behavior governed by the ultimate stress

Fm = 1.00

VM = 0.06

VF = 0.05 for structural members and bolted connections

= 0.15 for welded connections

In evaluating test results, adjustment shall be made for any differences between the yield strength of the material from which the tested sections are formed and the mini-mum yield strength specified for the material which the manufacturer intends to use. If the tensile yield strength of the aluminum from which the tested sections are formed is greater than the specified value, the test results shall be adjusted down to the specified minimum yield strength of the aluminum which the manufacturer intends to use. The test results shall not be adjusted upward if the yield strength of the test specimen is less than the minimum specified yield strength. Similar adjustments shall be made on the basis of tensile ultimate strength instead of yield strength when tensile ultimate strength is the critical factor.

Adjustments shall also be made for differences between nominal section properties and those of tested sections.

9.4 Testing Roofing and Siding

Where the configuration of roofing and siding installa-tions are such that calculation of their strength cannot be made in accordance with the provisions of this Specifica-tion, their bending strength shall be established from tests.

Tests are also required in the following cases:

a. When web angles θ are asymmetrical about the center-line of a valley, rib, flute, crimp, or other corrugation.

b. When web angles θ are less than 45o.c. When aluminum panels are alternated with panels

composed of any material having significantly dif-ferent strengths or deflection characteristics.

d. When flats spanning from rib to rib or other corruga-tion in the transverse direction have a width to thick-ness ratio greater than either of the following:

1) 1230 _____ 3 √

__ q where q is the design load in psf ( 447 ____

3 √__

q where

q is the design load in kN/m2)

2) 435 √___

Fty ___ q where Fty is in ksi and q is in psf

(37 √___

Fty ___ q where Fty is in MPa and q is in kN/m2).

e. When panel ribs, valleys, crimps, or other corruga-tions are of unequal depths.

f. When specifications prescribe less than one fastener per rib to resist negative or uplift loading at each pur-lin, girt, or other transverse supporting member.

g. When panels are attached to supporting members by profile interlocking straps or clips.

9.4.1 Test Method

Tests shall be conducted in accordance with ASTM E 1592.

9.4.2 Different Thicknesses

Only the thinnest and thickest specimens manufactured are required to be tested when panels are of like configura-tion, differing only in material thickness. Where the failure of the test specimens is from bending stress, the bending strength for intermediate thicknesses shall be interpolated as follows:

log Mi = log M1 + ( log ti – log tmin ______________ log tmax – log tmin

) ( log M2 – log M1 )

(Eq. 9.4.2-1)

where Mi = bending strength of member of intermediate thick-

ness ti

M1 = bending strength of member of thinnest material M2 = bending strength of member of thickest material ti = thickness of intermediate thickness material tmin = thickness of thinnest material tested tmax = thickness of thickest material tested

9.4.3 Allowable Loads from Tests

Allowable loads shall be determined using the safety fac-tors given in Section 9.3.2 for bending and Section 5 applied to the minimum test strength achieved for fasteners.

9.4.4 Deflections

Live load deflections shall not exceed 1/60 of the span length.


PART I-B

Specification for Aluminum Structures–

Building Load and Resistance Factor Design


Third Edition, January 2005

January 2005 I-B-3

FOREWORD

The first edition of the Specification for Aluminum Structures Load and Resistance Factor Design was published in October, 1994, and a second edition in 2000. This third edition of the LRFD Specification, developed as a consensus document, includes new or revised provisions concerning

• shear yield strengths• welded strengths• adding 6063-T52, 6351-T6, and 7005-T53 • materials for screws used to connect aluminum parts• factors on welded tensile ultimate strength and compressive yield strength• welded connections (groove, fillet, plug and slot, and stud welds)• screw pull-over• revision of Section 1.2, Materials• revision of Section 5, Mechanical Connections• revision of Section 6, Fabrication and Erection• a new Section 8, Castings• weighted average strengths• design stresses for wind loads• fatigue strength for welds with permanent backing• net effective areas for channels, I beams, zees, angles, and tees• single angles in flexure• tapered thickness element strength• web crippling of extrusions• compressive strength of complex cross sections• strength of elements in bending in their own plane• unbraced length in bending

These improvements and additions are the result of studies sponsored by the Aluminum Association and others. The Aluminum Association gratefully acknowledges the efforts of the Engineering and Design Task Force in drafting this Specification and the Engineering Advisory Committee in reviewing them.



The Aluminum Association Engineering Advisory Committee

Includes the members of the Engineering and Design Task force and the following persons:

Robert E. Abendroth, Iowa State UniversityFrancisco Castano, Geometrica, Inc.Terence Cavanagh, Terrapin Testing, Inc.Karen C. Chou, Minnesota State University, MankatoCynthia Ebert, Larson Engineering of Missouri

I-B-4 January 2005

Andrew J. Hinkle, S & K TechnologiesDimitris Kosteas, Technical University of MunichLeRoy Lutz, Computerized Structural DesignBrian Malloy, Alcoa Engineered ProductsRay Minor, Hapco American FlagCarl Wagus, American Architectural Manufacturers AssociationRobert W. Walton, Texas Wall Systems

Guidelines for the Preparation of Technical Inquiries on the Specification for Aluminum Structures

Technical inquiries to obtain an interpretation or request a revision to the Specification for Aluminum Structures should be directed to:

VP, TechnologyThe Aluminum Association900 19th Street, NWWashington, DC 20006 Fax: 202-862-5164email: [email protected]

Comments on other parts of the Aluminum Design Manual are also welcome.

Inquiries should be typewritten and include the inquirer’s name, affiliation, and address. Each inquiry should address a single section of the Specification unless the inquiry involves two or more interrelated sections. The section and edition of the Speci-fication should be identified.

Requests for interpretations should be phrased, where possible, to permit a “yes” or “no” answer and include the necessary background information, including sketches where appropriate.

Requests for revisions should include proposed wording for the revision and technical justification.

Inquiries are considered at the first meeting of the Engineering and Design Task Force following receipt of the inquiry.

January 2005 I-B-5

IBSpecification for Aluminum Structures – Load and Resistance Factor Design

TABLE OF CONTENTS

Section 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .91.1 Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.2 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91.3 Design Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Section 2. Design Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.1 Section Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.2 Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102.3 Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Section 3. General Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.1 Material Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.2 Nomenclature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.3 Tables Relating to Mechanical Properties and Buckling Constants . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 143.4 Design Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3.4.1 Tension, Axial . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.2 Tension in Extreme Fibers of Beams – Flat Elements In Uniform Tension . . . . . . . . . . . . . . . . . . . . . . 263.4.3 Tension in Extreme Fibers of Beams – Round or Oval Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.4 Tension in Extreme Fibers of Beams – Flat Elements In Bending in Their Own Plane . . . . . . . . . . . . . 263.4.5 Bearing on Rivets and Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.6 Bearing on Flat Surfaces and Pins and on Bolts in Slotted Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 263.4.7 Compression in Columns, Axial, Gross Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3.4.7.1 Sections Not Subject to Torsional or Torsional-Flexural Buckling . . . . . . . . . . . . . . . . . . . . . 273.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or

Torsional-Flexural Buckling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 273.4.7.3 Nonsymmetric Sections Subject to Torsional or Torsional-Flexural Buckling . . . . . . . . . . . . 27

3.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of Symmetry – Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 273.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is not an

Axis of Symmetry – Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . . . . . 283.4.9 Uniform Compression in Elements of Columns – Flat Elements Supported on Both Edges . . . . . . . . . 30

3.4.9.1 Uniform Compression in Elements of Columns – Flat Elements Supported on One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

3.4.9.2 Uniform Compression in Elements of Columns – Flat Elements Supported on Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

3.4.10 Uniform Compression in Elements of Columns – Curved Elements Supported on Both Edges . . . . . . . 353.4.11 Compression in Beams, Extreme Fiber, Gross Section – Single Web Shapes . . . . . . . . . . . . . . . . . . . . 353.4.12 Compression in Beams, Extreme Fiber, Gross Section – Round or Oval Tubes . . . . . . . . . . . . . . . . . . . 353.4.13 Compression in Beams, Extreme Fiber, Gross Section – Solid Rectangular and Round Sections . . . . . 363.4.14 Compression in Beams, Extreme Fiber, Gross Section – Tubular Shapes . . . . . . . . . . . . . . . . . . . . . . . . 363.4.15 Uniform Compression in Elements of Beams – Flat Elements Supported on One Edge . . . . . . . . . . . . 373.4.16 Uniform Compression in Elements of Beams – Flat Elements Supported on Both Edges . . . . . . . . . . . 37

3.4.16.1 Uniform Compression in Elements of Beams – Curved Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

3.4.16.2 Uniform Compression in Elements of Beams – Flat Elements Supported on One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

3.4.16.3 Uniform Compression in Elements of Beams – Flat Elements Supported on Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

3.4.17 Compression in Elements of Beams (Element in Bending in Own Plane) – Flat Elements Supported on Tension Edge, Compression Edge Free . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

I-B-6 January 2005

3.4.18 Compression in Elements of Beams (Element in Bending in Own Plane) – Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

3.4.19 Compression in Elements of Beams (Element in Bending in Own Plane) – Flat Elements Supported on Both Edges and With a Longitudinal Stiffener . . . . . . . . . . . . . . . . . . . . . . 40

3.4.20 Shear in Elements – Unstiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . 403.4.21 Shear in Elements – Stiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . 40

Section 4. Special Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .414.1 Combined Axial Load and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

4.1.1 Combined Compression and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.1.2 Combined Tension and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

4.2 Torsion and Shear in Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.3 Torsion and Bending in Open Shapes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 414.4 Combined Shear, Compression, and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 424.5 Longitudinal Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 424.6 Transverse Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

4.6.1 Stiffeners for Web Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 424.6.2 Bearing Stiffeners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

4.7 Effects of Local Buckling on Member Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 434.7.1 Local Buckling Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 434.7.2 Weighted Average Axial Compressive Stress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 434.7.3 Weighted Average Bending Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 434.7.4 Effect of Local Buckling on Column Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 454.7.5 Effect of Local Buckling on Beam Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 454.7.6 Effective Width for Calculation of Bending Deflection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 454.7.7 Web Crippling of Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 454.7.8 Combined Web Crippling and Bending for Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

4.8 Fatigue . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 464.8.1 Constant Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 464.8.2 Variable Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

4.9 Compression in Single Web Beams Including Single Web Beams With Tubular Portions . . . . . . . . . . . . . . . . . . 524.9.1 Doubly Symmetric Sections and Sections Symmetric About the Bending Axis . . . . . . . . . . . . . . . . . . . 524.9.2 Singly Symmetric Sections Unsymmetric about the Bending Axis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 524.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis,

Doubly Symmetric Sections and Sections Without an Axis of Symmetry . . . . . . . . . . . . . . . . . . . . . . . . 524.9.4 Lateral Buckling Coefficients . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

4.9.4.1 Doubly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 534.9.4.2 Singly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 534.9.4.3 Special Cases – Doubly or Singly Symmetric Sections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 544.9.4.4 Cantilever Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54


4.11.1 Bending About Geometric Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 554.11.2 Bending About Principal Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55


4.13.1 Compressive Strength of Beam Elements – Flat Elements in Uniform Compression . . . . . . . . . . . . . . . 564.13.2 Compressive Strength of Beam Elements – Flat Elements in Bending In Their Own Plane . . . . . . . . . . 57

Section 5. Mechanical Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .585.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

5.1.1 Minimum Edge Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.1.2 Maximum Spacing of Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.1.3 Block Shear Rupture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.1.4 Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.1.5 Effective Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 585.1.6 Long Grips . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

January 2005 I-B-7

5.1.7 Strength and Arrangement of Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.1.8 Countersunk Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

5.2 Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.1 Bolt Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.2 Holes and Slots for Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.3 Bolt Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.4 Bolt Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.5 Bolt Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.6 Minimum Spacing of Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.7 Lockbolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.8 Slip-Critical Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

5.2.8.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 595.2.8.2 Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.2.8.3 Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.2.8.4 Design for Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.2.8.5 Design for Slip Resistance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.2.8.6 Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.2.8.7 Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

5.3 Riveted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.3.1 Rivet Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.3.2 Holes for Cold-Driven Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.3.3 Rivet Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 605.3.4 Rivet Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.3.5 Rivet Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.3.6 Minimum Spacing of Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.3.7 Blind Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.3.8 Hollow-End (Semi-tubular) Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

5.4 Tapping Screw Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.4.1 Screw Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.4.2 Screw Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61

5.4.2.1 Pull-Out . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 615.4.2.2 Pull-Over . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

5.4.3 Screw Shear and Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625.4.4 Minimum Spacing of Screws . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

5.5 Building Sheathing Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625.5.1 Endlaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625.5.2 Sidelaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625.5.3 Fasteners in Laps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625.5.4 Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

Section 6. Fabrication and Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .656.1 Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

6.1.1 Punch and Scribe Marks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.1.2 Temperature Correction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

6.2 Cutting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.2.1 Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.2.2 Edge Quality . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.2.3 Re-entrant Corners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.2.4 Oxygen Cutting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

6.3 Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.4 Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

6.4.1 Fabrication Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 656.4.2 Hole Alignment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

6.5 Riveting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.5.1 Driven Head . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

6.5.1.1 Flat Heads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.5.1.2 Cone-Point Heads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

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6.5.2 Hole Filling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.5.3 Defective Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

6.6 Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.6.1 Where Painting Is Required . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.6.2 Surface Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

6.7 Contact with Dissimilar Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.7.1 Steel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.7.2 Wood, Fiberboard, or Other Porous Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.7.3 Concrete or Masonry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 666.7.4 Runoff From Heavy Metals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

6.8 Mechanical Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 676.9 Fabrication Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 676.10 Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 676.11 Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

6.11.1 Erection Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 676.11.2 Bolt Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

Section 7. Welded Construction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .687.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 687.2 Welded Members . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

7.2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 687.2.2 Members with Part of the Cross Section Weld-Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 687.2.3 Columns or Beams with Transverse Welds Away from Supports and Cantilevers with

Transverse Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 687.3 Welded Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

7.3.1 Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 687.3.1.1 Complete Penetration and Partial Penetration Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . 687.3.1.2 Effective Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 707.3.1.3 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

7.3.2 Fillet Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 707.3.2.1 Effective Throat and Effective Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 707.3.2.2 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

7.3.3 Plug and Slot Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 717.3.3.1 Effective Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 717.3.3.2 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

7.3.4 Stud Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 717.4 Post-Weld Heat Treating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72

Section 8. Castings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .738.1 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 738.2 Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 738.3 Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 748.4 Welding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

Section 9. Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .769.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 769.2 Test Loading and Behavior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 769.3 Number of Tests and the Evaluation of Test Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

9.3.1 Tests for Determining Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 769.3.2 Tests for Determining Structural Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

9.4 Testing Roofing and Siding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779.4.1 Test Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779.4.2 Different Thicknesses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779.4.3 Design Loads from Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 779.4.4 Deflections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77

January 2005 I-B-9

Section 1. General

1.1 Scope

This Specification shall apply to the design of aluminum alloy load-carrying members.

1.2 Materials

This Specification applies to the aluminum alloys listed in Tables 3.3-1, 5.2.3-1, and 5.3.4-1 and produced to the following ASTM specifications:

B 209 Aluminum and Aluminum-Alloy Sheet and PlateB 210 Aluminum and Aluminum-Alloy Drawn Seam-

less TubesB 211 Aluminum and Aluminum-Alloy Bar, Rod, and

WireB 221 Aluminum and Aluminum-Alloy Extruded Bars,

Rods, Wire, Profiles, and TubesB 241 Aluminum and Aluminum-Alloy Seamless Pipe

and Seamless Extruded TubeB 247 Aluminum and Aluminum-Alloy Die Forgings,

Hand Forgings, and Rolled Ring ForgingsB 308 Aluminum-Alloy 6061-T6 Standard Structural

ProfilesB 316 Aluminum and Aluminum-Alloy Rivet and

Cold-Heading Wire and RodsB 429 Aluminum Alloy Extruded Structural Pipe and

TubeB 632 Aluminum Alloy Rolled Tread PlateB 928 High Magnesium Aluminum-Alloy Sheet and

Plate for Marine ServiceF 468 Nonferrous Bolts, Hex Cap Screws, and Studs

for General Use

This Specification also applies to castings that meet the requirements of Section 8.1.

1.3 Design Stresses

The design stresses ϕFL shall be larger than or equal to the stresses computed for the factored nominal loads acting on the structure. The method of analysis, nominal loads, load factors, and load combinations are defined in Section 2. The resistance factor (ϕ) accounts for the uncertainties inherent in the prediction of limit stresses. Resistance factors shall be determined in accordance with Sections 3, 4, 5, and 7.

I-B-10 January 2005



Section properties such as cross-sectional area, moment of inertia, section modulus, radius of gyration, and torsion and warping constants shall be determined using nominal dimensions. Cross section dimensions shall not vary by more than the tolerances given in Aluminum Standards and Data.

2.2 Procedure

Computations of forces, moments, stresses, and deflec-tions shall be in accordance with accepted methods of elas-tic structural analysis and engineering design. Two types of limit states are to be considered:

1) Ultimate limit states, the strength required to resist loads, such as yielding, fracture, buckling, crippling, and

2) Serviceability limit states, the ability to perform the intended function under normal service conditions, avoiding excessive deflection or the appearance of buckling.

The forces, moments, and stresses for the ultimate limit states shall be determined by structural analysis for the fac-tored loads as defined in Section 2.3 and the deflections for the serviceability limit states shall be calculated for the unfactored (working) loads.

2.3 Loads

Building-type structures shall be designed for the nomi-nal loads given in the applicable building code or perfor-mance specification. Nominal loads shall be factored and combined in accordance with the applicable building code or performance specification. In the absence of a code or performance specification, ASCE 7-02, Minimum Design Loads for Buildings and Other Structures, shall be used.

January 2005 I-B-11


3.1 Material Properties

Minimum mechanical properties used for non-welded material shall be as listed in Table 3.3-1.

Minimum mechanical properties used for welded material shall be as listed in Table 3.3-2.

The following properties shall be used unless more pre-cise values are specified:Coefficient of thermal expansion

13 × 10-6/oF (23 × 10-6/oC)

Density 0.1 lb/in3 (2.7 × 103 kg/m3)Poisson’s ratio 0.33

3.2 Nomenclature

A consistent set of units shall be used throughout this Specification. a = detail dimension parallel to the direction of

stress ae = equivalent width of rectangular panel al = shorter dimension of rectangular panel a2 = longer dimension of rectangular panel A = cross sectional area Ac = area of compression element (compression

flange plus 1/3 of area of web between compression flange and neutral axis)

Ah = gross area of cross section of longitudinal stiffener

As = area of the stiffener Asn = thread stripping area of internal thread per unit

length of engagement Aw = the portion of area of cross section A lying

within 1.0 in. (25 mm) of a weld b = width of section or element be = effective width of flat element to be used in

deflection calculations bo = width of element with an intermediate stiffener

as shown in Fig. 3.4.9.2-1 b/t = width to thickness ratio of a flat element of a

cross section B = buckling formula intercept with the following

subscripts: c – compression in columns p – compression in flat elements t – compression in curved elements tb – bending in curved elements br – bending in flat elements s – shear in flat elements c = distance from neutral axis to extreme fiber C = buckling formula intersection (see B for

subscripts) C = coefficient which depends on screw location Cb = coefficient which depends on moment gradient

Cf = constant to be determined from Table 4.8.1-1 and Figure 4.8.1-1

Cm = 0.6 - 0.4(M1/M2) for members whose ends are prevented from sway


CP = correction factor Cw = torsional warping constant of the cross section Cwa = t2 sin θ(0.46Fcy + 0.02 √

____ EFcy )

Cwb = Cw3 + Ri (1 – cosθ) Cw1 = 5.4 in. (140 mm) Cw2 = 1.3 in. (33 mm) Cw3 = 0.4 in. or 10 mm consistent with other units used C1 = coefficient defined in Section 4.9.4 C2 = coefficient defined in Section 4.9.4 d = depth of section or beam df = distance between flange centroids ds = flat width of lip stiffener shown in Fig. 3.4.9.1-1 d1 = clear distance from the neutral axis to the com-

pression flange D = buckling formula slope (see B for subscripts) D = diameter Dh = nominal hole diameter Dn = nominal dead load Ds = defined in Fig. 3.4.9.1-1 Dw = nominal washer diameter Dws = larger of the nominal washer diameter and the

screw head e = base for natural logarithms ≈2.72 E = compressive modulus of elasticity

(See Table 3.3-1) f = calculated stress fa = average stress on cross section produced by

axial load fb = maximum bending stress produced by transverse

loads and/or bending moment fs = shear stress caused by torsion or transverse

shear loads Fa = design compressive stress for a member consid-

ered as an axially loaded column according to Sections 3.4.7 through 3.4.10

Fao = design compressive stress of axially loaded member considered as a short column according to Section 4.7.2.

Fb = design bending stress for members subjected to bending only

Fc = design compressive stress Fcr = local buckling stress for element from

Section 4.7.1 Fcy = compressive yield strength Fcyw = compressive yield strength across a groove weld

(0.2% offset in 2 in. (50 mm) gage length)

I-B-12 January 2005

Fe = elastic buckling stress multiplied by ϕcc

= ϕccπ2E

______ (kL/r)2

Feb = elastic lateral buckling stress of beam calculated using Eq. 3.4.11-3 or Section 4.9 with ϕb = 1.0

Fec = elastic critical stress Fec = design elastic lateral buckling stress of beam

calculated assuming that the elements are not buckled

Fef = elastic torsional-flexural buckling stress Fet = elastic torsional buckling stress

Fet = 1 ____ Ar 2 o

( GJ + π2ECw ______ (Kt Lt)2 )

Fex = π2E ______

( kxLb ____ rx ) 2

FL = limit state stress Fm = mean value of the fabrication factor Fn = limit state stress for cross section 1.0 in.

(25 mm) or more from weld Fpw = limit state stress on cross section, part of whose

area lies within 1.0 in. (25 mm) of a weld Frb = limit state stress for beam with buckled elements Frc = limit state stress for column with buckled

elements Fs = design shear stress for members subjected only

to torsion or shear FST = design stress according to Section 3.4.9.1 or

3.4.16.2 Fsu = shear ultimate strength Fsuw = shear ultimate strength within 1.0 in. (25 mm) of

a weld Ft = design tensile stress for the member loaded only

axially according to Section 3.4.1 Ftu = tensile ultimate strength Ftuw = tensile ultimate strength across a groove weld Ftu1 = tensile ultimate strength of member in contact

with the screw head Ftu2 = tensile ultimate strength of member not in

contact with the screw head Fty = tensile yield strength Ftyw = tensile yield strength across a groove weld

(0.2% offset in 2 in. (50 mm) gage length) FUT = design stress according to Section 3.4.9.1 or

3.4.16.2 Fw = limit state stress on cross section if entire area

were to lie within 1.0 in. (25 mm) of a weld Fy = either Fty or Fcy, whichever is smaller g = spacing of rivet or bolt holes perpendicular to

direction of load go = distance from shear center to the point of

application of load G = shear modulus Gf = grip of rivet or bolt

h = clear height of shear web I = moment of inertia Ib = required moment of inertia of bearing stiffener Icy = moment of inertia of compression flange about

web Ih = moment of inertia of longitudinal stiffener Io = moment of inertia of the stiffener about the

centroidal axis of the stiffener parallel to the flat element that is stiffened

Is = moment of inertia of transverse stiffener to resist shear buckling

Ix = moment of inertia of a beam about axis perpendicular to web

Iy = moment of inertia of a beam about axis parallel to web

Iyc = moment of inertia of compression element about axis parallel to vertical web

j = parameter defined by Eq. 4.9.3-5 or -6 J = torsion constant k = the effective length factor. k shall be taken larger

than or equal to unity unless rational analysis justifies a smaller value

kt = coefficient for tension members kx = effective length coefficient for buckling about

the x-axis ky = effective length coefficient for buckling about

the y-axis k1 = coefficient for determining slenderness limit S2

for sections for which the limit state compressive stress is based on ultimate strength

k2 = coefficient for determining design compressive stress in sections with slenderness ratio above S2 for which the limit state compressive stress is based on ultimate strength

Ks = coefficient in Section 5.4.2.1 Kt = effective length coefficient for torsional

buckling. Kt shall be taken larger than or equal to unity unless rational analysis justifies a smaller value

L = unsupported length in the plane of bending Lb = unbraced length for bending Ln = nominal live load Ls = length of tube between circumferential stiffeners Lt = unbraced length for twisting m = constant to be determined from Table 4.8.1-1 M = bending moment applied to the member Ma = limit state bending moment for the member if

bending moment alone is applied to the member MA = absolute value of moment at quarter-point of the

unbraced beam segment MB = absolute value of moment at mid-point of the

unbraced beam segment MC = absolute value of moment at three-quarter point

of the unbraced beam segment

January 2005 I-B-13

Me = elastic critical moment Mi = bending strength of member with intermediate

thickness Mm = mean value of the material factor MMAX = absolute value of maximum moment in the

unbraced beam segment M1 = bending strength of member of thinnest material M2 = bending strength of member of thickest material M1/M2 = ratio of end moments where M2 is the larger

of the two end moments and M1/M2 is positive when the member is bent in reverse curvature, negative when bent in single curvature

n = number of tests n = number of threads per unit length for a screw N = length of bearing at reaction or concentrated

load N = number of cycles to failure Ns = number of stress ranges in the spectrum P = applied interior reaction or concentrated load

per web for flat webs Pas = limit state shear force per screw Pat = limit state tensile force per screw Pbs = concentrated load on bearing stiffener PL = limit state reaction or concentrated load

per web for flat webs calculated according to Section 4.7.7

Pnot = nominal pull-out strength per screw Pnov = nominal pull-over strength per screw Pns = nominal shear strength per screw Pnt = nominal tensile strength per screw q = uniform design load r = radius of gyration

ro = √_______________

r 2 x + r 2 y + x 2 o + y 2 o

rs = radius of gyration of the stiffener rx , ry = radii of gyration of the cross-section about the

centroidal principal axes (see Section 4.9.2 for rye of singly symmetric sections unsymmetric about the bending axis)

rye = effective radius of gyration R = transition radius, the radius of an attachment of

the weld detail Rb = mid-thickness radius of a round element or

maximum mid-thickness radius of an oval element

Ri = bend radius at juncture of flange and web measured to inside surface of bend

Rs = stress ratio, the ratio of minimum stress to maximum stress

s = spacing of transverse stiffeners (clear distance between stiffeners for stiffeners consisting of a pair of members, one on each side of the web, center-to-center distance between stiffeners consisting of a member on one side of the web only); spacing of rivet or bolt holes parallel to direction of load

S = 1.28 √___

E ___ Fcy

Sc = section modulus of a beam, compression side Sra = the applied stress range Srd = allowable stress range Sre = equivalent stress range Sri = the ith stress range in the spectrum St = section modulus of a beam, tension side Sw = size of a weld Sx = standard deviation of the test results S1, S2 = slenderness limits (with superscript for columns) t = thickness of element tavg = the average thickness of the element tc = depth of full thread engagement of screw into t2

not including tapping or drilling point ti = thickness of the intermediate thickness material

tested tmax = thickness of thickest material tested tmax = greater thickness of a tapered thickness element tmin = thickness of thinnest material tested tmin = lesser thickness of a tapered thickness element t1 = thickness of member in contact with the screw

head t2 = thickness of member not in contact with the

screw head U = parameter defined by Eq. 4.9.3-8 V = shear force on web at stiffener location VF = coefficient of variation of the fabrication factor VM = coefficient of variation of the material factor VP = coefficient of variation of the ratio of the

observed failure loads divided by the average value of all the observed failure loads

VQ = coefficient of variation of the loads xo = x - coordinate of the shear center Xa = strength at which 99% of the material is

expected to conform at a confidence level of 95%

Xi = failure load of ith test Xm = mean of the test results yo = y - coordinate of the shear center α = Dn /Ln


αs = a factor equal to unity for a stiffener consisting of equal members on both sides of the web and equal to 3.5 for a stiffener consisting of a member on one side only

β = 1 – (xo /ro)2

βo = the target reliability index βs = spring constant (transverse force applied to the


δ = (tmax - tmin) _________ tmin

for tapered thickness elements

λ = slenderness parameter

I-B-14 January 2005

λs = equivalent slenderness ratio for an intermediate stiffener

ρst = ratio defined in Section 3.4.9.1 and 3.4.16.2 ϕ = resistance factor (depending on the

application this notation has different subscripts) θ = angle between plane of web and plane of bear-

ing surface (θ < 90º)

3.3 Tables Relating to Mechanical Properties and Buckling Constants

This Section consists of the following tables concerning formulas for determining allowable stresses and constants and coefficients needed for these formulas:

3.3-1 Minimum Mechanical Properties for Aluminum Alloys

3.3-1M Minimum Mechanical Properties for Aluminum Alloys

3.3-2 Minimum Mechanical Properties for Welded Aluminum Alloys

3.3-2M Minimum Mechanical Properties for Welded Aluminum Alloys

3.3-3 Formulas for Buckling Constants for Products Whose Temper Designation Begins With -O, -H, -T1, -T2, -T3, or –T4

3.3-4 Formulas for Buckling Constants for Products Whose Temper Designation Begins With -T5, -T6, -T7, -T8, or –T9

January 2005 I-B-15



RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi


E (ksi)1100-H12


AllAll

1416

1114

1013

910

10,10010,100

2014-T6-T651-T6, T6510, T6511-T6, T651


0.040 to 0.2490.250 to 2.000

AllAll

66676065

58595355

59585253

40403538

10,90010,90010,90010,900

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.025 to 0.0390.040 to 0.2490.250 to 0.499

636464

555757

565856

383939

10,80010,80010,800

3003-H12-H14-H16-H18-H12-H14-H16-H18


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.128

AllAllAllAll

1720242717202427

1217212412172124

1014182011161921

1112141511121415

10,10010,10010,10010,10010,10010,10010,10010,100

Alclad3003-H12

-H14-H16-H18-H14-H18


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.025 to 0.2590.010 to 0.500

161923261926

111620231623

91317191520

101214151215

10,10010,10010,10010,10010,10010,100

3004-H32-H34-H36-H38-H34-H36


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.018 to 0.4500.018 to 0.450

283235383235

212528312528

182225292427

171920211920

10,10010,10010,10010,10010,10010,100

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361


0.017 to 0.2490.009 to 0.2490.006 to 0.1620.006 to 0.1280.024 to 0.0500.024 to 0.050

273134373134

202427302630

172124282228

161819211819

10,10010,10010,10010,10010,10010,100

3005-H25-H28

SheetSheet

0.013 to 0.0500.006 to 0.080

2631

2227

2025

1517

10,10010,100

3105-H25 Sheet 0.013 to 0.080 23 19 17 14 10,100

5005-H12-H14-H16-H32-H34-H36


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.017 to 2.0000.009 to 1.0000.006 to 0.162

182124172023

141720121518

131518111416

111214111213

10,10010,10010,10010,10010,10010,100

5050-H32-H34-H32

-H34


0.017 to 2.0000.009 to 0.249

All

All

222522 25

162016

20

141815

19

141513

15

10,10010,10010,100

10,100


( )

I-B-16 January 2005



RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi


E (ksi)5052-O

-H32-H34-H36



0.006 to 0.162

253134

37

9.52326

29

9.52124

26

161920

22

10,20010,20010,200

10,2005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321



3940404044444141

1624241831312929

1621211826262424

2424232526262424

10,40010,40010,40010,40010,40010,40010,40010,400

5086-O-H111-H111 -O-H112-H112-H112-H116-H112-H32

-H34



AllAll

All

35363635363535344040

44

14212114181614142828

34

14181814171615152626

32

21212121222121212424

26

10,40010,40010,40010,40010,40010,40010,40010,40010,40010,400

10,400

5154-H38 Sheet 0.006 to 0.128 45 35 33 24 10,3005454-O

-H111-H111-H112-O-H32-H34



31333331313639

12191912122629

12161613122427

19201919192123

10,40010,40010,40010,40010,40010,40010,400

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321


0.051 to 1.5000.188 to 1.2500.188 to 1.2501.251 to 1.5001.251 to 1.5001.501 to 3.0001.501 to 3.000

42464644444141

19333331312929

19272725252525

26272725252525

10,40010,40010,40010,40010,40010,40010,400


-T6, T6510, T6511-T6, T651-T6-T6


0.010 to 4.000All

up thru 8.0000.025 to 0.500

All

4238424238

3535353535

3535353535

2724252724

10,10010,10010,10010,10010,100

6063-T5, -T52-T5-T6


up thru 0.500up thru 1.0000.500 to 1.000

All

22222130

16161525

16161525

13131219

10,10010,10010,10010,100


-T5-T6



3842

3537

3537

2427

10,10010,100




( )

January 2005 I-B-17



RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)1100-H12


AllAll

95110

7595

7090

6270

69,60069,600

2014-T6-T651-T6, T6510, T6511-T6, T651


1.00 to 6.306.30 to 50.00

AllAll

455460415450

400405365380

405400360365

275275240260

75,20075,20075,20075,200

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.63 to 1.001.00 to 6.30

6.30 to 12.50

435440440

380395395

385400385

260270270

74,50074,50074,500

3003-H12-H14-H16-H18-H12-H14-H16-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.20

AllAllAllAll

120140165185120140165185

8511514516585115145165

709512514075110130145

758595105758595105

69,60069,60069,60069,60069,60069,60069,60069,600

Alclad3003-H12

-H14-H16-H18-H14-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.63 to 6.300.25 to 12.50

115135160180135180

80110140160110160

6290115130105140

70859510585105

69,60069,60069,60069,60069,60069,600

3004-H32-H34-H36-H38-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.45 to 11.500.45 to 11.50

190220240260220240

145170190215170190

125150170200165185

115130140145130140

69,60069,60069,60069,60069,60069,600

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361


0.40 to 6.300.20 to 6.300.15 to 4.000.15 to 3.200.60 to 1.200.60 to 1.20

185215235255215235

140165185205180205

115145165195150195

110125130145125130

69,60069,60069,60069,60069,60069,600

3005-H25-H28

SheetSheet

0.32 to 1.200.15 to 2.00

180215

150185

140170

105115

69,60069,600

3105-H25 Sheet 0.32 to 2.00 160 130 115 95 69,600

5005-H12-H14-H16-H32-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.00

0.40 to 50.000.20 to 25.000.15 to 4.00

125145165120140160

9511513585105125

901051257595110

758595758590

69,60069,60069,60069,60069,60069,600

5050-H32-H34-H32

-H34


0.40 to 6.300.20 to 6.30

All

All

150170150

170

110140110

140

95125105

130

9510590

105

69,60069,60069,600

69,600


( )

I-B-18 January 2005



RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)5052-O

-H32-H34

-H36


0.15 to 80.00AllAll

0.15 to 4.00

170215235

255

65160180

200

66145165

180

110130140

150

70,30070,30070,300

70,3005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321



270275275275305305285285

110165165125215215200200

110145145125180180165165

165165160170180180165165

71,70071,70071,70071,70071,70071,70071,70071,700

5086-O-H111-H111 -O-H112-H112-H112-H116-H32

-H34


up thru 130.00up thru 12.7012.70 to 130.000.50 to 50.004.00 to 12.5012.50 to 40.0040.00 to 80.001.60 to 50.00All

All

240250250240250240235275275

300

95145145 9512510595195195

235

95125125 95115110105180180

220

145145145145150145145165165

180

71,70071,70071,70071,70071,70071,70071,70071,70071,700

71,700

5154-H38 Sheet 0.15 to 3.20 310 240 230 165 71,7005454-O

-H111-H111-H112-O-H32-H34



215230230215215250270

85130130 85 85180200

85110110 90 85165185

130140130130130145160

71,70071,70071,70071,70071,70071,70071,700

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321


1.20 to 6.304.00 to 12.504.00 to 12.5012.50 to 40.0012.50 to 40.0040.00 to 80.0040.00 to 80.00

290315315305305285285

130230230215215200200

130185185170170170170

180185185170170170170

71,70071,70071,70071,70071,70071,70071,700


-T6, T6510, T6511-T6, T651-T6-T6


0.25 to 100.00Allup thru 2000.63 to 12.50All

290260290290260

240240240240240

240240240240240

185165170185165

69,60069,60069,60069,60069,600

6063-T5, -T52-T5-T6


up thru 12.50up thru 25.0012.50 to 25.00All

150150145205

110110105170

110110105170

909085130

69,60069,60069,60069,600




( )

January 2005 I-B-19

Table 3.3-2MINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEin.


2

ksi

SHEARFsuw ksi

Ftuw1

ksiFtyw

2 ksi

1100-H12, H14 All 11 3.5 3.5 8

3003-H12, H14, H16, H18 All 14 5 5 10

Alclad 3003-

H12, H14, H16, H18

All

13

4.5

4.5

10

3004-H32, H34, H36, H38 All 22 8.5 8.5 14

Alclad 3004-

H32, H34, H36, H38

All

21

8

8

13

3005-H25 Sheet 17 6.5 6.5 12

5005-H12, H14, H32, H34 All 15 5 5 9

5050-H32, H34 All 18 6 6 12

5052-O, H32, H34 All 25 9.5 9.5 16

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321


0.188-1.5001.501-3.000

394039

161817

151817

232424

5086-5086-5086-

O, H111H112O, H32, H34, H116


0.250-2.000353535

141414

131414

212121

5154-H38 Sheet 30 11 11 19

5454-5454-5454-

O, H111H112O, H32, H34


313131

121212

111212

191919

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

0.188-1.5001.501-3.000

4241

1918

1817

2525


6061-6061-

T6, T651, T6510, T65113

T6, T651, T6510, T65114

AllAll over 0.375

2424

1511

1511

1515

6063-T5, T52, T6 All 17 8 8 11

6351-6351-

T5, T63

T5, T64


2424

1511

1511

1515

6463-T6 Extrusions 0.125-0.500 17 8 8 11






I-B-20 January 2005

Table 3.3-2MMINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEmm


2

MPa

SHEARFsuw MPa

Ftuw1

MPaFtyw

2 MPa

1100-H12, H14 All 75 25 25 55

3003-H12, H14, H16, H18 All 95 35 35 70

Alclad 3003-

H12, H14, H16, H18

All

90

30

30

70

3004-H32, H34, H36, H38 All 150 60 60 95

Alclad 3004-

H32, H34, H36, H38

All

145

55

55

90

3005-H25 Sheet 115 45 45 85

5005-H12, H14, H32, H34 All 105 35 35 62

5050-H32, H34 All 125 40 40 85

5052-O, H32, H34 All 170 65 65 110

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321


6.30-38.0038.00-80.00

270270270

110115115

110115115

160165165

5086-5086-5086-

O, H111H112O, H32, H34, H116


6.30-50.00240240240

959595

859595

145145145

5154-H38 Sheet 205 75 75 130

5454-5454-5454-

O, H111H112O, H32, H34


215215215

858585

858585

130130130

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

6.30-38.0038.00-80.00

285285

125125

125120

170170


6061-6061-

T6, T651, T6510, T65113

T6, T651, T6510, T65114

AllAll over 9.50

165165

10580

10580

105105

6063-T5, T52, T6 All 115 55 55 75

6351-6351-

T5, T63

T5, T64


165165

10580

10580

105105

6463-T6 Extrusions 3.20-12.50 115 55 55 75



2. 0.2% offset in 50 mm gage length across a groove weld.

3. Values when welded with 5183, 5356, or 5556 alloy filler wire, regardless of thickness. Values also apply to thicknesses less than or equal to 9.5 mm when welded with 4043, 5554, or 5654 alloy filler wire.


January 2005 I-B-21


DESIGNATION BEGINS WITH –O, -H, -T1, -T2, -T3, OR -T4


ksiIntercept



1000 ) 1/2

] Bc = Fcy [ 1 + ( Fcy _____ 6900

) 1/2

] Dc = Bc ___ 20

( 6Bc ___ E

) 1/2

Cc = 2Bc ____ 3Dc


( Fcy ) 1/3

______ 7.6

] Bp = Fcy [ 1 + ( Fcy ) 1/3

______ 14.5

] Dp = Bp ___ 20

( 6Bp ___ E

) 1/2

Cp = 2Bp ____ 3Dp


( Fcy ) 1/5

______ 5.8

] Bt = Fcy [ 1 + ( Fcy ) 1/5

______ 8.5

] Dt = Bt ___ 3.7

( Bt __ E

) 1/3

Ct*


( Fcy ) 1/3

______ 7

] Bbr = 1.3Fcy [ 1 + ( Fcy ) 1/3

_____ 13.3

] Dbr = Bbr ___ 20

( 6Bbr ____ E

) 1/2



( Fy ) 1/5

_____ 5.8

] Btb = 1.5Fy [ 1 + ( Fy ) 1/5

_____ 8.5

] Dtb = Btb ___ 2.7

( Btb ___ E

) 1/3

Ctb = ( Btb - Bt _______ Dtb - Dt

) 2


Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 6.2

] Bs = Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 11.8

] Ds = Bs ___ 20

( 6Bs ___ E

) 1/2

Cs = 2Bs ____ 3Ds

Ultimate Strength of Flat Elements in Compression or Bending

k1 = 0.50, k2 = 2.04


I-B-22 January 2005


DESIGNATION BEGINS WITH -T5, -T6, -T7, -T8, OR -T9


ksiIntercept



2250 ) 1/2

] Bc = Fcy [ 1 + ( Fcy ______ 15510

) 1/2

] Dc = Bc ___ 10

( Bc __ E

) 1/2

Cc = 0.41 Bc ___ Dc


( Fcy ) 1/3

______ 11.4

] Bp = Fcy [ 1 + ( Fcy ) 1/3

______ 21.7

] Dp = Bp ___ 10

( Bp __ E

) 1/2

Cp = 0.41 Bp ___ Dp


( Fcy ) 1/5

______ 8.7

] Bt = Fcy [ 1 + ( Fy ) 1/5

______ 12.8

] Dt = Bt ___ 4.5

( Bt __ E

) 1/3

Ct*


( Fcy ) 1/3

______ 7 ] Bbr = 1.3Fcy [ 1 +

( Fcy ) 1/3

_____ 13.3

] Dbr = Bbr ___ 20

( 6Bbr ____ E

) 1/2



( Fy ) 1/5

_____ 8.7

] Btb = 1.5Fy [ 1 + ( Fy ) 1/5

_____ 12.8

] Dtb = Btb ___ 2.7

( Btb ___ E

) 1/3

Ctb = ( Btb - Bt ______ Dtb - Dt

) 2


Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 9.3

] Bs = Fty ___ √

__ 3 [ 1 +

( Fty / √__

3 ) 1/3

_________ 17.7

] Ds = Bs ___ 10

( Bs __ E

) 1/2

Cs = 0.41 Bs ___ Ds

Ultimate Strength of Flat Elements in Compression k1 = 0.35, k2 = 2.27

Ultimate Strength of Flat Elements in Bending k1 = 0.50, k2 = 2.04


January 2005 I-B-23

3.4 Design Stresses

Design stresses ϕFL shall be determined in accordance with the provisions of this Specification.

In the following subsections:• The resistance factor ϕ shall be taken from Table 3.4-1.• Values of coefficient kt shall be taken from Table 3.4-2.

• Values of k1 and k2 shall be taken from Tables 3.3-3 and 3.3-4.The formulas of this Section are also listed in Table 3.4-3.

Table 3.4-1COMMONLY USED RESISTANCE FACTORS

Resistance Factor Value Applicable Limit State

ϕy 0.95 general yield

ϕb 0.85 beams or elements of beams

ϕc 0.85 elements of columns

ϕu* 0.85 ultimate

ϕcc 1 – 0.21λ < 0.95 for λ < 1.20.14λ + 0.58 < 0.95 for λ > 1.2

columns

ϕcp 0.80 elastic buckling of tubes

ϕv 0.80 elastic shear buckling

ϕvp 0.90 inelastic shear buckling

ϕw 0.90 web crippling

*see Section 3.4.2 for an exceptionOther resistance factors for connections are given throughout the Specification.

Table 3.4-2COEFFICIENT kt

Alloy and TemperNon-welded or Regions

Farther than 1.0 in. (25 mm) from a Weld

Regions Within 1.0 in. (25 mm) of a Weld

2014-T6, -T651, -T6510, -T6511Alclad 2014-T6, -T651

1.25 –

6066-T6, -T6510, -T6511 1.1 –

6070-T6, -T62 1.1 –

All Others Listed in Table 3.3-1 1.0 1.0

kt is used in Sections 3.4.1, 3.4.2, 3.4.3, and 3.4.4.

I-B-24 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Des

ign

Str

ess

Tab

le 3

.4-3

G

EN

ER

AL

FO

RM

UL

AS

FO

R

DE

TE

RM

ININ

G D

ES

IGN

ST

RE

SS

F

RO

M S

EC

TIO

N 3

.4T

EN

SIO

N, a

xial

Any

tens

ion

mem

ber

gr

oss

sect

ion

ne

t sec

tion

1ϕ y

Fty

ϕ uF

tu /k

t

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

(flan

ges)

2ϕ y

Fty

or ϕ u

Ftu

/kt

Rou

nd o

r ov

al tu

bes

31.

17 ϕ

yFty

or

1.24

ϕuF

tu /k

t

Fla

t ele

men

ts in

ben

ding

in th

eir

ow

n pl

ane

(web

s)4

for

sym

met

ric s

hape

s:

1.3

ϕ yF

ty o

r1.

42 ϕ

uFtu

/kt

for

unsy

mm

etric

sha

pes

se

e S

ectio

n 3.

4.4

BE

AR

ING

On

rivet

s an

d bo

lts

52ϕ

uFtu

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d

hole

s6

2ϕuF

tu /1

.5F

or tu

bes

with

circ

umfe

rent

ial w

elds

, equ

atio

ns o

f Sec

tions

3.4

.10,

3.

4.12

, and

3.4

.16.

1 ap

ply

for

Rb

/t ≤

20.

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Des

ign

Str

ess

S ≤

S1

Sle

nd

ern

ess

Lim

it

S1

Des

ign

Str

ess

S1

< S

< S

2

Sle

nd

ern

ess

Lim

it

S2

Des

ign

Str

ess

S ≥

S2

CO

MP

RE

SS

ION

IN

CO

LU

MN

S,

axia

l, gr

oss

se

ctio

n

All

colu

mns

7S

ee S

ectio

n 3.

4.7

CO

MP

RE

SS

ION

IN

CO

LU

MN

E

LE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e—co

lum

ns

buck

ling

abou

t a s

ymm

etry

ax

is

8ϕ y

Fcy

b __

t = B

p – ϕ y

Fcy

____

_ ϕ c

____

____

_ 5.

1 D

p

ϕ c ( B

p – 5

.1 D

p b __

t ) b __

t =

k 1 B

p __

___

5.1

Dp

ϕ c k

2 √__

__

Bp E

__

____

___

5.1

b/t

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e—co

lum

ns

not b

uckl

ing

abou

t a

sym

met

ry a

xis

8.1

ϕ yF

cy b __

t = B

p – ϕ y

Fcy

____

_ ϕ c

____

____

_ 5.

1 D

p

ϕ c ( B

p – 5

.1 D

p b __

t ) b __

t = C

p __

_ 5.

1 ϕ c

π2 E

____

____

( 5.1

b/t

) 2

Fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

9ϕ y

Fcy

b __

t = B

p – ϕ y

Fcy

____

_ ϕ c

____

____

_ 1.

6 D

p

ϕ c ( B

p – 1

.6 D

p b __

t ) b __

t =

k 1 B

p __

___

1.6

Dp

ϕ c k

2 √__

__

Bp E

__

____

___

1.6

b/t

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

b

9.1

See

Sec

tion

3.4.

9.1

Fla

t ele

men

ts

supp

orte

d on

bot

h

edge

s an

d w

ith a

n

inte

rmed

iate

stif

fene

r

b ob o

9.2

See

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

su

ppor

ted

on b

oth

ed

ges

10ϕ y

Fcy

R

b __

t =

( Bt –

ϕ y F

cy

____

_ ϕ c

________

Dt

) 2

ϕ c ( B t

– D

t √___

Rb

__

t ) S

ee 3

.4.1

0

ϕ cp π2

E

________________

16 ( R

b __

t ) ( 1 +

√____

Rb /t

__

___

35

) 2

January 2005 I-B-25

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ub

-S

ec.

Des

ign

Str

ess

S ≤

S1

Sle

nd

ern

ess

Lim

it

S1

Des

ign

Str

ess

S1

< S

< S

2

Sle

nd

ern

ess

Lim

it

S2

Des

ign

Str

ess

S ≥

S2

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

11ϕ y

Fcy

L

b ____

r y √__

C

b = 1.

2 ( B

c – ϕ

y F

cy /ϕ

b )

__

__

__

__

__

__

__

_

Dc

ϕ b

( Bc –

D

c L

b __

____

_ 1.

2 r y

√__

Cb )

L

b ____

r y √__

C

b = 1

.2 C

c

ϕ b π

2 E

Cb

____

___

( L

b ____

1.2r

y ) 2

Rou

nd o

r ov

al tu

bes

121.

17ϕ y

Fcy

Rb

__

t =

( Btb –

1.17

( Fcy

ϕy /ϕ

b )

_____________

Dtb

) 2

ϕ b ( B tb

– D

tb √__

_ R

b __

t ) R

b __

t =

[ Btb –

( ϕc/

ϕ b ) B

t

_____________

D

tb –

( ϕc/

ϕ b ) D

t ] 2S

ame

as

Sec

ion

3.4.

10

Sol

id r

ecta

ngul

ar a

nd

roun

d se

ctio

ns

131.

3ϕy F

cy d __

t √___

Lb

___

Cb d =

( Bbr

– 1

.3 ( ϕ

y F

cy /

ϕ b )

_

__

__

__

__

__

__

2.3

Dbr

) ϕ

b ( B br –

2.3

Dbr

d _ t √___

Lb

___

Cb d )

d __

t √___

Lb

___

Cb d =

Cbr

___

2.3

ϕ b π

2 E

Cb

__

__

__

__

5.29

( d _ t ) 2 Lb __

d

Tubu

lar

shap

es

14

ϕ y F

cy

Lb S c

____

___

Cb √

____

I yJ/

2 =

( Bc –

( ϕy F

cy /ϕ

b ) _

__

__

__

__

__

__

1.6

Dc

) 2

ϕ b ( B c

– 1

.6D

c √_

______

LbS

c __

____

_ C

b √__

__

I yJ/

2 )

L

b S c

____

___

Cb √

____

I y J

/2 =

( Cc

___

1.6 ) 2

ϕ b

π2 E

____

____

____

2.

56 (

Lb S c

____

___

Cb √

____

I y J

/2 )

CO

MP

RE

SS

ION

IN

BE

AM

E

LE

ME

NT

S,

(ele

men

t in

un

iform

co

mpr

essi

on),

gr

oss

sect

ion

Fla

t ele

men

ts

supp

orte

d on

one

edg

e 15

ϕ y F

cy b __

t = B

p – ( ϕ

y F

cy /ϕ

b ) __

____

____

_ 5.

1 D

p

ϕ b [ B p –

5.1

Dp b __

t ] b __

t =

k 1 B

p __

____

5.1

Dp

ϕ b k

2 √__

__

Bp E

__________

5.1

b/t

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

16

ϕ y F

cy b __

t = B

p – ( ϕ

y F

cy /ϕ

b )

____

____

____

_ 1.

6 D

p

ϕ b [ B p –

1.6

Dp

b __

t ] b __

t =

k 1 B

p __

____

1.6

Dp

ϕ b k

2 √__

__

BpE

_

__

__

__

__

1.6

b/t

Cur

ved

elem

ents

sup

port

ed

on b

oth

edge

s 16

.11.

17ϕ y

Fcy

Rb

__

t =

( Bt –

1.1

7 ( ϕ

y F

cy /ϕ

b )

__

__

__

__

__

__

__

__

Dt

) 2

ϕ b ( B t

– D

t √___

Rb

__

t ) R

b __

t =

Ct

ϕ c

p π2

E

_

__

__

__

__

__

__

__

__

16 ( R

b __

t ) ( 1 +

√____

Rb/

t __

____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16

.2S

ee S

ectio

n 3.

4.16

.2

Fla

t ele

men

ts

supp

orte

d on

bot

h

edge

s an

d w

ith a

n

inte

rmed

iate

stif

fene

r

b ob o

16.3

See

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LE

ME

NT

S,

(ele

men

t in

bend

ing

in o

wn

plan

e), g

ross

se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

te

nsio

n ed

ge, c

ompr

essi

on

edge

free

17

1.3ϕ

y F

cy b __

t = B

br –

( ϕy /

ϕb ) 1

.3F

cy

________________

3.5

Dbr

ϕ b [ B br

– 3.

5 D

br b __

t ] b __

t = C

br

___

3.5

ϕ b π

2 E

____

____

( 3.5

b/t

) 2

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

18

1.3ϕ

y F

cy

h __

t = B

br –

( ϕy /

ϕb ) 1

.3F

cy

________________

mD

br

ϕ b [ B

br –

mD

br h __

t ] h __

t = k 1

Bbr

____

_ m

Dbr

ϕ b

k 2 √__

__

Bbr

E

____

____

_ m

h/t

Fla

t ele

men

ts s

uppo

rted

on

bo

th e

dges

and

with

a

long

itudi

nal s

tiffe

ner

191.

3ϕy F

cy h __

t = B

br –

( ϕy /

ϕb ) 1

.3F

cy

________________

0.29

Dbr

ϕ b [ B b

r – 0

.29D

br h _ t ]

h __

t = k 1

Bbr

____

_ 0.

29D

br

ϕ b

k 2 √_

___

Bbr

E

__

__

__

__

0.29

h/t

SH

EA

R IN

E

LE

ME

NT

S,

gros

s se

ctio

n

Uns

tiffe

ned

flat e

lem

ents

su

ppor

ted

on b

oth

edge

s 20

ϕ yF

ty

____

√__

3

h __

t = B

s – ϕ

yFty /

( ϕvp √__

3 )

_

__

__

__

__

__

_

1.25

Ds

ϕ v

p [ Bs –

1.2

5Ds h

__ t ]

See

3.4

.20

ϕ v

π2 E

__

__

__

__

( 1.2

5h/t

) 2

Stif

fene

d fla

t ele

men

ts

supp

orte

d on

bot

h ed

ges

21 ϕ y

Fty

____

√__

3

a e

__

t = B

s – ϕ

yFty /

( 1.3

75ϕ v

p √_

3 )

_

__

__

__

__

__

__

__

__

1.25

Ds

1.

375ϕ

vp [ B s

– 1

.25D

s a e

__

t ] S

ee 3

.4.2

1 1.

375ϕ

v π2 E

____

____

__

( 1.2

5ae /t

) 2

I-B-26 January 2005


Axial tensile stress produced by the factored loads shall not exceed

ϕFL = ϕyFty (Eq. 3.4.1-1)

on the gross area and

ϕFL = ϕuFtu /kt (Eq. 3.4.1-2)

on the effective net area (see Section 5.1.5).

where ϕy = 0.95, ϕu = 0.85

Values of kt are listed in Table 3.4-2.

Block shear rupture strength provisions for the end connec-tions of tension members are given in Section 5.1.3.

3.4.2 Tension in Extreme Fibers of Beams— Flat Elements In Uniform Tension

The design stress is the lesser of:

ϕFL = ϕyFty (Eq. 3.4.2-1)

and

ϕFL = ϕuFtu /kt (Eq. 3.4.2-2)

where ϕy = 0.95

ϕu = 0.85

3.4.3 Tension in Extreme Fibers of Beams—Round or Oval Tubes

The design stress is the lesser of:

ϕFL = 1.17ϕyFty (Eq. 3.4.3-1)

and

ϕFL = 1.24ϕuFtu /kt (Eq. 3.4.3-2)

where ϕy = 0.95

ϕu = 0.85

3.4.4 Tension in Extreme Fibers of Beams— Flat Elements In Bending in Their Own Plane

a. For elements symmetric about the bending axis, the design stress is the lesser of:

ϕFL = 1.3ϕyFty (Eq. 3.4.4-1)

and

ϕFL = 1.42ϕuFtu /kt (Eq. 3.4.4-2)

b. For elements unsymmetric about the bending axis, the extreme fiber stress of the element shall not exceed the limiting value from a. and the stress at midheight of the element shall not exceed the stress given in Section 3.4.2.

where ϕy = 0.95, ϕu = 0.85


ϕFL = 2ϕuFtu (Eq. 3.4.5-1)

where ϕu = 0.85

This value shall be used for a ratio of edge distance to fas-tener diameter of 2 or greater. For smaller ratios this design stress shall be multiplied by the ratio: (edge distance)/ (2 × fastener diameter). Edge distance is the distance from the center of the fastener to the edge of the material in the direction of the applied load and shall not be less than 1.5 times the fastener diameter to extruded, sheared, sawed, rolled, or planed edges.


ϕFL = 2ϕu Ftu / 1.5 (Eq. 3.4.6-1)

where ϕu = 0.85

(See Section 5.2.2 for limits on slot lengths.)


For members in axial compression, the design stress is the lesser of that determined from this Section and Sections 3.4.8 through 3.4.10.

a. ϕFL = ϕccFcy (Eq. 3.4.7-1)

for λ < S1

b. ϕFL = ϕcc ( Bc – Dc*λ ) (Eq. 3.4.7-2)

for S1* < λ < S2*

c. ϕFL = ϕccFcy ______

λ2 (Eq. 3.4.7-3)

for λ > S2

January 2005 I-B-27

where

λ = ( kl __ r ) ( 1 __ π ) √______

Fcy / E , slenderness parameter (Eq. 3.4.7-4)

Dc* = πDc √______

E / Fcy (Eq. 3.4.7-5)

S*1 =

Bc –Fcy ______ D*

c

(Eq. 3.4.7-6)

S*2 =

Cc __ π √_____

Fcy /E (Eq. 3.4.7-7)

ϕcc = 1 – 0.21λ ≤ 0.95 for λ ≤ 1.2 (Eq. 3.4.7-8)

ϕcc = 0.14λ + 0.58 ≤ 0.95 for λ > 1.2 (Eq. 3.4.7-9)

k = the effective length factor by rational analysis. k shall be taken larger than or equal to unity unless rational analysis justifies a smaller value.

L = the unsupported length r = radius of gyration of the column about the axis of

buckling

3.4.7.1 Sections Not Subject to Torsional or Torsional-Flexural Buckling

For closed sections and other sections that are not sub-ject to torsional or torsional-flexural buckling, kL/r shall be the largest slenderness ratio for flexural buckling of the column.

3.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or Torsional-Flexural Buckling

For doubly or singly symmetric sections subject to tor-sional or torsional-flexural buckling kL/r shall be the larger of the largest slenderness ratio for flexural buckling and the equivalent slenderness ratio determined for torsional-flexural buckling as follows:

( kL ___ r ) e = π √___

E __ Fe

(Eq. 3.4.7.2-1)

where Fe is the elastic critical stress determined as follows:

For torsional buckling:

Fe = Fet (Eq. 3.4.7.2-2)

For torsional-flexural buckling:

Fe = Fef = 1 ___ 2β

[ ( Fex + Fet ) – √_________________

( Fex + Fet ) 2 – 4βFexFet ]

(Eq. 3.4.7.2-3)

As an alternative, Fe for torsional-flexural buckling shall be obtained as follows:

Fe = Fef = FexFet _______

Fex + Fet (Eq. 3.4.7.2-4)

In the above equationsx-axis is the centroidal symmetry axisA = cross-sectional areaCw = torsional warping constant of the cross-sectionE = compressive modulus of elasticity (See

Table 3.3-1)

Fex = π2E ______ ( kxLb ____ rx

) 2 (Eq. 3.4.7.2-5)

Fet = 1 ____ Ar 2

0 ( GJ +

π2ECw ______ ( KtLt ) 2

) (Eq. 3.4.7.2-6)

G = shear modulus = 3E/8 (Eq. 3.4.7.2-7)J = torsion constantkx = effective length coefficient for buckling about

the x-axisKt = effective length coefficient for torsional

buckling. Kt shall be taken larger than or equal to unity unless rational analysis justifies a smaller value.

Lt = unbraced length for twistingLb = unbraced length for bending about the x-axis

ro = √___________

r 2 x + r 2 y + x 2 o (Eq. 3.4.7.2-8) polar radius of gyration of the cross-section about the shear center.

rx, ry = radii of gyration of the cross-section about the centroidal principal axes

xo = x - coordinate of the shear centerβ = 1 – (xo /ro)2 (Eq. 3.4.7.2-9)


For nonsymmetric sections subject to torsional or torsional-flexural buckling kL/r shall be determined by rational analysis.

3.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of Symmetry – Flat Elements Supported On One Edge

a. ϕFL = ϕyFcy (Eq. 3.4.8-1)

for b /t < S1

b. ϕFL = ϕc [ Bp – 5.1 Dp b __ t ] (Eq. 3.4.8-2)

for S1 S2

I-B-28 January 2005

where

S1 = Bp –

ϕy __ ϕc Fcy

_________ 5.1Dp

(Eq. 3.4.8-4)

S2 = k1Bp _____

5.1Dp (Eq. 3.4.8-5)

b = distance from unsupported edge of element to toe of the fillet or bend, except if the inside corner radius exceeds 4 times the thickness; then the inside radius shall be assumed equal to 4 times the thickness in calculating b. Element width b is illustrated in Fig-ure 3.4.8-1.

ϕy = 0.95

ϕc = 0.85

3.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is not an Axis of Symmetry – Flat Elements Supported On One Edge

a. ϕFL = ϕyFcy (Eq. 3.4.8.1-1)

for b /t < S1

b. ϕFL = ϕc [ Bp – 5.1Dp b __ t ] (Eq. 3.4.8.1-2)

for S1 S2

where

S1 = Bp –

ϕy __ ϕc Fcy

_________ 5.1Dp

(Eq. 3.4.8.1-4)

S2 = Cp ___ 5.1

(Eq. 3.4.8.1-5)

b = distance from unsupported edge of element to toe of the fillet or bend, except if the inside cor-ner radius exceeds 4 times the thickness; then the inside radius shall be assumed equal to 4 times the thickness in calculating b. Element width b is illus-trated in Figure 3.4.8-1.

ϕy = 0.95

ϕc = 0.85

January 2005 I-B-29

Figure 3.4.8-1FLAT ELEMENTS SUPPORTED ON ONE EDGE

if r > 4t, then use r = 4t to calculate b.

I-B-30 January 2005


a. ϕFL = ϕyFcy (Eq. 3.4.9-1)

for b /t ≤ S1

b. ϕFL = ϕc [ Bp – 1.6Dp b __ t ] (Eq. 3.4.9-2)

for S1 < b /t < S2

c. ϕFL = ϕc k2 √

____ BpE ________

1.6b/t (Eq. 3.4.9-3)

for b /t ≥ S2

where

S1 = Bp –

ϕy __ ϕc Fcy

_________ 1.6Dp

(Eq. 3.4.9-4)

S2 = k1Bp _____

1.6Dp (Eq. 3.4.9-5)


ϕy = 0.95

ϕc = 0.85

Figure 3.4.9-1FLAT ELEMENTS SUPPORTED ON BOTH EDGES


January 2005 I-B-31


The provisions of this Section apply when Ds /b ≤ 0.8. The design stress is the lesser of

ϕFL = ϕyFcy (Eq. 3.4.9.1-1)

and

ϕFL = FUT + ( FST – FUT ) ρST ≤ FST (Eq. 3.4.9.1-2)

For a simple straight lip edge stiffener of constant thick-ness, ϕFL shall not exceed the design stress for the stiffener according to Section 3.4.8.


Ds = defined in Figure 3.4.9.1-1 and -2FUT = design stress according to Section 3.4.8 neglect-

ing the stiffenerFST = design stress according to Section 3.4.9ρST = ratio to be determined as follows:

ρST = 1.0 for b/t ≤ S/3 (Eq. 3.4.9.1-3)

ρST = rs _________

9t ( b/ t ___ S – 1 __

3 ) ≤ 1.0 for S/3 < b/t ≤ S

(Eq. 3.4.9.1-4)

ρST = rs ____________

1.5t ( b/ t ___ S + 3 )

≤ 1.0 for 2S > b/t > S

(Eq. 3.4.9.1-5)


- For simple straight lip stiffeners of constant thick-ness similar to that shown in Fig. 3.4.9.1-1, rs shall be calculated as:


√__

3 (Eq. 3.4.9.1-6)



S =1.28 √___

E ___ Fcy

(Eq. 3.4.9.1-7)

b = distance from unsupported edge of element to toe of fillet or bend, except if the inside corner radius exceeds 4 times the thickness; then the inside radius shall be assumed to equal 4 times the thickness in calculating b. Element width b is illustrated in Figures 3.4.9.1-1 and 3.4.9.1-2.

ϕy = 0.95

I-B-32 January 2005





January 2005 I-B-33


a. ϕFL = ϕyFcy (Eq. 3.4.9.2-1)

for λs ≤ S1

b. ϕFL = ϕc ( Bc – Dcλs ) (Eq. 3.4.9.2-2)

for S1 < λs < S2

c. ϕFL = ϕcπ2E

_____ λ 2

s (Eq. 3.4.9.2-3)

for λs ≥ S2

The design stress ϕFL obtained above shall not be more than the design stress according to Section 3.4.9 for the sub-elements of the intermediately stiffened element.

The design stress ϕFL obtained above shall not be less than that determined according to Section 3.4.9 ignoring the intermediate stiffener.


As = area of the stiffenerIo = moment of inertia of a section comprising the stiff-

ener and one half of the width of the adjacent sub-elements and the transition corners between them taken about the centroidal axis of the section parallel to the element that is stiffened (Figure 3.4.9.2-1).

S1 = Bc –

ϕyFcy _____ ϕc ________

Dc (Eq. 3.4.9.2-4)

S2 = Cc (Eq. 3.4.9.2-5)

λs = 4.62 ( b __ t ) √______________

1 + As / bt

______________ 1 + √

__________

1 + 10.67Io ______

bt3 (Eq. 3.4.9.2-6)

ϕy = 0.95

ϕc = 0.85

I-B-34 January 2005

Figure 3.4.9.2-1FLAT ELEMENTS WITH AN INTERMEDIATE STIFFENER

Line o - o is the neutral axis of the stiffener and plate of width b/2 on each side of the stiffener. Io is the moment of inertia of the portion shown in the partial section.


January 2005 I-B-35


a. ϕFL = ϕyFcy (Eq. 3.4.10-1)

for Rb /t ≤ S1

b. ϕFL = ϕc [ Bt – Dt √___

Rb __ t ] (Eq. 3.4.10-2)

for S1 < Rb /t < S2

c. ϕFL = ϕcpπ2E

_________________

16 ( Rb __ t ) ( 1 + √

____ Rb /t _____

35 ) 2

(Eq. 3.4.10-3)

for Rb /t ≥ S2

where

S1 = ( Bt – ϕy __ ϕc

Fcy

________ Dt

) 2 (Eq. 3.4.10-4)

S2 = Rb /t at the intersection of Eqs. 3.4.10-2 and 3.4.10-3

ϕy = 0.95

ϕc = 0.85

ϕcp = 0.80

For tubes with circumferential welds, the equations of this Section apply for Rb /t < 20.


For single web shapes not subject to lateral buckling (bent about the strong axis with continuous lateral support or bent about the weak axis), determine the compressive design stress ϕFL from Sections 3.4.15 through 3.4.19 as applicable.

For single web shapes subject to lateral buckling (bent about the strong axis without continuous lateral support), the compressive design stress ϕFL is the lesser of that deter-mined from Sections 3.4.15 through 3.4.19 as applicable and the following:

a. ϕFL = ϕyFcy (Eq. 3.4.11-1)

for Lb _____

ry √___

Cb ≤ S1

b. ϕFL = ϕb [ Bc – DcLb ________

1.2ry √___

Cb ] (Eq. 3.4.11-2)

for S1 < Lb _____

ry √___

Cb < S2

c. ϕFL = ϕbCbπ2E

_______ ( Lb ____

1.2ry

) 2 (Eq. 3.4.11-3)

for Lb _____

ry √___

Cb ≥ S2

where

S1 = 1.2 ( Bc –

ϕyFcy _____ ϕb ) _____________

Dc (Eq. 3.4.11-4)

S2 = 1.2Cc (Eq. 3.4.11-5)

ϕy = 0.95

ϕb = 0.85

ry = radius of gyration of the shape (about an axis paral-lel to the web) (For shapes that are unsymmetrical about the horizontal axis, ry shall be calculated as though both flanges were the same as the compres-sion flange).

Lb = length of the beam between bracing points or between a brace point and the free end of a canti-lever beam. Bracing points are the points at which the compression flange is restrained against lateral movement or the cross section is restrained against twisting.


Alternatively, ϕFL may be calculated by replacing ry by rye given in Section 4.9.


a. ϕFL = 1.17ϕyFcy (Eq. 3.4.12-1)

for Rb /t < S1

b. ϕFL = ϕb ( Btb – Dtb √___

Rb __ t ) (Eq. 3.4.12-2)

for S1 < Rb /t < S2

c. For Rb /t > S2, the design bending stress shall be deter-mined from the formulas for tubes in compression in Sec-tion 3.4.10 using the formula that is appropriate for the particular value of Rb /t.

I-B-36 January 2005


Rb = mid-thickness radius of a round element or maxi-mum mid-thickness radius of an oval element

S1 = ( Btb – 1.17Fcyϕy /ϕb _______________ Dtb

) 2 (Eq. 3.4.12-3)

S2 = ( Btb – ϕc __ ϕb

Bt

_________ Dtb –

ϕc __ ϕb Dt

) 2 (Eq. 3.4.12-4)


ϕy = 0.95

ϕc = 0.85

ϕb = 0.85


For rectangular sections bent about the weak axis, rod, and square bar: ϕFL = 1.3ϕyFcy.

For rectangular sections bent about the strong axis:

a. ϕFL = 1.3ϕyFcy (Eq. 3.4.13-1)

for d __ t √____

Lb ____

Cb d ≤ S1

b. ϕFL = ϕb ( Bbr – 2.3Dbr d __ t √

____

Lb ____

Cb d ) (Eq. 3.4.13-2)

for S1 < d __ t √____

Lb ____

Cb d < S2

c. ϕFL = ϕbπ2E Cb _________

5.29 ( d __ t ) 2 Lb __ d (Eq. 3.4.1-3)

for d __ t √____

Lb ____

Cb d ≥ S2

where

S1 = Bbr – 1.3

ϕyFcy _____ ϕb

___________

2.3Dbr (Eq. 3.4.13-4)

S2 = Cbr ___ 2.3

(Eq. 3.4.13-5)

ϕy = 0.95 (Eq. 3.4.13-6)

ϕb = 0.85 (Eq. 3.4.13-7)

d = depth of sectionLb = length of the beam between bracing points or

between a brace point and the free end of a canti-

lever beam. Bracing points are the points at which the compression flange is restrained against lateral movement or the cross section is restrained against twisting.



For the purposes of this Specification, tubular shapes are defined as closed sections.

For tubular shapes not subject to lateral buckling (bent about the strong axis with continuous lateral support or bent about the weak axis) and round, square, hexagonal, and octagonal tubes, determine the compressive design stress ϕFL from Sections 3.4.12 and 3.4.15 through 3.4.19 as applicable.

For tubular shapes subject to lateral buckling (bent about the strong axis without continuous lateral support), the compressive allowable stress (ϕFL) is the lesser of that determined from Sections 3.4.12 and 3.4.15 through 3.4.19 as applicable and the following:

a. ϕFL = ϕyFcy (Eq. 3.4.14-1)

for Lb Sc __________

Cb ( √___

Iy J / 2 ) ≤ S1

b. ϕFL = ϕb ( Bc – 1.6Dc √___________

LbSc ___________

Cb ( √___

Iy J / 2 ) ) (Eq. 3.4.14-2)

for S1 < Lb Sc _________

Cb √___

Iy J / 2 < S2

c. ϕFL = ϕbπ2E ________________

2.56 ( LbSc __________ Cb ( √

___ Iy J / 2 )

) (Eq. 3.4.14-3)

for LbSc _________

Cb √___

Iy J / 2 ≥ S2

where

S1 = ( Bc – ϕyFcy _____ ϕb

_________

1.6Dc )

2

(Eq. 3.4.14-4)

S2 = ( Cc ___ 1.6

) 2 (Eq. 3.4.14-5)

ϕy = 0.95ϕb = 0.85Iy = moment of inertia of the beam about the minor axis J = torsion constantLb = length of the beam between bracing points or between

a brace point and the free end of a cantilever beam. Bracing points are the points at which the compres-sion flange is restrained against lateral movement or the cross section is restrained against twisting.

January 2005 I-B-37


Alternatively, ϕFL may be calculated by using the equa-tions in Section 3.4.11 and replacing ry by rye given in Sec-tion 4.9.

For narrow rectangular tubes bent about the strong axis with a depth-to-width ratio greater than or equal to 6, the term √

___ IyJ /2 may be replaced by Iy.


a. ϕFL = ϕyFcy (Eq. 3.4.15-1)

for b /t < S1

b. ϕFL = ϕb [ Bp – 5.1Dp b __ t ] (Eq. 3.4.15-2)

for S1 S2

where

S1 = Bp – ϕyFcy / ϕb ____________

5.1Dp (Eq. 3.4.15-4)

S2 = k1Bp _____

5.1Dp (Eq. 3.4.15-5)


ϕy = 0.95

ϕb = 0.85


a. ϕFL = ϕyFcy (Eq. 3.4.16-1)

for b /t < S1

b. ϕFL = ϕb [ Bp – 1.6Dp b __ t ] (Eq. 3.4.16-2)

for S1 S2

where

S1 = Bp –

ϕy __ ϕb Fcy

_________ 1.6Dp

(Eq. 3.4.16-4)

S2 = k1Bp _____

1.6Dp (Eq. 3.4.16-5)


ϕy = 0.95

ϕb = 0.85


a. ϕFL = 1.17ϕyFcy (Eq. 3.4.16.1-1)

for Rb /t < S1

b. ϕFL = ϕb [ Bt – Dt √___

Rb __ t ] (Eq. 3.4.16.1-2)

for S1 < Rb /t < S2

c. ϕFL = ϕcpπ2E

_________________

16 ( Rb __ t ) ( 1 + √

_____ Rb / t ______

35 ) 2

(Eq. 3.4.16.1-3)

for Rb /t > S2

where

S1 = ( Bt – 1.17Fcy ϕy /ϕb ______________ Dt

) 2 (Eq. 3.4.16.1-4)

S2 = Ct (Eq. 3.4.16.1-5)

ϕy = 0.95

ϕb = 0.85

ϕcp = 0.80

Ct shall be determined using a plot of the curves of design stress for values of Rb /t less than and greater than S2 or by a trial and error solution.

I-B-38 January 2005

For tubes with circumferential welds, the equations of this Section apply for Rb /t < 20.


The provisions of this Section apply when Ds /b < 0.8. The design stress is the lesser of

ϕFL = ϕyFcy (Eq. 3.4.16.2-1)

and

ϕFL = FUT + ( FST – FUT ) ρST ≤ FST (Eq. 3.4.16.2-2)

For a straight stiffener of constant thickness, ϕFL shall not exceed the design stress for the stiffener according to Section 3.4.8.


Ds = defined in Figure 3.4.9.1-1 and -2FUT = design stress according to Section 3.4.15 neglect-

ing the stiffenerFST = design stress according to Section 3.4.16ρST = ratio to be determined as follows:ρST = 1.0 for b/t ≤ S/3

ρST = rs ___________

9t ( b / t ____ S – 1 __

3 ) ≤ 1.0 for S/3 < b/t ≤ S

ρST = rs _____________

1.5t ( b / t ____ S + 3 )

≤ 1.0 for 2S > b/t > S


- For simple straight lip stiffeners of constant thick-ness similar to that shown in Figure 3.4.9.1-1, rs shall be calculated as:


√__

3



S = 1.28 √___

E ___ Fcy

b = distance from unsupported edge of element to toe of fillet or bend, unless the inside corner radius exceeds 4t; then the inside radius shall be assumed to be 4t to calculate b. Element width b is illustrated in Figure 3.4.9.1-1.

ϕy = 0.95


a. ϕFL = ϕyFcy (Eq. 3.4.16.3-1)

for λs ≤ S1

b. ϕFL = ϕb ( Bc – Dcλs ) (Eq. 3.4.16.3-2)

for S1 < λs < S2

c. ϕFL = ϕbπ2E

_____ λ 2

s (Eq. 3.4.16.3-3)

for λs ≥ S2

The design stress Fc obtained above shall not be more than the design stress according to Section 3.4.16 for the sub-elements of the intermediately stiffened element.

The design stress Fc obtained above shall not be less than that determined according to Section 3.4.16 ignoring the intermediate stiffener.


As = area of the stiffenerIo = moment of inertia of a section comprising the stiff-

ener and one half of the width of the adjacent sub-elements and the transition corners between them taken about the centroidal axis of the section parallel to the element that is stiffened (Figure 3.4.9.2-1).

S1 = Bc –

ϕy __ ϕb Fcy

_________ Dc

(Eq. 3.4.16.3-4)

S2 = Cc (Eq. 3.4.16.3-5)

λs = 4.62 ( b __ t ) √______________

1 + As / bt

______________ 1 + √

__________

1 + 10.67Io ______

bt3 (Eq. 3.4.16.3-6)

ϕy = 0.95ϕb = 0.85


a. ϕFL = 1.3ϕyFcy (Eq. 3.4.17-1)

for b /t < S1

b. ϕFL = ϕb [ Bbr – 3.5Dbr b __ t ] (Eq. 3.4.17-2)

for S1 S2

where

S1 = Bbr – 1.3Fcy ϕy /ϕb ______________

3.5Dbr (Eq. 3.4.17-4)

S2 = Cbr ___ 3.5

(Eq. 3.4.17-5)

ϕy = 0.95

ϕb = 0.85


a. ϕFL = 1.3ϕyFcy (Eq. 3.4.18-1)

for h /t < S1

b. ϕFL = ϕb [ Bbr – mDbr h __ t ] (Eq. 3.4.18-2)

for S1 < h /t < S2

c. ϕFL = ϕbk2 √

____ BbrE _________

( mh / t ) (Eq. 3.4.18-3)

for h /t > S2

where

S1 = Bbr – ( ϕy /ϕb ) 1.3Fcy

_______________ mDbr

(Eq. 3.4.18-4)

S2 = k1Bbr _____ mDbr

(Eq. 3.4.18-5)

m = 1.15 + co /(2cc) for –1 < co /cc < 1m = 1.3/(1 – co /cc) for co /cc < –1cc = distance from neutral axis to extreme fiber of the

element with the greatest compressive stressco = distance from neutral axis to other extreme fiber of

the element

Distances to compressive fibers are negative and dis-tances to tensile fibers are positive.

h = clear height of web (illustrated in Figure 3.4.18-1)

ϕy = 0.95

ϕb = 0.85

Figure 3.4.18-1DIMENSION NOTATION

I-B-40 January 2005


The provisions of this Section apply for stiffeners located at 0.4d1 from the flange as shown in Figure 3.4.19-1.

a. ϕFL = 1.3ϕyFcy (Eq. 3.4.19-1)

for h /t ≤ S1

b. ϕFL = ϕb [ Bbr – 0.29Dbr h __ t ] (Eq. 3.4.19-2)

for S1 < h /t < S2

c. ϕFL = ϕbk2 √

____ BbrE _________

0.29h / t (Eq. 3.4.19-3)

for h /t ≥ S2

where

S1 = Bbr – 1.3ϕyFcy / ϕb ______________

0.29Dbr (Eq. 3.4.19-4)

S2 = k1Bbr _______

0.29Dbr (Eq. 3.4.19-5)

h = clear web height (see Fig. 3.4.19-1)d1 = clear distance from the neutral axis to the compres-

sion flange (see Fig. 3.4.19-1)ϕy = 0.95ϕb = 0.85


a. ϕFL = ϕyFty _____ √

__ 3 (Eq. 3.4.20-1)

for h /t ≤ S1

b. ϕFL = ϕvp [ Bs – 1.25Ds h __ t ] (Eq. 3.4.20-2)

for S1 < h /t < S2

c. ϕFL = ϕvπ2E

_________ ( 1.25h / t ) 2

(Eq. 3.4.20-3)

for h /t ≥ S2

where

h = clear web height (see Fig. 3.4.18-1)

S1 = Bs – Fty ϕy / ( ϕvp √

__ 3 ) _________________

1.25Ds (Eq. 3.4.20-4)

S2 = h/t at the intersection of Eqs. 3.4.20-2 and 3.4.20-3ϕy = 0.95ϕv = 0.80ϕvp = 0.90

3.4.21 Shear in Elements – Stiffened Flat Elements Supported on Both Edges

a. ϕFL = ϕyFty ____ √

__ 3 (Eq. 3.4.21-1)

for ae /t ≤ S1

b. ϕFL = 1.375ϕvp [ Bs – 1.25Ds ae __ t ] (Eq. 3.4.21-2)

for S1 < ae /t < S2

c. ϕFL = 1.375ϕvπ2E

__________ ( 1.25ae / t ) 2

(Eq. 3.4.21-3)

for ae /t ≥ S2

where

ae = a1 ____________

√___________

1 + 0.7 ( a1 __ a2 ) 2

a1 = shorter dimension of rectangular panela2 = longer dimension of rectangular panel

S1 =

Bs – ϕyFty __________

1.375 ϕvp √__

3

______________ 1.25Ds

(Eq. 3.4.21-4)

S2 = ae /t at the intersection of Eqs. 3.4.21-2 and 3.4.21-3

ϕy = 0.95ϕv = 0.80ϕvp = 0.90

Figure 3.4.19-1DIMENSIONS h AND d1

January 2005 I-B-41




A member subjected to axial compression and bending moment loads shall be proportioned in accordance with the following two formulas (both equations must be checked):

fa __ Fa

+ Cmxfbx _____________

Fbx ( 1 – fa / Fex ) +

Cmy fby ____________ Fby ( 1– fa / Fey )

≤ 1.0

(Eq. 4.1.1-1)

fa ___

Fao +

fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.1-2)

When fa /Fa < 0.15, the following Equation 4.1.1-3 shall be permitted to be used in lieu of Equations 4.1.1-1 and 4.1.1-2:

fa __ Fa

+ fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.1-3)

In Equations 4.1.1-1, 4.1.1-2, and 4.1.1-3, the subscripts x and y, combined with subscripts b, m, and e indicate the axis of bending about which a particular stress or design parameter applies and

fa = average compressive stress on cross section produced by the factored compressive load

fb = maximum compressive bending stress pro-duced by the factored transverse loads and/or end moments

Fa = design compressive stress ϕFL for member considered as axially loaded column according either to Sections 3.4.7 through 3.4.10 or 4.7.2

Fb = design compressive stress ϕFL for member considered as a beam according to either Sec-tions 3.4.11 through 3.4.19 or 4.7.2

Cm = 0.6 – 0.4(M1/M2) for members whose ends are prevented from sway



Fao = design compressive stress ϕFL of an axially loaded member considered as a short column according to Section 4.7.2 without consideration of Section 3.4.7

Fe = design elastic buckling stress

= ϕccπ2E

_______ ( k L /r ) 2

r = radius of gyration about the bending axisL = unsupported length in the plane of bending k = effective length factor in the plane of bending


A member subjected to axial tension and bending shall be proportioned in accordance with the formula:

fa __ Ft

+ fbx ___ Fbx

+ fby ___ Fby

≤ 1.0 (Eq. 4.1.2-1)

In Equation 4.1.2-1, the subscripts x and y, combined with the subscript b indicate the axis of bending about which a particular stress or design parameter applies and where

fa = average tensile stress on cross section produced by the factored tensile load

fb = maximum tensile bending stress produced by the factored transverse loads and/or end moments

Fb = design tensile stress for the member as a beam according to Section 3.4.2 through 3.4.4 and 4.7.3

Ft = design tensile stress for the member loaded only axially according to Section 3.4.1


Design shear stresses in round or oval tubes subjected to torsion or shear loads shall be determined from Section 3.4.20 with the ratio h/t given by

h __ t = 2.9 ( Rb __ t ) 5/8

( Ls __ Rb

) 1/4

(Eq. 4.2-1)

where

Rb = mid-thickness radius of a round tube or maximum mid-thickness radius of an oval tube

t = thickness of tubeLs = length of tube between circumferential stiffeners,

or overall length if no circumferential stiffeners are present

4.3 Torsion and Bending in Open Shapes

The stresses in open sections caused by torsion due to twisting moments applied directly or due to lateral loads or supports not in the plane of the shear center of open sections shall include shear, flexural and warping stresses. The stresses thus computed plus those due to bending shall not exceed the appropriate design stress for the type of stress in the element considered.

I-B-42 January 2005

4.4 Combined Shear, Compression, and Bending

Design combinations of shear, compression, and bending shall be determined from either of the following formulas:

a. For walls of curved surfaces or round tubular members:

fa __ Fa

+ fb __ Fb

+ ( fs __ Fs

) 2 ≤ 1.0 (Eq. 4.4-1)

b. For webs of rectilinear shapes, plates of built-up girders or similar members:

fa __ Fa

+ ( fb __ Fb

) 2 + ( fs __ Fs

) 2 ≤ 1.0 (Eq. 4.4-2)

where

fa = average compressive stress produced by factored axial compressive load

Fa = design compressive stress for members subjected to compression only

fb = maximum bending stress (compression) produced by applied factored bending moment

Fb = design bending stress (compression) for members subjected to bending only

fs = shear stress caused by factored torsion or trans-verse shear loads

Fs = design shear stress for members subjected only to torsion or shear


If a longitudinal stiffener is used on a beam web, it shall be located so that the distance from the toe of the compres-sion flange to the centroid of the stiffener is 0.4 of the dis-tance from the toe of the compression flange to the neutral axis of the beam. The longitudinal stiffener shall have a moment of inertia, about the web of the beam, not less than that given by the expression:

Ih = 0.02αs fth3

_________ E

[ ( 1 + 6Ah ___ ht

) ( s __ h ) 2 + 0.4 ] (Eq. 4.5-1)

where

Ah = gross cross sectional area of longitudinal stiffenerf = compressive stress at toe of flangeh = clear height of web between flangesIh = moment of inertia of the longitudinal stiffener. For

a stiffener consisting of equal members on both sides of the web, the moment of inertia Ih shall be the sum of the moments of inertia about the cen-terline of the web. For a stiffener consisting of a member on one side only, the moment of inertia shall be taken about the face of the web in contact with the stiffener.

s = distance between transverse stiffenerst = thickness of the webαs = 1, for stiffener consisting of equal members on

both sides of web

αs = 3.5, for stiffener consisting of member on only one side of web


When a stiffener is composed of a pair of members, one on each side of the web, the stiffener spacing s shall be the clear distance between the pairs of stiffeners. When a stiffener is composed of a member on one side only of the web, the stiffener spacing s shall be the distance between rivet lines or other connecting lines.

For a stiffener composed of members of equal size on each side of the web, the moment of inertia of the stiffener shall be computed about the centerline of the web. For a stiff-ener composed of a member on one side only of the web, the moment of inertia of the stiffener shall be computed about the face of the web in contact with the stiffener.

In the determination of the required moment of inertia of stiffeners, the distance h shall be taken as the full clear height of the web regardless of whether or not a longitudi-nal stiffener is present.

Unless the outer edge of a stiffener is continuously stiff-ened, its thickness shall not be less than 1/12th the clear width of the outstanding leg.

4.6.1 Stiffeners for Web Shear

Stiffeners applied to beam webs to resist shear buckling shall have a moment of inertia not less than the value given by the following expression:

s __ h ≤ 0.4, Is =

0.55Vh2

_______ E

( s __ h ) (Eq. 4.6.1-1)

s __ h > 0.4, Is =

0.088Vh2

________ E

( h __ s ) (Eq. 4.6.1-2)

where

h = clear height of webIs = moment of inertia of stiffeners = stiffener spacingV = unfactored shear force on web at stiffener location

Stiffeners shall extend from flange to flange but need not be connected to either flange.

4.6.2 Bearing Stiffeners

Bearing stiffeners at points of support of concentrated loads shall be connected to the web by enough rivets, or other means, to transmit the load. Such stiffeners shall be fitted to form a tight and uniform bearing against the loaded flanges, unless welds, designed to transmit the full reaction or load, are provided between flange and stiffener.

Only that part of a stiffener cross section which lies outside the fillet of the flange angle shall be considered as effective in bearing.

January 2005 I-B-43

The moment of inertia of the bearing stiffener shall not be less than that given by the following expression:

Ib = Is + 1.95Pbsh2

________ π2E

(Eq. 4.6.2-1)

where

E = compressive modulus of elasticityh = clear height of web between flangesIb = required moment of inertia of bearing stiffener Is = moment of inertia required to resist shear bucklingPbs = concentrated load on stiffener



Where local buckling stress values are required to be cal-culated, the critical stresses, Fcr, given in Table 4.7.1-1 shall be used. For cases not covered in Table 4.7.1-1, the value of Fcr shall be determined using the expression for ϕFL in the appropriate subsection of Section 3.4 for the case b/t > S2 with the resistance factors ϕ taken as 1.0.


As an alternative to using the least of the design com-pressive stresses of a section’s elements for the design axial compressive stress of the section, the weighted aver-age design axial compressive stress shall be determined in accordance with this Section.

The weighted average design axial compressive stress of a section is the average design stress of the section’s ele-ments, where the design stress for each element is weighted by the ratio of the area of the element to the total area of the section.

The design stress in elements with stiffeners shall not exceed the design stress in an intermediate stiffener or an edge stiffener.

The design axial compressive stress of the section shall not exceed that given by Section 3.4.7.


As an alternative to using the least of the strengths of a section’s elements for the bending strength of the section, the strength shall be determined in accordance with this Section.

The design stress in elements with stiffeners shall not exceed the design stress in an intermediate stiffener or an edge stiffener.

For shapes not subject to lateral buckling, the design bending moment Ma is the lesser of the design compressive bending moment and the design tensile bending moment.

The design compressive bending moment is

Mac = Fcf If / ccf + FcwIw / ccw (Eq. 4.7.3-1)

where

Fcf = the design compressive stress for the flat elements in uniform compression

Fcw = the design compressive stress for the flat elements in bending in their own plane

If = the moment of inertia of the flange group about the neutral axis of the entire section. The flange group consists of the flat elements in uniform compression and the flat elements in uniform ten-sion and their edge or intermediate stiffeners.

Iw = the moment of inertia of the web group about the neutral axis of the entire section. The web group consists of the flat elements in bending in their own plane and their intermediate stiffeners.

ccf = the distance from the centerline of the compression flange to the neutral axis of the entire cross-section

ccw = the distance from the web group’s extreme com-pression fiber to the neutral axis of the entire cross-section

(See Figure 4.7.3-1).

Table 4.7.1-1Section Local Buckling Stress, Fcr

3.4.8 and 3.4.15 π2E ________ ( 5.1b / t ) 2

3.4.9 and 3.4.16 π2E ________ ( 1.6b / t ) 2

3.4.9.1 and 3.4.16.2 ( ϕFL ) 2 ______ ϕyFcy

3.4.18 π2E _______ ( mh / t ) 2

π2E _________ ( 0.65h / t ) 2

for yNA = h/2

3.4.19 π2E _________ ( 0.29h / t ) 2

I-B-44 January 2005

If there are stiffeners located farther than the compres-sion flange from the neutral axis of the entire cross-section, the design compressive bending moment shall not exceed

ϕyFcf If / ccs + FcwIw / ccw (Eq. 4.7.3-2)

where

ccs = the distance from the neutral axis of the entire cross-section to the extreme fiber of compression flange stiffeners

The design tensile bending moment is

Mat = Ftf If / ctf + FtwIw / ctw (Eq. 4.7.3-3)

where

Ftf = the design tensile stress for the flat elements in uniform tension

Ftw = the design tensile stress for the flat elements in bending in their own plane

If , Iw = the same as abovectf = the distance from the extreme tension fiber to the

neutral axis of the entire cross-sectionctw = the distance from the web group’s extreme ten-

sion fiber to the neutral axis of the entire cross-section

For shapes subject to lateral buckling, the design bend-ing moment Ma is the least of the design compressive bend-ing moment Mac, the design tensile bending moment Mat, and Fb S where

Fb = design compression bending stress given by Section 3.4.11 or 3.4.14

S = section modulus of the entire cross-section

Figure 4.7.3-1

January 2005 I-B-45


An additional limitation shall be placed on the design stress for columns in which local buckling of the cross section occurs at a stress that is less than the calculated flexural buckling stress of the column, assuming that the elements are not buckled. The design stress ϕFL shall not exceed the value given by

ϕFrc = ϕuFec1/3Fcr

2/3 (Eq. 4.7.4-1)

For ϕuFcr < ϕFL (Eq. 4.7.4-2)

where

ϕFL = design stress for column given in Section 3.4.7Fcr = element local buckling stress given in Section 4.7.1

Fec = π2E ______ ( kL /r ) 2

ϕFrc = design stress for column with buckled elementsϕu = 0.85

The design stress also shall not exceed the design stress given in Section 4.7.2.


The design compressive bending stress shall be reduced for single web beams whose flanges consist of thin, flat elements supported on one edge and in which local buck-ling of the cross section occurs at a stress that is less than the lateral buckling stress of the beam, calculated assuming that the elements are not buckled. The design stress shall not exceed the value given by

ϕFrb = ϕy ( Feb ) 1/3 ( Fcr ) 2/3 (Eq. 4.7.5-1)

For ϕyFcr < ϕFL (Eq. 4.7.5-2)

where

Fcr = element local buckling stress given in Section 4.7.1Feb = elastic lateral buckling stress of beam calculated

using Eq. 3.4.11-3 with ϕb = 1.0 or the equations of Section 4.9

ϕFrb = design stress for beam with buckled elementsϕFL = design stress for beam given in Section 3.4.11 or

Section 4.9ϕy = 0.95

The design stress also shall not exceed the design stress for the section given in Section 4.7.2.


The effective width concept shall be used to determine an effective section for the moment of inertia used to cal-culate deflections.

For sections containing elements covered in Sections 3.4.15, 3.4.16, 3.4.18, or 3.4.19 with b/t or h/t values exceeding 1.65S2 and elements covered in Sections 3.4.16.2 or 3.4.16.3 with Fcr < fa, the effective width be of a thin ele-ment subjected to direct compression stresses is:

If fa ≤ Fcr , be = b (Eq. 4.7.6-1)

If fa > Fcr , be = b √_____

Fcr /fa (Eq. 4.7.6-2)

where

be = effective width of flat element to be used in deflec-tion calculations

b = width of element as defined in Sections referred to above

Fcr = local buckling stress for element from Section 4.7.1fa = compressive stress for element due to applied

unfactored loads

The same expression is used to calculate the effective width on the compression side of a web in bending, with the maximum compressive bending stress due to the applied loads, fb, replacing fa. In this case the effective web area is to be placed next to the compression flange.


For interior reactions and concentrated loads:

ϕPL = ϕwCwa ( N + Cw1 ) _____________

Cwb (Eq. 4.7.7-1)

For end reactions and concentrated loads:

ϕPL = 1.2ϕwCwa ( N + Cw2 ) ________________

Cwb (Eq. 4.7.7-2)

where

Cwa = t2 sin θ ( 0.46Fcy + 0.02 √____

EFcy ) (Eq. 4.7.7-3)

Cwb = Cw3 + Ri ( 1 – cos θ ) (Eq. 4.7.7-4)

Cw1 = 5.4 in. (140 mm)Cw2 = 1.3 in. (33 mm)Cw3 = 0.4 in. (10 mm)E = compressive modulus of elasticity of the webFcy = compressive yield strength of the webϕ PL = design transverse force per web for flat websN = length of bearing at the reaction or concentrated

load Ri : for shapes made by bending, Ri = bend radius at juncture of the flange and web measured to the inside of the bend; for extruded shapes, Ri = 0

I-B-46 January 2005

t = web thickness θ = angle between the plane of web and the plane of

the bearing surface (θ < 90 degrees)ϕw = resistance factor = 0.90


Design combinations of interior reactions and concen-trated loads and bending shall be determined from the fol-lowing formula:

( M ____ ϕMa )

1.5

+ ( P ___ ϕPL )

1.5

≤ 1.0 (Eq. 4.7.8-1)

where

M = bending moment due to factored loads applied to the member

ϕMa = design bending moment for the member if bend-ing moment alone is applied to the member

P = applied interior reaction or concentrated load due to factored loads per web for flat webs

ϕPL = design interior reaction or concentrated load per web for flat webs calculated according to Section 4.7.7.

4.8 Fatigue

Welded details, mechanically fastened joints and base material of aluminum alloys subjected to repeated fluctua-tions of stress shall meet all the static requirements of this Specification as well as the fatigue requirements of this Sec-tion. Fatigue design of castings and associated details shall be made by testing in accordance with Section 9.

Categories of details for fatigue design parameters shall be chosen from Figure 4.8-1 and Table 4.8-1.

The maximum and minimum stresses used to calculate the stress range are nominal stresses caused by unfac-tored loads and determined by standard elastic methods. Stresses perpendicular to the expected plane of cracking shall be used.


For constant amplitude loading

Sra ≤ Srd (Eq. 4.8.1-1)

where

Sra = applied stress range at service loads, the algebraic difference between the minimum and maximum calculated stress in the member or detail


Srd = Cf N–1/m (Eq. 4.8.1-2)

Cf , m = constants from Table 4.8.1-1 and shown in Fig-ure 4.8.1-1


If the applied stress range, Sra, is less than the constant amplitude fatigue limit as given in Table 4.8.1-1, then no further fatigue consideration shall be needed. The allow-able stress range, Srd shall not be less than the value from Equation 4.8.1-2 when N = 5 × 106 cycles and shall not be greater than the value from Equation 4.8.1-2 when N = 105 cycles.


If the maximum stress range in the spectrum at unfac-tored loads is less than the fatigue limit, then no further fatigue assessment shall be needed.

For variable amplitude loading:

Sre ≤ Srd (Eq. 4.8.2-1)

where

Sre = equivalent stress range

Sre = ( ∑ i = 1

Ns

αi S m ri ) 1/m

(Eq. 4.8.2-2)

Srd = the allowable stress range at unfactored loads

Srd = Cf N–1/m (Eq. 4.8.2-3)


Sri = the ith stress range in the spectrumCf , m = constants from Table 4.8.1-1 and shown in

Figure 4.8.1-1NS = the number of stress ranges in the spectrum N = the number of cycles to failure

The allowable stress range Srd shall not be greater than the value from Equation 4.8.2-3 when N = 105 cycles.

January 2005 I-B-47




Plain Material Base metal with rolled, extruded, drawn, or cold finished surfaces; cut or sheared surfaces with ANSI/ASME B46.1 surface roughness of 1000μ in. (25μm) or less.

A 1, 2

Built up Members Base metal and weld metal in members, without attachments, built-up of plates or shapes connected by continuous full- or partial-penetration groove welds or continuous fillet welds parallel to the direction of applied stress.

Calculated flexural stress, fb, in base metal at toe of welds on girder webs or flanges adjacent to welded transverse stiffeners.

Base metal at end of partial-length welded cover plates having square or tapered ends, with or without welds across the ends.

B

C

E

3, 4, 5

6, 21

5

Mechanically Fastened Base metal at the gross section of slip-critical connections and at the net section of bearing connections, where the joint configuration does not result in out-of-plane bending in the connected material and the stress ratio (the ratio of minimum stress to maximum stress)3 Rs is

Rs ≤ 0 0 < Rs < 0.5 0.5 ≤ Rs

Base metal at the gross section of slip-critical connections and at the net section of bearing connections, where the joint configuration results in out-of-plane bending in connected material.

BDE

E

777

8

Fillet Welds Base metal at intermittent fillet welds.

Base metal at junction of axially loaded members with fillet welded end connections. Welds shall be disposed about the axis of the members so as to balance weld stresses.

Weld metal of continuous or intermittent longitudinal or transverse fillet welds.

E

E

F

15, 17

5, 15,18

Groove Welds Base metal and weld metal at full-penetration groove welded splices of parts of similar cross section ground flush, with grinding in the direction of applied stress and with weld soundness established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welded splices at transitions in width or thickness, with welds ground to slopes no steeper than 1 to 2.5, with grinding in the direction of applied stress, and with weld soundness established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welded splices, with or without transitions having slopes no greater than 1 to 2.5, when reinforcement is not removed and/or weld soundness is not established by radiographic or ultrasonic inspection.

Base metal and weld metal at full-penetration groove welds with perma-nent backing

B

B

C

E

9, 10

11, 12

9, 10, 11, 12

22

See last page of this table for footnotes.

I-B-48 January 2005


(Continued)



Attachments Base metal detail of any length attached by groove welds subject to transverse and/or longitudinal loading, when the detail embodies a tran-sition radius, R, not less than 2 in. (50 mm) and with the weld termina-tion ground smooth:

R ≥ 24 in. (610 mm) 24 in. > R ≥ 6 in. (150 mm) 6 in. > R ≥ 2 in. (50 mm)

Base metal at a detail attached by groove welds or fillet welds, where the detail dimension parallel to the direction of stress, a, is less than 2 in. (50 mm)

Base metal at detail attached by groove welds or fillet welds subject to longitudinal loading, with transition radius, if any, less than 2 in. (50 mm):

2 in. (50 mm ) ≤ a ≤ 12b or 4 in. (100 mm) a > 12b or 4 in. (100 mm)

where a = detail dimension parallel to the direction of stress b = detail dimension normal to the direction of stress and the surface of

the base metal

Base metal at a detail of any length attached by fillet welds or partial- penetration groove welds in the direction parallel to the stress, when the detail embodies a transition radius, R, not less than 2 in. (50 mm) and weld termination ground smooth: R ≥ 24 in. (610 mm) 24 in. (610 mm) > R ≥ 6 in. (150 mm) 6 in. (150 mm) > R ≥ 2 in. (50 mm)

BCD

C

DE

BCD

131313

19

1414, 19, 20

161616

1. See Table 4.8.1-1. All stresses are T and Rev., where “T” signifies range in tensile stress only; “Rev.” signifies a range involving reversal of tensile or compressive stress; except Category F where stress range is in shear including shear stress reversal.

2. See Figure 4.8-1. These examples are provided as guidelines and are not intended to exclude other reasonably similar situations.

3. Tensile stresses are considered to be positive and compressive stresses are considered to be negative.

January 2005 I-B-49


I-B-50 January 2005


(continued)

January 2005 I-B-51

Table 4.8.1-1CONSTANTS FOR S-N CURVES1

Detail Category3

Cf

mFatigue Limit2

ksi MPa ksi MPa

A 96.5 665 6.85 10.2 70

B130 900 4.84 5.4 37

C278 1920 3.64 4.0 28

D157 1080 3.73 2.5 17

E160 1100 3.45 1.8 13

F174 1200 3.42 1.9 13

1. Different constants are to be used for calculations in ksi and MPa

2. Fatigue limit is based on N = 5x106

3. See Table 4.8-1

Figure 4.8.1-1SCHEMATIC FATIGUE CURVE

I-B-52 January 2005

4.9 Compression in Single Web Beams Including Single Web Beams With Tubular Portions

For compression in single web beams including single web beams with tubular portions, analysis shall be con-ducted using either the provisions of Section 3.4.11 or by replacing ry in Section 3.4.11 with rye determined in accor-dance with Sections 4.9.1 through 4.9.3. Sections with the tension flange partially or fully braced and with the com-pression flange laterally unbraced shall be designed using Section 4.9 without consideration of tensile flange restraint or another rational method of analysis.

4.9.1 Doubly Symmetric Sections and Sections Symmetric About the Bending Axis

For checking beam sections at brace or support points or between brace or support points of beam spans subjected to end moment only or to transverse loads applied at the neutral axis of the beam:

rye = 1 ___ 1.7

√____________________

Iyd ___ Sc

√________________

1 + 0.152 J __ Iy

( kyLb ____ d ) 2 (Eq. 4.9.1-1)

For checking beam spans between brace or support points of beams subjected to transverse loads applied on the top or bottom flange (where the load is free to move laterally with the beam if the beam buckles):

rye = 1 ___ 1.7

√_______________________________

Iyd

___ Sc

[ ± 0.5 + √__________________

1.25 + 0.152 J __ Iy

( kyLb ____ d ) 2 ]

(Eq. 4.9.1-2)

The minus sign in front of the term ‘0.5’ shall be used when the load is on a flange acting towards the shear cen-ter; the plus sign shall be used when the load is on a flange acting away from the shear center.

In the above equations y-axis is the centroidal symmetry or principal axis such that the tension flange has a positive y coordi-nate and bending is about the x-axis

rye = effective radius of gyrationIy = moment of inertia of beam about axis parallel to webSc = section modulus of beam, compression sideJ = torsion constant of beam. For non-tubular open sec-

tions an approximate value of J shall be calculated by assuming the section to be composed of rectangles and letting J equal the sum of the terms bt3/3 for each rectangle where b is the larger dimension. The term for each rectangle whose b/t ratio is less than 10 shall be computed by the expression (1/3 – 0.2t/b) bt3.

For sections containing open parts and tubular por-tions, J shall be taken as the sum of J for the open parts and the tubular parts.

ky = effective length coefficient for compression flange about the y-axis. ky shall not be taken less than 1.

Lb = length of the beam between bracing points or between a brace point and the free end of a cantilever beam. Bracing points are the points at which the compres-sion flange is restrained against lateral movement or the cross section is restrained against twisting

d = depth of beam.


For a beam that is unsymmetric about the bending axis, the rye in Section 4.9.1 is calculated by taking Iy, Sc, and J as though both flanges were the same as the compression flange with the overall depth remaining the same.

4.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis, Doubly Symmetric Sections and Sections Without an Axis of Symmetry

For a loading that does not cause torsion or lateral bend-ing a more accurate value of rye is determined according to this Section. If the loading causes torsion and/or lateral bend-ing, warping stress and/or lateral bending flexural stress, the provisions of Section 4.3 shall apply.

rye = Lb ____

1.2π √____

Me ___ ESc

(Eq. 4.9.3-1)

where

Me = the elastic critical moment determined as follows:

Me = AFey [ U + √___________

U2 + r 2 o ( Fet ___ Fey

) ] (Eq. 4.9.3-2)

Me for cantilever beams shall be determined by rational analysis unless the free end is braced or if the beam load-ing is covered in Section 4.9.4. References for rational analysis are given in the Commentary.

In the above equations y-axis is the centroidal symmetry or principal axis such that the tension flange has a positive y coordinate and bending is about the x-axisA = cross-sectional areaC1 and C2 = coefficients to be taken from Section 4.9.4,

or, for cases not covered in Section 4.9.4, determined by rational analysis

Cw = torsional warping constant of the cross sectionE = compressive modulus of elasticity (see Table 3.3-1)

Fey = π2E ______ ( kyLb ____ ry

) 2 (Eq. 4.9.3-3)

Fet = 1 ____ Ar 2 o

( GJ + π2ECw ______ ( Kt Lt ) 2

) (Eq. 4.9.3-4)

January 2005 I-B-53

G = shear modulus = 3E/8g0 = distance from the shear center to the point of

application of the load; taken as + when the load is applied directed away from the shear center and – when the load is directed towards the shear cen-ter. When there is no transverse load (pure moment cases) g0 = 0.

Iy = moment of inertia of the section about the y axisJ = torsion constant (See definition in Section 4.9.1)

j = 1 ___ 2Ix

( ∫ A

y3dA + ∫ A

yx2dA ) – yo (Eq. 4.9.3-5)

For doubly symmetric I sections, j = 0For singly symmetric I sections, as an alternative to

equation 4.9.3-5,

j = 0.45df ( 2Icy ___ Iy

–1 ) [ 1 – ( Iy __ Ix

) 2 ] (Eq. 4.9.3-6)

where Icy is the moment of inertia of the compression flange taken about the web, Ix and Iy are the moments of inertia of the entire section about the x- and y-axes and df is the distance between the flange centroids or for T-sections df is the distance between the flange centroid and the tip of the stem.

For singly symmetric I sections where the smaller flange is not less than 80 percent of the area of the larger flange j shall be permitted to be taken as – yo.

ky = effective length coefficient for compression flange about the y-axis. ky shall not be taken less than 1.0.

Lt = unbraced length for twisting.

ro = √________________

r 2 x + r 2 y + x 2 o + y 2 o (Eq. 4.9.3-7)

= Polar radius of gyration of the cross-section about the shear center.

rx , ry = actual radii of gyration of the cross-section about the centroidal principal axes

Sc = section modulus for the extreme compression fiber for bending about the x-axis

U = C1g0 - C2 j (Eq. 4.9.3-8)

xo = x - coordinate of the shear centeryo = y - coordinate of the shear center

The origin of the coordinate system is the intersection of the principal axes.


For cases not covered in Sections 4.9.4.3 and 4.9.4.4, coefficients Cb, C1 and C2 shall be determined as specified in Section 4.9.4.1 or 4.9.4.2.

4.9.4.1 Doubly Symmetric Sections

Cb: Cb = 12.5MMAX _________________________

2.5MMAX + 3MA + 4MB + 3MC

(Eq. 4.9.4.1-1)

whereMMAX = absolute value of maximum moment in the

unbraced beam segment

MA = absolute value of moment at quarter point of the unbraced beam segment

MB = absolute value of moment at mid-point of the unbraced beam segment

MC = absolute value of moment at three-quarter point of the unbraced beam segment

Cb values for doubly symmetric section cantilever beams unbraced at the free end are given in Section 4.9.4.4. Cb values for cantilever beams braced at the free end can be evaluated using Eq. 4.9.4.1-1.

C1: When the moments vary linearly between the ends of the unbraced segment C1 = 0. For some special cases the values of C1 are given in Section 4.9.4.3. For other variations, unless more accurate values are available, C1 shall be taken as 0.5.

C2: Since j = 0, a value of C2 is not needed.

4.9.4.2 Singly Symmetric Sections

Cb: For sections with Icy /Iy less than or equal to 0.1 or greater than or equal to 0.9, Cb = 1.0

For sections with Icy /Iy greater than 0.1 and less than 0.9, the value of Cb shall be determined according to Eq. 4.9.4.1-1.

When MMAX produces compression on the larger flange and the smaller flange is also subjected to compres-sion in the unbraced length, then the member shall be checked at the location of MMAX as well as at the location where the smaller flange is subjected to its maximum compression. Cb at the location of MMAX shall be calculated using Eq. 4.9.4.1-1. Cb for the location where the smaller flange is subjected to its maximum compression shall be taken as 1.67.



I-B-54 January 2005

4.9.4.3 Special Cases—Doubly or Singly Symmetric Sections

For simply supported beams with loadings listed below, the following Cb, C1 and C2 values shall be used, except for sections with Icy /Iy less than or equal to 0.1 or greater than or equal to 0.9 where Cb shall be taken as 1.0:

a. Uniformly distributed load over the entire span Cb = 1.13, C1 = 0.41Cb, C2 = 0.47Cb

b. One concentrated load placed at a distance aL from one of the ends of span

Cb = 1.75 – 1.6a ( 1 – a ) (Eq. 4.9.4.3-1)

C1 = Cb _______

a ( 1-a ) π2 sin2πa (Eq. 4.9.4.3-2)

C2 = Cb – C1 ______

2 (Eq. 4.9.4.3-3)

c. Two concentrated loads placed symmetrically at a dis-tance aL from each end of span

Cb = 1 + 2.8a3 (Eq. 4.9.4.3-4)

C1 = 2Cb ____ aπ2 sin2πa (Eq. 4.9.4.3-5)

C2 = ( 1 – a ) Cb – C1 ___ 2 (Eq. 4.9.4.3-6)

4.9.4.4 Cantilever Beams

For cantilever beams braced at the support and unbraced at the free end Cb shall be taken as follows:

Concentrated load at free end applied at the centroid Cb = 1.28, ky = 1.0

Uniform transverse load applied at the centroid Cb = 2.08, ky = 1.0

Uniform bending moment Cb = 0.50, ky = 2.1


Design compressive stresses in elastically supported flanges, such as the compression flange of a standing seam roof or of a hat-shaped beam loaded with the two flanges in compression, shall be determined from Section 3.4.11 with the following effective value of Lb /ry, substituted in the formulas for design stress.

Effective Lb __ ry

= 2.7 ( EA 2 c ____ βsIyc

) 1/4

(Eq. 4.10-1)

where

Ac = area of compression element (compression flange plus 1/3 of the area of the web between the com-pression flange and the neutral axis

E = compressive modulus of elasticityIyc = moment of inertia of compression element about

an axis parallel to the vertical webβs = spring constant (transverse force applied to the



The strength of a single angle in flexure (Mn) is given in this Section. The design strength is ϕMn, where ϕ = 0.95 for yield limit states and ϕ = 0.85 for all other limit states.

a. For local buckling:

1) If a leg tip is a point of maximum compression (Fig-ure 4.11-1):

Figure 4.11-1

Mn = 1.3FcyS (Eq. 4.11-1)

for b/t ≤ S1

Mn = [ Bbr – 4Dbr ( b/t ) ] Sc (Eq. 4.11-2)

for S1 < b/t < S2

Mn = π2ESc/ ( 4 ( b/t ) ) 2 (Eq. 4.11-3)

for b/t ≥ S2

where

S1 = ( Bbr – 1.3Fcy ) / ( 4Dbr ) (Eq. 4.11-4)

S2 = Cbr /4 (Eq. 4.11-5)

2) If a leg is in uniform compression (Figure 4.11-2):

Figure 4.11-2

Mn = Fcy Sc (Eq. 4.11-6)

for b/t ≤ S1

January 2005 I-B-55

Mn = [ Bp – 5.1Dp ( b/t ) ] Sc (Eq. 4.11-7)

for S1 < b/t < S2

Mn = π2ESc/ ( 5.1 ( b/t ) ) 2 (Eq. 4.11-8)

for b/t ≥ S2

where

S1 = ( Bp – Fcy ) / ( 5.1Dp ) (Eq. 4.11-9)

S2 = Cp /5.1 (Eq. 4.11-10)

b. For yielding (Figure 4.11-3):

a. Angles with continuous lateral-torsional restraint: Mn is the lesser of:

1) local buckling strength determined by Section 4.11a.

2) yield strength determined by Section 4.11b.

b. Equal leg angles with lateral-torsional restraint only at the point of maximum moment: Strengths shall be calculated with Sc being the geometric section modu-lus. Mn is the least of:

1) local buckling strength determined by Section 4.11a.

2) yield strength determined by Section 4.11b. 3) If the leg tip is in compression, lateral-torsional

buckling strength determined by Section 4.11c with

Me = 0.82Eb4tCb _________

L 2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 – 1 ] (Eq. 4.11.1-1)

If the leg tip is in tension, lateral-torsional buckling strength determined by Section 4.11c with

Me = 0.82Eb4tCb _________

L 2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 + 1 ] (Eq. 4.11.1-2)

c. Equal leg angles without lateral-torsional restraint: Strengths shall be calculated with Sc being 0.80 of the geometric section modulus.

If the leg tip is in compression, Mn is the lesser of:

1) local buckling strength determined by Section 4.11a(1)

2) lateral-torsional buckling determined by Section 4.11c with

Me = 0.66Eb4tCb _________

L 2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 – 1 ] (Eq. 4.11.1-3)

If the leg tip is in tension, Mn is the lesser of:

1) yield strength determined by Section 4.11b 2) lateral-torsional buckling determined by Section

4.11c with

Me = 0.66Eb4tCb _________

L 2b

[ √______________

1 + 0.78 ( Lbt / b2 ) 2 + 1 ] (Eq. 4.11.1-4)

d. Unequal leg angles without lateral-torsional restraint: moments about the geometric axes shall be resolved into moments about the principal axes and the angle shall be designed as an angle bent about a principal axis (Section 4.11.2).


Bending about principal axes is shown in Figure 4.11.2-1.a. Equal leg angles, major axis bending: Mn is the lesser

of: 1) local buckling strength determined by

Section 4.11a

Figure 4.11-3

Mn = 1.3My (Eq. 4.11-11)

where My = yield moment about the axis of bending.

c. For lateral-torsional buckling:

for Me ≤ My, Mn = ( 0.92 – 0.17Me /My ) Me (Eq. 4.11-12)

for Me > My, Mn = ( 1.92 – 1.17 √______

My /Me ) My ≤ 1.3My

(Eq. 4.11-13)

where Me = elastic lateral-torsional buckling moment from Section 4.11.1 or 4.11.2 as applicable.

Cb shall be determined in accordance with Section 4.9.4.1 but shall not exceed 1.5.


Bending about a geometric axis is shown in Figure 4.11.1-1.

Subsections a. and b.

Subsection c.

Figure 4.11.1-1

I-B-56 January 2005

2) lateral-torsional buckling strength determined by Section 4.11c, with

Me = 0.46Cb Eb2t2

__________ Lb

(Eq. 4.11.2-1)

b. Unequal leg angles, major axis bending: Mn is the lesser of:

1) local buckling strength determined by Section 4.11a for the leg with its tip in compression

2) lateral-torsional strength determined by Section 4.11c, with

Me = 4.9E Iz __ L2

b

Cb [ √________________ βw

2 + 0.052 ( Lbt / rz ) 2 + βw ] (Eq. 4.11.2-2)

Iz = minor principal axis moment of inertiarz = minor principal axis radius of gyration

βw = [ 1 __ Iw

∫

z ( w2 + z2 ) dA ] – 2zo, (Eq. 4.11.2-3)

βw is a section property for unequal leg angles and is positive when the short leg is in compression and negative when the long leg is in compression. (See the Commentary for values for common angle sizes and equations for deter-mining βw.) If the long leg is in compression anywhere along the unbraced length of the angle, βw is negative.

zo = coordinate along the z-axis of the shear center with respect to the centroid

Iw = major principal axis moment of inertia c. Equal and unequal leg angles, minor axis bending: 1) If the leg tips are in compression, Mn is the lesser

of the local buckling strength determined by Section 4.11a(1) and the yield strength determined by Sec-tion 4.11b.

2) If the leg tips are in tension, Mn is the yield strength determined by Section 4.11b.


For uniform compression on elements with linearly varying thickness where δ < 2.0:

a. For tapered thickness elements with the thick edge sup-ported and the thin edge free, the slenderness ratio is

(1 – 0.12δ) ( b ___ tavg )

b. For tapered thickness elements with the thin edge sup-ported and the thick edge free, the slenderness ratio is

( b ___ tavg )

c. For tapered thickness elements supported on both edges, the slenderness ratio is

( b ___ tavg )

whereb = width of the element

tavg = tmax + tmin ________

2

= the average thickness of the elementtmin = lesser thickness tmax = greater thickness

δ = tmax – tmin ________ tmin

Figure 4.11.2-1

Figure 4.12-1


As an alternative to Section 3, the compressive strength of elements of beams composed entirely of flat elements addressed by Sections 3.4.15, 3.4.16, 3.4.16.2, 3.4.16.3, or 3.4.18 shall be determined as follows in Sections 4.13.1 and 4.13.2. The design stress for the shape shall then be determined using Section 4.7.3, except that the strength of any stiffened element need not be limited to the strength of the stiffener.

4.13.1 Compressive Strength of Beam Elements– Flat Elements in Uniform Compression

a. ϕFL = ϕyFcy (Eq. 4.13.1-1)

for λeq ≤ S1

b. ϕFL = ϕb ( Bp – Dpλeq ) (Eq. 4.13.1-2)

for S1 < λeq < S2

c. ϕFL = ϕbk2 √

____ BpE ________ λeq

(Eq. 4.13.1-3)

for λeq ≥ S2

Minor Axis Bending

Major Axis Bending

January 2005 I-B-57

where

S1 = Bp – ϕyFcy /ϕb ___________

Dp (Eq. 4.13.1-4)

S2 = k1Bp ____ Dp

(Eq. 4.13.1-5)

λeq = π √___

E ___ Fcr

(Eq. 4.13.1-6)

Fcr = Mcr /Sc

where Mcr is the elastic buckling moment of the beam under pure bending with continuous lateral support determined by linear elastic analysis and Sc is the com-pressive section modulus of the entire cross section.

4.13.2 Compressive Strength of Beam Elements– Flat Elements in Bending In Their Own Plane

a. ϕFL = 1.3ϕyFcy (Eq. 4.13.2-1)

for λeq ≤ S1

b. ϕFL = ϕb ( Bbr – Dbrλeq ) (Eq. 4.13.2-2)

for S1 < λeq < S2

c. ϕFL = ϕbk2 √

____ BbrE _________ λeq

(Eq. 4.13.2-3)

for λeq ≥ S2

where

S1 = Bbr – 1.3ϕyFcy /ϕb ______________

Dbr (Eq. 4.13.2-4)

S2 = k1Bbr ____ Dbr

(Eq. 4.13.2-5)

λeq = π √___

E ___ Fcr

(Eq. 4.13.2-6)

Fcr = Mcr /Sc

where Mcr is the elastic buckling moment of the beam under pure bending with continuous lateral support determined by linear elastic analysis and Sc is the com-pressive section modulus of the entire cross section.

I-B-58 January 2005


5.1 General


If the distance from the center of a fastener to the edge of the connected part in the direction of the force on the fastener is less than 2D, the design bearing strength of the connected part shall be factored by this distance divided by 2D, where D is the nominal diameter of the fastener. (See Sections 3.4.5 and 3.4.6).

The distance from the center of a fastener to an edge of a part shall not be less than 1.5D.


The pitch and gage of fasteners joining components of tension members shall not exceed (3 + 20t) in. [(75 + 20t) mm] where t is the thickness of the outside component.

In outside components of compression members:

1) the pitch of fasteners in the direction of stress shall be based on the design stress from Section 3.4.7 with an effective length kL = s/2, where s is the pitch, and

2) the gage of fasteners perpendicular to the direction of stress shall be based on the design stress from Sec-tion 3.4.9 with a width b = 0.8g where g is the gage. If only one line of fasteners is used, the design stress shall be based on Section 3.4.8.1 with a width b = the edge distance of the fastener.


The block shear rupture design strength ϕRn of bolted connections on a failure path with shear on some segments and tension on the other segments is:

For Ftu Ant ≥ Fsu Anv

ϕRn = ϕ ( ( Fty / √__

3 ) Agv + Ftu Ant ) (Eq. 5.1.3-1)

Otherwise

ϕRn = ϕ ( FsuAnv + Fty Agt ) (Eq. 5.1.3-2)

The block shear rupture design strength ϕRn of welded connections on a failure path with shear on some segments and tension on the other segments is:

For Ftu Agt ≥ Fsu Agv

ϕRn = ϕ ( ( Fty / √__

3 ) Agv + Ftu Agt ) (Eq. 5.1.3-3)

Otherwise

ϕRn = ϕ ( FsuAgv + Fty Agt ) (Eq. 5.1.3-4)

whereϕ = 0.85Agv = gross area in shearAgt = gross area in tensionAnv = net area in shearAnt = net area in tension

5.1.4 Net Area

The net area An of a member is the sum of the products of the thickness and the least net width of each element computed as follows:

The width of holes shall be taken as the nominal hole diameter for drilled or reamed holes and the nominal hole diameter plus 1/32 in. (0.8 mm) for punched holes.

For a chain of holes extending across a part in any diagonal or zigzag line, the net width of the part shall be obtained by deducting from the gross width the sum of the hole widths of all holes in the chain, and adding, for each gage space in the chain, the quantity s2/4g where

s = longitudinal center-to-center spacing (pitch) of any two consecutive holes

g = transverse center-to-center spacing (gage) between fastener gage lines

For angles, the gage for holes in opposite legs shall be the sum of the gages from the back of the angles less the thickness.

Weld metal in plug or slot welds shall not be included in the net area.


The effective net area for angles, channels, tees, zees, and I-shaped sections shall be determined as follows:

1) If tension is transmitted directly to each of the cross-sectional elements of the member by fasteners or welds, the effective net area Ae is the net area.

2) If tension is transmitted by fasteners or welds through some but not all of the cross-sectional elements of the member, the effective net area Ae is:

Ae = An ( 1 – _ x __

L ) ( 1 –

_ y __

L ) (Eq. 5.1.5-1)

whereAn = net area of the member at the connectionL = length of the connection in the direction of load,

measured from the center of fasteners or the end of welds

_ x = eccentricity of the connection in the x axis direction

_ y = eccentricity of the connection in the y axis direction

If the length of the connection L is zero, the net effective area is the net area of the connected elements.

January 2005 I-B-59

5.1.6 Long Grips

If the grip (total thickness of parts being fastened) of an aluminum fastener exceeds 4.5D, the fastener’s nominal shear strength shall be reduced by dividing by [1/2+Gf /(9D)] where Gf is the grip and D is the fastener’s nominal diameter.

5.1.7 Strength and Arrangement of Connections

If the center of resistance of a connection does not coin-cide with the resultant line of action of the load, members and connections shall be proportioned to account for load eccentricities at the connection.


The bearing length for countersunk holes shall be the part thickness less one-half the depth of the countersink.


5.2.1 Bolt Material

Bolt fastener material shall be one of the following:

a. Aluminum: Bolts shall meet ASTM F468 and be 2024-T4, 6061-T6, or 7075-T73. When 2024 bolts will be exposed to contact with liquid water or humidity near the dew point in the intended service, they shall have a minimum 0.0002 in. (0.005 mm) thick anodic coating. Nuts shall meet ASTM F467. Nuts for ¼ in. (M6) bolts and smaller shall be 2024-T4; larger nuts shall be 6061-T6 or 6262-T9. Flat washers shall be Alclad 2024-T4. Spring lock wash-ers shall be 7075-T6.

b. Carbon steel: Carbon steel bolts, nuts, and washers shall be hot-dip galvanized to ASTM A153 or electro- galvanized to ASTM B633. Galvanizing thickness shall be adequate to provide corrosion protection for the antici-pated service. Hot-dipped galvanized A490 bolts shall not be used. Galvanized steel fasteners shall be lubricated to eliminate galling and assure adequate preload. When other platings and/or coatings are used, evidence shall be submitted to substantiate their corrosion resistance when in contact in aluminum. Bolt hardness shall be less than Rockwell C35.

c. Stainless steel: Stainless steel bolts, nuts and wash-ers shall be 300 series stainless steel. Bolts shall meet ASTM F593. Nuts shall meet ASTM F594.

5.2.2 Holes and Slots for Bolts

The nominal diameter of holes for bolts shall not be more than 1/16 in. (2 mm) greater than the nominal diam-eter of the bolt unless slip-critical connections are used.

The nominal width of slots for bolts shall not be more than 1/16 in. (2 mm) greater than the nominal diameter of the bolt. If the nominal length of the slot exceeds 2.5D or the edge distance is less than 2D, where D is the nominal bolt diameter, the edge distance perpendicular to the slot

length and slot length shall be sized to avoid overstress-ing the material along the slot. Unless slip-critical connec-tions are used, the length shall be normal to the direction of load.

5.2.3 Bolt Tension

The design tension load on an aluminum bolt is the root area of the bolt (π/4[D − 1.191/n]2) times its design tensile stress, which is 0.65Ftu, where n = number of threads/in. (See Table 5.2.3-1 or Table 5.2.3-1M).

5.2.4 Bolt Shear

The design shear load on an aluminum bolt is its effec-tive shear area times its design shear stress, which is 0.65Fsu. (See Table 5.2.3-1 or Table 5.2.3-1M). The effec-tive shear area for bolts with no threads in the shear plane shall be based on the nominal diameter. The effective shear area for bolts with threads in the shear plane shall be based on the root diameter (D − 1.191/n).

5.2.5 Bolt Bearing

The design bearing load applied by a bolt to an alu-minum part is the part’s design bearing stress (see Sec-tions 3.4.5 and 3.4.6) times the effective bearing area of the bolt. The bolt’s effective bearing area is its nominal diameter multiplied by the bearing length (see Section 5.1.8 for countersunk holes). This applies to threaded and unthreaded surfaces.

5.2.6 Minimum Spacing of Bolts

The minimum distance between bolt centers shall be 2.5 times the nominal bolt diameter.

5.2.7 Lockbolts

Lockbolts shall meet the requirements in this Specifica-tion for conventional bolts and be installed in conformance with the lockbolt manufacturer’s specifications. The bear-ing areas under the head and collar shall not be less than those of a conventional bolt and nut.

5.2.8 Slip-Critical Bolted Connections

5.2.8.1 General

Slip-critical connections between aluminum members or between aluminum and steel members shall comply with the Research Council on Structural Connections (RCSC) Specification for Structural Joints Using ASTM A325 or A490 Bolts, Load and Resistance Factor Design, except as modified here. The factored shear on a bolt in a slip-critical connection shall not exceed the design shear for the bolt (Section 5.2.8.4), the design bearing for the connected members (Section 3.4.5), or the design slip load (Section 5.2.8.5).

I-B-60 January 2005

5.2.8.2 Material

Aluminum used in slip-critical connections shall have a tensile yield strength of at least 15 ksi (105 MPa). Bolts shall comply with ASTM A325, nuts shall comply with ASTM A563 Grade DH or ASTM A194 Grade 2H, and washers shall comply with ASTM F436. Bolts, nuts, and washers shall be zinc coated by the hot-dip or mechanically deposited processes as specified in ASTM A325.

5.2.8.3 Holes

Holes shall be standard holes, oversize holes, short slot-ted holes, or long slotted holes. The nominal dimensions for each hole type shall not exceed those shown in the RCSC Specification Table 1.


The factored shear load on a bolt shall not exceed the design shear strength of the bolt. The design shear strength of a bolt is ϕRn

where

Rn = Fn Ab (Eq. 5.2.8.4-1)

where

Rn = nominal bolt strength Fn = 48 ksi for shear on bolts with threads in the shear

planeFn = 60 ksi for shear on bolts without threads in the

shear planeAb = nominal cross sectional area (unthreaded body

area) of a boltϕ = resistance factor = 0.75

The factored shear load on a bolt divided by the nomi-nal bolt diameter and the thickness of the connected part shall not exceed the design bearing stress specified in Section 3.4.5.


In addition to the requirements of Section 5.2.8.4, bolts shall be proportioned so that the design slip resistance is not exceeded by the nominal loads. The design slip resistance is

ϕRs = ϕDµTm Ns (Eq. 5.2.8.5-1)

where

ϕ = resistance factor = 1.0 for standard holes = 0.85 for oversized and short-slotted holes = 0.70 for long-slotted holes transverse to the direc-

tion of load = 0.60 for long-slotted holes parallel to the direction

of load

Rs = nominal slip resistance for a single boltD = 0.80, slip probability factorµ = mean slip coefficient = 0.50 for aluminum surfaces abrasion blasted with

coal slag to SSPC SP-5 to an average substrate profile of 2.0 mils (0.05 mm) in contact with simi-lar aluminum surfaces or zinc painted steel sur-faces with a maximum dry film thickness of 4 mils (0.1 mm) are Class B surfaces. For other surfaces, slip coefficients shall be determined in accordance with the RCSC Specification Appendix A.

Tm = minimum fastener tension specified in Section 5.2.8.7.

Ns = number of slip planes

The effect on slip resistance of temperature changes from the installation temperature and the difference in coefficients of thermal expansion of aluminum and steel shall be addressed.

5.2.8.6 Washers

a. Washers shall be used under bolt heads and under nuts.b. At a long slotted hole in an outer ply, a galvanized steel

plate washer or bar at least 5/16 in. (8 mm) thick with standard holes, shall be used. The plate washer or bar shall completely cover the slot but need not be hard-ened.

c. Where the outer face of the bolted parts has a slope greater than 1:20 with respect to a plane normal to the bolt axis, a beveled washer shall be used.


Bolts shall be tightened in accordance with the RCSC Specification.



Rivet material shall be one of the following:a. Aluminum: Aluminum shall meet ASTM B 316.b. Carbon steel: Carbon steel shall not be used unless the

aluminum is joined to carbon steel (see Section 6.7.1), or corrosion resistance of the structure is not required, or the structure is protected against corrosion.

c. Stainless steel: Stainless steel shall be 300 series.

5.3.2 Holes for Cold-Driven Rivets

The finished diameter of holes for cold-driven rivets shall not be more than 4% greater than the nominal diam-eter of the rivet.

5.3.3 Rivet Tension

Rivets shall not be used to carry tensile loads.

January 2005 I-B-61

5.3.4 Rivet Shear

The design shear load on an aluminum rivet is its effective shear area times its design shear stress, which is 0.65Fsu. (See Table 5.3.4-1 or Table 5.3.4-1M). The effec-tive shear area of solid rivets shall be based on the nominal hole diameter. (See Section 5.3.2 for hole size limits and Section 5.3.8 for hollow-end rivets).

5.3.5 Rivet Bearing

The design bearing load applied by a rivet to an alumi-num part is the part’s design bearing stress (see Section 3.4.5) times the effective bearing area of the rivet. The rivet’s effective bearing area is the nominal hole diame-ter multiplied by the bearing length (see Section 5.1.8 for countersunk holes).

5.3.6 Minimum Spacing of Rivets

The minimum distance between rivet centers shall be 3 times the nominal rivet diameter.

5.3.7 Blind Rivets

Grip lengths and hole sizes for blind rivets shall comply with the rivet manufacturer’s specifications.

5.3.8 Hollow-End (Semi-tubular) Rivets

The shear strength of hollow-end rivets with solid cross sections for a portion of the length shall be taken equal to the strength of solid rivets of the same material if the bottom of the cavity is at least 25% of the rivet diameter from the plane of shear.


This Section applies to tapping screws with a nominal diameter from 0.164 in. (4.2 mm) through 0.25 in. (6.3 mm). Screws shall be thread-forming or thread-cutting, with or with-out a self-drilling point. As an alternate to Sections 5.4.1 and 5.4.2, strengths shall be based on tests according to Section 9.

Screws shall be installed and tightened in accordance with the manufacturer’s specifications.

The following nomenclature applies to this Section:

Asn = thread stripping area of internal thread per unit length of engagement

C = coefficient that depends on screw locationD = nominal screw diameterDh = nominal hole diameter Dw = nominal washer diameter Dws = larger of the nominal washer diameter and the

screw headFtu1 = tensile ultimate strength of member in contact

with the screw headFtu2 = tensile ultimate strength of member not in con-

tact with the screw head

Fty1 = tensile yield strength of member in contact with the screw head

Fty2 = tensile yield strength of member not in contact with the screw head

Ks = coefficient that depends on member thicknessn = number of threads per unit length for a screwϕsc = resistance factor = 0.5ϕu = resistance factor = 0.85Pnt = nominal tensile strength of a screwPnot = nominal pull-out strength of a screwPnov = nominal pull-over strength of a screwPns = nominal shear strength of a screwt1 = thickness of member in contact with the screw

headt2 = thickness of member not in contact with the

screw headtc = depth of full thread engagement of screw into t2

not including tapping or drilling point


Screws shall be:a. aluminum,b. austenitic stainless steel, orc. if the screw will not be exposed to contact with liquid

water or humidity near the dew point in its intended service:

1) non-austenitic stainless steel with a minimum nomi-nal composition of 16% chromium and a Rockwell hardness less than C35 in the load bearing portion of the shank, or

2) coated or plated carbon steel with a Rockwell hardness less than C35 in the load bearing por-tion of the shank. Screws shall be zinc coated per ASTM A123, A641, or B633 or nickel/chromium plated per ASTM B456, Type SC. When other platings and/or coatings are to be used, evidence shall be submitted to substantiate the corrosion resistance of these products.

5.4.2 Screw Tension

For screws that carry tensile loads, the head of the screw or washer, if a washer is provided, shall have a diameter Dw not less than 5/16 in. (8 mm). Washers shall be at least 0.050 in. (1.3 mm) thick.

The design tension force on a screw is the least of:1) ϕsc Pnot (see Section 5.4.2.1)2) ϕsc Pnov (see Section 5.4.2.2)3) ϕsc Pnt /1.25

5.4.2.1 Pull-Out

The nominal pull-out strength, Pnot, for pulling a screw out of a threaded part, is:

1) For UNC threads (screw thread types C, D, F, G, and T)

a. for 0.060 in. < tc < 0.125 in. (1.5 mm < tc < 3 mm)

I-B-62 January 2005


where Ks = 1.01 for 0.060 in. ≤ tc < 0.080 in.

(1.5 mm ≤ tc < 2 mm)

Ks = 1.20 for 0.080 in. ≤ tc ≤ 0.125 in.

(2 mm ≤ tc ≤ 3 mm)

b. for 0.125 in. < tc < 0.25 in. (3 mm < tc < 6.3 mm)

Pnot = 1.2DFty2(0.25 – tc) + 1.16AsnFtu2(tc – 0.125)

(Eq. 5.4.2.1-2)

c. for 0.25 in. ≤ tc ≤ 0.375 in. (6.3 mm ≤ tc ≤ 10 mm)

Pnot = 0.58 Asn tc Ftu2 (Eq. 5.4.2.1-3)

2) For spaced threads (screw thread types AB, B, BP, BF, and BT)

a. for 0.038 in. ≤ tc ≤ 2/n (1 mm < tc < 2/n)


where Ks = 1.01 for 0.038 in. ≤ tc < 0.080 in.

(1 mm ≤ tc < 2 mm)

Ks = 1.20 for 0.080 in. ≤ tc < 2/n (2 mm ≤ tc < 2/n)

b. for 2/n < tc < 4/n

Pnot = 1.2D Fty2 (4/n – tc) + 3.26D Ftu2 (tc – 2/n)

(Eq. 5.4.2.1-5)

c. for 4/n ≤ tc ≤ 0.375 in. (4/n ≤ tc ≤ 8 mm)

Pnot = 1.63D tc Ftu2 (Eq. 5.4.2.1-6)

5.4.2.2 Pull-Over

The nominal pull-over strength, Pnov, for pulling con-nected material over the head of a screw or washer, if present, is:

Pnov = C t1 Ftu1 (Dws – Dh) (Eq. 5.4.2.2-1)

where C is a coefficient that depends on screw location (1.0 for valley fastening and 0.7 for crown fastening), and Dws is the larger of the screw head diameter or the washer diameter, but no greater than 5/8 in. (16 mm). (See Section 5.4.2 for the washer thickness requirement.) The nomi-nal pull-over strength need not be less than the pull-over

strength computed from equation 5.4.2.2-2 for countersunk screws.

For countersunk screws with an 82o nominal angle head, the nominal pull-over strength is:

Pnov = (0.27 + 1.45t1 /D) D t1Fty1 (Eq. 5.4.2.2-2)

for 0.06 in. ≤ t1 < 0.19 in. (1.5 mm ≤ t1 < 5 mm) and t1 /D ≤ 1.1. If t1 /D > 1.1, use t1 /D = 1.1


The shear force on a screw shall not exceed the least of:

1) 2ϕu Ftu1 D t1. If the screw is countersunk, one-half the depth of the countersink shall be deducted from t1.

2) ϕu Ftu2 D t2

3) 4.2 (t23D)1/2 ϕsc Ftu2 , for t2 < t1

4) ϕsc Pss /1.25

5.4.4 Minimum Spacing of Screws

The minimum distance between screw centers shall be 2.5 times the nominal screw diameter.


5.5.1 Endlaps

Minimum endlaps shall be those expressed in Table 5.5.1-1.

5.5.2 Sidelaps

For a sinusoidal corrugated sheet, the minimum sidelap for roofing shall have a width equal to the pitch of the cor-rugations, and the minimum sidelap for siding shall have a width equal to half the pitch.

For a trapezoidal sheet of a depth greater than 1 in. (25 mm) the minimum sidelap for both roofing and siding shall have a developed width equal to the width of the narrowest flat plus 2 in. (50 mm). A trapezoidal sheet with a depth of 1 in. (25 mm) or less shall have an overlap of proven design includ-ing an anti-siphoning feature.


The minimum size of fasteners used in end laps and side laps shall be #12 (5.5 mm) for screws and 3/16 in. (5 mm) diameter for rivets. The maximum spacing for sidelap fas-teners shall be 12 in. (300 mm). Endlap fasteners shall be located no more than 2 in. (50 mm) from the end of the overlapping sheet.

5.5.4 Flashing

Flashing shall be formed from aluminum sheet.

January 2005 I-B-63

Table 5.2.3-1DESIGN STRESSES FOR BOLTS

Alloy and Temper


Fsu

(ksi)


(ksi)

Minimum Tensile Ultimate Strength1

Ftu

(ksi)

Design Tensile Stress on Root Area 2

(ksi)

2024-T4 37 24 62 40

6061-T6 25 16 42 27

7075-T73 41 27 68 44

1. From ASTM B316/B316M and F468

2. ϕ = 0.65

Table 5.2.3-1MDESIGN STRESSES FOR BOLTS

Alloy and Temper


Fsu

(MPa)

Design Shear Stress on Effective Area 2

(MPa)

Minimum Tensile Ultimate Strength1

Ftu

(MPa)

Design Tensile Stress on Root Area 2

(MPa)

2024-T4 255 165 425 275

6061-T6 170 110 290 190

7075-T73 280 180 470 305

1. From ASTM B316/B316M

2. ϕ = 0.65

Table 5.3.4-1DESIGN STRESSES FOR RIVETS



Fsu

(ksi)


(ksi)

2017-T4 33 21

2024-T42 37 24

2117-T4 26 17

2219-T6 30 20

6053-T61 20 13

6061-T6 25 16

7050-T7 39 25

7075-T6 42 27

7075-T73 41 27

7178-T6 46 30

1. From ASTM B316/B316M for heat treated alloys.

2. ϕ = 0.65

I-B-64 January 2005

Table 5.3.4-1MDESIGN STRESSES FOR RIVETS



Fsu

(MPa)


(MPa)

2017-T4 225 145

2024-T42 255 165

2117-T4 180 115

2219-T6 205 135

6053-T61 135 90

6061-T6 170 110

7050-T7 270 175

7075-T6 290 190

7075-T73 280 180

7178-T6 315 205

1. From ASTM B316/B316M for heat treated alloys.

2. ϕ = 0.65

Table 5.5.1-1MINIMUM END LAPS

Depth of section

Minimum End Laps

Roofing, slope greater than 2 on 12,

less than 3 on 12

Roofing, slope 3 on 12 or more

Siding

1 in. or less(25 mm or less)

– 6 in.(150 mm)

4 in.(100 mm)

Greater than 1 in., less than 2 in.

(Greater than 25 mm, less than 50 mm)

9 in.(230 mm)

6 in.(150 mm)

4 in.(100 mm)

2 in. or more(50 mm or more)

9 in.(230 mm)

6 in.(150 mm)

6 in.(150 mm)

January 2005 I-B-65


6.1 Layout


Punched or scribed layout marks shall not remain on fabricated material designed for fatigue.

6.1.2 Temperature Correction

A temperature correction shall be applied where neces-sary in the layout of dimensions. The coefficient of expan-sion used shall be 13 × 10-6 per oF (23 × 10-6 per oC).

6.2 Cutting

6.2.1 Methods

Cutting shall be by shearing, sawing, nibbling, routing, arc cutting, laser or abrasive water jet. Edges which have been arc or laser cut shall be planed to remove edge cracks.

6.2.2 Edge Quality

Cut edges shall be true, smooth, and free from excessive burrs or ragged breaks.

6.2.3 Re-entrant Corners

Re-entrant corners shall be filleted.

6.2.4 Oxygen Cutting

Oxygen cutting is prohibited.

6.3 Heating

Aluminum heated above 150oF (66oC) during fabrication other than welding is subject to the following requirements:

a. Temperature controls and supervision shall be pro-vided to ensure that time-temperature limits are met, and time and temperature exposure shall be docu-mented.

b. When heating reduces metal strengths, design stresses shall be reduced consistent with the mechanical prop-erties of the aluminum after the heating process. Reduced design stresses need not be used for the alloys and tempers in Table 6.3-1 if the cumulative time at the elevated temperature does not exceed the limits given.

Table 6.3-1TEMPERATURE EXPOSURE LIMITS

FOR ARTIFICIALLY AGED TEMPERS OF 6005, 6061, AND 6063

Temperature1 Time

oF oC

450 230 5 min

425 220 15 min

400 205 30 min

375 190 2 hr

350 175 10 hr

325 165 100 hr

300 150 1,000 hr

212 100 100,000 hr

1) Interpolate time (t) for other temperatures (T) using

logt = logt2 + log ( T2 / T )

__________ log ( T2 / T1 )

( log t1/t2 )

where

T1 = next lower temperature in Table 6.3-1 than T T2 = next higher temperature in Table 6.3-1 than T t1 = time corresponding to T1

t2 = time corresponding to T2

c. 5083, 5086, 5154, and 5456 shall not be held at tem-peratures from 150oF (66oC) to 450oF (230oC). To hot form such alloys, they shall be

1) rapidly heated to a temperature not to exceed 550oF (290oC),

2) formed before the metal cools below 450oF (230oC), and

3) rapidly cooled from 450oF (230oC) to 150oF (66oC).

6.4 Holes

6.4.1 Fabrication Methods

Holes shall be punched or drilled. Punching shall not be used for castings or if the metal thickness is greater than the diameter of the hole. The amount by which the diam-eter of a sub-punched hole is less than that of the finished hole shall be at least ¼ the thickness of the piece but not less than 1/32 in. (0.8 mm).

I-B-66 January 2005

6.4.2 Hole Alignment

If holes must be enlarged to admit fasteners, they shall be reamed. Poor matching holes shall be rejected. Holes shall not be drifted in a manner that distorts the metal. All chips and foreign matter between contacting surfaces shall be removed before assembly.

6.5 Riveting

6.5.1 Driven Head

The driven head of aluminum rivets shall be flat or cone-point, with dimensions as follows:

6.5.1.1 Flat Heads

Flat heads shall have a diameter at least 1.4 times the nominal diameter of the rivet and a height at least 0.4 times the nominal diameter of the rivet.

6.5.1.2 Cone-Point Heads

Cone-point heads shall have a diameter at least 1.4 times the nominal diameter of the rivet and a height to the apex of the cone at least 0.65 times the nominal diameter of the rivet. The nominal included angle at the apex of the cone shall be 127o.

6.5.2 Hole Filling

Rivets shall fill holes completely. Rivet heads shall be concentric with the rivet holes and shall be in continuous contact with the surface of the part joined.

6.5.3 Defective Rivets

Defective rivets shall be removed by drilling. The drill bit diameter shall not exceed the diameter of the replace-ment rivet.

6.6 Finishes

6.6.1 Where Painting Is Required

Aluminum shall be painted where:a. 2014 is in the presence of moisture,b. aluminum would otherwise be in contact with or fastened

to dissimilar materials as described in Section 6.7,c. aluminum is exposed to corrosive conditions.

6.6.2 Surface Preparation

Surfaces to be painted shall be prepared immediately before painting by:

a. a chemical cleaner (such as a solution of phosphoric acid and organic solvents),

b. abrasion blasting, c. unsealed anodizing, d. chemical conversion coating, or e. using the procedure specified by the coating supplier.


Where aluminum is in contact with or fastened to the materials specified in Sections 6.7.1 through 6.7.3, direct contact between the aluminum and the other material shall be prevented as specified in those sections or by placing a compatible, nonporous isolator between the aluminum and the other material.

6.7.1 Steel

Steel surfaces to be placed in contact with uncoated aluminum shall be painted with a coating suitable for the service. Where very corrosive conditions are expected, additional protection can be obtained by applying a sealant that excludes moisture from the joint during service. Alu-minized, hot-dip galvanized or electro-galvanized steel in contact with aluminum need not be painted. Stainless steel (300 series) in contact with aluminum need not be painted except in high chloride environments.

6.7.2 Wood, Fiberboard, or Other Porous Materials

Aluminum surfaces to be placed in contact with wood, fiberboard, or other porous material that absorbs water shall be factory painted or given a heavy coat of alkali resistant bituminous paint or other coating providing the equivalent protection before installation.


Aluminum shall not be embedded in concrete with cor-rosive additives such as chlorides if the aluminum will be electrically connected to steel.

Unless the concrete or masonry will remain dry after curing and no corrosive additives such as chlorides are used, aluminum surfaces to be placed next to or embedded in concrete or masonry shall be:

a. given one coat of suitable paint, such as zinc molyb-date primer conforming to Federal Specification TT-P-645B or equivalent, or

b. given a heavy coating of alkali resistant bituminous paint, or

c. isolated with a suitable plastic tape or other isolation material.

6.7.4 Runoff From Heavy Metals

Aluminum shall not be exposed to water that has come in contact with a heavy metal such as copper. The heavy metal shall be painted or coated or the drainage from the metal diverted away from the aluminum or painted alumi-num shall be used.

January 2005 I-B-67

6.8 Mechanical Finishes

Abrasion blasting shall not be used if it distorts, perfo-rates, or significantly reduces the thickness of the material blasted.


A fabricated member shall not vary from straight or from its intended curvature by more than its length divided by 960.

6.10 Bending

Bend radii shall be large enough to avoid cracking.

6.11 Erection

6.11.1 Erection Tolerances

Tolerances on erected dimensions shall be suitable for the intended service.


Unless the joint is a slip-critical connection, bolts shall be installed snug tight, defined as the tightness that exists when all plies in a joint are in firm but not necessarily con-tinuous contact. Slip-critical connections shall be tightened in accordance with Section 5.2.8.7.

I-B-68 January 2005


7.1 General

Welding shall comply with the American Welding Soci-ety’s D1.2 Structural Welding Code – Aluminum. Filler alloys shall meet AWS A5.10 and be selected from Table 7.1-1.

7.2 Welded Members

7.2.1 General

The weld-affected zone shall be taken to extend 1 in. (25 mm) to each side of the centerline of a weld. Mechani-cal properties for weld-affected metal shall be taken from Table 3.3-2. The modulus of elasticity for weld-affected metal is the same as for non-welded metal.

Design stresses calculated in accordance with Section 7.2.1 apply to:

1) Members in axial tension with transverse welds affecting their entire cross section,

2) Bearing stresses at weld-affected metal,3) Columns or beams supported at both ends with

transverse welds affecting their entire cross-section and no farther than 0.05L from the ends,

4) Columns or beams of tubes or curved elements with transverse welds affecting their entire cross section, and

5) Flat elements of columns or beams with welds at the supported edges only.

Design stresses for these welded members shall be cal-culated from the same formulas as for non-welded mem-bers with the following adjustments.

1) Design stresses for axial or flexural tension (Sec-tions 3.4.1 through 3.4.4), bearing (Sections 3.4.5 and 3.4.6), and axial or flexural compression or shear (Sections 3.4.7 through 3.4.21) with slenderness less than S1 shall be calculated using welded mechanical properties from Table 3.3-2.

2) Design stresses for tubes and curved elements in axial or flexural compression or shear (Section 3.4.10, 3.4.12, and 3.4.16.1) with slenderness greater than S1 shall be calculated using welded mechanical prop-erties from Table 3.3-2 and buckling constants from Table 3.3-3 regardless of temper before welding.

3) Design stresses for all other members and elements in axial or flexural compression or shear (Sections 3.4.7 through 3.4.21) with slenderness greater than S1 shall be calculated using non-welded mechanical properties from Table 3.3-1 and buckling constants from Table 3.3-3 or 3.3-4 as appropriate for the tem-per before welding.


For members with part of the cross section weld-affected, the design stress is

ϕFpw = ϕFn – Aw ___ A

( ϕFn – ϕFw ) (Eq. 7.2.2-1)

whereϕFpw = design stress on the cross section, part of which

is weld-affected.ϕFn = design stress if no part of the cross section

were weld-affected. Use buckling constants for unwelded metal from Table 3.3-3 or 3.3-4 and mechanical properties from Table 3.3-1.

ϕFw = design stress if the entire cross sectional area were weld-affected. Use buckling constants for annealed material (Table 3.3-3) regardless of the temper before welding, and mechanical properties from Table 3.3-2.

A = net cross sectional area of a tension member or tension flange of a beam; gross cross sectional area of a column or compression flange of a beam. A beam flange shall consist of the portion of the section farther than 2c/3 from the neutral axis, where c is the distance from the neutral axis to the extreme fiber.

Aw = weld-affected cross sectional area. If Aw < 0.15A, Aw shall be taken as zero.

7.2.3 Columns or Beams with Transverse Welds Away from Supports and Cantilevers with Transverse Welds

For columns or beams supported at both ends with transverse welds farther than 0.05L from the member ends and cantilever beams with transverse welds, design stresses shall be calculated in accordance with Section 7.2.2 as if the entire cross sectional area were weld-affected.


7.3.1 Groove Welds


The following types of groove welds are complete pen-etration welds:

1) Welds welded from both sides with the root of the first weld backgouged to sound metal before welding the second side.

2) Welds welded from one side using permanent or temporary backing.

January 2005 I-B-69

Tab

le 7

.1-1

WE

LD

FIL

LE

RS

FO

R W

RO

UG

HT

AL

LOY

S

Bas

e M

etal

Bas

e M

etal

1060

110

030

03A

lcla

d 3

003

2219

3004

A

lcla

d 3

004

5005

5050

5052

5083

5456

5086

5154

5454

6005

6061

6063

6105

6351

6463

7005

7005

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)55

56(5

183)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5556

(5

183,

535

6)

6005

, 606

1,

6063

, 610

5,

6351

, 646

3

4043

(404

7)41

4553

56(4

043,

404

7,

5183

, 555

6)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(404

3, 4

047,

51

83, 5

556)

5454

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6) 5

654

(518

3, 5

356,

5556

)

5554

(518

3, 5

356,

55

56)

5154

5356

(518

3, 5

556)

DN

W53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)56

54

(518

3, 5

356,

5556

)

5086

5356

(518

3, 5

556)

DN

W53

56(5

183,

5556

)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)53

56(5

183,

555

6)

5083

, 545

653

56(5

183,

555

6)D

NW

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5556

(518

3)

5052

5356

(5

183,

555

6)D

NW

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5356

(518

3, 5

556)

5005

, 505

040

43(1

100,

404

7)D

NW

5356

(404

3, 4

047,

51

83, 5

556)

5356

(404

3, 4

047,

51

83, 5

556)

3004

, A

lcla

d 3

004

4043

(40

47,

5183

,535

6,55

56)

DN

W53

56(5

183,

555

6)

2219

4145

2319

(414

5)

1060

, 110

0,

3003

, A

lcla

d 3

003

4043

(110

0, 4

047)

Not

es:

1) T

his

tabl

e is

for

stru

ctur

al a

pplic

atio

ns s

ubje

cted

to n

orm

al a

tmos

pher

ic c

ondi

tions

usi

ng G

TAW

or

GM

AW

.2)

DN

W =

Do

Not

Wel

d

I-B-70 January 2005

3) Welds welded from one side using AC-GTAW root pass without backing

4) Welds welded from one side using PAW-VP in the keyhole mode.

All other groove welds are partial penetration welds.


1) Size: The weld size of a complete joint penetra-tion groove weld is the thickness of the thinner part joined. The weld size of a partial joint penetration groove weld is the depth of preparation Sw (see Fig-ure 7.3-1) for all V and bevel groove welds with an included angle greater than 45o, and the depth of preparation for all J and U groove welds.

2) Length: The effective weld length for tension and compression is the length of the weld perpendicular to the direction of tensile or compressive stress. The effective weld length for shear is the length of the weld parallel to the direction of shear stress.

3) Area: The effective area of a groove weld is the effective weld length times the weld size.


The design tensile or compressive strength of a groove weld (Pgw) is

Pgw = ϕuFtuw Awe (Eq. 7.3.1.3-1)

where

Ftuw = least of the welded tensile ultimate strengths of the base metals and the filler. Welded tensile ultimate strengths of base metals shall be taken from Table 3.3-2 and tensile ultimate strengths of fillers from Table 7.3-1.

Awe = weld effective area ϕu = 0.85

The design shear strength of a groove weld (Vgw) is

Vgw = ϕFsuw Awe (Eq. 7.3.1.3-2)

where

Fsuw = least of the welded shear ultimate strengths of the base metals and the filler. Welded shear ulti-mate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1.

Awe = weld effective areaϕu = 0.85

7.3.2 Fillet Welds


The effective throat is the shortest distance from the joint root to the face of the diagrammatic weld.

The weld effective length Lwe is the overall length of the weld, including boxing. If the effective length of a fillet weld is less than 4 times its nominal size Sw (see Figure 7.3-2), the effective weld size shall be considered to be 25% of its effec-tive length. The minimum length of segments of an inter-mittent fillet weld shall be 1½ in. (40 mm). The maximum effective length of a longitudinal fillet weld is 100 times its nominal size.


Stress on a fillet weld shall be considered to be shear for any direction of applied load. The design shear strength of a fillet weld (Vw) is

Vw = ϕuFsw Lwe (Eq. 7.3.2.2-1)

where

Fsw = least of:

1) the product of the filler’s shear ultimate strength and the effective throat.

Figure 7.3-1PARTIAL JOINT PENETRATION GROOVE WELD

DEPTH OF PREPARATION Sw

January 2005 I-B-71

2) for base metal in shear at the weld-base metal joint, the product of the base metal’s welded shear ultimate strength and the fillet size Sw at the joint;

3) for base metal in tension at the weld-base metal joint, the product of the base metal’s welded tensile ultimate strength and the fillet size Sw at the joint.

Welded shear and tensile ultimate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1.

Lwe = weld effective lengthϕu = 0.80



The effective area of plug or slot welds is the nominal area of the hole or slot in the plane of the faying surface. Slot lengths shall not exceed 10 times the slotted material’s thickness.


The design shear strength of a plug or slot weld (Vw) is

Vw = ϕuFsw Awe (Eq. 7.3.3.2-1)

where

Fsw = lesser of the welded shear ultimate strengths of the filler and the base metal under the weld. Welded shear ultimate strengths of base metals shall be taken from Table 3.3-2 and shear ultimate strengths of fillers from Table 7.3-1

Awe = weld effective areaϕu = 0.85

7.3.4 Stud Welds

The design tensile strength of a stud weld (Tw) is

Tw = ϕuTuw (Eq. 7.3.4-1)

whereTuw = minimum tensile strength of the stud in Table 7.3-2ϕu = 0.85

Figure 7.3-2EFFECTIVE THROAT OF A FILLET WELD

Figure 7.3-3SLOT WELD PLAN VIEW

Table 7.3-1FILLER STRENGTHS


(ksi)


(ksi)

1100 11 7.5

2319 35 16

4043 24 11.5

4047 – 13

4643 – 13.5

5183 40 21

5356 35 17

5554 31 17

5556 42 20

5654 30 12

Table 7.3-1MFILLER STRENGTHS


(MPa)


(MPa)

1100 75 50

2319 240 110

4043 165 80

4047 – 90

4643 – 95

5183 275 145

5356 240 115

5554 215 115

5556 290 140

5654 205 85

I-B-72 January 2005

Table 7.3-2MINIMUM TENSILE STRENGTHS FOR

5183, 5356, AND 5556 STUDS

Stud SizeArc(lb)

Capacitor Discharge(lb)

6-32 – 375

8-32 – 635

10-24 770 770

1/4-20 1360 1360

5/16-18 2300 2300

3/8-16 3250 –

7/16-14 4400 –

1/2-13 5950 –


For alloy 6005 lighting pole assemblies, up through 0.250 in. (6 mm) thick which are welded in the –T1 temper with filler alloy 4043 and precipitation heat treated (arti-ficially aged) to the –T5 temper by an approved method after welding, the design stresses within 1.0 in. (25 mm) of the weld shall be 85% of the values for non-welded alloy 6005-T5.

For alloy 6063 lighting pole assemblies, up through 0.375 in. (10 mm) thick which are welded in the –T4 tem-per with filler alloy 4043 and precipitation heat treated (artificially aged) to the –T6 temper by an approved method after welding, the design stresses within 1.0 in. (25 mm) of the weld shall be 85% of the values for non-welded alloy 6063-T6.

Table 7.3-2MMINIMUM TENSILE STRENGTHS FOR

5183, 5356, AND 5556 STUDS

Stud SizeArc(N)

Capacitor Discharge(N)

6-32 – 1670

8-32 – 2820

10-24 3420 3420

1/4-20 6050 6050

5/16-18 10,200 10,200

3/8-16 14,500 –

7/16-14 19,600 –

1/2-13 26,500 –

January 2005 I-B-73

Section 8. Castings

8.1 Materials

Section 8 of this Specification applies to castings listed in Table 8.2-1 and produced to the following ASTM Speci-fications:

B 26 Aluminum-Alloy Sand Castings B 108 Aluminum-Alloy Permanent Mold Castings

Dimensional tolerances shall conform to Standards for Aluminum Sand and Permanent Mold Castings.

The purchaser shall require the casting producer to report tensile yield strengths. For sand castings, the pur-chaser shall require that tensile ultimate and tensile yield strengths of specimens cut from castings shall be at least 75% of the values specified in B 26.

Radiographic inspection to ASTM B 26 Grade C or B 108 Grade C criteria is required. The number of castings

radiographed and the lot acceptance criteria shall be as follows:

Lot Size

Number of Castings

Required to be Radiographed

Number of Castings

Required to Meet Grade C to Pass

Lot

2 through 50 2 2

51 through 500 8 7

over 500 13 11


Minimum strengths shall be taken from Table 8.2-1 or Table 8.2-1M.

Table 8.2-1MINIMUM STRENGTHS OF CASTINGS

Alloy-Temper Casting Type

Minimum TensileUltimate Strength

Ftu (ksi)


Fty (ksi) Note

356.0-T6 sand 22.5 15

A356.0-T6 sand 25.5 18

36 27.7 (1)


43 33 (3)

30 22.5 (1)

C355.0-T61 permanent mold 40 30 (2)

37 30 (3)


28.5 19.5 (1)

A356.0-T61 permanent mold 33 26 (2)

28 26 (3)

33.7 27 (1)


41 31 (3)

33.7 25.5 (1)


40 30 (3)

35.2 28.5 (1)


40 30 (3)

535.0-F permanent mold 26.2 13.5 (1)

1) These strengths apply at any location in the casting if the purchaser does not specify test specimens be cut from castings.2) These strengths apply in the locations specified by the purchaser if the purchaser specifies such locations. At other locations, the strengths



I-B-74 January 2005

Table 8.2-1MMINIMUM STRENGTHS OF CASTINGS

Alloy-Temper Casting Type

Minimum TensileUltimate Strength

Ftu (MPa)


Fty (MPa) Note

356.0-T6 sand 154 105

A356.0-T6 sand 176 124

248 191 (1)

354.0-T61 permanent mold 324 248 (2)

297 228 (3)

207 155 (1)

C355.0-T61 permanent mold 276 207 (2)

255 207 (3)


196 134 (1)


193 179 (3)

232 186 (1)


283 214 (3)

232 175 (1)

359.0-T61 permanent mold 310 234 (2)

276 207 (3)

243 196 (1)

359.0-T62 permanent mold 324 262 (2)

276 207 (3)

535.0-F permanent mold 180 93 (1)

Notes1) These strengths apply at any location in the casting if the purchaser does not specify test specimens be cut from castings.2) These strengths apply in the locations specified by the purchaser if the purchaser specifies such locations. At other locations, the strengths



The compressive yield strength Fcy of castings shall be taken as the tensile yield strength Fty.

The modulus of elasticity E of castings shall be taken as 10,000 ksi (70,000 MPa).

The tension coefficient kt for the alloy-tempers in Table 8.2-1 and Table 8.2-1M is 1.0.

8.3 Design

Design shall be in accordance with all the provisions of this Specification.

8.4 Welding

Fillers shall be selected from Table 8.4-1. Minimum welded strengths shall be those established in the AWS D1.2 weld procedure qualification test.

January 2005 I-B-75

Table 8.4-1WELD FILLERS FOR CAST ALLOYS

BASE METAL TOBASE METAL 535.0

356.0A356.0A357.0359.0

354.0C355.0

1060, 1100, 3003, Alclad 3003

5356 4043(4047)

4145

2219 4043 4145 4145

3004, Alclad 3004

5356 4043(4047)

4145(4043, 4047)

5005, 5050 5356 4043(4047)

4145(4043, 4047)

5052 5356 4043(4047)

4145(4043, 4047)

5083, 5456 5356 DNW DNW

5086 5356 DNW DNW

5154 5356 DNW DNW

5454 5356 4043(4047)

DNW

6005, 6061, 6063, 6105, 6351, 6463

5356 4043(4047, 4145, 4643)

4145(4043, 4047)

7005 5356 4043(4047)

DNW

354.0C355.0

DNW 4145 4145(note 1)

356.0, A356.0, A357.0, 359.0

4043(5356)

4043(note 1)

535.0 5356

Notes1) To weld C355.0 to itself, 4009 may be used; to weld A356.0 to itself, 4010 may be used; and to weld A357.0 to itself, 4011 may be used.2) DNW = Do not weld

I-B-76 January 2005

Section 9. Testing

9.1 General

Testing shall be considered to be an acceptable method for substantiating the design of aluminum alloy load carry-ing members, assemblies or connections whose strengths cannot otherwise be determined in accordance with Sec-tions 1 through 8. Tests shall be conducted by an indepen-dent testing laboratory or by a manufacturer’s testing labo-ratory when certified by a qualified independent witness.

General provisions for testing are given in Sections 9.2 and 9.3. Specific provisions for building sheathing are given in Section 9.4.

9.2 Test Loading and Behavior

In order to test a structure or load carrying member adequately, the loading shall be applied in a fashion that is representative of the loading during service. Further, the structure or member shall be supported in a manner that is equivalent to the supports available when the structure is in service.

In tests that require measurement of deflection of a panel or beam, a preload, that is a minimum of 20% of the design load, shall be applied to set the specimen before testing, and deflections shall be measured at the supports as well as at the point of maximum critical deflection, so that the difference will indicate the specimen deflection. The preload shall only be taken as a zero load for deflec-tion measurements when proper account of this is taken in reporting deflections.

As an alternative, the structural performance of exterior aluminum fenestration products such as windows, curtain walls, and doors shall be determined in accordance with ASTM E 330.



In determining yield strength and ultimate strength of material or fasteners, sufficient tests shall be conducted to statistically establish the strength at which 99% of the material is expected to exceed with a confidence of 95%. This strength shall be calculated as follows:

Xa = Xm – KSx (Eq. 9.3.1-1)

whereXa = strength at which 99% of the material is expected

to exceed with a confidence of 95%Xm = mean of the test resultsSx = standard deviation of the test resultsK = statistical coefficient based on the number of tests

(n). K is a one-sided factor for 99% of the popula-tion exceeding Xa with a confidence of 95%. Values of K for the following values of n are:

n K n K

3 10.55 18 3.370

4 7.042 19 3.331

5 5.741 20 3.295

6 5.062 21 3.262

7 4.641 22 3.233

8 4.353 23 3.206

9 4.143 24 3.181

10 3.981 25 3.158

11 3.852 30 3.064

12 3.747 35 2.994

13 3.659 40 2.941

14 3.585 45 2.897

15 3.520 50 2.863

16 3.463 100 2.684

17 3.415

9.3.2 Tests for Determining Structural Performance

Where practicable, in member and structural systems tests the evaluation of test results shall be made on the basis of not fewer than four identical specimens. If the deviation from the average value exceeds ±10%, at least three more tests of the same kind shall be made.

The design value shall be taken as the average of all test results multiplied by the resistance factor, ϕ, determined as follows:

ϕ= 1.5MmFm e–βo √______________

V M 2

+ V F 2

+ CP V P

2

+ V Q 2

(Eq. 9.3.2-1)

where

Cp = correction factor = n2 – 1 ______

n2 – 3n

Dn = nominal dead loade = base for natural logarithms ≈ 2.72Fm = mean value of the fabrication factorLn = nominal live loadMm = mean value of the material factorn = number of testsXi = failure load of ith testXm = average value of failure loads in all tests

= ∑

i = 1

n

X i ________ n

January 2005 I-B-77

VF = coefficient of variation of the fabrication factorVM = coefficient of variation of the material factorVp = coefficient of variation of the ratio of the observed

failure loads divided by the average value of all the observed failure loads

= √___________________

∑

i = 1

n

( Xi ___ Xm

) 2 – ( ∑

i = 1

n

Xi ___ Xm

) 2 _________ n __________________

n – 1

VQ = coefficient of variation of the loads

= √

___________________ ( 0.105Dn ) 2 + ( 0.25Ln ) 2 ____________________

1.05Dn + Ln ; in lieu of calculation

by the above formula, VQ = 0.21α = Dn / Ln ; in lieu of calculation by the above for-

mula, α = 0.2βo = the target reliability index, 2.5 for columns, beams

and beam columns, 3.0 for tension members and 3.5 for connections.

The following values shall be used when documented statistical data established from sufficient number of results on material properties does not exist for the member or connection:

Mm = 1.10 for behavior governed by the yield stress = 1.00 for behavior governed by the ultimate stressFm = 1.00VM = 0.06VF = 0.05 for structural members and bolted connections = 0.15 for welded connections

In evaluating test results, adjustment shall be made for any differences between the yield strength of the material from which the tested sections are formed and the mini-mum yield strength specified for the material which the manufacturer intends to use. If the tensile yield strength of the aluminum from which the tested sections are formed is greater than the specified value, the test results shall be adjusted down to the specified minimum yield strength of the aluminum which the manufacturer intends to use. The test results shall not be adjusted upward if the yield strength of the test specimen is less than the minimum specified yield strength. Similar adjustments shall be made on the basis of tensile ultimate strength instead of yield strength when tensile ultimate strength is the critical factor.

Adjustments shall also be made for differences between nominal section properties and those of tested sections.


Where the configuration of roofing and siding installa-tions are such that calculation of their strength cannot be made in accordance with the provisions of this Specifica-tion, their bending strength shall be established from tests.

Tests are also required in the following cases:

a. When web angles θ are asymmetrical about the center-line of a valley, rib, flute, crimp, or other corrugation.

b. When web angles θ are less than 45o.c. When aluminum panels are alternated with panels

composed of any material having significantly dif-ferent strengths or deflection characteristics.

d. When flats spanning from rib to rib or other corruga-tion in the transverse direction have a width to thick-ness ratio greater than either of the following:

1) 1230 _____ 3 √

__ q where q is the design load in psf ( 447 ____

3 √__

q

where q is the design load in kN/m2)

2) 435 √___

Fty ___ q where Fty is in ksi and q is in psf (37 √

___

Fty ___ q

where Fty is in MPa and q is in kN/m2).e. When panel ribs, valleys, crimps, or other corruga-

tions are of unequal depths.f. When specifications prescribe less than one fastener

per rib to resist negative or uplift loading at each pur-lin, girt, or other transverse supporting member.

g. When panels are attached to supporting members by profile interlocking straps or clips.

9.4.1 Test Method

Tests shall be conducted in accordance with ASTM E 1592.

9.4.2 Different Thicknesses

Only the thinnest and thickest specimens manufactured are required to be tested when panels are of like configura-tion, differing only in material thickness. Where the failure of the test specimens is from bending stress, the bending strength for intermediate thicknesses shall be interpolated as follows:

log Mi = log M1 + ( log ti – log tmin ______________ log tmax – log tmin

) ( log M2 – log M1 )

(Eq. 9.4.2-1)

whereMi = bending strength of member of intermediate

thickness ti

M1 = bending strength of member of thinnest materialM2 = bending strength of member of thickest materialti = thickness of intermediate thickness materialtmin = thickness of thinnest material testedtmax = thickness of thickest material tested

9.4.3 Design Loads from Tests

Design loads shall be determined using the resistance fac-tors given in Section 9.3.2 for bending and Section 5 applied to the minimum test strength achieved for fasteners.

9.4.4 Deflections

Live load deflections shall not exceed 1/60 of the span length.


PART II-A

Commentary on Specification for

Aluminum Structures– Allowable Stress Design


Eighth Edition, January 2005

January 2005 II-A-3

IIACommentary on Specification for Aluminum Structures—Allowable Stress Design

TABLE OF CONTENTS

Section 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .71.1 Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71.2 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71.3 Safety Factors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

Section 2. Design Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .72.1 Section Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2 Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.3 Loads . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

Section 3. General Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .73.4 Allowable Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

3.4.1 Tension, Axial . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.4.2 Tension in Extreme Fibers of Beams—Flat Elements In Uniform Tension . . . . . . . . . . . . . . . . . . . . . . . 83.4.3 Tension in Extreme Fibers of Beams—Round or Oval Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83.4.4 Tension in Extreme Fibers of Beams—Flat Elements In Bending in Their Own Plane . . . . . . . . . . . . . . 83.4.5 Bearing on Rivets and Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83.4.6 Bearing on Flat Surfaces and Pins and on Bolts in Slotted Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83.4.7 Compression in Columns, Axial, Gross Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

3.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or Torsional- Flexural Buckling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

3.4.7.3 Nonsymmetric Sections Subject to Torsional or Torsional-Flexural Buckling . . . . . . . . . . . . . 93.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of

Symmetry—Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is

not an Axis of Symmetry—Flat Elements Supported On One Edge . . . . . . . . . . . . . . . . . . . . 93.4.9 Uniform Compression in Elements of Columns—Flat Elements Supported on

Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93.4.9.1 Uniform Compression in Elements of Columns—Flat Elements Supported

on One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93.4.9.2 Uniform Compression in Elements of Columns—Flat Elements Supported

on Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103.4.10 Uniform Compression in Elements of Columns—Curved Elements Supported on

Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103.4.11 Compression in Beams, Extreme Fiber, Gross Section—Single Web Shapes . . . . . . . . . . . . . . . . . . . . 103.4.12 Compression in Beams, Extreme Fiber, Gross Section—Round or Oval Tubes . . . . . . . . . . . . . . . . . . . 103.4.13 Compression in Beams, Extreme Fiber, Gross Section—Solid Rectangular and Round Sections . . . . . 113.4.14 Compression in Beams, Extreme Fiber, Gross Section—Tubular Shapes . . . . . . . . . . . . . . . . . . . . . . . . 113.4.15 Uniform Compression in Elements of Beams—Flat Elements Supported on

One Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.4.16 Uniform Compression in Elements of Beams—Flat Elements Supported on

Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.4.16.1 Uniform Compression in Elements of Beams—Curved Elements

Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.4.16.2 Uniform Compression in Elements of Beams—Flat Elements Supported

on One Edge and With Stiffener on Other Edge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.4.16.3 Uniform Compression in Elements of Beams—Flat Elements Supported

on Both Edges and With an Intermediate Stiffener . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.4.17 Compression in Elements of Beams (Element in Bending in Own Plane)—

Flat Elements Supported on Tension Edge, Compression Edge Free . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

II-A-4 January 2005

3.4.18 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

3.4.19 Compression in Elements of Beams (Element in Bending in Own Plane)— Flat Elements Supported on Both Edges and With a Longitudinal Stiffener . . . . . . . . . . . . . . . . . . . . . . 13

3.4.20 Shear in Elements—Unstiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . 133.4.21 Shear in Elements—Stiffened Flat Elements Supported on Both Edges . . . . . . . . . . . . . . . . . . . . . . . . . 13

Section 4. Special Design Rules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .134.1 Combined Axial Load and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

4.1.1 Combined Compression and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134.1.2 Combined Tension and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

4.2 Torsion and Shear in Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134.4 Combined Shear, Compression, and Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134.5 Longitudinal Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134.6 Transverse Stiffeners for Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134.7 Effects of Local Buckling on Member Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

4.7.1 Local Buckling Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144.7.2 Weighted Average Axial Compressive Stress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144.7.3 Weighted Average Bending Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144.7.4 Effect of Local Buckling on Column Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144.7.5 Effect of Local Buckling on Beam Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154.7.6 Effective Width for Calculation of Bending Deflection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154.7.7 Web Crippling of Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154.7.8 Combined Web Crippling and Bending for Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4.8 Fatigue . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154.8.1 Constant Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154.8.2 Variable Amplitude Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4.9 Compression in Single Web Beams Including Single Web Beams With Tubular Portions . . . . . . . . . . . . . . . . . . 164.9.1 Doubly Symmetric Sections and Sections Symmetric About the Bending Axis . . . . . . . . . . . . . . . . . . . 164.9.2 Singly Symmetric Sections Unsymmetric about the Bending Axis . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 164.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis,

Doubly Symmetric Sections and Sections Without an Axis of Symmetry . . . . . . . . . . . . . . . . . . . . . . . . 164.9.4 Lateral Buckling Coefficients . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17


4.11.1 Bending About Geometric Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214.11.2 Bending About Principal Axes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21


Section 5. Mechanical Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .225.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

5.1.1 Minimum Edge Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 225.1.2 Maximum Spacing of Fasteners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 225.1.3 Block Shear Rupture . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 225.1.4 Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 225.1.5 Effective Net Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 235.1.8 Countersunk Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

5.2 Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 255.2.1 Bolt Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 255.2.3 Bolt Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 255.2.4 Bolt Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 255.2.5 Bolt Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 255.2.7 Lockbolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

January 2005 II-A-5

5.2.8 Slip-Critical Bolted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.2 Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.3 Holes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.4 Design for Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.5 Design for Slip Resistance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.2.8.6 Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275.2.8.7 Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

5.3 Riveted Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275.3.1 Rivet Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275.3.4 Rivet Shear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275.3.7 Blind Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

5.4 Tapping Screw Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 275.4.1 Screw Material . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.4.2 Screw Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

5.4.2.1 Pull-Out . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.4.2.2 Pull-Over . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

5.4.3 Screw Shear and Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.5 Building Sheathing Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

5.5.2 Sidelaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 295.5.3 Fasteners in Laps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

Section 6. Fabrication and Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .296.1 Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

6.1.1 Punch and Scribe Marks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 296.2 Cutting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

6.2.1 Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 296.2.3 Re-Entrant Corners . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

6.3 Heating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 296.6 Finishes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 296.7 Contact with Dissimilar Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

6.7.3 Concrete or Masonry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 306.7.4 Runoff from Heavy Metals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

6.9 Fabrication Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 306.10 Bending . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 306.11 Erection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

6.11.2 Bolt Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

Section 7. Welded Construction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .307.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 307.2 Welded Members . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

7.2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 307.2.2 Members with Part of the Cross Section Weld-Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.2.3 Columns or Beams with Transverse Welds Away from Supports and Cantilevers

with Transverse Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.3 Welded Connections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

7.3.1 Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.3.1.1 Complete Penetration and Partial Penetration Groove Welds . . . . . . . . . . . . . . . . . . . . . . . . . 31

7.3.2 Fillet Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.3.2.1 Effective Throat and Effective Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.3.2.2 Design Strength . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

7.3.3 Plug and Slot Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.3.4 Stud Welds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

7.4 Post-Weld Heat Treating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

II-A-6 January 2005

Section 8. Castings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .318.1 Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 318.2 Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 328.3 Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 328.4 Welding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

Section 9. Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .329.3 Number of Tests and the Evaluation of Test Results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

9.3.1 Tests for Determining Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 329.4 Testing Roofing and Siding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .32

January 2005 II-A-7

Section 1. General

1.1 Scope

This Specification applies to normal ambient tempera-ture uses of aluminum alloys. For higher temperatures, strengths and other properties (such as corrosion resis-tance) of different alloys are affected to varying degrees. Part V of the Aluminum Design Manual, Table 9, Typical Tensile Properties at Various Temperatures, provides typi-cal, but not minimum, properties and is not to be used for design. For information regarding properties at elevated temperatures, the supplier should be consulted.

1.2 Materials

The alloys addressed by the Specification are those used for general structural purposes and registered with the Aluminum Association. The Specification may be applied to alloys and tempers not listed in Table 3.3-1 if the engi-neer has the properties needed for proper design, including notch sensitivity. Additional information on alloys, temper designations, and products available is published in Alumi-num Standards and Data (1).

1.3 Safety Factors

The Specification is not limited as to type of structure. The general formulas in Table 3.4-3 can be applied to any structure, with appropriate values substituted for the factors of safety ny and nu. The values of factors of safety are given for in Table 3.4-1 for “Building Type Structures” and for “Bridge Structures”. “Building Type Structures” include highway signs, luminaires and traffic signals. The “bridge structures” cover bridges that are not designed according to References (2) or (3).



Section properties for many shapes are given in this Manual in Part VI. Formulas for calculating section prop-erties are also given in Part VI.

Nominal (rather than minimum) dimensions are used to calculate section properties. This is because safety or resistance factors account for the fact that an actual dimen-sion might be less than the nominal dimension, as long as tolerances do not exceed standard mill tolerances (given in Aluminum Standards and Data).

2.2 Procedure

Calculated stresses in the members resulting from exter-nal loading are compared with the appropriate allowable stresses. Alternatively, the provisions of Section 9, Test-ing, can be used. Procedures for using the Specification are

demonstrated in illustrative examples in Part VIII of this Manual.

2.3 Loads

The Specification for Aluminum Structures no longer includes a 1/3 allowable stress increase for wind or seis-mic loads. ASCE 7-98 and later ASCE 7 editions already include the factors that would fulfill the purpose of the pre-viously permitted stress increase.


The allowable stresses specified in subsections of this Section are listed in tables throughout the Specifi-cation. Part V Material Properties provides the basis for the mechanical properties for various alloys, tempers and product forms used in this Specification. The values of the allowable stresses are also given for various alloys in Part VII Design Aids.


The axial tensile strength is the lower of 1) the yield strength of the gross section, and 2) the ultimate (fracture) strength of the net section. This is because the net section usually exists over only a short portion of the overall length of the member, and the elongation of the member resulting from yielding across the net section is small. Thus, yielding on the net section is not a limit state.

In general, the allowable tensile stress for building struc-tures is the lower of two values that results from applying a factor of safety of 1.65 to the yield strength or 1.95 to the tensile strength. The corresponding factors of safety used to determine allowable tensile stresses for bridge structures are 1.85 and 2.2. These factors of safety are the same as those that were used in the ASCE papers published in 1962 (4, 5) and have been used in the Aluminum Association specifications since that time.

In the general formula for determining allowable ten-sile stress on the basis of the ultimate tensile strength, the factor of safety nu is multiplied by a factor kt. For regions farther than 1 in. (25 mm) from a weld, this factor is l.0 for most alloys that appear in the Specification. The exceptions are 2014-T6, 6066-T6, and 6070-T6. The value of kt for 2014-T6 is 1.25 and 1.1 for 6066-T6 and 6070-T6. This factor is introduced to take account of the fact that these high-strength alloys are somewhat more notch sensitive than the other alloys listed in the Specification. The result-ing allowable tensile stress for bridge structures of 2014-T6 is the same as that used in specifications for structures of this alloy published by the American Society of Civil Engineers (6).

II-A-8 January 2005

3.4.2 Tension in Extreme Fibers of Beams—Flat Elements In Uniform Tension

Sections 3.4.2 and 3.4.4 apply to tension elements of beams and can be used in two ways:

a. The least tensile strength of all the elements of the shape may be conservatively used for the entire shape. For example, for an I beam the strength would be the least of the strengths of the flange elements computed by Section 3.4.2 and the web element computed by Section 3.4.4.

b. The tensile strength of the elements may be deter-mined using Sections 3.4.2 and 3.4.4 and then Sec-tion 4.7.3 may be used to determine a weighted aver-age strength for the entire shape.

3.4.3 Tension in Extreme Fibers of Beams—Round or Oval Tubes

The allowable tensile stresses for round or oval tubes subjected to bending are somewhat higher than for struc-tural shapes. Analysis and tests (7) have demonstrated that yielding or failure of tubular beams does not occur until the bending moment considerably exceeds the yield moment predicted by the ordinary flexure formula. This results from the non-linear distribution of stress in the inelastic range. Yielding does not become apparent as soon as the calcu-lated stress in the extreme fiber reaches the yield strength because the less highly stressed fibers near the center of the beam are still in the elastic range. The constants 1.17 and 1.24 can be considered as shape factors for yielding and ultimate strength, respectively.

These constants were picked from curves of yield strengths at 0.2 percent offset for tubes of representative proportions. The shape factors on ultimate strength were deduced from apparent and actual stress-strain curves at a stress corresponding to tensile strength of the material.

3.4.4 Tension in Extreme Fibers of Beams—Flat Elements In Bending in Their Own Plane

As in the case of round tubes and solid rounds, theory and tests have shown that aluminum alloy members of these shapes can undergo bending moments that are con-siderably greater than those predicted on the basis of the ordinary flexure formula (8). In this case, the shape fac-tors used for yielding and ultimate strength, respectively, are 1.30 and 1.42. For elements unsymmetric about the bending axis, it is conservative to use the allowable stress obtained from 3.4.2.


Bearing failure is reached when elongation of the fas-tener hole becomes excessive. Bolted or riveted joints may also fail by shear of the fasteners, by shear rupture of the material between the holes and the end of the connected part, or by fracture on the net section. The factor of safety is higher for fastener shear (2.34) than the other failure modes (1.95) because the structural integrity of fasteners is less reliable than base metal. This is because fasteners are subjected to additional hazards that base metal is not—they may be improperly installed (for example, by being over- or under-tightened, missing nuts or washers, or with threads in the shear plane when this was not accounted for in the design). Prior to the 7th edition of the Specification the fac-tor of safety on bearing failure was the same as for fastener shear. The shear rupture provisions (Section 5.1.3), how-ever, added in the 7th edition of the Specification, produce calculated strengths for some connections that are less than those calculated under the provisions of earlier editions which did not contain this check.

Bearing tests show (9) that for ratios of edge distance to fastener diameter as small as 1.5, it is conservative to reduce the allowable bearing stress by the ratio of the edge distance to twice the fastener diameter. The Specification does not allow ratios of edge distance to fastener diameter smaller than 1.5.

Tests (10) have demonstrated that a relatively even dis-tribution of load among the fasteners is achieved before ultimate failure of mechanically fastened joints in struc-tural aluminum alloys.


The bearing strength for flat surfaces, elements with pins in holes and elements with pins or bolts in elongated holes is 2/3 the bearing strength of elements joined by properly fitting rivets and bolts. This requirement originally was adopted from steel specifications. A lower bearing strength appears to be reasonable in these cases because the applied pressure can be much more concentrated than that in riv-eted or bolted joints, because the diameter of the loading element (pin) can be small compared to the diameter of the opening in the element that is being loaded. Good prac-tice in bolted and riveted joints requires a reasonable fit between fastener and hole diameter.


The formulas in this Section for values of kL/r exceed-ing S1 approximate the column strength given by the tan-gent modulus column formula. The tangent modulus for-mula is

Fcr = π2Et _____ (kL/r)2 (Eq. C3.4.7-1)

January 2005 II-A-9

where Fcr = column strengthEt = tangent modulus (slope of stress strain curve)

corresponding to Fcr

kL = effective length of column r = least radius of gyration of column

In the elastic range, this formula is simply the Euler column formula, which is used as a basis for allowable stresses for values of kL/r exceeding S2. For values of kL/r between S1 and S2 the tangent modulus formula is approxi-mated closely by the straight line (8), which is used as a basis for the allowable stress formula.

Numerous tests have shown that these formulas closely predict the strength of essentially straight columns (8, 11). To ensure adequate safety in the presence of accidental eccentricity and initial crookedness, which may reduce the strength of practical columns (12, 13), the factor of safety nu rather than ny is applied to column strength.

The effective length of columns is normally defined as a factor k times the length of the column between lateral sup-port. Background for this can be found in Reference (14).

For values of kL/r less than Sl, the compressive strength of columns is the compressive yield strength. Such col-umns are sometimes referred to as stub columns, for which the failure mode is yielding rather than buckling.

A great deal of background information relating to col-umns and other buckling problems can be found in Refer-ence (15).

3.4.7.2 Doubly or Singly Symmetric Sections Subject to Torsional or Torsional-Flexural Buckling

Based on data in Reference (16), Reference (17) shows that the column design equations of Section 3.4.7 can be used for torsional-flexural buckling if an equivalent slen-derness ratio is defined. The redefinition is based on (kL/r)e

the elastic torsional-flexural buckling stress. The inelastic torsional-flexural buckling stress is then calculated using the column design equations used for flexural buckling. For point symmetric sections such as cruciforms, torsional buckling is the most likely mode of failure and Fe becomes equal to Fet.


Nonsymmetric sections that are subject to torsional or torsional-flexural buckling may be designed as follows:- determine the elastic torsional-flexural buckling stress

according to the torsional-flexural theory.- determine the equivalent slenderness ratio using Equa-

tion 3.4.7.2-1.- determine the limiting or allowable stress with the equa-

tions of Section 3.4.7.

3.4.8 Uniform Compression in Elements of Columns Whose Buckling Axis is an Axis of Symmetry—Flat Elements Supported On One Edge

Reference (18) addresses Sections 3.4.8(a) and 3.4.8(b). Section 3.4.8(c) is based on the post-buckling strength rather than the buckling strength of unstiffened plate ele-ments (19). Tests performed on stub-columns with cruci-form cross sections show post-buckling strength. These provisions apply to wide flange shapes buckling about either axis and channels buckling in the strong direction.

3.4.8.1 Uniform Compression in Elements of Columns Whose Buckling Axis is not an Axis of Symmetry—Flat Elements Supported On One Edge

In columns buckling about a principal axis that is not an axis of symmetry the centroid of the stresses may not be the same as that for the full section. This is due to the non-linear stress distribution in the post-buckling range of the flat plate elements of the section. In such cases though some postbuckling strength may exist, it may not be as large as that if the buckling axis were an axis of symme-try. For this reason the provisions of this Section limits the strength to local buckling strength. Column sections such as channels buckling about the weak axis are covered by these provisions.


The ultimate strength of a plate supported on both edges may be appreciably higher than the local buckling strength. Thus the allowable stress is obtained by applying the factor of safety nu to a formula that gives a conservative approxi-mation to the ultimate strength of the plate (20).

In the inelastic stress range, the ultimate strength is the same as local buckling strength, so the allowable stress is based on the local buckling formula with an equivalent slenderness ratio of 1.6 b/t and a factor of safety nu.

The coefficient 1.6 is approximately the value that applies to a plate simply supported on two longitudinal edges.


Equation 3.4.9.1-2 provides a transition between the allowable stress in an unstiffened plate element and the allowable stress in an edge stiffened plate element with a fully adequate stiffener. The predicted capacities using the provisions in this Section correlate well with the experi-mental capacities obtained from test on stub columns with edge stiffeners (19).

II-A-10 January 2005

Equations 3.4.9.1-3 through 3.4.9.1-5 are the rs /Ra ratios for different ranges of the (b/t) ratios where rs is the radius of gyration of an edge stiffener about the plate mid- thickness surface and Ra is the radius of gyration of a stiff-ener adequate to make the flange being stiffened function as a plate element supported on both longitudinal edges. Equations for Ra are given by the denominators of Equa-tions 3.4.9.1-4 and 3.4.9.1-5. The equations for determin-ing Ra are adapted from the AISI Specification (21) and compared with the equation proposed in Reference (23). The elastic buckling analysis in Reference (23) shows that an edge stiffener is adequate if rs = 6t. Elastic buckling begins at a (b/t) ratio equal to S where S is the limiting (b/t) ratio at which a stiffened element is fully effective. At this value of (b/t) ratio, the value of Ra obtained from Equation 3.4.9.1-4 is identical to the value of rs derived in Reference (23). A linear relationship is assumed between Ra and (b/t) ratio if the (b/t) ratio is between S/3 and S.

The value of rs necessary to be considered as an adequate edge stiffener is larger than 6t in the post-buckling range of the element being stiffened. Post-buckling strength exists in an edge stiffened plate element with a (b/t) ratio exceeding S. Equation 3.4.9.1-5 is valid for values of the (b/t) ratios between S and 2S. Sufficient test data does not exist to develop an equation for Ra when the (b/t) ratio exceeds 2S.

The limitation on the Ds /b ratio prevents any adverse interaction between the local buckling of the lip stiffener and the flange.

It should be noted that Fc determined according to Equa-tions 3.4.9.1-1 and -2, should not exceed the value of Fc deter-mined for the stiffening lip according to Section 3.4.8.

In this Section as well as in some of the subsequent sec-tions, it is stated that if the inside corner radius exceeds 4 times the thickness then the inside radius shall be assumed equal to 4 times the thickness in calculating b. This rule was reached on the basis that a radius that is too large would be detrimental to the post buckling strength of the element and that the flat element width would be too unconservative to take in calculating the strength.


The provisions in this Section are based on Reference (23) which is discussed further in Section 3.4.16.3.


In theory, the elastic buckling strength of an ideal cylin-drical shell loaded in compression can be determined by substituting an equivalent slenderness ratio of 4.0Rb /t into the column formula. The buckling strength of actual shells, however, is strongly affected by imperfections in the geom-

etry and end conditions of the shells. Tests indicate that this effect tends to increase with increasing Rb /t. This effect of imperfections is taken into account by the formulas in this Section, which are conservative when compared with the results of numerous tests on tubes and cylinders (7, 24). The formulas of this Section are based on local buckling strength, since severe deformations occur at this load.

The strength of circumferentially welded tubes has been shown to be given accurately by the same equations as those for unwelded tubes for cases in which Rb /t < 20 (approxi-mately). For circumferentially welded cylinders with much higher Rb /t, recent studies show that the provisions may be very unconservative (17), thus the restriction of Rb /t < 20 for tubes with circumferential welds.


The allowable compressive stresses in single-web struc-tural shapes and built-up sections bent about the strong axis are based on the lateral, torsional buckling strength of beams with a factor of safety ny. In the inelastic stress range the for-mulas employ the straight line approximation to the tangent modulus buckling curve that is also used for columns. Tests have shown this curve to be conservative for beams (8). The basis for the lateral torsional buckling of single web beams about their strong axis is in Reference (25).

A simple span beam restrained against movement later-ally and vertically at the supports, but free to rotate about the vertical and horizontal axes at the ends is assumed. A sym-metrical section and uniform moment are also assumed. The expressions derived for lateral buckling (25) were rather com-plicated. To simplify calculations an approximate method for estimating lateral buckling strength was developed. An effective slenderness ratio L/1.2ry was found to pro-vide conservative answers for standard aluminum shapes. Because of the conservatism of the approximate method, Section 4.9 allows the designer to calculate a more precise value for ry based on the “exact” solution.

The factor of safety applied to beam buckling is ny rather than the value used for columns, nu. The assumptions on restraint at ends and at loads are conservative. In addition, continuous beams can redistribute moment and beams attached at their ends can carry some load in membrane actions. All the assumptions err on the conservative side, and thus the lower factor of safety was used.


For values of Rb /t below the slenderness limit S1, the allowable stress is increased over the basic allowable com-pressive design stress for single web beams, since tests have demonstrated that a shape factor of 1.17 can be applied to the yielding of round tubes. For values of Rb /t between S1 and S2, the allowable stress is based on a formula that gives

January 2005 II-A-11

a close approximation to experimental values of buckling strength for round tubes in bending (7).

The value of S2 in this Section is the value of Rb /t at which the curve for bending strength intersects the curve for buckling stress under axial compression. For greater values of Rb /t, the conservative assumption is made that the allowable stress in bending is the same as that in direct compression. The limitation that the equations apply for Rb /t < 20 for tubes with circumferential welds is the same as that applied in Section 3.4.10.


If a solid rectangular beam is laterally unsupported and is sufficiently narrow in cross section, it can fail by lateral torsional buckling. This type of failure is taken into account in this Section, using 2.3(d/t) √

____ Lb /d as the equivalent slen-

derness ratio. If the beam is sufficiently wide, it will not buckle, and the allowable stress is controlled by the yield strength. When 2.3(d/t) √

____ Lb /d < S1 a shape factor of 1.3 for

yielding is assumed as for Section 3.4.4. In the intermediate slenderness ratio range, the buckling strength is consider-ably affected by a redistribution of stress that accompanies plastic yielding, so that the apparent stresses at buckling are appreciably higher than values for single web beams. The formula used to represent buckling strength has been shown to agree well with the results of buckling tests on rectangular beams (8).

The formulas are based on the conditions of a uniform moment on a single span beam, simply supported, with the ends prevented from lateral deflection, but free to rotate about the vertical axis.

The factor of safety applied to beam buckling is ny, as in Section 3.4.11. Experience indicates this factor of safety is adequate.


This section applies to closed shapes. The wall thick-ness need not be uniform.

The allowable stresses in this Section are based on the lateral torsional buckling strength of tubular shapes. The safety factor is ny, for the same reasons as discussed in Sec-tion 3.4.11.

Since the Specification may be used for a wide variety of extruded or formed shapes, the conservative assumption was made that the shape factor for yielding is 1.0.

The expression used for equivalent slenderness ratio of

a tubular shape is 1.6 √____

2LbSc ____ √

___ IyJ . This expression is more accu-

rate than the slenderness ratio of 1.6 √______

LbSc/Ic which was based on References (4) and (5). It was derived using the more general theoretical equation for lateral buckling strength and ignoring the term that represents the warping resistance of the beam, since, for closed sections, this term is usually

small in comparison to the term that represents St. Venant torsion. The two terms are equal when Cw = 0.038J(ky Lb)2. If Cw is not small compared to 0.038J(ky Lb)2 the use of Section 3.4.11 with the rye value calculated according to Section 4.9.3 gives more accurate results.

This Section allows replacing √

___ IyJ ___ 2 in the denominator of

the slenderness term with Iy for narrow rectangular tubes. Iy is an approximation, and since it is typically greater than

√

___ IyJ ___ 2 , using Iy gives less conservative results. This unconser-

vatism is limited to about 10% by limiting the use of Iy to tubes with a depth to width ratio of 6 or more.

The torsional constant J for a closed section is

J = 4A 2 m

____ ∫ ds __ t

(Eq. C3.4.14-1)

where Am is the mean of the areas between the inner and outer boundaries and ds is the incremental length along the perimeter of thickness t. For uniform thickness t, this equa-tion becomes:

J = 4A 2 m t

____ s (Eq. C3.4.14-2)

where s is the length of the boundary at mid-thickness. The expression for a hollow rectangular tube is

J = 2t2t1(a – t2)2 (b – t1)2

______________ at2 + bt1 – t22 – t1

2 (Eq. C3.4.14-3)

The dimensional notation is illustrated in Figure C3.4.14-1.

Figure C3.4.14-1CROSS-SECTIONAL NOTATION



Allowable stresses for values of b/t exceeding S1 were obtained by applying the factor of safety ny to the ulti-mate strength of an outstanding flange simply supported on one edge (20). If this Section were to be applied only to standard structural shapes, it would have been possible to assume some restraint against rotation at the supported edge of the flange, which would have resulted in somewhat higher allowable stresses. However, this Section also cov-ers other extruded shapes and formed sheet members, in which the web may offer little restraint against flange rota-tion. Therefore, the conservative assumption of simple sup-port was made.

This Section permits the designer to take advantage of the fact that the ultimate strength may exceed the local buckling strength for very thin sections.

Formulas (b) and (c) are based on the ultimate strength of an outstanding flange simply supported on one edge.


This is similar to Section 3.4.9 for components of col-umns, except that the factor of safety used is ny rather than nu because the strength prediction of beams and beam ele-ments are thought to be more conservative than those of compression members.

Equations 3.4.16-2 and 3.4.16-3 are based on the ulti-mate strength of a plate simply supported on both edges.


These expressions for curved sections are taken from Reference (26). They apply to curved components of beams other than round or oval tubes, which are covered in Sec-tion 3.4.12. For values of Rb /t between S1 and S2 the stresses allowed by Section 3.4.16.1 are somewhat lower than those allowed by Section 3.4.12 because tests have shown that not all beams with curved sections of these proportions can sustain the high apparent stresses developed by round or oval tubes.


The provisions in this Section are similar to that in Sec-tion 3.4.9.1. The commentary for Section 3.4.9.1 is equally applicable for this Section as well.

The predicted capacities using the provisions in this Section, in conjunction with the weighted allowable stress approach, correlate well with the experimental capacities obtained from beam tests (19).


The provisions in this Section are based on work per-formed by Sharp (23). Equation 3.4.16.3-6 is the equiva-lent slenderness ratio to be used with the column buckling equations given by Equations 3.4.16.3-2 and 3.4.16.3-3. The predicted capacities using the provisions in this Sec-tion, in conjunction with the weighted allowable stress approach, correlate well with the experimental capacities obtained from beam tests as shown in (19).


The coefficients in the formula for inelastic buckling strength were assumed to be the same as for rectangular beams (Section 3.4.13) because calculations and tests have shown that the apparent stress (Mc/I) at which the yield strength is reached in the outer fiber of sections such as tees, angles and channels is even higher than for rectangu-lar beams. The equivalent slenderness ratio was assumed to be 3.5b/t, which implies partial restraint against rotation at the supported edge.

This is based on elastic buckling strength. This type of component is assumed to have negligible post-buckling strength.


The comments under Section 3.4.17 concerning shape factor and buckling formula constants apply here also. When the neutral axis is at the midheight of the element, the equiva-lent slenderness ratio is 0.65h/t, which applies to a plate in bending with both edges simply supported. Simple support was assumed because the boundary conditions at the com-pression edge are more important than those at the tension edge and it is possible that compression elements support-ing the compression flange may buckle at the same time as the web.



Comments made with regard to Sections 3.4.17 and 3.4.18 apply here also. The equivalent slenderness ratio is 0.29h/t based on simple support at the edges and at the stiffener (27).


Allowable shear stresses in unstiffened flat webs are deter-mined by applying the factor of safety ny to the calculated buckling strength for a web with partial restraint against rota-tion at the attachment to the flanges. The corresponding value of the equivalent slenderness ratio is 1.25h/t (27, 28). The formulas for the buckling coefficients in the inelastic range were developed originally for shear buckling of tubes (7) but they apply also to flat plates in shear.

3.4.21 Shear in Elements—Stiffened Flat Elements Supported on Both Edges

A stiffened flat web that has buckled in shear can con-tinue to carry load by diagonal tension action in the web (29, 30, 31). Thus it is not necessary to use the same fac-tor of safety against shear buckling of the stiffened web as is used for an unstiffened web in which local buckling could bring about collapse. However, it was assumed that it would not be desirable to have local buckling of webs at design loads, both from the standpoint of appearance and because of the possibility of fatigue failure. Thus, the fac-tor of safety na was applied to the local buckling strength of stiffened flat webs in shear. This factor of safety is used to ensure that stresses at design loads are less than the local buckling stress. The edges were assumed to be partially restrained against rotation, giving an equivalent slender-ness ratio of

1.25a1 ____________

t √__________

1 + 0.7 ( a1 __ a2 ) 2




Provisions on combined compression and bending in this Section agree with the allowable stress design versions of other metal structural specifications (21).


The provisions in the Section are the same as those used in other metal structural specifications (21).


The equation for equivalent h/t is based on the theoreti-cal elastic buckling strength of cylinders in torsion. Tubes loaded in torsion are not as sensitive to the effect of ini-tial imperfections in the geometry as are tubes loaded in axial compression. The theoretical buckling strength has been found to give good agreement with the results of tests on thin cylinders that fail in the elastic range (32) and the use of this expression with the inelastic buckling equations employed in the Specification also gives good agreement with experimental results in the inelastic stress range (7).

4.4 Combined Shear, Compression and Bending

The formula for interaction of combined stresses in walls of curved surfaces or round tubular members is based on investigations reported in (15, 28, 33). Likewise, the interaction equation for combined stresses in webs of rectilinear shapes and plates of built-up girders or similar members is based on the buckling strength of these mem-bers (15, 27).


This Section requires that if a longitudinal stiffener is used on a beam web, it shall be located so that the distance from the toe of the compression flange to the centroid of the stiffener is 0.4 of the distance from the toe of the compres-sion flange to the neutral axis of the girder. This is the opti-mum location for increasing the buckling strength of the web under the influence of compressive bending stresses in the web. The resulting increase in allowable compressive stress in the web is reflected in Section 3.4.19 (27). The formula for stiffener moment of inertia which is the same as that used in earlier specifications published by ASCE (4, 5), agrees closely with the size recommended on the basis of theoretical considerations (27) and is also in good agreement with the results of tests (22). The factor α takes account of the effect of eccentricity for a stiffener on one side of the web only (34).


The stiffener size recommended is sufficient to limit local buckling of shear webs to the panels between stiff-eners and to provide considerable post-buckling strength in the web. These formulas were also used in the specifi-cations published by ASCE (4, 5). They agree well with the results of tests (35) and are conservative in comparison with stiffener sizes derived from theoretical considerations (36). Background for these provisions is discussed further in (37) and (38).

The Section requires that the moment of inertia of a stiffener at a point of bearing should be equal to the sum of the moment of inertia required to resist the tendency of the


web to buckle and the moment of inertia required for the stiffener to carry the bearing load as a column with thelength equal to the height of the web.


This Section applies to either thin or heavy gage con-struction. In some cases, consideration shall be given to the design of members that incorporate elements having rela-tively large ratios of width to thickness. In the following paragraphs such elements are referred to as “thin”, mean-ing that they are thin relative to their width, even though the thickness itself may be any value.


In Sections 3.4.8, 3.4.9, 3.4.9.1, 3.4.15, 3.4.16, 3.4.16.2, 3.4.18 and 3.4.19 for thin plate elements, namely, elements having b/t ratios in excess of S2, the ultimate load carry-ing capacity is based on the post buckling strength which can be quite significantly higher than the local buckling strength.

For these cases where the post buckling strength is the basis for design, the local buckling stresses are needed in certain situations. All the equations for local buckling stresses except in Sections 3.4.9.1 and 3.4.16.2 are based on plate or stiffener buckling theories. In Sections 3.4.9.1 and 3.4.16.2, the local buckling stress is based on the deri-vation given below. Limiting the stresses to the local buck-ling stress divided by a factor of safety of 1.2 would limit the appearance of buckling at allowable loads.

One can visualize the post buckling strength in terms of the effective width approach as is done for deflection cal-culations. Using the effective width approach, the ultimate axial load capacity of a plate element supported by webs on both longitudinal edges is determined as follows:

Pult = tbeFcy (Eq. C4.7.1-1)

where Fc y is the yield stress, be is the effective width and t is the thickness of the plate.

Using the average stress approach as is done in Section 4.7.2, the load capacity of the plate can be determined as follows:

Pult = tbnyFc (Eq. C4.7.1-2)

where b is the plate width, ny is the factor of safety, Fc is the allowable stress.

Setting Equations C4.7.1-1 and -2 equal, the follow-ing expression for the effective width at ultimate load is obtained:

be = b ny Fc ____ Fcy

(Eq. C4.7.1-3)

The effective width according to the effective width equa-tions in Section 4.7.6 can be written as

be = b √___

Fcr ___ Fcy

(Eq. C4.7.1-4)

where Fcr is the plate buckling stress.Setting Equations C4.7.1-3 and -4 equal, the following

expression for Fcr is obtained:

Fcr = (nyFc)2

______ Fcy

(Eq. C4.7.1-5)

Equation C4.7.1-5 is the equation used for the case of Sec-tion 3.4.16.2.

For cases where post buckling strength is used, the allowable compressive stresses given may result in visible local buckling, even though an adequate margin of safety is provided against ultimate failure.

In applications where any appearance of buckling must be avoided, the stresses for thin sections should not exceed the value of Fcr given divided by 1.2. The factor 1.2 is based on experience.


The ultimate strength of a member consisting of a num-ber of slender elements can be estimated by simply adding up the ultimate or buckling strengths of the individual ele-ments (39).


Tests of formed sheet beams (20) were the basis for the weighted average allowable compression and tensile bending stresses in Specification editions prior to 2005. More recent research (83) documents modifications to the weighted average method, improving its accuracy for a variety of members. The distance c for a tensile flange is the distance to its extreme fiber because tension fracture initiates there. The distance c for a compression flange is the distance to its centerline because buckling is based on the flange’s average stress.


Sections 3.4.8 and 3.4.9 take advantage of the postbuck-ling strength of plate elements, because in general such ele-ments may buckle without causing failure of the member. However if the local buckling stress of the section is lower than the flexural buckling strength of the column, the reduced stiffness that accompanies local buckling may reduce the allowable column stress as given by Section 3.4.7. The for-mula in Section 4.7.4 for allowable stress is based on an equation (40) that has been found to give good agreement with the results of compression tests on H-section and box section columns incorporating thin elements (41).

The local buckling values used in the calculations ref-erenced in Section 4.7.1 are accurate for shapes such as


square boxes and conservative for all other shapes. These values can be quite conservative for sections in which the edge restraint of the elements is much higher than the sim-ply supported cases used.


The provisions of this paragraph take into account the effect that the reduced stiffness due to local buckling may have on the lateral buckling strength of single web beams.

The basic relationship that applies to columns has been found to be useful also for beams (40). The local buckling values used in the calculations, referenced in Section 4.7.1, are based on flanges with a simply supported attached edge, and thus can be quite conservative for sections in which the edge restraint is much higher than the simply supported case.


One way to take into account the effect of local buck-ling on the post-buckling behavior of structural members is to consider that at stresses above the local buckling stress, only part of the cross-section of the buckled element is effective in carrying load. The formula given here has been found to be generally conservative for aluminum elements (19, 20).

As noted in Section 4.7.1 the allowable compressive stresses may in certain instances result in some local buck-ling at design loads for very thin sections, even though an adequate margin of safety is provided against ultimate fail-ure. This local buckling may result in increased deflections for sections with plate elements covered by Sections 3.4.8, 3.4.9, 3.4.15, 3.4.16, 3.4.18 and 3.4.19 with b/t values exceeding 1.65S2 where the value of S2 is obtained for the element in question.

The formulation of Sections 3.4.9.1 and 3.4.16.2 is somewhat different and a different criterion is used for deciding when the effective section is to be used.


The formulas given in this Section are based on Reference (42) which is also described in Reference (17). If the edge load is concentrated over a portion of the element length, web crip-pling needs to be considered. This failure mode is confined to the area of the web under the load. The equation for maximum strength for interior loads is given by Equation 4.7.7-1, and that for end loads is given by Equation 4.7.7-2. The strengths are effectively post-buckled values. Thus thin webs will have lateral displacements at the calculated strengths.


The formulas given in this Section are based on Refer-ence (42) which is also described in Reference (17).

4.8 Fatigue

The provisions of this Section are modifications of the original fatigue specifications (43). The modifications include changes to the fatigue strength curves and the addition of a method to determine life of parts under spectrum loading. The changes are based on recent tests of full scale welded beams in the United States (44) and Europe (45).

The analyses consider that the major factors affecting fatigue behavior are the number of stress cycles, the mag-nitude of the stress range and the type and location of the member or detail. The fatigue crack will generally grow perpendicular to the plane of maximum stress. This Section of the Specification uses a nominal stress range determined by elastic analysis. The effect of stress concentrations are accounted for through the proper selection of fatigue details. Many other factors, including environment, detrimental weld quality, and post-weld mechanical treatment can have an effect, but are not considered within the scope of this docu-ment. Special analysis or tests are required for details and conditions not specifically covered by the Specification.

Loads and number of load applications are not covered. If the information exists for structures of other materials, the same values may be used for aluminum structures of the same type. Wind induced vibrations of undamped structures or components can cause large numbers of cycles and high stresses and thus need to be avoided. Alternatively, vibration dampers may be used to limit wind induced vibrations.

The fatigue strength of mechanically fastened connec-tions with a stress ratio less than or equal to zero is based on Reference (74). This reference includes data from about 750 tests of bearing and friction joints with a wide vari-ety of conditions. The data used to determine the fatigue strength of joints with a stress ratio of zero conservatively include numerous tests with a stress ratio of 0.1.


The equations for allowable stress are based on the 95% confidence for 97.7% probability of survival. The results of the recent beam tests account for the revision of the previ-ous values. The fatigue limit was assumed to occur at 5 × 106 cycles for each detail. Static strength provisions in the other sections of the Specification limit the design fatigue strength for low numbers of cycles.


Real load histories are frequently more complicated than the constant amplitude loading discussed in the previous Sec-tion. This Section provides a method by which the engineer may design for more random variable amplitude loadings experienced by many structures. The equivalent stress method is based on nominal stress ranges, linear damage accumula-tion, and no sequencing effects. The engineer should also use a standard cycle counting algorithm, such as rainflow count-ing (71, 72) to determine the equivalent stress range.


The equation for the equivalent stress range is derived directly from Miner’s Rule when the S-N curve is a straight line in log-log space. Miner’s rule is given by

∑ni ____ Ni

≤ 1.0 (Eq. C4.8.2-1)

where ni = number of cycles of the ith stress range Ni = number of cycles constituting failure at the ith stress

rangeThe equation states that when this fraction approaches

unity, some of the details within the group have begun to fail. The engineer may wish to use the Miner’s rule formu-lation over the equivalent stress range when assessing the remaining life of an existing structure or when fatigue data is not linear in the log(stress)-log(life) space.

The analysis is made as specified in Section 4.8.1 except that the fatigue limit is not used. In this case, the equa-tions for allowable stress are also used for number of cycles greater than 5 × 106 because available data for spectrum loads show continuing decrease at long lives.

4.9 Compression in Single Web Beams Including Single Web Beams with Tubular Portions

The formulas of Section 3.4.11 for single-web beams are based on an approximation in which the term Lb /ry replaces a more complicated expression involving several properties of the cross section. Because of this approxima-tion, the formulas give very conservative results for certain conditions, namely for values of Lb /ry exceeding about 50 and for beams with transverse loads applied to a flange and in a direction away from the beam’s shear center. To com-pute more precise allowable compressive stresses for these cases, the value of ry in Section 3.4.11 may be replaced by an “effective ry” denoted rye given by one of the formulas of Section 4.9.

For doubly symmetric sections either Section 4.9.1 or 4.9.3 may be used. The latter Section is more accurate and in general, yields higher design stresses. For singly-symmetric sections unsymmetric about the bending axis Section 4.9.2 or 4.9.3 may be used. The latter Section is the more accurate of the two.

This Section also recognizes the possibility of taking advantage of the effect of bracing the tension flange using a method of rational analysis. An example of a rational analy-sis is given in Reference (46). In this reference an expression for the elastic critical moment Me for a singly symmetric I-section with the tension flange prevented from lateral dis-placement but free to rotate is derived. For pure bending:

Me = EIc dπ2

______ Lb

2 + GJ ___ d (Eq. C4.9-1)

rye can be evaluated for this case using this Me in Equation 4.9.3-1. Equation C4.9-1 which was derived for uniform

moment is conservative for the case of uniform loading.In the above equation Ic is the moment of inertia of the

compression flange about the web, d, Lb, and J are as defined in Section 4.9.1.

4.9.1 Doubly Symmetric Sections and Sections Symmetric about the Bending Axis

Allowable stresses are determined at the ends or at the brace points of beams as well as between brace points. At brace or support points of a doubly symmetric beam Equa-tion 4.9.1-1 is to be used to calculate the allowable stress. The same equation is to be used between brace points if the beam is subjected to lateral loads that are applied only at the shear center of the section. Equation 4.9.1-2 is used to calculate the allowable stress between brace or support points when a transverse load is applied to the top or bot-tom flange of the beam and the load is free to move laterally with the beam if it should buckle.

The selection of the proper equation for rye can be illus-trated using Figure C4.9-1. At point B for both beams, Equation 4.9.1-1 is to be used. The same equation is also to be used for point A if the distributed load is applied at the level of the neutral axis. If the distributed load is not applied at the level of the neutral axis then Equation 4.9.1-2 is to be used. The approach for checking the moment at point C will be discussed in connection with the selection of Cb in Section 4.9.3.


For beams that are unsymmetrical about the x-axis, rye in Section 4.9.1 can be calculated approximately by tak-ing ry, Iy, Sc and J as though both flanges were the same as the compression flange with the overall depth remaining the same. This approximation is always quite conservative when the smaller flange is in compression. The approxi-mation may be somewhat unconservative when the larger flange is in compression. Any unconservatism inherent in assuming a larger than actual section in the case of larger flange in compression, may or may not be compensated by the conservative nature of the equations of Section 4.9.1.

4.9.3 Singly Symmetric Sections Symmetric or Unsymmetric about the Bending Axis, Doubly Symmetric Sections and Sections without an Axis of Symmetry

This Section is applicable to any beam bent about the strong axis by moments or by lateral loads applied through the shear center of the section. Equation 4.9.3-2 is derived in Reference (25) based on the elastic torsional-flexural buck-ling theory. This expression considers non-symmetry of the section about the bending axis as well as the location of the laterally applied load with respect to the shear center.


Figure C4.9-1BEAM AND MOMENT DIAGRAM EXAMPLES

Beam

Beam

A A

B

B

C

Moment diagram

Moment diagram

In calculating the section properties as well as the parameter g, it is essential to use the axis orientation speci-fied. The orientation of the axes and the cross-sectional notation are illustrated in Figure C4.9-2.

The magnitudes of yo, torsion constant J and the warp-ing constant Cw can be determined from the expressions given in references such as Reference (47).

The approximate formula for j given in Equation 4.9.3-6 as well as the approach for reverse curvature bending is based on information given by Reference (48). For cases when the areas of the compression and tension flanges are approxi-mately equal, j can also be approximated by -yo.


The increase in lateral buckling capacity due to moment variation over the unbraced length Lb is accounted for by using the factor Cb in Sections 3.4.11, 3.4.13, and 3.4.14.

A somewhat different form of the equation for Cb (Equa-tion 4.9.4.1-1) was originally proposed by Prof. M. Horne. It was later modified by Prof. D. Nethercot. The equation in the form given here is the same as in the second Edition of the AISC-LRFD Specification (49).

The expressions for Cb, C1 and C2 for the special cases are based on the work reported in Reference (50). The Cb expressions are somewhat simplified versions of the ones given in the reference.

Application of the Cb factor to singly symmetric sec-tions in the same manner as for doubly symmetric sections has been shown to be unconservative in certain situations by Reference (48). The unconservative cases arise if the Cb factor is applied to the critical moment determined for the case of larger flange in compression, ML, when it is possible that somewhere in the unbraced segment the smaller flange may be subject to compression. In such cases the proper Cb factor should also be applied to the critical moment deter-mined for the case of smaller flange in compression, MS.

The application of the coefficients Cb, C1 and C2 can be discussed with the help of examples given in Figures C4.9-1 and C4.9-3. In the single span beam of Figure C4.9-1, if the top flange is the smaller flange and MMAX occurs at a sec-tion (point B) with the smaller flange in compression, the application of the Cb factor to MS would be used in deter-mining the critical moment.


If the top flange is the larger flange of the single span beam in Figure C4.9-1, and MMAX occurs at a section with the large flange in compression (at point B), then determin-ing the critical moment as Cb ML may be unconservative because the presence of a segment with a smaller flange in compression could lead to a lower actual critical moment. A lower bound to the lateral buckling moment at the end with the smaller flange in compression (point C) can be found assuming the moment gradient in the beam to be as shown in Case 2 of Figure C4.9-3 and using the cor-responding value of Cb.

The application of the coefficients Cb, C1 and C2 to end moment cases can be demonstrated for the four beams shown in Figure C4.9-3. If the top flange is the smaller flange, the Cb factor can be applied to MS conservatively in each case.

The resulting lateral buckling moments are required to be larger than the actual applied maximum moments.

If the top flange is the larger flange, the Cb factor cannot be applied to ML conservatively in Case 3 without checking to see if a lower lateral buckling moment is possible, due to the fact that over a portion of the beam the smaller flange is in compression. A lower bound to the buckling moment for the case with the smaller flange in compression over a portion of the span can be found by assuming that the smaller flange is subjected to a moment distribution as shown for Case 2 with the small flange in compression, namely Cb = 1.67.

For Case 4 where the end moments are equal and oppo-site, only the smaller flange at the right end needs to be checked. For this check Cb = 2.27 according to Equation 4.9.4.1-1.

Figure C4.9-2ORIENTATION OF THE AXES AND CROSS-SECTIONAL NOTATION


In summary, Cb can be determined as usual for all cases except when MMAX produces compression on the larger flange and the smaller flange is also subjected to compres-sion in the unbraced length. In this case, the member need also be checked at the location where the smaller flange is subjected to its maximum compression.

If one of the two flanges is small such that Icy /Iy is less than or equal to 0.1 or greater than or equal to 0.9 then Cb shall be taken as 1.0 based on the information given in Reference (48). Cb is also to be taken as 1.0 when the rotational restraint is considered (ky < 1) since Equation 4.9.4.1-1 overestimates Cb when ky less than 1 is used.

For continuous beams there are no directly derived val-ues of C1 and C2. For this reason rational analysis must be used in estimating the values of these coefficients for such applications. It can be shown that for loading as shown in Figure C4.9-2, reasonably conservative results are obtained by taking:- C1 = 0.41Cb and C2 = 0.47Cb when the smaller (top)

flange is in compression (shown in the top two cases of Figure C4.9-2) and

- C1 = 0 and C2 = 0 when the larger (top) flange is in compression (shown in the bottom two cases of Figure C4.9-2).

Figure C4.9-3BEAM AND MOMENT DIAGRAM EXAMPLES


Alternatively, for continuous beams finite element pro-grams that are shown to be correct for those cases covered in this Section may be used.

Extensive provisions for cantilevers are not given in the Specification due to the complexity of the subject par-ticularly for singly symmetric sections. Guidance for the design of such members can be found in References (51, 52, 53, and 54).


Additional information on the use of Section 4.10 is pre-sented in Part VIII Illustrative Examples. The formula may be used for determining the allowable stress at the centroid of the compression flange of a beam that has lateral stays only at the tension flange where the stays are intermittent, such as stringers, girts, or purlins. This type of analysis is described in Reference (55). If the rotational stiffness of the joint between the stringer and the tension flange is not

Table C4.11-1 LOCAL BUCKLING STRENGTHS FOR ANGLE LEGS

Case Stress distribution on leg of angle

Equivalent slenderness

ratio/(b/t) (pinned support)

Equivalent slenderness

ratio/(b/t) (fixed support)

Angle orientation

1free edge

5.13 2.89supported edge

2free edge

4.45 2.62

supported edge

3free edge

3.64 2.27supported edge

4free edge

2.56 1.36

supported edge

known, it should be measured experimentally and intro-duced in the equation for βs (56).


The strength of single angles in flexure in this Section is the similar to the AISC Load and Resistance Factor Design Specification for Single-Angle Members, 2000.

One difference from the AISC Specification for Single-Angle Members is that the yield strength is limited to 1.3My rather than 1.5My. This is done to be consistent with Aluminum Specifica-tion Sections 3.4.4, 3.4.13, and 3.4.17 through 3.4.19.

The local buckling strength of an angle leg depends on the degree of end fixity that the other leg provides and the variation in stress across the width of the angle leg. The lower bound on end fixity is a pinned support and the upper bound is a fixed support. Buckling strengths (from Sharp’s Behav-ior and Design of Aluminum Structures (17) Table 7.1) are summarized in Table C4.11-1 for an angle leg of width b and thickness t:


Case 1, uniform compression in an angle leg, is addressed in Section 4.11a(2). Cases 2, 3, and 4 are addressed in Section 4.11a(1) by conservatively using the worst case (Case 2) and assuming that the support is restrained slightly more than the pinned condition so that a factor of 4 (vs. 4.45) can be used.


Bending about geometric axes occurs when the moment is applied about an axis parallel to a leg of the angle as shown in Figure 4.11.1-1. In such cases, when an angle is laterally restrained at the point under consideration, the neutral axis is the geometric axis as shown on the left side of Figure 4.11.1-1 and addressed in subsections a and b. When the angle is laterally unrestrained, the section will deflect laterally as well as normal to the bending axis, caus-ing the neutral axis to incline as shown on the right side of Figure 4.11.1-1 and addressed in subsection c.


Bending about principal axes is shown below:

Figure C4.11.2-1

Formulas for determining βw are given in Part VI. Since these formulas are cumbersome, βw values for some com-mon angle sizes are given in Table C4.11.2-1. βw varies only slightly with angle thickness.

TABLE C4.11.2-1

Angle Size (in.) βw (in.)

8 × 6 3.31

8 × 4 5.48

7 × 4 4.37

6 × 4 3.14

6 × 3.5 3.69

5 × 3.5 2.40

5 × 3 2.99

4 × 3.5 0.87

4 × 3 1.65

3.5 × 3 0.87

3.5 × 2.5 1.62

3 × 2.5 0.86

3 × 2 1.56

2.5 × 2 0.85

equal legs 0.00

βw is positive or negative depending on the direction of bending.


This section has been developed to provide a method for determining a more accurate slenderness ratio for members which have linearly tapered thickness elements with δ < 2.0 (i.e., tmax < 3tmin). The tapered flanges of American Standard channels and American Standard I beams meet this criterion.

Three types of edge supports for elements with tapered thickness are addressed in the Specification: (83)

a. Tapered thickness elements with the thick edge sup-ported and the thin edge free (Figure C.4.12-1(a)): For such elements, it is conservative to use b/tavg for the slenderness ratio. Using b/tavg gives a slender-ness ratio that is conservative by as much as 28% compared to finite element analysis for δ = 2. Section 4.12a. provides an approximate expression for the slenderness ratio that is less conservative and more accurate than using b/tavg.

b. Tapered thickness elements with the thin edge sup-ported and the thick edge free (Figure C.4.12-1(b)): For such elements, the slenderness ratio can be

approximated by (1.02) ( b ___ tavg ) . Using b/tavg understates

the slenderness ratio by only 3% compared to finite element analysis, so the Specification allows the use of b/tavg.

c. Tapered thickness elements supported on both edges (Figure C.4.12-1(c)): The slenderness ratio can be

approximated by (1.02 + 0.02δ) ( b ___ tavg ) . Using b/tavg

understates the slenderness ratio by only 5% at most compared to finite element analysis, so the Specifica-tion allows the use of b/tavg.

Once the slenderness ratio has been determined, use the Specification section for a constant thickness element with the same edge conditions to determine the allowable uni-form compressive stress of the element.

Section 4.12 is limited to elements with δ = (tmax – tmin) _________ tmin

≤ 2.0.

For other elements, use a rational method of analysis.


Specification Sections 3.4.15 through 3.4.19 for deter-mining compressive strengths of beam elements assume that the supported edges of elements are fixed against trans-lation and free to rotate. Section 4.13 provides an alternate method by which a more accurate assessment of element support conditions can be used to determine the compres-sive strength. Section 4.13 is also reasonably accurate for any shape composed entirely of flat elements, including those with single or multiple intermediate stiffeners. For examples, see Reference (83).

When Section 4.13 is used in combination with the weighted average strength method given in Section 4.7.3,


the strength of a stiffened element need not be limited to the strength of the stiffener since the elastic buckling strength determined is the strength of the entire section, accounting for all elements.

To apply Section 4.13:a. First determine Fcr , the elastic buckling strength of the

beam with continuous lateral support, using a linear elastic analysis. An example is a numerical method called the finite strip method, by which a member is divided into strips which run the length of the mem-ber (CUFSM (2003) v2.5, author Ben Schafer, www.ce.jhu.edu/bschafer/cufsm (visited on 9/25/03)).

b. Next, determine the equivalent slenderness ratio for

the shape λeq = π √___

E ___ Fcr

.

c. Determine the design stress for the flat elements in uniform compression using Section 4.13.1 and the design stress for the flat elements in bending in their own plane using Section 4.13.2.

d. Determine the strength for the entire shape using the weighted average method given in Section 4.7.3.


5.1 General


Edge distance requirements (2D for full bearing strength and a minimum of 1.5D with reduced bearing strength) have been selected so that for a single fastener, the block shear strength equals or exceeds the bearing strength. So for a single fastener, meeting the bearing requirements negates the need to check block shear.


The maximum spacing of fasteners in built-up compres-sion members is based on preventing buckling of the com-ponents between points of attachment.

The limits on fastener spacing for components of ten-sion members are based on experience rather than tests or theory. Limiting the spacing of fasteners joining compo-nents of tension members helps avoid buckling if unantici-pated compression acts on the member.


The block shear rupture strength in this Specification is the same as in the AISC LRFD Specification for Structural Steel Buildings 1993 edition, section J4.3 (76).

5.1.4 Net Area

Figures C5.1.4-1 and 5.1.4-2 illustrate the notation of this Section. The net section area for the strap shown in Figure C5.1.4-1 is

Anet = ( b – 2d + s2 ___

4g ) t (Eq. C5.1.4-1)

where t is the thickness of the strap and d is the diameter of the hole. In Figure C5.1.4-2, the angle section is flattened out into a strap for the purpose of calculating the net sec-tion. The flattened width is a + b – t.

Figure C5.1.4-1STRAP IN TENSION

Figure C4.12-1


Figure C5.1.4-2ANGLE IN TENSION


A study of angles, tees, and channels connected by some but not all of their elements showed that the effective area in tension is less than the net area due to the non-uniform stress distribution across the section at the connection. This is accounted for by using the net effective area given by Equation 5.1.5-1 to calculate the tensile stress in the section. Designers should not combine bending stress due to the con-nection eccentricity with axial stress on the net effective area since the effect of the eccentricity is accounted for in the net effective area determination.

To determine the eccentricities:

a. For tees connected only by their flanges (Figure C5.1.5-1(a)), the eccentricity in the y direction is the distance from the outside face of the flange to the neutral axis of the tee parallel to the flange. The eccentricity in the x direction is zero. For I beams connected only by their flanges (Figure C5.1.5-1(b)), split the section at the neu-tral axis parallel to the flanges to create two tees.

b. For channels connected only by their webs the eccen-tricities are as shown in Figure C5.1.5-2.

c. For angles connected only by one leg, the eccentric-ity in one direction is the distance from the face of the connected leg to the neutral axis of the angle par-allel to the connected leg (Figure C5.1.5-3(a)). The eccentricity in the other direction is determined from a section obtained by subtracting the portion of the connected leg outside the centerline of the fastener closest to the unconnected leg. The eccentricity is the distance perpendicular to the unconnected leg from the centerline of the fastener closest to the uncon-nected leg to the neutral axis of the remaining section (Figure C5.1.5-3(b)).

d. For I beams connected only by the web, eccentrici-ties are determined as shown in Figure C5.1.5-4.

If there is only one row of bolts in the direction of load or the only weld has an axis perpendicular to the direction of load, the length of the connection L is zero and the net effective area is the net area of the connected elements.

Figure C5.1.5-1


Figure C5.1.5-2

Figure C5.1.5-3



Caution should be exercised when the depth of the countersink approaches the thickness of the part, creating a knife-edge on the hole which may be easily damaged.


5.2.1 Bolt Material

a. (1) ASTM F468, Nonferrous Bolts, Hex Cap Screws, and Studs for General Use, includes 2024-T4, 6061-T6, and 7075-T73 aluminum bolts and provides the minimum strengths that are used in Table 5.2.3-1. Bolt dimensions are given in Part VII, Table 5-15. (2) ASTM F467, Nonferrous Nuts for General Use, includes 2024-T4, 6061-T6, and 6262-T9 aluminum nuts. Nut dimensions are given in Part VII, Tables 5-16 and 5-17. (3) Spring lock washer dimensions are given in Part VII, Table 5-18. Plain flat washer dimensions are given in Part VII, Table 5-19.

b. The AISC Specification for Structural Steel Buildings includes design rules for ASTM A307, A325, and A449 steel bolts. The Rockwell C35 hardness limit is intended to avoid hydrogen-assisted stress corrosion cracking of the bolt (see 5.4.1 commentary).

c. ASCE 8-02, Specification for the Design of Cold-Formed Stainless Steel Structural Members, provides design rules for fasteners meeting ASTM F593, Stainless Steel Bolts, Hex Cap Screws, and Studs.

AAMA TIR-A9, Metal Curtain Wall Fasteners, (75) pro-vides design rules for carbon and stainless steel fasteners.

5.2.3 Bolt Tension

The use of the root area for determining the tensile strength of aluminum fasteners rather than the slightly larger tensile stress area used for steel fasteners is based on Ref-erence (79). The root area is based on the nominal minor diameter of external threads (D – 1.191/n) given in ASME B1.1-1989, Unified Inch Screw Threads (the most current version of this document, reaffirmed in 2001) section 10.1.

Part VII, Table 5-5 gives tensile strengths for 2024-T4 and 7075-T73 bolts and cap screws.

5.2.4 Bolt Shear

Rather than using approximate relationships between the threaded and unthreaded areas of bolts and a different allowable stress when threads are in the shear plane, the same allowable stress is used in both cases and the effective shear area is adjusted appropriately.

Part VII, Table 5-5 gives shear strengths for 2024-T4 and 7075-T73 bolts and cap screws with threads in and out of the shear plane.

5.2.5 Bolt Bearing

The bearing strength (2Ftu) is the load at which hole deformation is approximately D/4, where D is the nominal diameter of the bolt (84).

See also Section 5.1.1 Commentary.

5.2.7 Lockbolts

A lockbolt assembly includes a pin, which is similar to a bolt, and a collar, which performs the function of a nut. The collar is swaged onto locking grooves on the pin.

Figure C5.1.5-4


Lockbolts are available in carbon steel, stainless steel, and aluminum.

5.2.8 Slip-Critical Connections

5.2.8.1 General

This Section is based on specifications and research from Europe and testing conducted in the US (73). Aluminum slip-critical connections are included in Canadian, British, ISO, and proposed Eurocode specifications. In the US, use of high strength steel bolts is governed by the Research Council on Structural Connections (RCSC) Specification for Structural Joints Using ASTM A325 or A490 Bolts. The RCSC Specification addresses the use of these high strength steel bolts to connect steel parts, and so is modified here for connections using aluminum parts. All parts of the RCSC Specification not modified by the provi-sions of Section 5.2.8 (for example, provisions on inspection) apply to aluminum slip-critical connections.

Slip-critical connections resist shear by friction between the faying surfaces of the connected parts, which are tightly clamped together by high strength steel bolts. Slip-critical connections are used when it is desirable to prevent move-ment of connected parts relative to one another. Such con-nections are useful for joints subjected to dynamic or fatigue loads, as well as joints in which both bolts and welds share the load, joints with oversize holes, and joints with slotted holes with loads not applied normal to the axis of the slot.

In addition to the requirements for bearing connec-tions, slip-critical connections are subject to the additional requirement that the slip resistance of the joint be greater than the applied shear loads. The design strength of slip-critical connections cannot be greater than the design strength of the same connection designed as a bearing con-nection. The design strength of a slip-critical connection is limited to the lesser of the design strength of the bolt in shear and bearing and the slip resistance of the joint.

5.2.8.2 Material

Since hot-dip galvanizing may cause embrittlement of A490 bolts and galvanizing is required to discourage gal-vanic corrosion between the steel fastener and the alumi-num parts, A490 bolts are not allowed in aluminum slip-critical connections.

The RCSC Specification limits the bearing stress under the bolt head in steel to 64 ksi for steel with a yield strength less than 40 ksi, by requiring such steel with A490 bolts to have washers. The Specification for Aluminum Structures requires the use of washers under bolt heads and nuts, and bearing stresses under the washer can reach approximately 24 ksi (165 MPa) with A325 bolts. Therefore, aluminum slip-critical connections are limited to those alloys with a tensile yield strength of 15 ksi (105 MPa) or greater.

Thin parts such as aluminum sheet and drawn tube are effectively prohibited from slip-critical connections by bearing stress limitations on the sides of the hole.

ASTM A325 allows both hot-dip galvanizing and mechan-ical galvanizing of fasteners. A325 further requires that all components of a fastener assembly (bolt, nut, and washer) be coated by the same process, since mixing bolts and nuts gal-vanized by different processes may result in an unworkable assembly.

5.2.8.3 Holes

For convenience, nominal hole dimensions from the RCSC Specification are given in the following table:

Bolt Diameter

(in.)

Hole Dimensions (in.)

Standard(Diameter)

Oversized(Diameter)

Short Slotted(Width × Length)

Long Slotted(Width × Length)

1/2 9/16 5/8 9/16 × 11/16 9/16 × 1 1/4

5/8 11/16 13/16 11/16 × 7/8 11/16 × 1 9/16

3/4 13/16 15/16 13/16 × 1 13/16 × 1 7/8

7/8 15/16 1 1/16 15/16 × 1 1/8 15/16 × 2 3/16

1 1 1/16 1 1/4 1 1/16×1 5/16 1 1/16 × 2 1/2

>1 1/8 d + 1/16 d + 5/16 (d + 1/16) × (d + 3/8)

(d + 1/16) × (2.5 d )


Slip-critical connections must be designed assuming slip could occur, placing shear on the bolt and bearing on the sides of the hole. Bolt shear strengths are the same as in the RCSC Specification. Bolt design shear strengths should be reduced appropriately in long connections since bolts at the end of such connections bear a higher shear force than bolts near the middle of the length of these connections. (The RCSC Specifi-cation requires shear strengths be reduced by 20% in connec-tions whose length between extreme fasteners measured parallel to the line of force exceeds 50 in. (1300 mm)).


Slip coefficients are given for two contact surfaces: roughened aluminum on roughened aluminum, and rough-ened aluminum on zinc-rich painted steel. These surfaces were tested in accordance with the test method given in the RCSC Specification for both slip and creep (73). Slip coef-ficients for other surfaces may be determined by testing in accordance with the RCSC Specification.

Because aluminum has a higher coefficient of thermal expansion than steel, the tension in the steel bolt may change if an aluminum slip resistant connection is subjected to a change in temperature from the installation temperature. When the temperature drops below the installation temper-ature, the bolt tension may decrease since the aluminum in the grip would contract more than the steel fastener if the aluminum were unrestrained. For temperature drops the design shear strength may be reduced using a rational anal-ysis that takes into account the proportions of the joint and the properties of the materials. The effect of temperature


drops may also be accounted for by conducting the RCSC tests for creep at a lower temperature than installation and determining the slip coefficient accordingly. The steel bolts are installed at a tension slightly above their yield strength, so a temperature increase above the installation tempera-ture will generally not cause significant additional tension since the bolt strain hardens. The temperature increase may, however, result in permanent elongation of the bolt and consequent partial loss of pretension on subsequent temperature drops. For this reason the effect of temperature changes depends on the temperature extremes the bolted assembly will experience.

References (77) and (78) offer more information on the effect of temperature on slip-critical bolted aluminum joints.

5.2.8.6 Washers

Washers are required under all bolt heads and nuts. This requirement is intended to minimize galling of the outer ply of aluminum and creep relaxation of bolt tension.


For convenience, minimum bolt tensions from the RCSC Specification are given in the following table:

Bolt Diameter (in.) A325 Bolt Tension (kips)

½ 125⁄8 19

¾ 287⁄8 39

1 51

11⁄8 56

1¼ 71

13⁄8 85

1½ 103

Turn-of-nut tightening is performed by bringing the assembly to a snug tight condition and then applying a pre-scribed number of turns of the nut. (A snug tight condition is achieved when all plies in a joint are in firm but not nec-essarily continuous contact. This may be attained by a few impacts of an impact wrench or the full effort of a man using an ordinary spud wrench). Aluminum’s lower modulus of elasticity versus steel means more turns would be needed for aluminum assemblies than for steel assemblies if the bolt tension at the start of turn-of-nut tightening were the same for both steel and aluminum assemblies. However, the flexi-bility of aluminum parts enables them to be brought closer to full contact by snug tightening than steel, resulting in higher bolt tension in aluminum assemblies at the beginning of turn-of-nut tightening. The net effect, confirmed by testing, is that aluminum assemblies require approximately the same number of turns as steel assemblies after the snug tight con-dition is attained to reach the bolt tension prescribed above.

Galvanizing increases the friction between the bolt and nut threads and makes torque-induced tension more vari-able, but lubrication both reduces the torque and makes it more consistent. Therefore, ASTM A325 requires that a galvanized bolt and lubricated galvanized nut be assem-bled in a steel joint with a galvanized washer and tested in accordance with ASTM A563 by the manufacturer prior to shipping to assure that the fastener can be rotated beyond the required rotation from the snug-tight condition without breaking. Since some lubricants are water soluble, galva-nized bolts and nuts should be shipped in plastic bags in wood or metal containers.

In joints where bolts and welds share the load, bolts should be installed and tightened first.



ASTM B316, Aluminum and Aluminum-Alloy Rivet and Cold-Heading Wire and Rods, provides the minimum strengths that are used in Table 5.3.4-1. Rivet head styles are shown in Part VII, Table 5-6.

5.3.4 Rivet Shear

The shear strength of aluminum rivets is based on the rivet filling the hole so the effective shear area of the rivet is the nominal hole diameter. Recommended hole sizes are given in Part VII, Table 5-8 for cold-driven rivets. Part VII, Table 5-1 gives rivet shear strengths.

5.3.7 Blind Rivets

Blind rivets can be installed with access to only one side of a connection.


Results of over 3500 tests on light-gage steel and alu-minum connections worldwide were analyzed to formulate screw connection provisions (57). European Recommenda-tions (58) and British Standards (59) were considered and modified as appropriate. These provisions are intended to be used when a sufficient number of test results is not available for the particular application. A higher degree of accuracy can be obtained by testing any particular application.

Proper installation of screws is important to achieve sat-isfactory performance. Power tools with adjustable torque controls and driving depth limitations are usually used.

Screw connection tests used to formulate the provisions included single fastener specimens as well as multiple fas-tener specimens. However, it is recommended that at least two screws should be used to connect individual elements. This provides redundancy against under torquing, over torquing, etc., and limits lap shear connection distortion of flat unformed members such as straps.



The material for screws used to connect aluminum parts is selected to meet strength and corrosion resistance consid-erations. Steel screws with a Rockwell hardness of C35 or greater may suffer hydrogen-assisted stress corrosion crack-ing (HASCC) where exposed to certain dissimilar metals, moisture, and tension stress due to installation or loading. For this reason, steel screws with a Rockwell hardness of C35 or greater are no longer permitted in the Specifica-tion. Aluminum and austenitic stainless steel screws do not experience HASCC. When fasteners will not be exposed to contact with liquid water or humidity near the dew point, certain other steels, with appropriate hardness, and appropri-ately coated and/or plated are also acceptable. An example is 430 stainless steel, which has a nominal composition of 16% chromium.

5.4.2 Screw Tension

5.4.2.1 Pull-Out

The equations for pull-out are derived from research con-ducted by AAMA, including over 400 pull-out tests (75). These equations are based on three regions of behavior: yield (circumferential stretching and bending of the aluminum around the screw), shearing of the internal threads in the hole, and a transition region between yield and shearing. For most cases they are less conservative than the pull-out equation in the 6th edition (Pnot = 0.85tc DFtu2), especially for UNC threads in aluminum parts thicker than 0.084 in. (2.1 mm). Pull-out strengths are a function of the type of thread: coarse (UNC) or spaced. A UNC thread is often referred to as a “machine” thread and a spaced thread screw is termed a “sheet metal” screw. Internal thread stripping areas (Asn in equations 5.3.2.1-2 and 5.3.2.1-3) are given in Part VII Table 5-20 for Class 2B UNC threads.

5.4.2.2 Pull-Over

The pull-over strength equation for non-countersunk screws is based on Reference (17). Screws may be placed

through the valley or the crown of corrugated roofing and siding. (See Figure C5.4.2-1). A coefficient of 0.7 is used when the connected parts are not in contact, such as for fastening through the crown of roofing when a spacer block is not used between the roofing and the structural member supporting the roofing. The test strengths of such screwed connections are more variable than those with the con-nected parts in direct contact at the connection such as the fastener through the valley in Figure C5.4.2-1.

The equation for the pull-over strength of countersunk screws is based on over 200 tests using 5 different flathead screw sizes, 6 sheet thicknesses, and 2 alloy-tempers. Test-ing was limited to commonly used screws with 82 degree nominal angle heads, so the equation is not known to apply to other head angles.

Variation in actual diameters of hand-drilled countersunk holes can have a significant effect on pull-over strength. Caution should be used to avoid excessive oversizing of countersunk holes. Oversizing should be limited so that the top of the screw head is no more than the lesser of t1/4 and 1/32 in. (0.8 mm) below the top of the sheet.


Screw connections loaded in shear can fail in one mode or in combination of several modes. These modes are screw shear, edge tearing, tilting and subsequent pull-out of the screw and bearing of the joined materials.

Tilting of the screw followed by threads tearing out of the lower sheet reduces the connection shear capacity from that of the typical connection bearing strength. Equation 5.4.3-4 cov-ers the cases when the screw tilting can lower the strength.

Diameter and rigidity of the fastener head assembly as well as sheet thickness and tensile strength have a signifi-cant effect on the shear failure load of a connection. There are a variety of washers and head styles in use. Washers must be at least 0.050 in. (1.3 mm) thick to withstand bend-ing forces with little or no deformation.

Based on limited testing, it appears that the bearing force on a screw should be limited to that which produces

Figure C5.4.2-1 FASTENERS IN ROOFING


a hole elongation of D/8 to avoid threads disengaging from the sides of the hole. Testing is recommended to establish the bearing strength of screwed connections. This recom-mendation is only for those screw connections which are subjected to both bearing and tensile loads.


5.5.2 Sidelaps

Sidelaps should, where possible, be oriented to give maximum protection against the prevailing winds; i.e., dur-ing installation the horizontal progress in placing sheets on the building should be in the direction opposite to that of the prevailing winds.


Minimum size of #12 screws or 3/16 in. (5 mm) diam-eter rivets is specified in end laps and side laps to give neat, weather-resistant closures. In many cases, the primary, sheet-to-support fasteners will give satisfactory closures at the endlaps, but in sidelaps additional fasteners should be used if the joint does not interlock.


6.1 Layout


Hole centers are commonly located by punching and cut-off lines are often scribed. Center punching and scribing should be avoided where such marks would remain on fabricated material if appearances are a concern.

6.2 Cutting

6.2.1 Methods

Special attention should be paid to edge cracking in heat treatable alloys cut by laser or arc.

6.2.3 Re-Entrant Corners

Fillets are needed to reduce corner stress. The appropri-ate corner radius varies depending on the item and its use. AWS D1.1:2000, the steel structural welding code, Section 5.16, uses a minimum fillet radius of 1 in.. AWS D1.2:2003, the aluminum welding code, Section 4.11.6, requires ½ in. for statically loaded members and ¾ in. for cyclically loaded members. In Specification Table 4.8-1, the smallest radius for attachments for which fatigue categories are pro-vided is 2 in.. Since the Specification also applies to small parts, it is impractical to specify a minimum radius.

6.3 Heating

The strength of tempered metal can be reduced after exposure to elevated temperature processes (such as fac-tory paint curing, firing of porcelain enamel coatings, and hot forming). The amount of the reduction in strength var-ies with alloy, temper, and temperature exposure. Suppli-ers may be consulted for strengths of material subjected to such processes. Because the reduction in strength will not exceed 5% for the alloys, tempers, and exposures given in Table 6.3-1, no reduction in design stresses is necessary for these temperature limits. The logarithmic formula is needed for accurate interpolation between Table 6.3-1 values.

5XXX series alloys with magnesium contents greater than 3% held within the temperature range of 150oF (66oC) to 450oF (230oC) may subsequently suffer exfoliation and stress corrosion cracking. The length of time at temperature is a critical factor in determining the degree of sensitization to exfoliation and stress corrosion cracking.

6.6 Finishes

The American Architectural Manufacturers Association offers these Voluntary Specification, Performance Require-ments and Test Procedures for coating aluminum:AAMA 2603 Pigmented Organic Coatings on Aluminum Extrusions and Panels AAMA 2604 High Performance Organic Coatings on Alu-minum Extrusions and PanelsAAMA 2605 Superior Performing Organic Coatings on Aluminum Extrusions and Panels

Abrasion blasting can be used to clean material or finish the surface. Abrasive media includes steel grit, silica sand, aluminum oxide, crushed walnut shells, or coal slag. Peening can be used to improve fatigue strength by introducing com-pressive stress near the surface and is achieved with steel or stainless steel shot. Residual stresses from blasting or peening can curl thin material.

Where water is allowed to stand between aluminum parts in contact, oxidation called water staining may result. While this oxidation has no effect on material strength and will not progress after the water is removed, it is unsightly and difficult to remove. It can be prevented by keeping alu-minum dry or out of contact with other aluminum parts when moisture can be present.


Isolators such as Teflon, neoprene, and 300 series stain-less steel may be placed between aluminum and other mate-rials to prevent contact. The isolator should be nonporous to avoid trapping water or other substances in the joint, and compatible with both the aluminum and the dissimilar mate-rial in the intended service.



To avoid staining and surface corrosion, mill finished alu-minum and anodized aluminum should be protected from uncured concrete, mortar, and similar alkaline substances and muriatic acid used in cleaning concrete and masonry.

Masonry products designed to remain at a relatively low pH during and after curing (such as magnesium phosphate grout, which does not exceed a pH of 8.5) do not corrode aluminum.

6.7.4 Runoff from Heavy Metals

Heavy metals can cause deposition corrosion of alumi-num. Copper is the most common of these of metals used in construction, but terne-coated steel (which has a lead/tin coating) may also have this effect.


The L/960 straightness tolerance was chosen so that the reduction in buckling strength versus a perfectly straight member is no less than about 20%. The standard tolerance for some mill products does not meet the L/960 straightness tolerance for fabricated members required here. (An exam-ple is T6511 extrusions with wall thicknesses less than 0.095 in.). Such members may require additional straightening or tighter tolerance specifications to meet the requirements of this section.

6.10 Bending

Minimum bend radii for 90o cold forming of sheet and plate are given in Part VII Table 6-1 for a number of alloys and tempers. These radii are approximate and are a func-tion of the direction of the bend line with respect to the roll-ing or extruding direction. Cracking of heat treated alloys is more readily avoided with the bend line perpendicular to the rolling or extrusion direction, while the opposite is true for non-heat treatable alloys.

6.11 Erection


Snug tightness can usually be attained by a few impacts of an impact wrench or the full effort of person using an ordinary spud wrench. A specific clamping force is not nec-essary in non-slip-critical connections because the design accounts for parts slipping relative to each other.


7.1 General

Most of the structural aluminum alloys attain their strength by heat treatment or strain hardening. Welding causes local annealing which produces a zone of lower strength along both sides of the weld. The resulting variation in mechani-

cal properties in the vicinity of a weld is illustrated by the typical distribution in Figure C7-1. When designing welded members this decrease in strength shall be considered in addition to the design rules outlined in Section 3.

Figure C7-1DISTRIBUTION OF MECHANICAL

PROPERTIES NEAR A WELD

The effect of welding heat on aluminum mechanical properties has been discussed extensively (60, 61, 62, 63). For the non-heat-treatable alloys, the strength in the heat-affected zone after welding is essentially that of annealed material. The strength of welds in heat-treated alloys, such as 6061-T6, lies between the annealed strength and that of the original heat-treated material.

The minimum ultimate tensile strength of welded alloys given in Table 3.3-2 are the AWS D1.2 weld qualification strengths, which are the same as the annealed strengths for non-heat treatable alloys and slightly less than the solution heat treated strengths for heat treatable alloys (64).

7.2 Welded Members

7.2.1 General

Welds have little effect on buckling strength except in the range of slenderness ratios where the strength is controlled by the welded yield strength (68), so unwelded parent metal minimum mechanical properties (from Table 3.3-1) are used in the formulas for buckling constants (Table 3.3-3 or 3.3-4 as appropriate) for most welded members. Welded tubes (sec-tions 3.4.10, 3.4.12, and 3.4.16.1) are an exception. For these, welded compressive yield strengths (from Table 3.3-2) are used in the formulas for buckling constants, which are taken from Table 3.3-3 regardless of the temper of the parent metal before welding. Buckling tests on welded tubes have shown this approach to be conservative (7).Other exceptions are col-umns with welds at locations other than the ends and cantile-vers with a weld at the supported end.


Compressive tests on welded aluminum plates (62, 69) have demonstrated that the welds have little effect on post-buckling strength.


The equation in this Section is based on the fact that the strength of a cross section with only part of its area heat affected can be estimated by adding up the strength of the softened material in the heat-affected zone and the unaf-fected material outside this zone (62, 67).

The yield strength of heat-affected material is based on a 2 in. (50 mm) gage length yield strength provided in Table 3.3-2. For calculating the column buckling strength of the heat-affected material the buckling formula constants given in Table 3.3-3 are used for all alloys and tempers because they best represent the heat affected material (17).

7.2.3 Columns or Beams with Transverse Welds Away From Supports and Cantilevers with Transverse Welds

Welds at the center of a column supported on both ends or at the fixed end of a cantilever column may have an appreciable effect on the buckling strength. For these cases the strength is calculated as though the entire column were of welded material. This procedure is conservative (17).


Aluminum welded connection types include groove welds, fillet welds, plug and slot welds, and stud welds. Numerous tests have been conducted on these welds (63, 66).

7.3.1 Groove Welds


Groove welds are classified as either complete penetra-tion or partial penetration for the purpose of determining the weld size. The method of classifying a groove weld is the same as that in AWS D1.2. Groove welds made with permanent backing have less fatigue strength than groove welds without permanent backing.

7.3.2 Fillet Welds


The effective throat of an equal leg fillet weld of size Sw is 0.707Sw.


The shear strengths of 4047, 4643, and 5183 are taken from Reference (80); shear strengths of the other fillers are taken from Reference (65). Both references use the same

method and tests to determine the shear strength of other fillers should also follow this method.


Plug and slot welds are primarily used to transmit shear in the plane of the weld. An example is a cover plate attached to a flange with plug welds.

7.3.4 Stud Welds

The strengths of stud welds are taken from AWS D1.2.


The allowable stresses for 6005 and 6063 lighting pole assemblies heat treated (artificially aged) after welding are based on numerous tests.

Section 8. Castings

8.1 Materials

ASTM B 26 and B 108 do not specify minimum ten-sile yield strengths for some of the cast alloy-tempers they include (for example, sand cast 356.0-T7, which appeared in the Specification for Aluminum Structures 7th edition in Table 3.4-4). These alloy-tempers are not included in Table 8.2-1 (and therefore are excluded from the scope of the Specifica-tion) since design usually requires the yield strength. There are also other alloy-tempers in B 26 or B 108 that are not included in Table 8.2-1 and therefore not included in the Specification.

Since ASTM B 26 and B 108 do not require confor-mance with dimensional standards (tolerances) as do ASTM specifications for wrought products (for example, B 209), standards for castings must be established in the Specification. Dimensional standards required in this Spec-ification are those in the Aluminum Association Standards for Aluminum Sand and Permanent Mold Castings.

The minimum strengths specified in ASTM B 26 Table 2 for sand castings are for separately cast test bars and not for the castings themselves. As stated in section 11.3 of ASTM B 26 “When specified, the tensile strength, yield strength, and elongation values of specimens cut from castings shall not be less than 75% of the tensile and yield strength values and not less than 25% of the elongation values specified in Table 2.” Therefore, the minimum strengths as given in Table 8.2-1 are based on 75% of the ASTM B 26 Table 2 mini-mum strengths to represent what a purchaser would expect to receive if he specifies testing of the actual castings.

Castings are more prone to discontinuities than wrought products. Therefore, the Specification includes discontinu-ity standards for castings in order for them to be designed to the same Specification provisions as wrought products. The quality standards are based on the following:

ASTM B 26 and B 108 (section 20) both include options for liquid penetrant and radiographic inspection that may


be specified by the purchaser. Liquid penetrant inspection detects only surface flaws and so it is insufficient. ASTM B 26 and B 108 only require radiographic inspection be performed if the purchaser specifies such inspection. If such inspection is specified, the purchaser must also specify which of 4 quality grades: A, B, C, or D, must be met. Grade A allows no discontinuities at all; this is more stringent than wrought product quality levels and so it is unwarranted. When Grade D is specified, no tensile tests of coupons cut from castings can be required. Therefore, only grade B or C are suitable for the type of structural compo-nents addressed by the Specification. Grade C is used, since Grade C allows gas holes no larger than approximately ⅛ in. and this is the same as the ultrasonic inspection Grade B flaw size limit for wrought plate in Aluminum Standards and Data (Table 6.3). (Only a few 2xxx and 7xxx wrought alloys have any specified discontinuity limits in Aluminum Standards and Data).

Once the acceptance criteria for an individual casting is determined, the number of castings from a given lot to be radiographed and the acceptance criteria for the lot must be set. Standards for Aluminum Sand and Permanent Mold Castings establishes 4 frequency levels for inspection, 1 being the most frequent inspection. Inspection level 2 is used here since level 1 requires radiographing every casting, level 3 leaves the inspection frequency up to the foundry and so it is unspecified, and level 4 requires no radiographs.


Strengths given in Table 8.2-1 and Table 8.2-1M are taken from ASTM B 26 for sand castings and B108 for per-manent mold castings. B 26 allows the purchaser to require that the minimum strength of coupons cut from production castings be 75% of the specified strength, so the values in Table 8.2-1 are the B 26 values factored by 0.75. B 108 has the same requirement, but for certain alloy-tempers allows the purchaser to specify either 1) locations in the casting that shall have certain B 108-specified tensile strengths; or 2) that any location in the casting shall have certain B 108-specified tensile strengths. The strengths for case 2) are usually lower than those for case 1). For both cases 1) and 2), the minimum strengths in Table 8.2-1 are the B 108-specified strengths without any factors.

Kaufman’s Fracture Resistance of Aluminum Alloys Figure 5.4 provides notch-strength-to-yield-strength ratios for various sand and permanent mold alloy-tempers. The alloy-tempers in Section 8 have notch-yield ratios > 1.0, so no reduction in tensile fracture strength is required for notch sensitivity for these alloy-tempers and the tension coefficient kt is 1.0.

8.3 Design

The design of castings is the same as the design of wrought products, except that Section 4.8, Fatigue, applies different rules for castings than for wrought products. Castings must be tested to establish their fatigue strength.

8.4 Welding

356.0 is the only cast alloy-temper included in Section 8 with a welded strength given in AWS D1.2:2003 Table 3.2, which gives a value of 23 ksi. This is apparently for a sepa-rately cast coupon rather than a coupon cut from a casting, since the minimum unwelded strength of coupons cut from 356.0-T6 sand castings is 22.5 ksi (see Table 8.2-1). Because of this and since D1.2:2003 provides no welded strengths for the other alloy-tempers in this Specification, welded strengths are not given in Section 8. Instead, they must be established from the weld procedure qualification required by D1.2:2003.

Section 9. Testing



Equation 9.3.1-1 is from the ASTM volume 02.02, Alu-minum and Magnesium Alloys, article “Statistical Aspects of Mechanical Property Assurance” by W.P. Goepfert (70). Values for K are taken from Juran’s Quality Control Hand-book, edited by Juran, J.M., 4th ed., published by McGraw-Hill, and are one-sided factors affording 95% confidence that at least 99% of the population would fall above the pre-dicted minimum value. (See Part V, Section 1.0 for further discussion of the statistical basis for minimum mechanical properties of aluminum alloys).


The ASTM standard test method referenced in this Section is E1592, Structural Performance of Sheet Metal Roof and Siding Systems by Uniform Static Air Pressure Difference.

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48. Kitipornchai, S., Wang, C. M. and Trahair, N. S. in “Buckling of Monosymmetric I-Beams Under Moment Gradient,” Journal of the Structural Division, Vol. 112, No. ST4, April, 1986, ASCE, pp. 781-799.

49. Load and Resistance Factor Design, Specification for Structural Steel Buildings, American Institute of Steel Construction, Second Edition, Chicago, IL, December, 1993.

50. Wang, C. M. and Kitipornchai, S. “Buckling Capacities of Mono Symmetric I-Beams,” Journal of the Structural Division, Vol. 112, No. ST11, November, 1986, ASCE, pp. 2373-2391.

51. Kirby, P. A. and Nethercot, D. A., “Design for Struc-tural Stability,” Constrado Nomographs, A Halstead Press Book, John Wiley & Sons, New York, 1979.

52. Dux, P. F. and Kitipornchai, “Elastic Buckling Strength of Braced Beams,” Journal of the Australian Institute of Steel Construction, May, 1986.

53. Anderson, J. M. and Trahair, N. S., “Stability of Mono-symmetric Beams and Cantilevers,” Journal of the Structural Division, ASCE, January, 1972.

54. Wang, C. M. and Kitipornchai, S., “On the Stability of Monosymmetric Cantilevers,” Eng. Structures, Vol. 8, July, 1986.

55. Haussler, R. W., “Strength of Elastically Stabilized Beams,” Journal of the Structural Division, Proceedings ASCE, Vol. 90, No. ST3, June, 1964, Part 1, p. 219.

56. Haussler, R. W., and Pabers, R. F., “Some Aspects of the Stability of Cold-Formed Shapes,” Preprint MTS-21, ASCE/EIC/RTAC Joint Transportation Engineer-ing Meeting, July 15, 1974.

57. Peköz, T., “Designs of Cold-Formed Steel Screw Connec-tions,” Proceedings of the Tenth International Specialty Conference on Cold-Formed Steel Structures, October 23-24, 1990, University of Missouri-Rolla, MO.

58. European Convention for Constructional Steelwork, Euro-pean Recommendations for the Design of Light Gage Steel Members, First Edition, 1987, Brussels, Belgium.

59. British Standards Institution, British Standard-Structural Use of Steelwork in Building - Part 5. Code of Practice for Design of Cold-Formed Sections, BS 5950: Part 5:1987.

60. Doerr, D. D., “Engineering Design Considerations of Aluminum,” Proceedings of the Aluminum Welding Seminar, The Aluminum Association, February, 1966.

61. Brooks, C. L., “Effect of Weld Heat in Arc Welding Aluminum,” Proceedings of the Aluminum Welding Seminar, The Aluminum Association, February, 1966.

62. Clark, J. W., “Design of Welded Aluminum Structures and Choice of Filler Metal,” Proceedings of the Alu-minum Welding Seminar, The Aluminum Association, February, 1966.

63. Moore, R. L., Jombock, J. R., and Kelsey, R. A., Strength of Welded Joints in Aluminum Alloy 6061-T6 Tubular Members, The Welding Journal, April, 1971.

64. Nelson, F. G. Jr., and Howell, F. M., “The Strength and Ductility of Welds in Aluminum Alloy Plate,” The Welding Journal, September, 1952.

65. Nelson, F. G. Jr., and Rolf, R. L., “Shear Strength of Aluminum Alloy Fillet Welds,” The Welding Journal, February, 1966.

66. Sharp, M. L., Rolf. R. L., Nordmark, G. E., and Clark, J. W., “Tests of Fillet Welds in Aluminum,” The Weld-ing Journal, April, 1982.

67. Hill, H. N., Clark, J. W., and Brungraber, R. J., “Design of Welded Aluminum Structures,” Transactions ASCE, Vol. 127, Part II, p. 102, 1962.

68. Brungraber, R. J., and Clark, J. W., “Strength of Welded Aluminum Columns,” Transactions ASCE, Vol. 127, Part II, p. 202, 1962.

69. Conley, W. F., Becker, L. A., and Allnutt, R. B., “Buck-ling and Ultimate Strength of Plating Loaded in Edge Compression. Progress Report 2: Unstiffened Panels,” Report 1682, David Taylor Model Basin, U. S. Depart-ment of the Navy, Washington, DC, May, 1963.

70. Goepfert, W.P., “Statistical Aspects of Mechanical Prop-erty Assurance”, Aluminum and Magnesium Alloys, ASTM Volume 02.02, 1994.


71. Fuchs, H. O. and Stephens, R. I., Metal Fatigue in Engineering, John Wiley & Sons, New York, 1980.

72. Smith, I. F. C, Castiglioni, C. A. and Keating. P. B., “An Analysis of Fatigue Recommendations Consider-ing New Data”, Proceedings IABSE Meeting, Decem-ber 1988.

73. Kissell, J.R. and Ferry, R.L., “Aluminum Friction Connections”, Proceedings of Structures Congress XV, April, 1997.

74. Atzori, B., Lazzarin, P., and Quaresimin, M., “A Re-Analysis on Fatigue Data of Aluminum Alloy Bolted Joints,” International Journal on Fatigue, Vol. 19, No. 7, 1997.

75. American Architectural Manufacturers Association, AAMA TIR-A9-91 Metal Curtain Wall Fasteners, with 2000 Addendum, Schaumberg, IL, 2001.

76. Menzemer, Craig, “Failure of Bolted Connections in an Aluminum Alloy,” Journal of Materials Engineering and Performance, ASM, Vol. 8, No. 2, April, 1999.

77. Luttrell, C. R., “Thermal Cycling of Slip-Critical Alumi-num Joints”, Proceeding of Structures Congress XVII, American Society of Civil Engineers, Reston, VA, April, 1999.

78. Fortlin, Beaulieu, and Bastien, Experimental Investiga-tion of Aluminum Friction-Type Connections, INALCO 2001, Munich, 2001.

79. Dewalt, W.J. and Mack, R.E., Design Considerations for Aluminum Fasteners, SAE Technical Paper 800455, 1980.

80. Menzemer, C. and Iasconne, R., “Reestablishing the Shear Strength of Aluminum Alloy Fillet Welds”, Weld-ing Journal, April, 2002.

81. Kaufman, J. G., Fracture Resistance of Aluminum Alloys, ASM International, Materials Park, OH, 2001.

82. ASTM International, B 26-99 Standard Specification for Aluminum-Alloy Sand Castings, West Conshohocken, PA, 1999.

83. Kim, Yongwook, Behavior and Design of Aluminum Members in Bending, Cornell University, Ithaca, NY, 2003.

84. Menzemer, C.C, Ortiz-Morgado, R., Iascone, R., and Srivatsan, T., INALCO 2001, Bearing Capacity of Alu-minum Alloys in Bolted Connections, Munich, 2001.


PART II-B

Commentary on Specification for Aluminum Structures

Load and Resistance Factor Design



January 2005 II-B-3

General Introduction

This Commentary is not intended to provide a general primer to probability-based Load and Resistance Factor Design (LRFD) criteria. This is provided in Reference (2) and the further references cited therein. The purpose of this commentary is to give an explanation for the reasons for the recommended resistance factors in Part IB, Load and Resistance Factor Design of Buildings and Similar Type Structures.

Section 2.3 Loads

Factored load combinations for building type structures given in ASCE 7-02 are:

1) 1.4(D + F)2) 1.2(D + F + T) + 1.6(L + H) + 0.5(Lr or S or R)3) 1.2D + 1.6 (Lr or S or R) + (L or 0.8W)4) 1.2D + 1.6W + L + 0.5(Lr or S or R)5) 1.2D + 1.0E + L + 0.2S6) 0.9D + 1.6W + 1.6H 7) 0.9D + 1.0E + 1.6H

Exceptions:1. The load factor on L in combinations (3), (4), and (5)

is permitted to equal 0.5 for all occupancies in which L is less than or equal to 100 psf, with the exception of garages or areas of public assembly.

2. The load factor on H shall be set equal to zero in com-binations (6) and (7) if the structural action due to H

counteracts that due to W or E. Where lateral earth pres-sure provides resistance to structural actions from other forces, it shall not be included in H but shall be included in the design resistance.

where

D = dead load E = earthquake load F = loads due to fluids with well-defined pressures and

maximum heights H = load due to lateral earth pressure, ground water pres-

sure, or pressure of bulk materials L = live load Lr = roof live load R = rain load S = snow load T = self-straining force W = wind load


The general procedure of applying the Load and Resis-tance Factor Design (LRFD) method for aluminum build-ing structures consists of the following steps:

1) Determine the stress due to the factored loads, f, by con-ventional elastic structural analysis. The factored loads are the code-specified dead, live, wind, rain, snow or earthquake loads multiplied by the load factors given in Section 2.3.

2) Compute the factored limit state stress ϕFL from Sec-tion 3.4 and verify that ϕFL ≥ f

Section 3.4 gives the resistance factor ϕ and the limit state stress FL for a variety of commonly encountered alu-minum structural members and elements. The limit state stress FL is dependent on the material properties and the member geometry. It reflects the ultimate load carrying capacity of the member or element, be that yield, fracture, plastification, buckling or crippling. The limit state stresses

in these LRFD criteria are identical to those which are given in the ASD Specification for Aluminum Structures. They can be determined simply by setting the factors of safety equal to unity in the various formulas given in Sec-tion 3.4 of Part IA.

The resistance factor ϕ accounts for the uncertainties of determining the limit state stress. It is computed by the method of first-order second-moment probabilistic analy-sis presented in Reference (2) for a target reliability index of βT = 2.5 for the yield limit state and βT = 3.0 for the frac-ture limit state. Following is a detailed account presenting the background for each of the resistance factors used in Section 3.4 of the LRFD criteria.

Prior to this detailed account it will be instructive to dis-cuss in a simple manner the basic concepts of probabilistic design. Failure is defined when the resistance, as character-ized by a limit state, is less than or equal to the load effect on the structural element. The load effect in these LRFD criteria for aluminum structures is characterized by the

II-B-4 January 2005

stress computed by elastic analysis from the forces acting on the structure. Both the resistance R and the load effect Q are random quantities (Fig.C1).

Limit states are either ultimate or serviceability limit states. These LRFD criteria pertain to the ultimate limit states of yield, fracture, plastification, buckling and crippling, although the serviceability limit states of deflection and the appearance of buckling are also featured (in Section 4).

Failure is then not necessarily the total collapse of the member, but the reaching of a practically defined ulti-mate limit state. It occurs when R < Q. Alternately, failure also is defined as in ln(R/Q) ≤ 0, as shown in Fig.C2. The probability of exceeding a limit state is the shaded area. According to present practice, it is not necessary to define a desired probability of failure, but a “reliability index” β is determined such that the “target reliability index” βT for a new code is approximately equal to the value of β inherent in the traditional specification for standard design situations (2). This process of selecting a target reliability index is called “code calibration.” It will be illustrated for the simple case of tension members.

According to first-order statistical derivations, the value of β from Fig.C2 is expressed by the following formula.

β = ln(

__ R / __

Q ) ________

√_______

V 2 R + V 2 Q (1)

In this equation __

R and __

Q and are the mean values of the resistance R and the load effects Q, respectively, and VR and VQ are the corresponding coefficients of variation.

The resistance of a tension member for the limit state of yielding is

R = A Fty (2)

and thus

__

R = __

A __

F ty (3)

and

VR = √________

V 2 A + V 2 Fty (4)

The available data on dimensions and yield stress of alu-minum structures were evaluated in Reference (3), and the following conservative estimates of the statistical proper-ties were suggested:

__

F ty = 1.10Ftyn, VFty = 0.06, __

A = An, VA = 0.05

where Ftyn is the minimum specified yield stress and An is the handbook area. These are the “nominal” values the designer uses. With these values

__

R = 1.10Rn and VR = √___________

0.055 + 0.062 = 0.08

Rn is the “nominal” resistance, Rn = An Ftyn.

The load effect Q is the tensile force in the member due to the applied loads. For purposes of illustration only dead and live load will be used, i.e.,

Q = D + L (5)

__

Q = __

D + __

L (6)

VQ = √

_____________ (

__ D VD)2 + (

__ L VL)2 ______________

__

D + __

L (7)

The following statistical data about load are taken from Reference (2):

__

D = 1.05Dn, __

L = Ln, VD = 0.1 , VL = 0.25

where Dn and Ln are the “nominal”, code specified, loads.

Figure C-1SCHEMATIC REPRESENTATION OF

PROBABILITIES OF THE LOAD EFFECT AND THE RESISTANCE

Figure C-2DEFINITION OF THE RELIABILITY

INDEX ß

January 2005 II-B-5

Rearrangement of Eqs. 6 and 7 leads to the following equations:

__

Q = Ln (1.05 D/L + 1) (8)

VQ = √

__________________ (1.05 × D/L)2 + 0.252 ___________________

1.05 D/L + 1 (9)

where D/L is the nominal dead-to-live load ratio.The process of calibrating to the ASD Specification is

performed as follows:

An Ftyn/F.S. = Dn + Ln (10)

or

Rn = F.S. (Dn + Ln) = F.S. (Ln)(D/L + 1) (11)

F.S. is the specified factor of safety, which is equal to 1.65 in the ASD Specification for the limit state of yield.

Substitution of F.S. = 1.65 into Eq. 11, and use of Eq. 11 in the relationship

__ R / __

Q gives

__

R __ __

Q =

1.0 × 1.65 (D/L + 1) _________________

1.05 D/L + 1 (12)

__

R / __

Q and VQ (Eq. 9), and thus also β (Eq. 1), depend on the dead-to-live load ratio. Aluminum structures usually have a low dead-to-live load ratio. Following are values of β determined from Eq. 1 for the limit state of yield (F.S. = 1.65) and the limit state of fracture (F.S. = 1.95). For this latter case

__ R = 1.10 Rn and VR = 0.08, as for the limit state

of yield (Reference 3).

D/L ß Yield ß Fracture0.2 2.6 3.40.1 2.5 3.2

A similar exercise can also be performed for the pro-posed LRFD method. According to this approach

ϕ An Ftyn = γD Dn + γL Ln (13)

Again, using Rn = An Ftyn, and γD = 1.2 and γL = 1.6 as recommended in Reference (2),

Rn = Ln __ ϕ (1.2 D/L + 1.6) (14)

from which

__

R / __

Q = 1.10 ____ ϕ [ 1.2 D/L + 1.6 ___________ 1.05 D/L +1

] (15)

The calculations show the following results:

ϕ D/L ß

0.95 0.2 2.5 } limit state yield0.95 0.1 2.50.85 0.2 3.1 } limit state fracture0.85 0.1 2.9

The values of ϕ were rounded off to the nearest 0.05, and comparison of the β’s indicates that for typical dead-to-live load ratios of aluminum structures (i.e., D/L of 0.2 to 0.1) the values of β are near the target of 2.5 for the limit state of yield, and the target of βT = 3.0 for the fracture limit state. This difference reflects the fact of the greater reli-ability demanded for the more serious type of limit state, as already recognized in the ASD Specification with its two kinds of safety factors, i.e., 1.65 and 1.95. These target reliability indices are similar to those used by the AISI for cold-formed steel.

Based on the results presented above ϕ = 0.95 is rec-ommended for the limit state of yield, and ϕ = 0.85 for the limit state of fracture. Methods are available to easily check the consequences of changing ϕ as regards reliabil-ity. The economic consequences can also be ascertained by comparing designs required by the ASD and the LRFD method, as follows:

(Rn)ASD = Ln (D/L + 1)(F.S.) (16)

(Rn)LRFD = Ln (1.2 D/L + 1.6)(1/ϕ) (17)

when (Rn)ASD is the nominal design requirement according to Part I-A, and (Rn)LRFD is the requirement of the LRFD criteria. The ratio LRFD/ASD is then

1.2 D/L + 1.6 _______________ ϕ (F.S.) (D/L + 1) (18)

The curves in Fig. C-3 show the variation of this ratio for various values of ϕ and for F.S. = 1.65 and 1.95 for the range D/L = 0.2 to 0.5. It can be seen that the ratio decreases with an increase of the dead-to-live load ratio.

The following portions of this commentary will give the basic data used to arrive at the recommended ϕ-factors in Section 3.4.


The selection of ϕy = 0.95 and ϕu = 0.85 was discussed in the previous part of this Commentary.

II-B-6 January 2005

3.4.2 through 3.4.4 Tension in Extreme Fibers of Beams

Two limit states apply to the tension flange: limit state of yield when the strain is that corresponding to the yield stress Fty, and limit state of fracture. The resistance is the bending moment M, and its mean value and coefficient of variation is, for the yield limit state,

__

R = __

Sxt _ g ___

Fty (19)

and

VR = √____________

V 2 Sxt + V 2 g +V 2 Fty

(20)

where Sxt is the elastic section modulus on the tension side, g is the “shape factor”, and Fty is the tensile yield stress. The same expressions hold for the limit state of fracture, with the exception that Fty is replaced by Ftu. The shape fac-tor accounts for partial plastification due to the non-linear nature of the stress-strain curves. The nominal resistance is

RN = Sxtn gn Ftyn (21)

and so

__

R = Rn = ( _ S xt ___

Sxtn ) (

_ g __ gn ) (

__ F ty ___

Ftyn ) (22)

Reference (3), as noted before for the tension member, gives the values

_ S xt = Sxt, VSxt = 0.05,

__ F ty = 1.10Ftyn, VFty = 0.06

It will be assumed that gn equals the shape factors in Part I-A, and equals the values given in Reference (4), which were also corroborated for some sections and alloys in Ref-erence (5). It will be assumed that Vg = 0.0. From these data __

R and VR can be determined as

__

R = Rn (1.1 _ g /gn) and VR = √

___________ 0.055 + 0.062 = 0.08

The results of the analysis for the recommended ϕ-factors are given in Table C-3.4.1. The values of β are near the target values.

3.4.5 and 3.4.6 Bearing

In the absence any statistically significant data on bear-ing capacities, it was decided to use ϕu = 0.85, giving essen-tially the same requirements as the ASD Specification.

Figure C-3THE EFFECTS OF CHANGING THE RESISTANCE FACTOR Ф

ON THE REQUIRED AREA FOR TENSION MEMBERS

January 2005 II-B-7


The nominal column strength equations of the ASD Specification were retained, i.e.,

FL = Bc – Dc kL/r ≤ Fcy (23)

for kL/r ≤ S2 = Cc, and

FL = π2 E ______ (kL/r)2 (24)

for kL/r ≥ Cc

It was found convenient in the background research to introduce a non-dimensional slenderness ratio

λ = kL ___ r ( 1 __ π ) √_____

Fcy/E (25)

and the equations actually given in Section 3.4.7 are in terms of λ rather than the effective slenderness ratio. The definitions of Bc, Dc, S2 and Cc remain the same as in Part I-A. The relationship between the nominal limit state stress FL and the factored limit state stress ϕ FL, and the slender-ness parameter λ, is shown in Fig. C-4 for one particular alloy.

The resistance factor ϕcc varies with the slenderness parameter. The particular equation for ϕcc given in Section 3.4.7 is similar to, but not identical to, the resistance factors recommended in References (3) and (5), where consider-able work was done in the development of LRFD provi-sions for columns, and therefore, a detailed accounting is presented on the way ϕcc was selected.

The mean resistance of an ideally pinned-end but ini-tially crooked column was shown to be equal to (3, 5):

__

R = __

A __

σ TM __

B T __

B u (26)

The coefficient of variation is then

VR = √__________________

V 2 A + V 2 σTM + V 2 BT

+ V 2 Bu (27)

The terms in Eq. 26 are defined as follows:

__

A : mean cross-sectional area of column

In accordance with previous usage, __

A = An and VA = 0.05, where An is the nominal area.

σTM : mean buckling stress of an ideally straight column as determined by the tangent modulus theory, i.e.,

σTM = π2 Et ______

(kL/r)2 (28)

In the derivation of References (3) and (5) a Ramberg-Osgood type stress-strain curve was assumed, and thus the tangent modulus Et is equal to

Et = E ____________________ 1 + 0.002n ( E ___ σ0.2

) ( σ ___ σ0.2 ) n-1

(29)

In this equation E is the elastic modulus, σ is the aver-age stress under this buckling load, σ0.2 is the compressive stress when the strain is equal to 0.2 percent, and n is the strain-hardening parameter. The coefficient of variation of σTM, VσTM , was shown to be 0.06 in Reference (5).

Table C-3.4-1DATA FOR TENSION IN EXTREME FIBERS OF BEAMS

Cross Section and Flexure PlaneArticle

in LRFD Criteria

Limit State

gn _ g

(Ref. 5) __

R /Rn ϕß

(D/L = 0.2)

I and C shapes major axis flexure 3.4.2 YieldFracture

1.0 1.0

1.071.16

1.181.28

0.950.85

2.93.7

I shapes minor axis flexure 3.4.4 YieldFracture

1.301.42

1.301.50

1.101.16

0.950.85

2.53.3

Box shapes 3.4.2 YieldFracture

1.0 1.0

1.101.22

1.211.34

0.950.90

3.03.7

Circular tubes 3.4.3 YieldFracture

1.171.24

1.171.35

1.101.20

0.950.85

2.53.4

Solid rectangular bars 3.4.4 YieldFracture

1.301.42

1.301.50

1.101.16

0.950.85

2.53.3

II-B-8 January 2005

gated (Table C-3.4.2). A number of types of relationship for ϕ were tried, and the following expressions were finally selected as being reasonably accurate and yet still fairly simple:

ϕc = 1 - 0.21λ ≤ 0.95 for λ ≤ 1.2

ϕc = 0.58 + 0.14λ ≤ 0.95 for λ > 1.2 } (31)

The resistance factor thus varies linearly as the slenderness parameter λ. The β values resulting from the use of ϕcc (Eq. 31) is the LRFD design criteria are shown as the solid curve in Fig. C-5. The target value of βT = 2.5 is fairly closely approximated.

In Reference (5) considerable work was done on one addi-tional aspect of column design. Real pinned-end columns rarely exist in practice. Even nominally pinned columns have some end restraint, and most columns are actually restrained by the connection to the base or to members framing into their ends. Furthermore, intentionally axially loaded members are also rare, most compression members being actually beam-columns subjected to both compression and bending. It was shown that each of these effects have a conservative influence and thus they tend to increase β. A number of additional cases were studied, showing the same general trend of a somewhat increased value of β due to restraint.

3.4.8 through 3.4.21

The statistical basis for selecting the ϕ values in these Sections is presented in Reference (3). The same values of ϕy were recommended as for tension of the corresponding member types of Sections 3.4.2 through 3.4.4, thus equat-

__

B T : mean value of the ratio of test results of straight columns to the tangent modulus load. Analysis of the avail-able test results in Reference (3) resulted in the following statistics:

__

B T = 1.0 and VBT = 0.05

This means that the tangent modulus theory is indeed a very good predictor for straight columns.

__

B u : mean value of the ratio of the ultimate strength of an initially crooked pinned end column to the strength pre-dicted by the tangent modulus theory for straight columns. It was assumed that the initial crookedness of the column is a sine-wave with a maximum amplitude of one-thousandths of the length. This is in accordance with the procedure recom-mended by the Structural Stability Research Council (Ch. 3, Reference (6)).

The following formulas were derived in Reference (5) for the ratio Bu:

__

B u = 1.0 for λ ≤ 0.263

__

B u = 1.05 - 0.19 λ for 0.263 ≤ λ ≤ 1.20

__

B u = 0.63 + 0.16 for 1.20 ≤ λ ≤ 2.0 (30)

__

B u = 0.95 for λ ≤ 2.0

VBu = 0.10

}A calibration study similar to that presented previously

for tension members was performed, using Eq. 1 to deter-mine β, and employing Eqs. 23 and 24 as the nominal col-umn strength: Four different kinds of alloys were investi-

Figure C-4COLUMN CURVE FOR 6061-T6 ALLOY

January 2005 II-B-9

ing the reliability of short compressed members and ele-ments to that underlying tension elements. The relevant data for choosing the ϕ values, which apply to buckling or crippling type limit states, are summarized in Tables C-3.4-3, C3.4-4, C3.4-5, and C3.4-6. For certain alloys and Specifi-cation Sections, a negative S1 slenderness limit may result from the equations given in Table 3.4-3. In such cases S1 should be taken as 0.

Figure C-5

Table C-3.4-2DATA USED IN COLUMN CALIBRATION STUDIES

Ref. Material Heat Treatment

n σ0.2

ksiE

ksiFcy

ksiVR

***

7 European No 8 22.78 10,180 20.7* 0.14

8 – Yes 18.55 40.15 10,100 36.5* 0.14

7 European Yes 28.60 43.99 10,790 40.0* 0.14

9 6061-T6 Yes 15.5 40.8 10,100 35** 0.14

* Fcy = σ0.2/1.1, assuming σ0.2 to be the mean yield stress

** Specified value

*** VR = √_______________________

0.052 + 0.062 + 0.052 + 0.102 = ___________________

√__________________

V 2 A + V 2 σTM + V 2 BT

+ V 2 Bu

II-B-10 January 2005

Table C-3.4-3SUMMARY OF STATISTICAL DATA

Sec. inRef. 1

Limit State

F.S. Pm Mm Fm Rm ___ Rn

VP VM VF VR Category

3.4.1, 2, 3, 4

YU

ny

kt nu

1.01.0

1.101.10

1.01.0

1.101.10

00

0.060.06

0.050.05

0.080.08

AB

3.4.8, 9 YB

ny

nu

1.01.0

1.101.0

1.01.0

1.101.0

00.05

0.060.06

0.050.05

0.080.09

CD

3.4.10 YIBEB

ny

nu

nu

1.01.01.24

1.101.01.0

1.01.01.0

1.101.01.24

00.050.27

0.060.060.06

0.050.050.05

0.080.090.28

CDE

3.4.11, 13, 14

YB

ny

ny

1.01.03

1.101.0

1.01.0

1.101.03

00.11

0.060.06

0.050.05

0.080.13

AF

3.4.12, 16.1

YIBEB

ny

ny

ny

1.01.011.24

1.101.01.0

1.01.01.0

1.101.011.24

00.050.27

0.060.060.06

0.050.050.05

0.080.090.28

AGH

3.4.15, 16, 17

YB

ny

ny

1.01.0

1.101.0

1.01.0

1.101.0

00.05

0.060.06

0.050.05

0.080.09

AI

3.4.20 YIBEB

ny

ny

ny

1.01.070.93

1.101.01.0

1.01.01.0

1.101.070.93

00.090.09

0.060.060.06

0.050.050.05

0.080.120.12

AJK

Table C-3.4-4LIMIT STATE CATEGORIES

Category FS __

R /Rn VR Description

A 1.65 1.10 0.08 yield in tension

B 1.95 1.10 0.08 fracture in tension

C 1.65 1.10 0.08 yield in compression

D 1.95 1.00 0.09 buckling of column componentsinelastic column buckling

E 1.95 1.24 0.28 elastic column buckling

F 1.65 1.03 0.13 beam buckling, overall

G 1.65 1.01 0.09 inelastic local buckling

H 1.65 1.24 0.28 elastic local buckling

I 1.65 1.00 0.09 local buckling of beams

J 1.65 1.07 0.12 inelastic shear buckling

K 1.65 0.93 0.12 elastic shear buckling

Table C-3.4-5RELIABILITY INDICES FOR ASD

SPECIFICATION

Categoryβ

for D/L = 0.1β

for D/L = 0.2

A 2.46 2.64

B 3.16 3.40

C 2.87 3.09

D 2.72 2.92

E 2.44 2.51

F 2.01 2.13

G 2.08 2.22

H 1.98 2.03

I 2.04 2.18

J 2.20 2.34

K 1.65 1.75

January 2005 II-B-11

Table C-3.4-6RESISTANCE FACTORS FOR LRFD SPECIFICATION

Category Target β ϕ for D/L = 0.1

ϕ for D/L = 0.2

ϕ Rounded off

A 2.5 0.94 0.96 0.95

B 3.0 0.83 0.86 0.85

C 2.5 0.94 0.96 0.95

D 2.5 0.85 0.86 0.85

E 2.5 0.78 0.79 0.80

F 2.5 0.83 0.85 0.85

G 2.5 0.85 0.87 0.85

H 2.5 0.78 0.79 0.80

I 2.5 0.85 0.86 0.85

J 2.5 0.88 0.89 0.90

K 2.5 0.76 0.78 0.80

recommended for use in LRFD Spec.

II-B-12 January 2005


The value of ϕ = 0.65 for shear stress on rivets and bolts was determined by the following derivation. It was assumed that the “typical” shear strength values for rivets given in Reference (10) represent mean values. The ratio of the mean to the “minimum expected” values was found to be 1.15. A coefficient of variation of 0.1 was assumed. It was also assumed that the nominal rivet area is equal to the mean, with a coefficient of variation of 0.1. The mean shear capacity of a rivet is thus

__

R = __

A __

F su = 1.0 × 1.15 An Fsun (32)

and

VR = √________

V 2 A + V 2 Fsu = √

_________ 0.12 + 0.12 = 0.14 (33)

With these statistics a calibration was performed using Eq. 1, and for a D/L = 0.2 it was found that ASD design gave β = 3.9. The LRFD design with ϕ = 0.65 gave β = 4.0.


The design shear stress for fillet welds is based on ϕ = 0.80. This value was determined so that an ASD-sized weld would be approximately the same size as an LRFD-sized weld:

The mean shear strength of a fillet weld is equal to

__

R = _ τ u

__ A (34)

where _ τ u is the mean shear strength and

__ A is the weld throat

area. From Reference (11):

Table C-7.1FILLET WELD STRENGTHS

Filler Alloy __

V su /Fw Vsu Orientation of Weld

1100 1.62 0.18 longitudinal

1100 1.78 0.23 transverse

4043 1.45 0.17 longitudinal

Assuming the coefficient of variation Vsu = 0.2 (com-pared to 0.18, 0.23, and 0.17 in Table C-7.1) and the mean resistance

__ R = 1.5 Rn (compared to 1.62, 1.78, 1.45 in Table

C-7.1), and the mean weld area equals the nominal area with VA = 0.1, the safety index β ranged from 3.9 to 4.4 for D/L ranging from 0.1 to 0.5 for a safety factor of 2.34. With the change in safety factor from 2.34 to 1.95 on fillet welds, the safety index β ranges from 3.3 to 3.7. Because weld quality is considered to have improved since 1966, the safety index now is probably higher, but data has not been collected recently.

Table C-7.2RATIO OF FILLET WELD AREAS REQUIRED BY LRFD TO THAT

REQUIRED BY THE ALLOWABLE STRESS SPECIFICATION

LRFD/ASD for ϕ = 0.80 and SF = 1.95 for

D/L = 0.1 D/L = 0.25 D/L = 0.5

1.00 0.97 0.94

Section 9. Testing

The test criteria are very similar to those in the ASD Specification, except they provide guidance in determining

a resistance factor (as opposed to a safety factor) on the basis of tests (Section 9.3.2).

January 2005 II-B-13

References

1. Aluminum Association, Specifications for Aluminum Structures, Fifth Ed., December, 1986.

2. B. Ellingwood, T.V. Galambos, J.G. MacGregor, C.A. Cornell “Development of a Probability Based Load Crite-rion for American National Standard A58-Building Code Requirements for Minimum Design Loads in Buildings and Other Structures” National Bureau of Standards, Spe-cial Publication 577, June 1980.

3. T.V. Galambos, “Load and Resistance Factor Design for Aluminum Structures” Research Report No. 54, Civil Engineering Department, Washington University, St. Louis, Mo.

4. J.W. Clark, “Design of Aluminum Structural Mem-bers”, Ch. 10 in Structural Engineering Handbook, ed. E.H. Gaylord and C.N. Gaylord, McGraw-Hill Book Co., New York, 1979.

5. J.C. Chapuis and T.V. Galambos, “Design Criteria for Aluminum Columns and Beam-Columns” Research Report No. 58, Civil Engineering Department, Wash-ington University, St. Louis, Mo.

6. B.G. Johnston, Editor, Guide to Stability Design Cri-teria for Metal Structures, Third Ed., John Wiley and Sons, Inc., New York, 1976.

7. A. Bernard, F. Frey, J. Janss, C. Massonnet, “Research on the Behavior and Buckling of Aluminum Bars” (in French), LABSE Publications, Vol. 33-I, 1973.

8. R.H. Batterman, G.G. Johnston, “Behavior and Maxi-mum Strength of Metal Columns” Journal of the Struc-tural Division, ASCE, Vol. 93, ST2, April 1967.

9. J.W. Clark, “Statistical Aspects of Strength of Alumi-num”, ALCOA Report No. 76-74-10, June 20, 1974.

10. ASCE Task Committee on Lightweight Alloys, “Sug-gested Specifications for Structures of Aluminum Alloys 6061-T6 and 6062-T6” Journal of the Structural Division, ASCE, Vol. 88, ST6, Dec. 1962.

11. F.G. Nelson, R.L. Rolf, “Shear Strengths of Aluminum Alloy Fillet Welds” Welding Journal Research Supple-ment, Feb. 1966.


PART III

Design Guide



January 2005 III-3

IIIDesign Guide

TABLE OF CONTENTS

1.0 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5

2.0 Design of Aluminum Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .62.1 Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62.2 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

2.2.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.2 Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.3 Alloys and Products . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.4 Aerospace . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.5 Automotive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.6 Bridges and Highway Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.7 Railroad Cars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.8 Ships . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.9 Storage Tanks, Pressure Vessels, and Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72.2.10 Material Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82.2.11 Other Codes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

3.0 Member and Component Behavior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93.1 Tension Members . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103.2 Tension Flange of Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103.3 Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113.4 Compression in Columns . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 123.5 Compression in Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 133.6 Compression in Flat Elements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3.6.1 Elements with Constant Thickness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 143.6.2 Elements with Non-Uniform Thickness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3.7 Compression in Tubes and Curved Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 163.8 Shear in Flat Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3.8.1 Buckling of Stiffened and Unstiffened Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 173.8.2 Tension Field Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 173.8.3 Corrugated Webs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3.9 Shear in Tubes and Curved Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183.10 Combined Stresses/Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183.11 Stiffeners for Flat Plates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183.12 Pipe Bursting Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 193.13 Biaxial and Triaxial Stresses . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4.0 Fatigue . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .21

5.0 Joints and Joining . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .235.1 Mechanical Joints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 235.2 Welded Joints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

5.2.1 Welding Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 245.2.2 Design of Welded Joints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

5.3 Adhesive Bonded Joints . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.3.1 Advantages and Disadvantages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 265.3.2 Adhesive Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.3.3 Types of Adhesives . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.3.4 Aluminum Surface Pretreatments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.3.5 Joint Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 285.3.6 Current Adhesive Applications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

III-4 January 2005

6.0 Sandwich Panels and Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .30

7.0 Extrusion Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.1 Replacement of Fabrications with Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 317.2 Design Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 337.3 Design Guidelines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 387.4 Design for Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

8.0 Prevention of Corrosion . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

9.0 Fire Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .44

10.0 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .45

January 2005 III-5

1.0 Introduction

This part of the design handbook provides general, non-mandatory information that may be of interest to a designer of aluminum products of any type. Included are references to the strength formulas given in Part IA, Allowable Stress Design Specification (Part IB, LRFD Specification, has sim-ilar equations). These formulas are applicable to the design of all types of products; such as building, bridges, ships, railroad cars, automobiles, trucks, highway structures and machinery. For example, the formulas for a column given in the Specification apply equally well to a column for a patio roof, a member in a latticed roof, a strut in a rail car or automobile, a member in a bridge truss, and a stanchion/ pillar in a ship. When formulas exist in the Specification and are discussed in this part, they are referenced by num-ber (italicized) and thus are not duplicated.

The designer can determine the strength of the part from the formulas given in the Specification by setting the fac-tors of safety on appearance, yielding and ultimate strength equal to 1.0. The designer can also incorporate other fac-tors of safety into the formulas for the product commensu-rate with the uncertainties of the load and member strength and with the importance of the structure, and the safety of the user of the structure. Of course the margins of safety for buildings and bridges are specified in the requirements of Part IA and IB.

Also covered in this part are topics that are not currently in the Specification but are believed to be of interest to the designer. Commentary of the Specification, past handbooks from the aluminum producers and published and unpub-lished reports are the major resources of this material.

III-6 January 2005

2.0 Design of Aluminum Structures

The various parts of this handbook provide most of the information that designers need to properly design alumi-num structures. Part IV Materials, provides general infor-mation about aluminum and alloys, the alloy and temper designation system, and comparative characteristics and applications. Part V Material Properties, gives mechanical and physical properties of alloys. Part VI Section Proper-ties, has tables of section properties of many shapes and general equations for the calculation of various section properties, including torsional and warping values. Part VII Design Aids, has charts and tables containing allow-able stresses for various alloys and beam formulas. Part VIII Illustrative Examples of Design, provides detailed calculations for the design of many specific components and the location of necessary information provided in the parts of this manual. Some additional general guidance for design is provided in this section along with references to other technical literature that provide additional resource material.

2.1 Considerations

Part IV discusses attributes of aluminum that allow it to be used as a cost effective material in structures. Most of the applications make use of a favorable life cycle cost; the combined costs of the material and its fabrication into the finished product, erection or installation of the product, operation and maintenance, and disposal or reuse of the material after its useful life in the product. For example, aluminum is the principal material in aerospace structures, primarily because of its high strength to weight ratio. The density of aluminum is about ⅓ that of steel and alumi-num alloys have strengths similar to those of constructional steels. The aerospace structures are cost effective because smaller engines and less fuel are needed during service compared to those that would be required for heavier struc-tures. The excellent corrosion resistance of aluminum (see Section 8.0) also is a factor in minimizing maintenance costs. Weights of aluminum structures generally are ⅓ to ½ those of steel (see Section 3.0). Light weight and cor-rosion resistance are also the major factors for the selec-tion of aluminum for trucks, automobiles and railroad cars. Low maintenance and fuel savings are the important issues. Aluminum’s corrosion resistance in the environment and its appearance, bare or finished, are the major factors in its use in commercial and residential buildings. Many alumi-num structures, such as light poles, overhead sign trusses, latticed roofs, bridges and bridge decks are not painted because of the good corrosion resistance of aluminum. Appearance and light weight are also important in truck and automo-bile wheels.

Sheet, plate, extrusions, forgings and castings are made of aluminum. Alloys and tempers that possess both good

strength and corrosion resistance are available for use in most structures. Aerospace alloys are generally not used for other types of structures because their cost is higher and their corrosion resistance is lower than those of the moderate strength alloys. Examples of the common alloys and tempers used for each product form are given in the following table. A more complete list of commonly used alloys and their properties and applications are given in Parts IA, IV and V.

Product form Application Alloys

Sheet and Plate Building

Heavy Duty Structures

3105-H25, 5052-H34, 3004-H165083-H116, 5086-H116, 5456-H116, 6061-T6

Extrusions BuildingGeneral Purpose

6063-T66061-T6

Forgings Wheels 6061-T6

Castings General PurposeHigh Elongation

356.0-T6A444.0-T4

The extrusion process is unique to aluminum (compared to steel), and allows the designer to place the material where it is most effective. Section 7.0 provides details on extrusion design. The extrusion process consists of pushing hot aluminum through a die, likened to pushing tooth paste out of the tube. Cross sections generally must stay constant along the length but they can have detailed cross sections. Often fabrication costs can be lowered by consolidation of parts or the incorporation of aids for assembly by the use of extrusions. Extrusions up to about 30 in. are possible, but the more common ones fit within a circle size of 15 in.

All the common joining methods may be used for attachment of assemblies of aluminum structures; welding, mechanical fastening, adhesive bonding, and a combina-tion of adhesive bonding and one of the other joining meth-ods (see Section 5.0). Welding is done in the shop or in an enclosure because the shielding gas must cover the arc and wind can remove the shield.

Although aluminum has excellent corrosion resistance (see Section 8.0) protection is needed when it is attached to steel, or it is joined by steel bolts, to prevent galvanic action. Painting the parts and galvanizing the bolts is a minimum treatment. Sometimes it is desired to protect an aluminum part from pitting or further oxidation. Clear and decorative finishes can be applied to these cases.

2.2 References

The following references are additional sources of infor-mation on aluminum structural design. References marked * are available from the Aluminum Association (www. aluminum.org)

January 2005 III-7

2.2.1 General

1. Sharp, Maurice L., Behavior and Design of Alumi-num Structures, McGraw-Hill, Inc., New York, NY, 1993.

*2. Kissell, J. Randolph, and Ferry, Robert L., Alumi-num Structures, 2nd ed., John Wiley & Sons, New York, NY, 2002.

3. Sharp, M.L., Nordmark, G.E., and Menzemer, C.C., Fatigue Design of Aluminum Components and Struc-tures, McGraw-Hill, Inc., New York, NY, 1996.

2.2.2 Fabrication

*1. Forming and Machining Aluminum, Aluminum Association, Washington, DC, 1988.

*2. AWS D1.2/D1.2M:2003 Structural Welding Code-Aluminum, American Welding Society, Miami, FL, 2003.

*3. Welding Aluminum: Theory and Practice, 4th ed., Aluminum Association, Washington, DC, 2002.

*4. Minford, J. Dean, Handbook of Aluminum Bonding Technology and Data, Marcel Dekker, Inc., New York, NY, 1993.

2.2.3 Alloys and Products

*1. Aluminum Standards and Data, 2003, Aluminum Association, Washington, DC, 2003.

*2. Aluminum Standards and Data Metric SI 2003, Aluminum Association, Washington, DC, 2003.

*3. Standards for Aluminum Sand and Permanent Mold Castings, Aluminum Association, Washington, DC, 14th ed., 2000.

*4. AWS A5.10/A5.10M: 1999 Specification for Bare Aluminum and Aluminum-Alloy Welding Electrodes and Rods, American Welding Society, Miami, FL, 2000.

2.2.4 Aerospace

1. DOT/FAA/AR-MMPDS-01, Metallic Materi-als Properties Development and Standardization (MMPDS), (formerly MIL Handbook 5) Chapter 3, January, 2003, U.S. Department of Transportation, Federal Aviation Administration, Washington, DC. Copies available through the National Technical Information Service (NTIS), 5285 Port Royal Road, Springfield, VA 22161-0001; www.ntis.gov or down-loadable from http://www.tc.faa.gov/its/worldpac/ techrpt/armmpds-01.pdf

2.2.5 Automotive

*1. AT3 Aluminum for Automotive Body Sheet Panels, Aluminum Association, Washington, DC, 1996.

*2. AT5 Automotive Aluminum Crash Energy Manage-ment Manual, Aluminum Association, Washington, DC, 1998.

*3. AT6 Aluminum Automotive Extrusion Manual, Aluminum Association, Washington, DC, 1998.

*4. A Guide to Practices for the Repair of Automotive Sheet Aluminum, Aluminum Association, Washing-ton, DC, 1998.

2.2.6 Bridge and Highway Structures

1. AASHTO LRFD Bridge Design Specifications, 2nd ed., American Association of State Highway and Transportation Officials, Washington, DC, 1998.

2. Guide Specifications for Aluminum Highway Bridges, American Association of State Highway and Transpor-tation Officials, Washington, DC, 1991.

3. Standard Specifications for Structural Supports for Highway Signs, Luminaires and Traffic Signals, 4th ed., American Association of State Highway and Transportation Officials, Washington, DC, 2001.

2.2.7 Railroad Cars

1. Manual of Standards and Recommended Practices Section C, Part II, Design, Fabrication, and Con-struction of Freight Cars, Association of Ameri-can Railroads, Transportation Technology Center, Pueblo, CO.

2. AWS D15.1:2001 Railroad Welding Specification– Cars and Locomotives, American Welding Society, Miami, FL, 2001.

2.2.8 Ships

*1. ANSI/AWS D3.7:2004 Guide for Aluminum Hull Welding, American Welding Society, Inc., Miami, FL, 2004.

2. Rules for Building and Classing Aluminum Vessels, American Bureau of Shipping, Houston, TX, 1996.

2.2.9 Storage Tanks, Pressure Vessels, and Pipe

1. ASME B31.3:2002 Edition, Process Piping, Ameri-can Society of Mechanical Engineers, New York, NY, 2002.

2. ASME Boiler and Pressure Vessel Code, Section II, Materials, American Society of Mechanical Engi-neers, New York, NY, 2004.

3. ASME B96.1-1999, Welded Aluminum-Alloy Stor-age Tanks, American Society of Mechanical Engi-neers, New York, NY, 2000.

4. API Standard 620, Design and Construction of Large, Welded, Low-Pressure Storage Tanks, 10th ed., Amer-ican Petroleum Institute, Washington, DC, 2002.

5. API Standard 650, Welded Steel Tanks for Oil Stor-age, 10th ed., American Petroleum Institute, Wash-ington, DC, 1998.

*6. Aluminum Alloys for Cryogenic Applications, Aluminum Association, Washington, DC, 1999.

III-8 January 2005

2.2.10 Material Properties

*1. Kaufman, J. Gilbert, Fracture Resistance of Alumi-num Alloys: Notch Toughness, Tear Resistance, and Fracture Toughness, ASM International, Materials Park, OH, 2001.

*2. Kaufman, J. Gilbert, Properties of Aluminum Alloys: Tensile, Creep, and Fatigue Data at High and Low Temperatures, ASM International, Materials Park, OH, 1999.

2.2.11 Other Codes

1. Structural Use of Aluminium. Code of Practice for Design, British Standard BS 8118-1, 1991.

2. ENV 1999 Eurocode 9 Design of Aluminium Struc-tures, European Committee for Standardization (CEN), Brussels, 1998.

3. CSA S157 Strength Design in Aluminum, Canadian Standards Association, Rexdale, Ontario, Canada, 1983.

January 2005 III-9

3.0 Member and Component Behavior

The structural design of aluminum components and structures is very similar to that for steel and other metal structures. The primary difference is that properties of the various alloys, some of which are different from those of steel, are incorporated into the equations defining struc-tural behavior. Because many engineers are trained in steel technology to a larger extent than aluminum technology, similarities and differences between aluminum and steel are summarized in Table 3.0-1(1).

Because of the difference in properties (modulus for example) an aluminum design should be different than that for steel in order to use the material effectively. An example is illustrated in Figure 3.0-1; the relative weights of box beams of aluminum and steel with the same bend-ing strength and deflection. The yield strength of the two materials is the same. The weight of the aluminum part is about 50% that of the steel part when its size is about 1.4 times that of steel. Other configurations generally will provide weight savings but less than the optimum. Weights of aluminum structures of 50% that of steel structures have been achieved for bridge girders, automotive frames and other transportation vehicles, in which deflection and fatigue are controlling. For structures controlled by static strength, such as automobile hoods and decklids, and some building panels, weights of aluminum structures of about ⅓ that of steel have been achieved. In all these cases the

structures are designed for aluminum, not converted from an existing steel design.

The availability of economical aluminum extrusions allows the designer to consolidate parts normally made by fabrication, thereby saving on joining costs. Also the designer can place the material in the section to optimize the section property governing the design. Various quick attachment schemes can be employed. Section 7.0 gives more details on extrusion design.

The inherent corrosion resistance of aluminum offers positive potential for long life structures that require a minimum of maintenance. Many aluminum structures, e.g., light poles, have performed satisfactorily for decades without painting. Life cycle considerations should be used when comparing the merits of aluminum structures with those of other materials, particularly when the other struc-tures need periodic painting and other maintenance. Life cycle should include the costs of the as-fabricated structure, erection/installation, operation/maintenance and disposal/ recycling. Information on corrosion resistance is given in Section 8.0.

The following subsections provide more detailed design information for the components and members covered in the Specification. As noted previously other information has been included when available.

Table 3.0-1DIFFERENCES—ALUMINUM AND STEEL (1)

Property Steel Aluminum Importance forDesign

Modulus of elasticity 29 × 103 ksi 10.1 × 103 ksi Deflection of members VibrationBuckling

Weight per volume 0.284 lb/in3 0.10 lb/in3 Weight of Product, Vibration

Thermal expansion 7 × 10-6 in/in/oF 13 × 10-6 /in/in/oF Thermal expansionThermal stress

Stress-strain curves Varies Varies Depends on alloysSteel often has higherstrength and elongation at room temperatureAluminum has betterperformance at lowtemperatures

Fatigue Varies Varies For joints, aluminum has about 1/3 to ½ fatigue strength as steel for same detail

Corrosion resistance Needs protection Often used unpainted Aluminum usually ismaintenance freeAluminum is nonstaining

Strain rate effects—mechanical properties

High strain rates increase properties—varies with type of steel

Much less change inproperties compared to steel

Need to use dynamicproperties for high-strain rate loadings

III-10 January 2005

3.1 Tension Members

The accepted measure of ductility of aluminum alloys is fracture toughness and many of the high strength alloys used for aerospace applications have been evaluated (2). The alloys considered in the Specification (non-aerospace applications) are too ductile to be evaluated by fracture mechanics methods. Thus, “ductility” generally is not a design issue for wrought products. The best proof of ade-quate ductility of alloys is the satisfactory service in build-ings, bridges, automobiles, trucks, railroad cars etc. Labo-ratory fracture tests show that the normalized resistance curves (same fatigue strength) of parts made from one of the alloys, 5456-H116 were higher than those of A36 steel, at temperatures from –200 to +75 oF(3). Additional infor-mation on ductility/toughness of aluminum alloys has been published (1).

Some practical members, such as angles attached by one leg, have not only the stress concentration at the bolt, but also the non-uniform stresses across the cross section from the eccentricity of the load. This effect is accounted for by the use of the net effective area of the cross section, where the area on which the tensile stress is calculated is reduced below the net area.

The ultimate or yield strength of tensile members with elements of different strength may be estimated by the use of the weighted average method. In this case the weighted average strength is the sum of the quantities, each element area times the element strength, divided by the total area.

Some increase in strength of welded parts can be achieved by either welding in the –T4 temper and aging,

or by resolution heat treating and aging after welding. The light pole manufacturers, for example, have justified improved as-welded strength as a result of post weld treat-ment. Usually ductility of transversely welded structures is reduced by post weld thermal treatment because the width of the zone of lower strength material is decreased (plas-tic deformation may be confined to a narrow zone). Post weld processes usually are not employed without careful evaluation of strength, ductility and corrosion resistance implications.

3.2 Tension Flange of Beams

The strengths of beams of round or oval tubes (Part IA, Equations 3.4.3-1,2) and of shapes bent about the weak axis, rectangular bars, solid round bars and plates (Part IA, Equa-tions 3.4.4-1,2) are higher than those calculated assuming failure when yield or tensile strengths are calculated at the extreme fiber. Figure 3.2.-1 shows the stress-strain behavior of axially loaded and bending members of the same alloy. The beams exhibit higher strength compared with that for the axially loaded members. The ratio of the beam yield or ultimate to that for the tensile properties is referred to as the shape factor, and is dependent upon the cross sectional shape, the alloy, temper and the failure condition; yield or ultimate. Values used in the Specification are summarized in Table 3.2-1. The values for shape factors for aluminum are less than the rigid plastic cases commonly used for mild steel, because of the rounded stress-strain curves for alumi-num alloys. The effect of alloy on shape factor is not very large, so only one set of values is given for each shape. The

Figure 3.0-1MINIMUM WEIGHT OF SQUARE TUBULAR SECTIONS

January 2005 III-11

yield or tensile strength of the alloy is multiplied by the shape factor to define the higher strength values for beam behavior. Shape factors for other shapes, and methods to estimate these factors from rigid plastic cases are available (1, p. 96).

The use of shape factors greater than 1.0 may be uncon-servative at locations of transverse welds in some beams because of the limited deformation capacity across the weld (1, p. 97). Tests may be required to establish beam strength in this case. A shape factor of 1.0 is always con-servative and may be used.

The ultimate or yield strength of the beam flange can be estimated by the use of the weighted average method as described in Section 3.1. The strength of flanges with welds also are calculated using the same equations as defined for tension members. The flange area includes a portion of the web as defined previously.

3.3 Bearing

The bearing strength for the part when using rivets or bolts is given by Equation 3.4.5-1 of Part IA. The strengths are for the sheet or plate being joined and apply for edge distances (center of hole to edge of part in the direction of the applied load) equal to 2.0 times the fastener diameter or more. For edge distances less than 2.0 times the fastener diameter, the bearing strength is reduced by the ratio of edge distance divided by twice the fastener diameter. These bearing strengths apply when pressure is toward the edge of the part. Figure 3.3-1 shows that the bearing strength when pressure is parallel to the edge of part is higher than that when the load is toward the edge (1). In this figure the bearing strength has been divided by the tensile strength of the material. The joints covered are those in which

Figure 3.2-1STRESS-STRAIN CURVES FOR AXIAL AND BEAM MEMBERS

Table 3.2-1SHAPE FACTORS FOR

ALUMINUM BEAMS USED IN THE AA SPECIFICATION

Shape Factor on Yield

Factor on Ultimate

1.0 1.0

1.17 1.24

1.30 1.42

Figure 3.3-1BEARING STRENGTHS

III-12 January 2005

there is a proper fit between fastener and hole; the rivet fills the hole and the hole for the bolt is no more than ⅟₁ ₆ in. oversized.

3.4 Compression in Columns

The strength of columns under flexural buckling is given by Equations 3.4.7-1,2,3 of Part IA. The strength of columns under flexural-torsional buckling is determined using these same formulas and the equivalent slenderness ratio given by Equation 3.4.7.2-1. The effective length fac-tor suggested in the Specification is 1.0 for members sup-ported at both ends and 2.0 for cantilevers. However, the designer can input other values appropriate for the struc-ture. Conservative values of the slenderness ratio should be chosen, because they compensate somewhat for the reduc-tion of strength due to crookedness that is not included in the column formulas. Some values of effective length are provided in Figure 3.4-1(1), with some guidance for “prac-tical columns”.

In the case of torsional buckling, “design” values are not shown in Figure 3.4-1 because of lack of informa-tion. However, based on laboratory test results shown in

Figure 3.4-2, it is likely that the theoretical values of k for pinned ends (k = 1.0) should be used for flexural-torsional buckling.

More information on effective length of columns is available in the literature (4). Columns are usually parts of a structure. Thus in determining an effective length, the entire structure needs to be considered. The characteristics of the joints and the resistance of the structure to rotation and translation of the ends of the column have a large effect on column strength.

The equation for flexural-torsional buckling of un-symmetrical shapes is not covered in the Specification but is available elsewhere (1, p. 84). The equivalent slender-ness ratio may be solved by trial, and is always larger than those for torsional buckling and flexural buckling about the x and y axes.

Welding decreases column strength for most alloys and tempers. For columns with only longitudinal welds, the strength is reasonably given by the same equation provided for tension members (7.3-1). The column strengths calcu-lated assuming all parent and all reduced strength mate-rial are used in this equation. The column strengths for the reduced strength material are best estimated using

Figure 3.4-1EFFECTIVE LENGTH FACTORS FOR CENTRALLY LOADED COLUMNS (1)

January 2005 III-13

buckling constants from Table 3.3-3. This procedure apparently is sufficient to cover effects of both the reduced strength material and the residual stresses due to welding.

The strength of columns with transverse welds depends on the location and number of welds. If the welds are at the ends only, the column is designed as a pinned-end column with a limiting stress equal to the compressive yield strength of welded construction provided in Table 3.3-2. Transverse welds away from the ends of the column reduce the strength below that for welds at the ends only. In this case the col-umn should be designed as though the entire column has a compressive strength as given in Table 3.3-2. Figure 3.4-3 shows the strength (factor of safety = 1.0) of 6061-T6 and 5083-H116 transversely welded and unwelded columns. If the column has both longitudinal and transverse welds, the provisions for transverse welds generally govern.

3.5 Compression in Beams

Strength equations for lateral buckling are available for three general types of cross sectional shapes as summarized in Table 3.5-1. The designer has the option of using more accurate but more complicated equations than the basic equations. The basic equations are very conservative. In order to get efficient designs the “more accurate equations” (column b) or “most accurate equations” (column c) should be used. Figure 3.5-1 compares the calculated equivalent slenderness ratios of 17 American Standard I-beams, to the basic (column a) and the more accurate equations (column b). The basic equations are overly conservative for moder-ate and high slenderness ratios and for all of the sections, in many cases by a factor of two or more. Comparisons of test data and calculations using the equations given in column b show that this method is conservative (1).

In the inelastic region of the buckling curves, single web and rectangular tube beams are assumed to have a shape fac-tor of 1.0. The inelastic buckling curve is the same as that used for columns. The inelastic curve for lateral buckling of solid rectangular shapes, however, is much higher (see

Figure 3.4-2FLEXURAL TORSIONAL BUCKLING (1)

Figure 3.4-3EFFECT OF TRANSVERSE WELD

Table 3.5-1COMPRESSIVE STRENGTH OF

BEAMS IN BENDING

III-14 January 2005

Figure 3.5-2) reflecting the shape factor of 1.3 on yield strength used for these sections. Most sections have a shape factor greater than 1.0 and the strength would lie somewhere between the solid lines in Figure 3.5.2; there currently have been no engineering methods proposed to calculate the inelastic buckling curves for these intermediate values.

For welded beams, the compressive strength may be calculated using the same principles employed for column design. The flange is defined similarly to that for tension members; that portion of the member further than 2c/3 from the neutral axis, where c is the distance from the neu-tral axis of the beam to the extreme fiber in compression. The principles are the following.

1. For members with longitudinal welds, the strength is calculated by the addition of the strength for the parts of the section with parent material and those with reduced strength material.

2. For members with transverse welds at the points of lateral support, assume that the member is simply sup-ported about the axis normal to the axis of bending, and limit the bending stress to the strength of the material across a butt weld.

3. For members with transverse welds interior to the points of lateral support, calculate the strength as though the entire member had the strength corresponding to that across a butt weld.

If there are loads on the beams that do not pass through the shear center torsional moments are generated. The stresses and deformation due to the torsion must be considered. Cal-culation procedures are given in Reference 5.

3.6 Compression in Flat Elements

3.6.1 Elements with Constant Thickness

Five types of elements and loading have been defined for aluminum structures as shown in Table 3.6-1. Also shown are the equivalent slenderness ratios for each case and the strength equations. The basic strength equations (factor of safety = 1.0) for Cases 1 and 2 are the same for columns and beams, but the applied factors of safety in the Specification are different. Cases 3, 4 and 5 apply to webs of beams only. The equivalent slenderness values are the parameters introduced in the general strength equation, both for buckling and ultimate strength of the element.

Figure 3.6-1 shows an example (6061-T6) of the various inelastic, straight-line equations used for aluminum ele-ments and members. Columns, single web beams and rect-angular tubes are represented by the lower curve, which is an approximation to the tangent modulus curve. Plates in

Figure 3.5-1EQUIVALENT SLENDERNESS RATIOS

FOR LATERAL BUCKLING

Figure 3.5-2LATERAL BUCKLING OF BEAMS

January 2005 III-15

uniform compression best fit a straight line that is interme-diate to a tangent modulus and a secant modulus curve, but higher than that for columns. Plates under bending employ the same curve as that utilized for lateral buckling of solid rectangular beams, and the straight line is much higher than the other two cases, primarily because of the effect of shape factor.

Post buckling strength is allowed for all cases except Case 3 (Table 3.6-1), where the strength is limited to the buckling value. Figure 3.6-2 shows an example of buck-ling and post buckling strength (ultimate strength). If the design of a beam is based on stresses above the buckling value, the use of full section properties in beam formulas will underestimate deflections. The calculation of section properties for the buckled shape using an effective width of elements as given by Equations 4.7.6-1,2, and beam equations, will provide a good estimate of deflections. The strength of a section is obtained by the weighted average concept; the addition of the strength contribution of all elements (strength of element times the ratio of area of element to the area of the entire cross section).

In the Specification the same strength equations for compression on unwelded plates are applied to plates with welds. The strength of the welded plate, however, is limited to the strength of the material across a butt weld. There is some information on welded plates (1), that indicates that

this design procedure can be somewhat unconservative for ultimate strength for alloys with a large difference between welded and base metal strengths, particularly for thin sheet. To design welded plates assuming that the plate has all heat affected material, however, would be ultraconservative. Thus if more accurate estimates are desired, advanced analytical methods or tests are needed to verify performance.

Another area that needs additional research is the defini-tion of plate width for calculating post-buckling strength, particularly when the ends have radii. The equations for post buckling strength of elements is based on the redistri-bution of stresses and end conditions that support the edges of the plate sufficiently to develop the yield strength of the material at these edges. The requirement that the radius at the edges be limited to 4t for determination of width of the element (for calculating post buckling strength) is to pro-vide for the necessary strength and support at the corners.

3.6.2 Elements with Non-Uniform Thickness

Strength equations are provided for elements of constant thickness. Some limited studies show that the buckling load for an element much thicker at the edges than at the center can be over 40% higher than that for an element of con-stant thickness, but having the same area (1, p. 283). Post buckling strength may also be higher, but there are no

Table 3.6-1STRENGTH EQUATIONS FOR ELEMENTS UNDER COMPRESSION

CaseEquivalent Slender-

ness RatioStrength Equations

Columns Beams

(1) Plate supported on one edge under uniform compression

5.1 b/t 3.4.8-1,2,3 3.4.15-1,2,3

(2) Plate supported on two edges under uniform compression

1.6b/t 3.4.9-1,2,3 3.4.16-1,2,3

(3) Plate suppoted on one edge under bending with free edge in compression

3.5h/t — 3.4.17-1,2,3

(4)

Plate supported on two edges under bending

0.67h/t — 3.4.18-1,2,3

(5)

Plate supported on two edges under bending with stiffener in compressive region

0.29h/t — 3.4.19-1,2,3

III-16 January 2005

studies available. Advanced analyses and/or tests are needed to verify the improved performance in plates of nonuniform thickness. The extrusion process should be able to produce the geometries of the more efficient sections.

3.7 Compression in Tubes and Curved Panels

The strength of unwelded cylinders, tubes and curved panels supported on the edges is given by Equations 3.4.10- 1,2,3. The bending strength of cylinders, and round and oval tubes is provided by Equations 3.4.12-1,2 and Equa-tions 3.4.10-2,3. For curved panels in bending members the strength is given by Equations 3.4.16.1-1,2,3. These equa-tions are provided by 6061-T6 members in Figure 3.7-1. All of these provisions are based on the local buckling strength of accurately fabricated tubes and curved panels: thus for large R/t ratios the strength is the same for all parts.

The lower set of curves, two straight lines and a curved line, applies to both tubes and curved panels under uni-form compression. The upper set of curves, three straight lines and one curved line, applies to the bending of tubes. The higher strengths at low R/t ratios reflect the additional strength due to the shape factor on bending for a tube (1.17 used). For larger R/t ratios the strength equations for axial compression also apply to bending members. For curved elements in bending members, the experience with build-ing sheathing products shows that their strength is lower than that for complete cylinders for low R/t ratios, and thus the dashed line on Figure 3.7-1 is used for this case.

Figure 3.6-1PLATE BUCKLING EQUATIONS

Figure 3.6-2BUCKLING/POST BUCKLING BEHAVIOR

OF FLAT PLATE ELEMENTS

Figure 3.7-1TUBES/CURVED PANELS UNDER

COMPRESSION AND BENDING

January 2005 III-17

For circumferentially welded cylinders with low R/t ratios the same strength formulas apply. In this case the yield strength across a butt weld is used and the buckling constants are obtained from Table 3.3-3. Test data for cylinders with circumferential welds and with R/t ratios less than about 20, show that this procedure is accurate. There is some limited data, however, that suggest that the compressive strength of circumferentially welded cylinders with much higher R/t ratios, can be much lower than that given by the specified strength equations (1, p. 185). Apparently the circumferen-tial welds can cause more severe geometric imperfections in the thin-walled cylinder than those that were present in the cylinders used in the original derivations of the strength formulas. The strength of cylinders with longitudinal welds only, seems to be consistent with that given by the specified strength equations (1). More research is needed in this area to establish accurate design rules. However, the designers of tanks with large R/t ratios should consider the design impli-cations of the limited data provided above.

3.8 Shear in Flat Webs

3.8.1 Buckling of Stiffened and Unstiffened Webs

There are two sets of strength equations available for shear in webs, one for unstiffened webs given by Equations 3.4.20-1,2,3; the other for stiffened webs given by Equations 3.4.21-1,2,3. These provisions are based on the buckling strength of shear panels with supported edges partially fixed against rotation. The same equations are utilized for welded construction. The maximum strength is limited to shear yield or ultimate strength of the welded material.

3.8.2 Tension Field Webs

The static strength of thin, stiffened webs is much higher than the buckling strength provided by the above equations because of the “tension field action” that develops in the web at loads above the buckling value. There is some infor-mation available on the behavior of tension field girders (1). A much more efficient structure can result from a static strength design using tension field behavior. Figure 3.8-1 shows the strength available above the buckling value for one case. There are a number of considerations that need to be addressed when designing girders for ultimate rather than shear buckling as summarized below (1, p. 151).

1. The ultimate strength of the web is a function of the material properties and the strength and stiffness of the beam flanges and intermediate stiffeners.

2. Additional forces are imposed on flanges and intermedi-ate stiffeners by the tension field stresses that must be taken into account in the design of these members.

3. Intermediate stiffeners must be sufficiently thick so they are not distorted in torsion by the buckles in the web, and fail because of this imposed distortion.

4. If appearance is important, the amount of stress allowed above the shear buckling stress must be limited.

5. The buckles in the web will cause local bending stresses at the boundaries of the panel that will be detrimental for fatigue. The current fatigue design guidelines do not include a case in which buckling is allowed. Fatigue tests will be needed to verify performance.

3.8.3 Corrugated Webs

Corrugated webs and shear diaphragms are efficient in carrying shear loads. Corrugated panels can be the web of a girder or the side and roof of a building. The strength and stiffness of a corrugated panel under shear are dependent on the alloy, configuration of the corrugation, size of the panel, and the type and configuration of the fastening to the framing members. Some of the design considerations based on information presented elsewhere (1, p. 165) are listed below.

1. Overall shear buckling of the panel may control strength. An equivalent slenderness ratio is defined for this mode of failure that is used with the buckling equations for shear.

2. Local buckling of the shear elements of the corrugations is given by the same equations as those for unstiffened webs covered previously in this section.

3. Failure of the corrugations and of the fastening at the supports need to be calculated. Local failure of the cor-rugations at their attachment to supporting members, can occur particularly if only part of the shape is con-nected.

4. The shear deflection of the panel is much larger than a flat panel of the same size. The major factors are size

Figure 3.8-1STRENGTH OF SHEAR PANELS (1)

III-18 January 2005

of panel, shape and thickness or corrugation, and the type and arrangement of the attachments. Equations of behavior are provided for several standard shapes.

Additional information on building diaphragms and their interaction with the building frames is given in Reference 6.

3.9 Shear in Tubes and Curved Panels

Shear buckling of tubes is calculated by the use of an equivalent slenderness ratio (Equation 4.2-1), which is based on buckling of the walls between circumferential stiffeners from torsional loads. This equation can be very conservative for long tubes with both longitudinal and circumferential stiffeners. Figure 3.9-1 shows the change in the coefficient in Equation 4.2-1 with length of tube. A coefficient of 2.9 is specified for all cases (solid line in Figure 3.9-1). A more accurate and less conservative value for long tubes is less than 2.9 as illustrated by the dashed line in Figure 3.9-1. The ordinate in this figure is a rear-rangement of Equation 4.2-1. The addition of longitudi-nal stiffeners as well as circumferential stiffeners usually increases the shear strength of a tube compared to a tube with circumferential stiffeners only. The behavior of all of the above cases has been published (1, p. 191).

3.10 Combined Stresses/Loading

There are five cases of combined loading that are avail-able to the designer. All make use of an interaction equa-tion. Information on each is provided below.

Combined Axial Compression and Compression due to Bending—Beam-column interaction equations are given

by Equations 4.1.1-1,2. The equations provide for the esti-mated strength of a member that is loaded both axially as a column and in bending as a beam. They apply to all of the failure modes for beams and columns.

Combined Axial Tension and Tension due to Bending—This interaction formula is given by Equation 4.1.2-1, and limits the combined tensile stresses in members.

Combined Shear, Compression and Compression due to Bending—For walls of curved surfaces or round tubular shapes the interaction equation is Equation 4.4-1, and for rectangular shapes and plates of built-up girders the equation is Equation 4.4-2. Both of these equations are based on local buckling of the elements.

Combined Local and Overall Buckling—If local buckling of the elements occurs at an elastic stress below that for overall buckling of a column or beam, the strength of the member is less than that calculated for the member assuming no local buckling. The strength of the member with buckled elements is given by Equation 4.7.4-1 (col-umns) and Equation 4.7.5-1 for beams. The strength is lim-ited by the weighted average crippling strength (maximum strength) of the section. If buckling of the elements occurs in the inelastic range, the strength of the column or beam is limited to the local buckling stress. Figure 3.10-1 illus-trates the use of these interaction curves. The solid curves are the strengths assuming no buckled elements, the dashed lines are for members with buckled elements.

Combined Web Crippling and Bending of Members— Equation 4.7.8-1 gives interaction between the concen-trated load causing web crippling and the moment causing failure of the compression flange (weighted average). The empirical relationship is based on available test data.

3.11 Stiffeners for Flat Plates

Longitudinal stiffeners for elements under compression and stiffeners for girder webs are discussed here. Normally stiffeners improve the efficiency of the design resulting in a lower weight. The fabrication cost of adding stiffeners can be low (or essentially zero). Formed in stiffeners are effective on sheet products (7) and stiffeners can be added to extruded shapes easily.

Plates with One Edge Supported and the Other Edge with Stiffener—The strength of the stiffened plate is given by Equations 3.4.9.1-1,2 for components of columns and by Equations 3.4.16.2-1,2 for compressive components of beams in the Specification. Two sets of equations are used because of differences in factors of safety applied to columns and beams; the strengths (factor of safety of 1.0) are the same. The provisions cover all sizes of stiffener, from those too small to effect the strength of the plate to those sufficient to fully support the edge of the plate. The stiffener itself also must be checked, to ensure that it has sufficient buckling strength.

These provisions apply to a stiffener of the same thick-ness as the flange and are conservative for other types of stiffeners. Stiffening bulbs and other complex shapes may

Figure 3.9-1SHEAR BUCKLING OF TUBES WITH CIRCUMFERENTIAL STIFFENERS

January 2005 III-19

provide higher strengths than those provided for in the Specification. A method for estimating buckling strength for these other shapes is given elsewhere (1, p. 135).

Plates with Both Edges Supported and With an Intermediate Stiffener—The equivalent slenderness ratio to be used in column buckling equations is given by Equa-tion 3.4.9.2-6 for column elements and Equation 3.4.16.3-6 for compressive elements of beams. The two equations are the same.

These provisions apply to a plate with one intermediate stiffener, which probably is the most efficient arrangement. Provisions elsewhere (1, p. 138) give the general formula for buckling of panels with one or more stiffeners.

Unsupported Compression Flanges—Equation 4.10-1 is a slenderness ratio to be used in column buckling equa-tions. These provisions apply to sections whose compres-sion flanges are not supported against lateral movement, but the tension flange is supported laterally and provides some resistance to lateral movement of the compression flange. A hat section with the two flanges in compression is an example of the type of member covered. The resistance to rotation at the tension flange may be continuous or inter-mittent. Calculations or tests may be required to evaluate

the spring constant needed in Equation 4.10-1. More dis-cussion on the behavior of this type of member is available (1, p. 146).

Longitudinal Stiffeners for Beam Webs—The required moment of inertia for a longitudinal stiffener on a beam web, to support the web at that location against compres-sive buckling is given by Equation 4.5-1. The distance of the stiffener from the toe of the compression flange is 0.4 times the distance from the toe of the compression flange to the neutral axis. With a sufficient stiffener the compres-sive buckling strength of the web is given by Equations 3.4.19-1,2,3.

Transverse Stiffeners for Shear Webs—The moment of inertia needed for intermediate stiffeners on girder webs is given by Equations 4.6-1,2. The requirement is based on the minimum requirements of a stiffener to subdivide the web into panels, and to develop the shear buckling strength of the panel. This moment of inertia is multiplied by the ratio of the applied shear load to the shear load causing buckling to allow for some adjustment of size of stiffener depending on the actual load applied. Equation 4.6-3 pro-vides for additional moment of inertia for cases in which an additional concentrated load is carried by the stiffener.

3.12 Pipe Bursting Pressure

The bursting pressure of aluminum pipe may be estimated from the equation (1, p. 178):

P = 2tFtuK _____ D – 0.8t

Where:

P = bursting pressure t = pipe wall thickness Ftu = tensile ultimate strength K = 0.73 + 0.33Fty /Ftu

D = pipe outside diameter Fty = tensile yield strength

Specific applications of aluminum pipe may be gov-erned by standards for that use. For example, aluminum pipe used in chemical plants and petroleum refineries is often designed in accordance with ASME B31.3, which provides a slightly different equation and factors of safety appropriate to such applications.

3.13 Biaxial and Triaxial Stresses

The Aluminum Specification predates finite element analysis (FEA) and doesn’t directly address issues that arise from such analyses. For example, the Specification provides design stresses for prismatic members primar-ily under uniaxial stress, such as columns. FEA, on the other hand, can provide triaxial stresses by reporting, in addition to longitudinal stresses, through-thickness and transverse stresses. Many FEA programs calculate a von Mises stress (explained below) from the triaxial stresses at a given element.

Figure 3.10-1COMBINED LOCAL AND OVERALL

BUCKLING - 6061-T6

III-20 January 2005

Yielding occurs in ductile materials like aluminum when

( f1 - f2)2 + (f2 - f3)2 + (f3 - f1)2 > 2 Fty2

where f1, f2, f3 = principal stresses (the normal stress on each of three orthogonal surfaces such that the shear stresses on the surfaces are zero)

Fty = tensile yield stress

This equation is called the von Mises criterion or dis-tortion energy criterion. It predicts that yielding will occur when the distortion energy equals the distortion energy in an axially loaded member at yield. The above equation is for the general triaxial stress state. If stresses are biaxial, f3 = 0, and the equation above predicts yielding when

(f1 - f2)2 + f 22 + f 1

2 > 2 F 2ty

For convenience, the von Mises stress is defined from the von Mises criterion as

√____________________

(f1 - f2)2 + (f2 - f3)2 + (f3 - f1)2

___________________ 2

so that it may be compared directly to the yield stress to determine if yielding will occur. In the biaxial stress state, the von Mises stress becomes

√__________

f 12 - f1 f2 + f 2

2

The von Mises criterion is used in the Aluminum Speci-fication to determine the shear yield strength of aluminum alloys, since there is no established test method to measure

shear yield strength. In the case of pure shear, the shear stresses in a biaxial stress element are τ and – τ. Mohr’s circle can be used to show that the principal stresses f1 and f2 are, then, also τ and – τ, so the von Mises stress is

√___________

τ2 - τ(-τ) + τ2 = τ √__

3

When the von Mises stress equals Fty, yielding occurs, so shear yield τy is

τy = Fty

___ √

__ 3

Local yielding in a member may not limit its usefulness if the amount of material that yields is small or positioned so as to have only a negligible effect on the shape and load-carrying capacity of the member. Where yielding does rep-resent a limit state, the von Mises stress should be limited to the yield strength of the material divided by the safety factor on yield. This limit is:

√________________________

( f1 - f2)2 + ( f2 - f3)2 + ( f3 - f1)2

________________________ 2 ≤

Fty ___ ny

where f1, f2, f3 = principal stresses (the normal stress on each of three orthogonal surfaces such that the shear stresses on the surfaces are zero)

Fty = tensile yield strength ny = safety factor on yield

January 2005 III-21

4.0 Fatigue

Design of components for fatigue is covered by Equa-tions 4.8.1-1 and 4.8.1-2 for constant amplitude loadings and by Equations 4.8.2-1 and 4.8.2-3 for spectrum load-ings. Various standard details are provided and stress/ number of cycle (S-N) curves are given for all the details. The S-N curves are based on the curve providing 97.7% probability of survival with 95% confidence level. The pro-cedure for design is to use the fatigue strength of the stan-dard detail that most closely approximates the new detail being designed.

When designing for fatigue there are defined or assumed cyclic loads and a number of cycles. Joints or geometrical discontinuities, such as holes, are usually areas in which fatigue cracks originate. The designer must establish the geometry and joining method such that the resulting stresses are within those given by Equations 4.8.1-1 and 4.8.2-1.

The aluminum component generally must be different from the steel component for the same load spectrum. Fig-ure 4.0-1 shows fatigue strengths for aluminum and steel for groove welds (a Category C detail). For long lives the fatigue strength of aluminum groove welds is about 40% that for steel. There is a smaller difference at short lives. The design of the aluminum component must be consistent with the fatigue strength curves for aluminum.

There are a number of factors that should be considered when designing for fatigue.

1. The light weight of the aluminum structure may result in reduced design loads. Examples are automotive frames and some ship structures in which the loading is proportional to the mass of the structure. In cases in which the imposed loads are large compared to the mass of the structure, the design loads are about the same for all materials.

2. There are some general guidelines (as compared to steel design) that will provide for more efficient aluminum structures. Aluminum members in bending should be deeper than those of steel. The spacing of stiffeners on plates should be smaller for aluminum components com-pared to that for steel components. These geometrical differences will help meet any deflection requirements for the aluminum component and will lower the stresses in the parts, helping with any fatigue requirements.

3. Joints may be eliminated by the use of extrusions and castings, thus removing sites for fatigue crack initiation. In some cases the designer can locate joints or discon-tinuities in areas of low stress, thus improving fatigue resistance.

4. The type of joint affects fatigue strength significantly, whether welded, mechanically fastened or adhesively bonded. The designer should select the joint that best meets the need.

5. There are enhancements to joints that can improve fatigue strength. These include shaping the weld toes and peen-ing the edges of the welds. Adhesives can be employed in mechanically fastened (and spot welded) joints. All of these enhancements increase fatigue strength. Tests will be needed to establish fatigue strength.

Much more information is available on designing for fatigue (1,3,8). In many cases the cause of fatigue behav-ior has to be minimized or eliminated. Wind induced vibra-tion of members can be prevented by proper design or by the addition of damping. Vibration of structures caused by unbalanced forces from machinery, can be minimized by the use of properly designed vibration mounts and proper design of the structure (natural frequency less than ½ or more than 2 times the exciting frequency). Design for fatigue would not be possible without the control of the forces in these cases.

Fatigue resistant joints should always be employed. Gradual changes in geometry of components and joints and avoiding areas of concentrated load and stress are two of many good design practices. Because most fatigue failures initiate at areas of localized high stress, particularly joints, these details need to be designed carefully. Environment, temperature, air quality and corrosive substances can influ-ence fatigue strength in some cases.

The use of S-N curves is the most common but only one of perhaps four methods of designing for fatigue. The others are hot spot (30), strain-life, fracture mechanics and good practice design methods. All of the techniques have merit and can be applied to most types of structures (8).

Components under constant amplitude loading gener-ally have a fatigue endurance limit, a stress below which failure should not occur. Components of variable ampli-tude loading may not exhibit an endurance limit, because a crack can be initiated by the higher stress cycles of the spectrum and propagate at stresses below the constant

Figure 4.0-1FATIGUE DESIGN CURVES

FOR ALUMINUM AND STEEL

III-22 January 2005

amplitude endurance limit. Miner’s rule is generally used for spectrum loading with the straight-line portion of the fatigue curves (assuming no endurance limit) (8). There also may not be an endurance limit in mechanical connec-tions that fail by fretting. Tests may be required to evaluate the possibility of fretting failures.

The stress amplitudes in a spectrum usually are difficult to determine unless a cycle-counting procedure is employed. Of the several procedures that are available (8), the rainflow counting method is commonly used.

January 2005 III-23

5.0 Joints and Joining

Mechanical, welded and adhesive joints are discussed in this section. Joining affects most of the design consider-ations for structures.

5.1 Mechanical Joints

Bolts, rivets, screws, staples and clinches are employed in aluminum structures. Aluminum, stainless steel (300 series), and galvanized steel fasteners are the acceptable materials. For aluminum fasteners the tensile and shear strengths can be determined by multiplying the tensile and shear strengths by the net area of the fastener. The strengths of fasteners of other materials should be obtained from their manufacturer.

Figure 5.1-1 shows a riveted or bolted joint. The joint is normally designed as a bearing joint. Several modes of failure need to be considered.

1. Shear failure of the fasteners. The fasteners will be equally loaded at failure.

2. Bearing failure. Edge distance is a factor with loads directed toward the edge or directed parallel to the edge (see Section 3.3).

3. Tension failure of the net section. The horizontal line is the width to use in calculating net area.

4. Tearout of bolt group (9). The cross hatched area in Fig-ure 5.1-1 can tear out. The strength can be estimated by adding the shear portion (shear area on each side of the cross hatched area times the shear strength of the material) plus the tension portion (tension area at the top of the cross hatched area times the tensile strength of the material).

Aluminum parts connected with high strength steel bolts have been tested for their resistance to slip under shear forces. Tests of mill finish aluminum surfaces degreased and dried have generally achieved relatively low coeffi-cients of friction. The Research Council on Structural Con-nections (RCSC) Specification for Structural Joints Using ASTM A325 or A490 Bolts provides a test method to deter-mine the coefficient of friction for various surfaces. Tests conducted by this method of aluminum surfaces abrasion blasted with coal slag to SSPC SP-5 to an average substrate profile of 2.0 mils in contact with similar aluminum sur-faces or zinc painted steel surfaces gave results for Class B surfaces, which have a design slip coefficient of 0.50. The British Standards (10) allow a coefficient of friction of 0.33, if the total thickness of parts exceeds the bolt diameter and the faying surfaces are blasted with aluminum oxide grit to achieve the necessary roughness. Temperature changes cause a reduction or increase in the friction capacity due to the different coefficients of thermal expansion of steel and aluminum and should be considered in design. Bolts must be tightened in accordance with the RCSC Specification to achieve the required preload.

Bolts may also be designed to resist shear by bearing on the sides of the holes rather than by friction between the faying surfaces. No definite rules for determining the mag-nitude of the tightening torque for such connections have been established because test results vary widely depend-ing on the friction developed in the threads and other bear-ing surfaces. One recommendation that is sometimes made for establishing a tightening torque for aluminum bolts is as follows: Tighten several bolts of any given size and type to the breaking point under the same conditions of lubrica-tion as will be encountered on the job and then use 70% or 80% of the lowest torque obtained from the tests. The 70% value should be used for “temporary” bolts, or those that may need to be removed occasionally, while the 80% value applies to “permanent” bolts. The use of a lubricant on the threads and bearing surfaces is useful.

These recommendations for tightening may be modified for bolts or other threaded parts that carry fluctuating axial tensile loads that can cause fatigue failures. Under these conditions, the tightness (initial axial tensile load) should be slightly more (about 5%) than the maximum tensile load on the bolts during service.

Figure 5.1-1FAILURE MODES OF

BOLTED/RIVETED JOINT

III-24 January 2005

Aluminum bolts, particularly those with lubricated threads and bearing surfaces, may loosen under cyclic loading or vibration. There are many devices available to prevent loos-ening, and guidance available for their use in practical struc-tures (11). Devices commonly used are various types of lock washers, less commonly used are locking inserts built into the nut threads.

5.2 Welded Joints

5.2.1 Welding Fabrication

The general recommendations and regulations for weld-ing are provided in the American Welding Society D1.2 Structural Welding Code Aluminum. Acceptable weld pro-files, standard welding symbols, inspection, and joint pro-cedure qualification requirements are also provided in this code. Inspection methods are described in this code but are not required unless specified in contract documents.

5.2.2 Design of Welded Joints (12,13,14)

5.2.2.1 General

Continuous structural integrity between components in a fabricated structure is the key to good design for weld-ing. Strength loss and any interference with the continuous distribution of stresses across a joint should be minimized. When welding, accessible joints between components of identical alloys are preferred. Mixed alloy joints can be made between compatible alloys. In these joints, the mechanical properties of the lower strength material must be utilized for design.

5.2.2.2 Groove Welds

Groove welds (Figure 5.2-1) are utilized for butt joints. The butt joint is easily designed. The strength of a sound groove weld meets or exceeds the weld qualification strength of the alloy, for a given temper and filler alloy. There is rarely a problem of joint inaccessibility for welding. Groove welds are shaped for ease of root penetration, to allow for less dilution of the filler by the base metal (where hot crack-ing is a problem), or to permit a desirable sequence of weld bead strength depositions when welding in other than flat positions. Fatigue strength can be significantly increased by removing the weld bead reinforcement.

5.2.2.3 Fillet Welds

Fillet welds (Figure 5.2-2) are used to join surfaces to each other in lap, T, or corner joints; the welds determine the strength of these joints. A sounder and more economi-cal structure results from using continuous welds as opposed to intermittent ones. While an intermittent weld may reduce time, filler wire, heat input or distortion, it may exhibit unfa-vorable local stress concentrations at its ends. The possibility for poor metal quality and end craters in the weld increases with the repeated stopping and restarting of the welding

equipment. Since the cost of fillet welds is mainly a function of the square of their size, large intermittent welds are not as efficient in carrying loads as small continuous fillets. In addition, some design standards specify that the ends of each weld are to be considered non load carrying, which means that intermittent welds must be longer than theoretically nec-essary. Intermittent welds also make a structure more sus-ceptible to moisture infiltration which may ultimately lead to corrosion.

Fillet welds exhibit different strengths depending on the geometry of the part and the type of loading on the weld. The fillet weld strengths as provided in Tables 7.2-2,3 are based on tests of longitudinal fillet welds (see Figure 5.2- 2a). Transverse welds (Figure 5.2-2b is one type) can have higher strengths in some cases. Table 5.2-1 presents some strengths relative to that for longitudinal welds (1). The stress condition in the fillet weld affects the strength, with the lowest strengths for the one sided fillet welds. Tests may be required to determine fillet weld strength in components that are different from those previously evaluated.

5.2.2.4 Unequal Thickness Transition

A butt joint between different thicknesses of metal should have the thicker one beveled to match the thinner one (Figure 5.2-3). This tends to balance the heat sink for uniform melting and good fusion, and reduces the stress raiser caused by change in thickness.

Figure 5.2-1

January 2005 III-25

5.2.2.5 Welded Joint at Point of Flexure

When a thin gauge of metal is welded to a thicker piece (Figure 5.2-4), the weld seam should be away from the point of flexure for improved stress resistance.

5.2.2.6 Welds in Low Stress Areas

Welds may have lower strength than the base metal (e.g., welds in 6061-T6 alloy). One way to reduce the inherent loss of load carrying capacity is by locating the welds in areas of low stress. Beams loaded in bending can be fab-ricated by welding together longitudinal extrusions with

joints located in webs near the neutral axis (Figure 5.2-5). Since the web’s metal thickness is often much thinner than the flanges, quantity and cost of welding is reduced.

5.2.2.7 Doubler Plates

The commonly used rectangular doubler plate welded on four sides offers transverse welds which reduce the main member strength. If only the sides of this doubler are welded, the longitudinal welds may become so highly stressed that they progressively fail. When a doubler plate is necessary, it should be diamond shaped (Figure 5.2-6), avoiding sudden cross-sectional change.

No welding should be done across the ends. The dou-blers should be as wide as possible, consistent with leaving

Table 5.2-1FILLET WELD STRENGTHS

Case Filler Metal Ratio: Strenth of Fillet Weld Str. of Longit. Fillet Weld

(1) 404353565556

1.31.51.5

Symmetrical fillets on plate

(2) 53565556

0.80.7–1.0

One sided fillets on tube

Figure 5.2-2

a. Longitudinal Fillet b. Transverse Fillet c. Corner Weld

Figure 5.2-3 Figure 5.2-4

III-26 January 2005

room for a fillet weld on each side. The doubler length (l) should be much greater than its width (w) (ratio of at least 3 to 1), which orients the fillet welds nearly parallel to the stress direction.

5.2.2.8 Stiffeners

When stiffening a panel or member, care must be taken to avoid sudden cross-sectional changes. If a member must be reinforced, the reinforcing plate must provide for a gradual change in cross-section (Figure 5.2-7), otherwise fatigue cracks at the ends of the plate may result.

5.2.2.9 Corner Constructions

A common design problem is joining members at cor-ners to give an economical, structurally sound connection that has good appearance. Figure 5.2-8 illustrates various corner designs with comments on their relative suitability. Double fillets, or bends to allow a butt or a lap joint should be used.

5.2.2.10 Combined Lap and Butt Joints

When sheet metal panels are to be welded to extruded members, an attempt is sometimes made to use a joint opening between panels and set the welding procedure to make a groove weld and also provide adequate attachment to the extrusion (Figure 5.2-9). In effect, what is desired resembles a slot weld which seldom proves practical. The joint fit and the welding procedure are both critical if the sheet edges are hot enough to melt back from the joint when the welding current is high enough to penetrate the extrusion. Therefore, conventional lap joints are typically specified for this application.

5.3 Adhesive Bonded Joints

An adhesive can be defined as a substance capable of holding materials, similar and dissimilar, together by sur-face attachment. The critical substrate surfaces can be held together by chemical and/or mechanical adhesion at the interfacial layer of contact between surfaces (15).

5.3.1 Advantages and Disadvantages

Some of the advantages of adhesive bonding are (16,17)

• Ability to bond a variety of materials which may exhibit differing coefficients of thermal expansion, moduli, thick-ness, etc., with proper joint design and material selection.

• Improved cosmetics of the finished product by the elimi-nation of protruding mechanical fasteners, such as rivets or bolts.

• Excellent strength to weight ratio in comparison to other joining methods.

• Good joint stiffness and fatigue performance, with appro-priate choice of adhesive.

• Elimination of stress concentrations inherent to mechan-ical fastening methods, and a more uniform stress distri-bution over the bonded surface area.

• Adaptable to many production processes because of the variety of forms (pastes, films, emulsions, etc.) and methods of application of adhesives.

Figure 5.2-5

Figure 5.2-6

Figure 5.2-7

January 2005 III-27

Figure 5.2-8

Figure 5.2-9

The advantages of adhesive bonding are most evident when joining relatively thin materials and components. The cost advantages and joint efficiencies decrease as the members become thick.

Some of the disadvantages of adhesive bonding are (16,17)

• Expert joint design is critical in order to minimize peel and/or cleavage stresses.

• Temperature limitations may restrict the use of many adhesives from high temperature applications.

• Adhesives will require surface pretreatment of the aluminum unless the adhesive manufacturer recommends no pretreat-ment necessary. Even with this recommendation, the dura-bility required for the application should be verified.

• Difficulties in inspecting for initial bond integrity and an insufficient understanding of the effects of in-service damage on subsequent bond performance limit confi-dence in adhesive bonding as a primary structural join-ing method.

III-28 January 2005

5.3.2 Adhesive Selection

Of the several classes of adhesives, there are literally thousands of commercial adhesives available from each class, in order to select the proper adhesive for a particu-lar application the adhesive end-user needs a systematic approach to adhesive selection. Listed below is an outline of major areas to address prior to undertaking an adhesive bonding application:

• Substrates• Pretreatment• Application• Production• Service Environments• Design

5.3.3 Types of Adhesives (18)

Adhesives are categorized into two generic groups: thermoplastics and thermosets. Thermoplastics are materials which can be repeatedly softened by heat and hardened by cooling to ambient temperature. Thermosets are materials that undergo chemical reactions initiated by heat, catalyst, UV light, etc., which lead to relatively infusible state or phase. Thermosets are generally more durable than thermo-plastics.

From the two groups of adhesives extend several classes of adhesives which include anaerobic, contact, cyanoacry-late, film, hot melt, one-part and two-part. Anaerobic adhe-sives are generally esters or acrylics in which, upon the restriction/lack of air/oxygen, curing of the adhesive initi-ates. Anaerobic adhesives can also be cured by UV expo-sure. Contact adhesives are coated to both substrate sur-faces and a solvent is allowed to evaporate before assem-bly of the substrates. Cyanocrylates are known as instant cure adhesives. They are derivatives of unsaturated acry-lates which cure at room temperature without the aid of a catalyst. Films are uniform layers of adhesives which are generally rolled onto coils. Films can be supported (with reinforcing fibers), unsupported, heat-activated, or pressure-sensitive. Hot melts are generally solvent-free thermoplastics which are solids at room temperature but soften and flow at heat activation temperature. Upon cool-ing the hot melt regains its structural strength. One-part adhesives are usually 99–100% solid systems. This class of adhesives includes epoxies, moisture activated silicones, and polyimides which can be waterborne or organic solvent based. Two-part epoxies and acrylics are generally cured at room temperature or accelerated with heat.

5.3.4 Aluminum Surface Pretreatments

In adhesive bonding of aluminum substrates, a surface pretreatment prior to bonding is usually necessary in order to achieve long-term bond strength, although in some cases an adhesive manufacturer may state that their adhesive requires no surface pretreatment or that their adhesive is

chemically incompatible with the proposed pretreatment. Over the years many aluminum surface pretreatments have been examined to determine which are the better adhesive substrates for bonding. It is commonly accepted that chem-ically pretreating the surface yields a more durable bond strength than that of mechanically abrading the aluminum surface. Some of the most popular chemical pretreatment systems to improve the adhesion of “as-received” alumi-num are degreasing, acid etching, and phosphoric acid anodizing.

5.3.5 Joint Design

The decision to use adhesive bonding to a joining method must consider joint geometry, the nature and magnitude of loading, the properties of the adhesive and the members to be joined, failure modes, and ease and reliability of manufactur-ing. Adapting a joint design intended for other joining meth-ods often results in ineffective designs. The design must also consider the assembly scheme including needs for surface pretreatment, part tolerances, and fixturing.

The stresses present in adhesive-bonded joints are clas-sified based on loading conditions: normal, shear, peel, and cleavage (Figure 5.3-1). Cleavage and peel conditions describe a combination of normal and shear stresses spe-cific to these two loading conditions. Cleavage stresses are concentrated on one side of the joint, while peel loads can occur with flexible members (18). Though technically different, tensile stresses normal to the bond line are also referred to as peel stresses in the literature. Because adhe-sives perform best when subjected to compressive and shear loads, joint design should distribute the loads in the adhesive layer as a combination of compressive and shear stresses to avoid tensile, cleavage and peel loadings.

There are four basic types of joints: angle, tee, butt, and surface or lap joints (Figure 5.3-2). In service, these joints may be subjected to the types of stresses mentioned in the previous paragraph. Most practical adhesive joint designs

Figure 5.3-1TYPES OF STRESSES: A) SHEAR,

B) TENSION, C) PEEL, D) CLEAVAGE

January 2005 III-29

can be classified as variations of lap joints. Lap joint con-figurations are usually preferred because they require little or no machining. For low loads, using overly complex con-figurations when simpler geometries are adequate results in unnecessarily expensive designs. On the other hand, simple configurations are unacceptable if smooth uninter-rupted surfaces are required, if high stresses are present in the bond or if high load levels must be sustained in the structure.

In single lap joints which are not supported or restrained against joint rotation, bending within the joint and at the ends of the overlap causes locally high transverse tensile stresses in the bond. In joints which are designed to prevent or minimize joint rotation, the bond strength can exceed the full nominal strength of the members.

Although adhesive bonding has benefits in joining dis-similar materials, the application imposes additional design considerations. Using materials with different moduli may result in reduced joint efficiencies. If the materials do not have similar thermal expansion coefficients, temperature changes during elevated temperature cures and due to inservice thermal cycles can increase stresses in adhesive bonds and lower joint strengths (19). If member materials are not identical, the design should equalize the in-plane and bending stiffnesses and the materials should have simi-lar thermal expansion coefficients.

The identification of possible failure modes is crucial to effective joint design and satisfactory performance. For joints consisting of ductile isotropic materials such as alu-minum alloys, four common failure modes are: (1) tensile or buckling failure of the member outside the joint area,

(2) shear failure of the adhesive, (3) tensile cracking in the adhesive layer due to tensile or cleavage forces in the joint, and (4) adhesion failure at the adhesive/member interface. Failures outside of the joint area are the most desirable, with 100% joint efficiency developed.

Adhesion failures are least desirable because such inter-facial failures typically result in low, inconsistent joint strengths. If the adhesive fails to adhere to the aluminum, this indicates incompatibility of the surface oxide of the aluminum with that particular adhesive. If the aluminum is pretreated, and failure occurs at that interface between the pretreatment and the adhesive, this indicates adhesive/ pretreatment incompatibility.

The adhesive properties for joint designs may be obtained from mechanical tests. Tensile properties can be obtained using cast adhesive specimens as described in ASTM D638 (20). Adhesive shear properties can be generated using thick adherend tests (21) or a torsion test described in ASTM E229 (22). Properties should be obtained for temperatures throughout the range expected in service. Temperature can affect adhesive properties, ductility and toughness, which will affect joint design and performance, including stiffness and failure loads and modes. The adequacy of the design should be checked for the range of service temperatures. Recent summaries of technology and data are provided in Reference 23.

For critical applications in complex structures, a com-plete analysis of the stress components is recommended along with the identification of the potential failure modes. Nonlinear behavior of the adhesive and members should be accounted for in the most effective method of conducting such analysis. Mechanical tests to simulate typical service conditions of adhesive-bonded joints should be performed to verify the predicted failure location and modes.

5.3.6 Current Adhesive Applications

Adhesives are gaining popularity as a viable structural means of joining aluminum. Today, aluminum adhesive bond-ing is being used in the transportation, construction products, automotive, marine, aerospace and electronic industries. Examples in each category are:

• Transportation: buses, trains and trailers• Construction products: bridges and architectural panels• Automotive: seats, hoods and air bags• Marine: boats, ships and desalination plants• Aerospace: space vehicles, aircraft and helicopter• Electronics: antennas, computer boards and cable wires

Figure 5.3-2TYPES OF JOINTS: A) ANGLE, B) TEE, C) BUTT, D) SURFACE

III-30 January 2005

6.0 Sandwich Panels and Beams

A typical aluminum sandwich panel consists of thin alu-minum facings, a plastic core and an adhesive layer that attaches the facings to the core (see Figure 6.0-1). Many other options are available, such as additional aluminum layers through the thickness, and other core materials; honeycomb, fiber reinforced composites and high density plastics. The product can have advantages in that the differ-ent materials act together, resulting in superior properties such as bending stiffness, bending strength, insulation, fire resistance, fatigue, etc. as compared to the properties of the monolithic construction. There are no well defined design procedures, nor design specifications in the United States for this product. Thus, commercial products have gener-ally been developed by the manufacturer for specific types of panel and for specific applications. Some of the design considerations are as follows.

1. Adhesive bonding is used to attach the skins to the core. Adhesive selection surface preparation and fabrication practice are important to achieve the proper attachment of skin to core and performance of the panel. There is no good way to nondestructively test the integrity of the bond.

2. Panels often have a requirement that they will not sup-port combustion, are fire resistant and do not have unde-sirable fumes.

3. Facings may need to have resistance to denting.4. The panels will need to be designed for general column

and beam strength. In addition the compressive wrin-kling strength of the face may be important.

5. The thermal gradient across the thickness of the panel may cause bowing of the panel or creep buckling of the panel.

6. The strength and stiffness of the core is important for deflection of the panel and for the strength of the panel and facing.

The most recent work in the area has been done in Europe. Both good practice and design are considered (24,25).

In a similar product, an aluminum-elastomer sandwich beam, the components comprising the structural elements also act together creating a combined strength and other characteristics which are greater than the sum of the parts. The composite beam may have to resist stresses due to a temperature gradient through the section as well as stresses from wind and dead loads. The amount of composite action can be determined by analysis (26) or tests.

Figure 6.0-1SANDWICH PANEL

January 2005 III-31

7.0 Extrusion Design

Extrusions may be customized to achieve unique shapes up a circle size of about 30 in. Their cost is competitive with other product forms, and varies with type of extrusion,

alloy and size of part. The information in this section is extracted from an existing publication (27).

7.1 Replacement of Fabrications with Extrusions

As shown at right, several rolled and riveted structural shapes (left) can be combined into a single aluminum extrusion, thus eliminating all joining costs.

Machined and stamped sections can be replaced by aluminum sections extruded to exact size and shape.

As another example, the machining cost and weight of a framing member is reduced by redesigning the member as an extruded section.

Aluminum extrusions may also replace wood sections. They can be made lighter, stiffer, and stronger, thus eliminating steel reinforcement.

III-32 January 2005

Welded assemblies are frequently rede-signed into extruded sections. Not only is cost reduced, but accuracy and strength are increased.

Because extrusions permit infinite changes in cross sectional design, they can be produced more readily to meet specific design require-ments than rolled sheet sections.

Crimped tubular sections frequently permit redesign in extruded shapes, with gains in both stiffness and strength. Cost of manufacture is also reduced.

Small castings, forgings, and parts machined from bar stock may also permit redesign as an extrusion, as long as the cross section is sym-metrical in at least one plane.

January 2005 III-33

7.2 Design Parameters

Five major factors should be considered in the detailed development of an aluminum extrusion design:

• Shape configuration.• Tolerances.• Surface finish.• Alloy.• Circumscribing circle size.

These parameters are interrelated in their effect on the extrusion design and its application.

Shape Configuration

The designer’s first priority is to satisfy a specific need, and aluminum extrusion allows you to design the shape that best meets your structural and esthetics requirements. Since extrusion dies cost little, designers can afford to use several different shapes, if that’s the best way to achieve their objectives.

Users of computer-aided design programs will find alu-minum extrusions a uniquely satisfying product because the cross-section can be profiled to meet optimum struc-tural requirements.

Extrusions can be designed to aid in assembly, improve product appearance, reduce or eliminate forming and weld-ing operations, and achieve many other purposes.

Extruded shapes are described in three general categories—solid, semihollow, and hollow. Dies to pro-duce solid shapes are the least complex. But the difference between a solid shape and a semihollow shape may not be obvious at first glance. It’s easier to describe and under-stand all three categories by working in reverse, starting with hollow shapes.

A hollow shape……is simply an extruded shape which, anywhere in its

cross section, completely encloses a void. The void itself may have any sort of shape, and the complete profile may include a variety of other forms; but if any part of it encloses a void, it’s classified as a “hollow.”

Extruders further divide hollow shapes into three classes:A Class 1 hollow shape is defined by three requirements:

a) Its internal void is round.b) This round void is one inch or more in diameter.c) The weight of the shape is balanced, that is, equally distrib-

uted on opposite sides of two or more equally spaced axes.

An example of a Class 1 Hollow Extruded Shape

A Class 2 hollow shape is defined by three other requirements:

a) It is not a Class 1 hollow (its internal void may not be round or, if round, may not be large enough to qualify for Class 1).

b) It has a single void no smaller than 0.375 in. in diam-eter, or 0.110 in2 in area.

c) The entire shape fits within a circle no larger than 5 in. in diameter (a 5 in. “circumscribing circle”).


A Class 3 hollow shape is any hollow extruded shape that is not a Class 1 or Class 2; it may, for example, have more than one enclosed void.


Tube and Pipe are specific forms of hollow shapes. “Tube” is a hollow section that is long in comparison

to its cross-sectional size. It is symmetrical and has uni-form wall thickness except as affected by corners. It may be round or elliptical, or square, rectangular, hexagonal, or octagonal. “Extruded tube,” as the name indicates, is tube produced by hot extrusion; “drawn tube” is produced by drawing through a die.

“Pipe” is a tube with certain standardized combinations of outside diameter and wall thickness. These are commonly designated by “Nominal Pipe Sizes” and by “ANSI (Ameri-can National Standards Institute) Schedule Numbers.”

A semihollow shape……is one that partially encloses a void—for example, a

circle or rectangle with a gap in one side; but a solid shape can also partially enclose a void, and the difference may not be obvious. It is defined mathematically, by compar-ing the area of the partially enclosed void to the size of the gap (actually, to the mathematical square of the gap size). If that ratio is larger than a certain number, the shape is classified as semihollow; if the ratio is smaller, the shape is considered a solid.

These typical semihollow shapes illustrate the selection of void areas and gap widths to be used in calculating the

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ratio. In each example, use either the innermost void and gap, or the complete void and gap—whichever combina-tion yields the largest calculated ratio.

The ratios that distinguish semihollow from solid shapes are listed in a standard table. But before you can use it, you must make one more determination about the shape: is it a “Class 1” or a “Class 2” shape?

Void Area (sq. in.) / [Gap (in.)]2 = Ratio

Typical semihollow extruded shapes. Use void area D and gap width B or void areas C & D and gap width A, which-

ever results in a larger ratio.

Class 1 and Class 2 semihollow shapes are differenti-ated by whether or not they are symmetrical.

A Class 1 semihollow is symmetrical about the center-line of the gap (or gaps, if there is more than one partially enclosed void): the shape on one side of each gap center-line is an exact mirror-image of the other side.

A Class 2 semihollow is not symmetrical about the cen-terline of the gap or gaps. The shape on one side is different from the other side, either in form or wall thickness.

For example, these two shapes are both Class 1 semihollows

These two shapes are examples of Class 2 semihollows

Now, here’s the Classification Table that determines whether a shape that partially encloses a void is a semihol-low or a solid shape:

An example: Suppose that one of the examples shown above has a square void measuring 1.5 in. on each side, and a gap 0.80 in. wide. Also, suppose it is a Class 2 shape (not symmetrical), and is to be extruded from one of the alloys in Group A

The void area is: 1.5 × 1.5 = 2.25The gap squared is: .80 × .80 = 0.64The ratio, then, is: 2.25 / .64 = 3.51

The Classification Table shows that a Class 2 shape with Group A alloys and a gap-width between 0.500 and 0.999 in. must have a ratio greater than 3.5 to be classified as a semihollow.

In this example, the ratio is 3.51. This is larger than 3.5, so the shape is a semihollow.

Of significance here is that the dies required to make semihollow shapes are moderately more expensive than solid shape dies, and the output of those dies tends to approach tolerance limits, rather than tolerance nomi-nals. Tooling life and productivity are both improved with decreasing ratios, thus reducing cost.

January 2005 III-35

A solid extruded shape……is any shape that is not a hollow or a semihollow.This covers a wide range including, for example, com-

pact cross-sections with or without projections; angular or curved shapes; and those wrap-around shapes whose void area/gap2 ratios are too low for the semihollow-class.

Example of a solid shape

Extruded rod is a solid shape with a round cross-section at least 0.375 in. in diameter.

Extruded bar is a solid shape whose cross-section is square, rectangular, hexagonal or octagonal, and whose width between parallel faces is a least 0.375 in.

If the dimension across any of these rod- or bar-type shapes is less than 0.375 in., it is classified as wire.

Tolerances

In many applications in which the extrusion will be part of an assembly of components, tolerances are critical. A designer should be aware of the standard dimensional toler-ances to which extrusions are commercially produced. These tolerances generally cover such characteristics as straight-ness, flatness, and twist, and such cross-sectional dimensions as thickness, angles, contours and corner or fillet radii.

Aluminum extrusions are often designed to minimize or eliminate the need for machining. If desired, extrusions can be produced to closer-than-standard tolerances, generating

cost savings in secondary operations; such savings may range from modest to very large, depending on circum-stances. The designer should consider his requirements carefully and order special tolerances only where they are really needed.

If extruded parts are to interlock in any manner, the designer should work with the supplier to make sure that tolerances will provide a proper fit.

Surface Finish

One advantage of aluminum extrusions is the variety of ways the surface can be finished, and this offers another range of choices to the designer.

As-extruded, or “mill,” finish can range from “struc-tural,” on which minor surface imperfections are accept-able, to “architectural,” presenting uniformly good appear-ance. It should be understood that under normal circum-stances aluminum will be marred because it is a soft metal and that special care is required if a blemish free surface is desired, i.e., this would not be a normal surface to expect.

Other finishes include scratch finishing, satin finishing and buffing. Aluminum can also be finished by clear or colored anodization, or by painting, enamelling or other coatings.

If a product will have surfaces that are exposed in use, where normal processing marks may be objectionable, the extruders should be told which surfaces are critical. They can design a die that orients the shape to protect those sur-faces during the extrusion process; they can also select packaging that will protect the product during shipment.

Alloy Selection

Aluminum extrusions are made in a wide variety of alloys and tempers to meet a broad spectrum of needs. Selection is made to meet the specific requirements in strength, weld-ability, forming characteristics, finish, corrosion resistance, machinability, and sometimes other properties.

CLASSIFICATION—SEMIHOLLOW EXTRUDED SHAPES

Gap Width Inches

Class 1 Class 2

Group A Alloys1

Group B Alloys2

Group A Alloys1

Group B Alloys2

Ratio

0.040–0.062 2.0 1.5 2.0 1.0

0.063–0.124 3.0 2.0 2.5 1.5

0.125–0.249 3.5 2.5 3.0 2.0

0.250–0.499 4.0 3.0 3.5 2.5

0.500–0.999 4.0 3.5 3.5 2.5

1.000–1.999 3.5 3.0 3.0 2.0

2.000 and over 3.0 2.5 3.0 2.0

1Group A alloys are 1060, 1100, 1350, 3003, 5454, 6061, 60632Group B alloys are 2011, 2014, 2024, 5083, 5086, 5456, 7050, 7075

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The complete list of registered aluminum alloys is quite long, but in practice a few alloys are chosen repeatedly for extrusion because of their versatility and highly suitable characteristics. Extruders generally stock the three or four most frequently used alloys. When their specialized mar-kets justify it, individual companies include in their inven-tories additional alloys which will vary with the needs of their major customers. Thus, a substantial variety of extru-sion alloys is regularly available.

The 6000-series of aluminum alloys (those whose four digit registration numbers begin with a 6) is selected for nearly 75 percent of extrusion applications. Of those, alloys 6063 and 6061 are used most frequently.

Alloy 6063 is used for a broad range of solid and hollow products. It is easily welded, and it has a pleasing natural finish and excellent corrosion resistance. 6063 is used in architecture and in many moderate-stress applications.

Alloy 6061 is a good all-purpose extrusion alloy, combin-ing high mechanical properties with good corrosion resis-tance, weldability and machining characteristics. Alloy 6061 is used in many structural applications.

Many other alloys are used for extrusions, to meet par-ticular requirements. For example, to mention only a few:

Characteristics AlloysHigh strength 7050, 7075, 2014High corrosion 1100, 3003 resistanceHigh electrical 6101 conductivity

For further details, the designer should consult current alloys and temper tables and discuss specific needs with the extrusion supplier.

January 2005 III-37

Circumscribing Circle Size

One measurement of the size of an extrusion is the diameter of the smallest circle that will entirely enclose its cross-section—its “circumscribing circle.” This dimen-sion is one factor in the economics of an extrusion. In gen-

eral, extrusions are most economical when they fit within a medium-sized circumscribing circle that is, one with a diameter between one and ten inches.

The example shown here would be classified as a 3-to-4 in. circle size shape.

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7.3 Design Guidelines

Good Extrusion Design Practices

At this stage in the development of an extruded product, the designer has determined its functional shape and size, and considered appropriate tolerances, surface finishes and alloys.

Before proceeding, it makes sense to review the extrud-er’s available standard shapes. It may be possible to adapt a standard shape to the needs of the product, with little or no modification.

If a standard shape is not readily adaptable, the design can be completed as a custom shape perfectly suited to the requirements of the product.

Here are a few tips on good practices in custom-designing aluminum extrusions:

Specify the Most Appropriate Metal Thicknesses

Specify metal thicknesses that are just heavy enough to meet your structural requirements. Even in low stress areas, however, keep sufficient thickness to avoid risking distortion or damage. Some shapes tend to invite distortion during the extrusion process (such as a asymmetric profile or thin details at the end of a long flange). Such tendencies exert more influence on thin-walled shapes than on those with normal metal thickness.

Keep Metal Thickness as Uniform as Possible

Extrusion allows you to put extra metal where it is needed—in high-stress areas, for example—and still save material by using normal dimensions elsewhere in the same piece. Adjacent wall thickness ratios of less than 2-to-1 are extruded without difficulty. But large contrasts between thick and thin areas may create uneven conditions during extrusion. It is best to maintain near uniform metal thickness throughout a shape if possible. When a design combines thick and thin dimensions, streamline the transi-tions with a radius (a curve, rather than a sharp angle) at junctions where the thickness changes sharply. Rounded corners ease the flow of metal.

Visualize the Die and the Metal Flow

Remember what extrusion die does; while it lets metal flow through its shaped aperture, it must hold back metal all around that aperture against great force. When you design a shape for extrusion, you are simultaneously designing a die aperture and you must take extrusion forces and metal flow into account.

For example, a U-shaped channel in an extrusion corre-sponds to a solid “tongue” in the die, attached at only one end. Flexibility in this tongue can alter the aperture slightly under the pressure of extrusion; the deeper you make the channel, the longer you make the tongue and the more difficult it becomes to regulate the extruded dimensions. On the other hand, rounding corners at the base and tip

of the tongue can ease metal flow and so help to keep the extruded dimensions more uniform. Even corners rounded to only ⅙₄ in. radius can make extrusion easier.

Visualize the shape of the die that must produce your design, and try to minimize shapes that would weaken the die or impede metal flow.

Use “Metal Dimensions” for Best Tolerance

Dimensions measured across solid metal are easier to pro-duce to closer tolerances than those measured across a gap or angle. So rely on “metal dimension” as much as possible when designing close-fitted mating parts or other shapes requiring closer tolerances. Standard industry dimensional tolerances are entirely adequate for many applications, but special tolerances can be specified if necessary.

“An Open Space Dimension” is more difficult to hold to close tolerances.

A “Metal Dimension” can be extruded to close tolerances.

January 2005 III-39

Smooth All TransitionsTransitions should be

streamlined by a generous radius at any thick-thin junction.

Instead of This

Consider This

Keep Wall Thickness Uniform

The preceding shape can be further improved by maintaining uniform wall thickness.

In addition to using more metal, thick-thin junctions give rise to distortion, die breakage or surface defects on the extrusion.

Ribs Help Straightening Operation

Wide, thin sections can be hard to straighten after extrusion. Ribs help to reduce twisting, and to improve flatness.

Symmetry Preferred in Semi-Hollow Areas

When designing visualize the die and tongue that will be necessary to produce a semi-hollow shape. By keeping the void symmetri-cal you lessen the chances that the die tongue may break.

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7.4 Design For Assembly

Aluminum extrusions can be designed for joining by a wide variety of methods such as riveting, bolting, welding, brazing, soldering and adhesive bonding.

They can also be designed to fit, hook or snap together mating with melting parts. Hinges or slides can often by “designed-in” as integral parts of extrusions, eliminating the need for additional assembly and moving parts.

Eight types of extruded joints are discussed in this section:

• Nesting Joints• Interlocking Joints• Snap-Fit Joints• Three-Piece, Blind-Fastened Joints• Combination Joints• Slip-Fit Joints: Dovetails and Hinges• Key-Locked Joints• Screw Slots

Nesting Joints

Nesting joints, which include “lap joints” and “tongue-and-groove” joints, have mating elements that are shaped to be assembled with little or no self-locking action.

They serve primarily to align adjoining parts, and they usually depend on rivets, bolts, adhesives, confinement within a rigid frame, or other fasteners, to hold them together.

Lap joints, shown here, are the simplest nesting joints.

Interlocking Joints

The interlocking joint is, in effect, a modified tongue-and-groove. But instead of being straight, the two mating elements are curved and so cannot be assembled or (more to the point) disassembled by simple straight-line motion. They are assembled by a rotating motion and will not sepa-rate without a corresponding counter-rotation. As long as the parts are held in their assembled position, they strongly resist separation and misalignment in both the horizontal and the vertical directions.

The amount of rotation required for interlocking assem-bly depends on the geometry of the design. It can be made more or less than 45 degrees, as long as the design allows enough clearance for the required rotation.

Interlocking joints can be secured after assembly in at least five ways, all based on preventing counter-rotation.

• Fastening the elements to structural cross-members.• Restraining the assembly within a rigid frame.• Restraining the assembly with channel end-closures.• Fastening the joint with rivets, welds, adhesives or other

devices.• Providing a folding, locking flange as shown below.

January 2005 III-41

Snap-Fit Joints

A “snap-fit” or “snap-lock” joint is one which is self-locking and requires no additional fasteners to hold the joint together.

The mating parts of a snap-fit joint exert a cam action on each other, flexing until one part slips past a raised lip on the other part. Once past this lip, the flexed parts snap back to their normal shape and the lip prevents them from separating. After it is snapped together, this joint cannot be disassembled unintentionally.

The strength of this joint can be increased by apply-ing adhesive to the mating surfaces before assembly. Even short lengths of an adhesively bonded snap-fit joint cannot be easily slid apart.

Precise dimensions are critical in a snap-fit joint. The dimensions of a snap-fit joint should only be referenced on drawings. Experienced extrusion designers who are fully conversant with snap-fit production requirements can determine the precise final dimensions.

Screw Slots

Screw slots are often used to facilitate the assembly of aluminum extrusions. Standard screw slots are illustrated here and should always be used with self tapping screws.

The screw slot should be designed so that the area of the void and the metal thickness surrounding it is symmetrical about the center line of the gap.

The type F self tapping screw is recommended for use with the extruded screw slot. This screw has threads which approximate machine screw threads . . . plus a blunt point that will stay within the screw slot.

“Sheet metal” type screws are not recommended since their thread projects to the very point and thereby can “walk” through the slot opening.

Self Tapping Screw Type F Screw OD (in.)

A DIA. (in.)NC NF

4–401 4–481 0.120 0.099 ± 0.006

6–321 6–401 0.138 0.120 ± 0.006

8–32 8–36 0.164 0.147 ± 0.007

10–24 10–32 0.190 0.169 ± 0.007

12–24 12–28 0.216 0.190 ± 0.007

¼ × 20 ¼ × 28 0.250 0.228 ± 0.007

1Not recommended for incorporation on inside wall of hollow or semihollow shapes.2The recommended location for screw slots on the inside of hollow or semihollow shapes is at the corners. When not located at cor-ners dimension “B” must be at least 0.250 in.

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8.0 Prevention of Corrosion

A great deal of technology and experience exist for suc-cessful prevention of corrosion in assemblies and struc-tures. Documentation of the technology and experience is scattered throughout the open literature. The following information has been adapted from Reference 28.

The seven types of measures listed below can be used individually or in combinations to address aluminum cor-rosion prevention.

• Alloy and temper selection• Design• Coatings and sealants• Inhibitors• Cathodic protection• Enhanced protective oxide films• Modification of environment

The following paragraphs in this section will provide guidelines for each of these types of measures. It is impor-tant to note that these guidelines are general in nature and may not apply to all cases.

Alloy and temper selection are based on many factors. From the standpoint of corrosion prevention, the selection process should consider the following guidelines. Alloys of the 1XXX, 3XXX, 5XXX, and 6XXX series generally have very good corrosion resistance in natural environ-ments and can be used without supplemental corrosion protection. Temper selection for the 1XXX, 3XXX, and 6XXX series alloys may be based on other-than corrosion factors. Temper selection for the 5XXX series alloys con-taining up to 3% magnesium (e.g. 5005, 5050, 5052, and 5454) may be based on other-than corrosion factors. How-ever, temper selection for the 5XXX series alloys contain-ing more than 3% magnesium (e.g. 5456, 5083, and 5086) for applications with service temperatures exceeding 150oF or in marine environments should be limited to –H116 or –H321 as a precaution against intergranular forms of cor-rosion. Alloys of the 2XXX and 7XXX series alloys have poor corrosion resistance and require supplemental corro-sion protection. Temper selection for the 2XXX and 7XXX series alloys can be a significant factor in the exfoliation and stress corrosion resistances.

During the design phase of a project utilizing aluminum, a number of factors that may impact on corrosion resis-tance can be conveniently considered. Often such consid-erations as part of this phase are much more cost effective than they are after the design is finalized. While a number of the following factors can, if adopted, prevent corrosion, it is recognized that there are times that such situations are unavoidable. Consequently, the subsequent paragraphs will discuss remedial actions.

• Avoid contacts with dissimilar metals (galvanic corrosion prevention discussed below).

• Avoid crevices, especially at joints (crevice corrosion prevention discussed below).

• Avoid skip welding by using continuous welding. • Avoid standing fluid and poultice catchments.• Avoid placement of absorbent materials, such as gaskets,

insulation, and soundproofing, against aluminum.• Avoid direct impingement by fluid stream, especially

sharp pipe bends.• Avoid heat transfer hot spots.• Avoid corrosive conditions when locating and orienting

equipment and joints.• Avoid sharp edges when coating will be used.

During the design phase of a project that involves alumi-num, one of the key areas for corrosion prevention consider-ation is joints between parts. Joints may involve aluminum and other metallic materials. Galvanic corrosion can occur when aluminum is joined to other metals and the joint is cov-ered by an aqueous, conductive fluid. Joints made in such a way that they are dry or the dissimilar metals are not electri-cally connected, even by a remote path, will be free from galvanic corrosion. Because galvanic couples are inevitable, it is important to be able to predict which metal will cor-rode (anode) in a given couple. A common tool for making this prediction is the galvanic series, which is environment- specific (see Table 8.0-1 for example in sodium chloride solution). In Table 8.0-1 the metal in a galvanic couple that is toward the active end of the galvanic series will corrode, and the other metal in the couple which is toward the noble end of the series will not corrode. It is important to remember that the galvanic series is useful only as a predictive tool as to location of corrosion in a galvanic couple, not rate of cor-rosion. However, as a general suggestion, selection of couple members that are close together in the galvanic series will tend to minimize galvanic corrosion. Based on the galvanic series and experience gained over many years, aluminum can be coupled to magnesium, zinc, cadmium, and passive stainless steel in most environments without the threat of galvanic corrosion. In most other galvanic couples alumi-num will experience galvanic corrosion.

In cases where dissimilar metals must be joined, creat-ing an undesirable galvanic couple, there are several steps that can be taken to minimize the galvanic corrosion. The exposed area of the more noble or cathodic metal should be minimized by design and by application of protective coatings (e.g. paint, gasket, tape, etc.). At bolted or riv-eted galvanic joints (e.g. aluminum to steel) the fasten-ers (the smaller exposed surface area) should be the more noble material, such as steel or 3XX series stainless steel rather than aluminum. A further step with steel would be to coat the fasteners with an organic coating or with zinc (galvanizing).

In cases where galvanic couples have only a few points of electrical contact, it may be possible to control corrosion

January 2005 III-43

by electrical insulation. Insulation can be effective only when all points of electrical contact are broken. Insulation can be achieved by inserting nonmetallic, non-wicking bushings, gaskets, sleeves, tapes, etc., into all aluminum to other metal joints. Such insulation is difficult to achieve in large, complex structures where remote electrical paths may exist.

Table 8.0-1GALVANIC SERIES IN SODIUM

CHLORIDE SOLUTION (similar to sea water)

Active Magnesium Zinc Aluminum alloy 7072 (Alcladding) 5XXX aluminum alloys 7XXX structural aluminum alloys 1XXX, 3XXX, 6XXX aluminum alloys Cadmium 2XXX aluminum alloys Iron and steel Lead Tin Brass Copper Stainless steel (3XX, passive)Noble Nickel

In fluid-carrying systems where piping of aluminum and other metals must be joined, a thick-walled, replace-able aluminum nipple should be used at the joint. In closed loop mixed metal fluid-carrying systems, such as automo-tive cooling systems, it may be possible to control galvanic corrosion by using a mixed metal corrosion inhibitor pack-age. Mixed metal fluid-carrying systems, which include aluminum and cannot be treated with inhibitors, should not contain copper-based materials.

Crevices are inevitable in the assembly of structures. When crevices trap or retain fluids, accelerated corrosion

may result. Often the location and orientation of crevices (joints) can be considered during design in order to mini-mize moisture ingress and retention. The use of adhesives, caulks, nonabsorbent gaskets, and sealants can prevent the ingress of moisture into crevices. Continuous welds are desirable because they leave no crevices, whereas skip or intermittent welds are undesirable because they do leave crevices. A type of crevice corrosion known as poultice corrosion can occur under deposited materials, such as mud, paper, or cloth. Poultice corrosion can often be mini-mized by avoiding catchments and pockets during design of a structure.

When surface treatments, such as anodizing, organic coating, or plating, are used on aluminum to provide con-sistent appearance or improved corrosion resistance, the quality of the treatment is extremely important. If flaws or points of damage occur which expose the substrate alumi-num surface, accelerated localized pitting corrosion may result. All steps of the treatment process must be controlled in order to obtain the desired durability.

For aluminum structures that are buried or immersed in aqueous environments, it may be feasible to control corro-sion by application of the electrochemical process known as cathodic (noncorroding) electrode in an electrochemi-cal corrosion cell. Expert assistance should be utilized in applying this corrosion control process.

In cases involving 2XXX and 7XXX series aluminum alloys, consideration should be given to stress corrosion cracking (SCC). SCC can be a problem when residual or assembly stresses can occur in the through-the-thickness or short transverse direction. This can be minimized by giving consideration to temper selection, residual stresses from fabrication (e.g. forming, machining, and thermal treat-ments), and fitup details.

Thus, when aluminum’s inherently good corrosion resis-tance is compromised by environmental conditions, galvanic couples, crevices, etc., there are approaches available to pre-vent problems.

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9.0 Fire Protection

There is limited information available on the behavior of aluminum in fires. Some of the similarities and differ-ences in the behavior of aluminum and steel members are provided below.

1. Both aluminum and steel members are noncombus-tible.

2. The cross sectional areas of the aluminum members usually will be about 40% larger than those of steel.

3. The thermal conductivity of aluminum is about 2.7 times that of steel.

4. Strength properties of aluminum degrade at much lower temperature compared to those of steel.

All of the above items have an effect on the relative per-formance of the two materials in a fire. Generally the alu-minum parts would be expected to reach a lower tempera-ture but the strength properties relative to those at room temperature would be more degraded compared to those for steel. The aluminum members thus need more insula-tion compared to steel members.

Some guidance has been published on fire protection for aluminum members (29). The criteria for establishing the amounts of fire protection for aluminum were as follows.

1. To ensure strengths at least equal to the design allow-able stresses during the test exposure, the limiting temperature for aluminum would be 500oF.

2. To ensure that there will be no substantial change in properties at room temperature as a result of the test exposure, the limiting temperature would be 375oF.

Light weight vermiculate plaster was used in the tests and specimens were as indicated on Figure 9.0-1. The rela-tive thicknesses of protection required for various periods of time are shown below (29).

RELATIVE THICKNESS OF VERMICULITE REQUIRED FOR FIRE PROTECTION OF STRUCTURAL ALUMINUM MEMBERS

Fire Protection Period, hours RatioThickness for Aluminum Member

Thickness for Steel Member

1 1.7

2 1.9

3 1.8

4 1.7

Numbers designate materials as follows:(1) 8 WF 10.72 column(2) Vermiculite plaster(3) Lath(4) Keystone key corner beads

Figure 9.0-1SPECIMENS FOR FIRE PROTECTION TESTS

January 2005 III-45

10.0 References

The following references apply the information presented in Sections 3.0 through 9.0 of this part of the manual.

1. Sharp, Maurice L., Behavior and Design of Aluminum Structures, McGraw-Hill Inc., New York, New York, 1993.

2. The Aluminum Association Position on Fracture Tough-ness Requirements and Quality Control Testing 1987, T-5, Aluminum Association, Washington, DC, 1987.

3. Menzemer, Craig C., Fatigue Behavior of Welded Alu-minum Structures, Dissertation in partial fulfillment of the requirements for the degree of Doctor of Philoso-phy, Lehigh University, Bethlehem, PA, July 1992.

4. Galambos, Theodore V., editor, Guide to Stability Design Criteria for Metal Structures, 5th edition John Wiley & Sons, 1998.

5. Torsional Analysis of Steel Members, American Insti-tute of Steel Construction, Chicago, IL, 1983.

6. Davis, J.M. and Bryan, E.R., Manual of Stressed Skin Diaphragm Design, Granada Publishing, Great Britain, 1982.

7. Sooi, Took Kowng, “Behavior of Component Elements of Aluminum Members,” Research Report No. 93-1, Teoman Peköz, Project Director, Cornell University, 1993.

8. Sharp, Maurice L., Nordmark, Glenn E. and Menzemer, Craig C., Fatigue Design of Aluminum Components and Structures, McGraw-Hill, Inc., New York, New York, 1996.

9. Marsh, Cedric, “Tear-out Failures of Bolt Groups,” Technical Notes, Journal of the Structural Division, Proceedings of the American Society of Civil Engi-neers, October, 1979.

10. Structural use of Aluminum Part I. Code of Practice for Design, British Standard BS 8118, 1991.

11. Metal Curtain Wall Fasteners, AAMA TIR-A9-91 (with 2000 adendum), American Architectural Manu-facturers Association, Schaumberg, IL.

12. Welding Aluminum, Theory and Practice, Aluminum Association, Washington, DC, 2002.

13. Angermayer, Karl, Structural Aluminum Design, CPE Corporation, Richmond, VA, 1987.

14. Structural Welding Code-Aluminum, AWS D1.2/D1.2M: 2003, American Welding Society, Miami, FL, 2003.

15. Adhesives, 4th Edition, D.A.T.A., Inc., 1986.

16. Shields, J., Adhesives Handbook, CRC Press, 1970.

17. Thrall, Edward W. and Shannon, Raymond W., Adhe-sive Bonding of Aluminum Alloys, Marcel Dekkar, New York, New York, 1984.

18. Kinloch, A.J., Adhesion and Adhesives, Science and Technology, Chapman and Hall, New York, NY, 1987.

19. Hart-Smith, A.J., “Design of Adhesively Bonded Joints,” Joining Fibre-Reinforced Plastics, F.L. Mathews, editor, Elsevier Applied Science Publishing, New York, NY, 1987.

20. Annual Book of ASTM Standards, Vol. 08.01, “Plas-tics,” American Society for Testing and Materials, Philadelphia, 1992.

21. Drieger, R.B., “Analyzing Joint Stresses Using an Exten-someter,” Adhesive Age, pp 26-28, October, 1985.

22. Annual Book of ASTM Standards, Vol. 15.06, “Adhe-sives,” American Society for Testing and Materials, Philadelphia, PA, 1992.

23. Minford, J. Dean, Handbook of Aluminum Bonding Technology and Data, Marcel Dekker, Inc., New York, 1993.

24. Preliminary European Recommendations Sandwich Panels, Part I Design and Part II Good Practice, ECCS Technical Committee 7-Working Group 7.4-Design and Application of Sandwich Panels, 1991.

25. Davis, J.M., “Sandwich Panels,” Thin-Walled Struc-tures, 16 (1993), pp. 179-198.

26. Structural Performance, Poured and Debridged Fram-ing Systems, AAMA, TIR-A8-90, Schaumberg, IL.

27. The Aluminum Extrusion Manual, Aluminum Asso-ciation, Washington, DC and the Aluminum Extruders Council, 1998.

28. Aluminum—Properties and Physical Metallurgy, Edited by John E. Hatch, American Society for Metals, 1984, pp. 300-309.

29. Kaufman, J.G. and Kasser, R.C., “Fire Protection for Aluminum Alloy Structural Shapes,” Civil Engineer-ing, March, 1963.

30. Sharp, M.L., Nordmark, G.E., and Menzemer, C.C., “Hot-Spot Fatigue Design of Aluminum Joints,” Pro-ceedings of the 1996 ASCE Materials Engineering Conference, Washington, DC.

31. Kissell, J.R. and Ferry, R.L., “Aluminum Friction Con-nections”, Proceedings of Structures Congress XV, April, 1997.

32. Kissell, J.R. and Ferry, R.L., Aluminum Structures, 2nd edition, John Wiley, New York, 2002.


PART IV

Materials



January 2005 IV-3

IVMaterials

TABLE OF CONTENTS

1.0 Features of Aluminum-General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

2.0 Features of Aluminum/Metallurgical Aspects . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

3.0 Designation System for Wrought Aluminum and Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63.1 Aluminum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.2 Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.3 Experimental Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73.4 National Variations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

4.0 Cast Aluminum and Aluminum Alloy Designation System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74.1 Aluminum Castings and Ingot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74.2 Aluminum Alloy Castings and Ingot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74.3 Experimental Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

5.0 Effect of Alloying Elements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

6.0 Temper Designation System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86.1 Basic Temper Designations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96.2 Subdivision of Basic Tempers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

6.2.1 Subdivisions of H Temper: Strain-hardened . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96.2.2 Subdivisions of T Temper: Thermally Treated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

6.3 Variations of O Temper: Annealed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

Table 1 Comparative Characteristics and Applications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13Table 2 Historical Foreign Alloy Designations and Similar AA Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

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1.0 Features of Aluminum-General

Light Weight – The specific gravity of aluminum is about 2.7 and its mass (“weight”) is roughly 35% that of iron and 30% that of copper.

A Range of Useful Strengths – The usefulness of “commercially pure” aluminum as a structural material is limited by its tensile strength of about 13 ksi. By work-ing the metal, such as by cold rolling, its strength can be approximately doubled. Much larger increases in strength are obtained, however, by alloying aluminum with small percentages of one or more other metals such as manganese, silicon, copper, magnesium or zinc. Many alloys can also be strengthened by heat treatments so that tensile strengths approaching 100 ksi are possible.

Aluminum and its alloys lose part of their strength at elevated temperatures, although some alloys retain good strength at temperatures from 300 to 400oF (150 to 200oC). At sub-freezing temperatures, however, their strength increases without loss of ductility so that aluminum is a particularly useful metal for low temperature applications.

Good Corrosion Resistance – When aluminum sur-faces are exposed to the atmosphere, a thin, invisible oxide skin forms immediately which protects the metal from further oxidation. This self-protecting characteristic gives aluminum its high resistance to corrosion. Unless exposed to some substance or condition which destroys this protec-tive oxide coating, the metal remains resistant to corrosion. Aluminum is highly resistant to weathering, even in many industrial atmospheres which often corrode other metals. It is also resistant to many acids.

Direct contact with certain other metals should be avoided in the presence of an electrolyte: otherwise, gal-vanic corrosion of the aluminum may take place in the vicinity of the contact area. Where these other metals must be fastened to aluminum, the use of a protective insulating coating is recommended.

High Electrical Conductivity – Aluminum is one of the two common metals having electrical conductivity high enough for use as an electric conductor. The conductivity of electric conductor grade (Alloy 1350) is about 62% of the International Annealed Copper Standard. Because alu-minum has less than one third the specific gravity of cop-per, a kilogram of aluminum will go about twice as far as a kilogram of copper when used for this purpose.

High Thermal Conductivity – The high thermal con-ductivity of aluminum is important wherever the transfer of thermal energy from one medium to another is involved, either heating or cooling. Thus, aluminum heat exchangers are widely used in automotive air conditioning systems and aluminum radiators are also becoming the standard for this application.

Useful Reflector of Radiant Energy – Aluminum is an excellent reflector of radiant energy through the entire range of wave lengths from ultraviolet, through the visible spectrum, to infrared and heat waves. It also reflects elec-tromagnetic wave lengths in the radio and radar range. Alu-minum has a light reflectivity of over 80% which has led to its wide use in automotive trim and in lighting fixtures.

Nonmagnetic and Resistance to Sparking – These properties are of great importance for some uses. Nonmag-netic properties of aluminum make it useful in electronics, as well as delicate moving parts, where various compo-nents must be shielded from electromagnetic disturbances that would upset their operation. The advantages of using a material of low sparking sensitivity around flammable or explosive substances are obvious.

Ease of Fabrication – The forming and fabrication characteristics of aluminum are perhaps among its most important assets. Often it can compete successfully with less expensive materials having a lower degree of work-ability. Aluminum can be rolled to any desired thickness down to foil thinner than paper: it can be stamped, drawn, spun or roll-formed. Aluminum may also be hammered or forged. Aluminum wire may be stranded into cable of any desired size and type. There is almost no limit to the differ-ent shapes in which the metal may be extruded.

Good Machinability – The ease and speed with which many aluminum alloys may be machined is one of the important factors contributing to the low cost of finished aluminum parts. The metal may be turned, milled, bored, or machined at the maximum speeds of which most machines are capable. An example of this is aluminum rod and bar employed in the high speed manufacture of parts of auto-matic screw machines.

Joining Flexibility – Almost any joining method is applicable to aluminum: riveting, welding, brazing or sol-dering. A wide variety of mechanical aluminum fasteners simplifies the assembly of many products. Adhesive bond-ing of aluminum parts is widely employed in aircraft com-ponents and is being used increasingly for automotive body panels.

Adaptability to Finishing – Aluminum needs no pro-tective coating for many applications. Mechanical finishes such as polishing, sandblasting or wire brushing will be sufficient to meet many needs. In many instances, the sur-face finish supplied is entirely adequate without further fin-ishing. Where the plain aluminum surface does not suffice, or where decorating or additional protection is required, a wide variety of surface finishes such as chemical, electro-chemical and paint finishes may be applied.

Chemical conversion coatings are available for addi-tional corrosion protection. They also provide an excellent base for paint. Electroplating procedures have been devel-

IV-6 January 2005

oped to give aluminum an attractive, durable finish. Anodic coatings are used for both decorative and functional appli-cations. Hardcoat anodized aluminum surfaces can provide wear resistance similar to case hardened steel. Vitreous enamels have also been developed for aluminum.

Environmental Compatibility-Recycling – Aluminum is very suitable for recycling. Recycled aluminum makes up more than 30% of the aluminum used in the United States, and its use saves nearly 95% of the energy needed for production from bauxite. Life cycle costs should be considered when designing with aluminum versus other materials. In general, aluminum has the advantage of hav-ing a high recycling value.

2.0 Features of Aluminum/ Metallurgical Aspects

In high purity form aluminum is soft and ductile and has relatively low strength. Most commercial uses, however, require greater strength than pure aluminum affords. This is achieved in aluminum first by the addition of other elements to produce various alloys, which singly or in combination impart strength to the metal. The numerical alloy desig-nation system adopted by the aluminum industry is based on the principal alloying elements in each class of alloy. Further strengthening is possible by means that classify the alloys roughly into two categories: non-heat-treatable and heat-treatable.

Non-heat-treatable Alloys – The initial strength of alloys in this group depends upon the hardening effect provided by manganese, silicon, iron and magnesium, singly or in vari-ous combinations. The non-heat-treatable alloys are usually designated as the 1xxx, 3xxx, 4xxx or 5xxx series. Since these alloys are work-hardenable, strengthening is achieved by various degrees of cold working, denoted by the “H” series of tempers. Alloys containing appreciable amounts of magnesium when supplied in strain-hardened tempers are usually given a final elevated-temperature treatment called stabilizing to insure stability of properties.

Heat-treatable Alloys – The initial strength of alloys in this group is enhanced by the addition of alloying elements such as copper, magnesium, zinc, silicon and lithium. Since these elements singly or in various combinations show increasing solid solubility in aluminum with increas-ing temperature, it is possible to subject them to thermal treatments which will cause pronounced strengthening. These alloys are usually designated as the 2xxx, 6xxx and 7xxx series.

The first step, called heat treatment or solution heat treat-ment, is an elevated-temperature process designed to put the soluble element or elements in solid solution. This is followed by rapid quenching, usually in water, which momentarily “freezes” the structure and renders the alloy very workable for a period of time. For a few cases some fabricators retain

this more workable structure by storing the alloys at below freezing temperatures until they are ready to form them. At room temperature alloys age with time which changes their mechanical properties. This change varies with alloy and is not typically relied on in design.

By heating for a controlled time at slightly elevated tem-peratures, even further strengthening is possible and prop-erties are stabilized. This is called artificial aging or pre-cipitation hardening. By the proper combination of solu-tion heat treatment, quenching, cold working and artificial aging, the highest strengths are obtained.

Clad Alloys – The heat-treatable alloys in which cop-per or zinc are major alloying constituents are less resistant to corrosive attack than the majority of non-heat-treatable alloys. To increase the corrosion resistance of these alloys in sheet and plate form they are often clad with high-purity aluminum, a low magnesium-silicon alloy, or an alloy containing 1% zinc. The cladding, usually from 2.5 to 5% of the total thickness on each side, not only protects the composite due to its own inherently excellent corrosion resistance but also exerts a galvanic effect which further protects the core material.

Special composites may be obtained, such as clad non-heat-treatable alloys, for extra corrosion protection, for braz-ing purposes, or for special surface finishes. Some alloys in wire and tubular form are clad for similar reasons, and on an experimental basis extrusions also have been clad.

Annealing Characteristics – All wrought aluminum alloys are available in annealed form. In addition, it may be desirable to anneal an alloy from any other initial temper, after working, or between successive stages of working such as in deep drawing.

3.0 Designation System for Wrought Aluminum and Aluminum Alloys

The Aluminum Association is the registrar for the com-position designation system under ANSI H35.1.

Designation No.Aluminum, 99.00% and greater 1xxxAluminum alloys grouped by major alloying elements Copper 2xxx Manganese 3xxx Silicon 4xxx Magnesium 5xxx Magnesium and Silicon 6xxx Zinc 7xxx Other element 8xxxUnused series 9xxx

A system of four-digit numerical designations is used to identify wrought aluminum and wrought aluminum alloys. The first digit indicates the alloy group. The last two dig-its identify the aluminum alloy or indicate the aluminum

January 2005 IV-7

purity. The second digit indicates modifications of the orig-inal alloy or impurity limits.

3.1 Aluminum

In the 1xxx group for minimum aluminum purities of 99.00% and greater, the last two of the four digits in the designation indicate the minimum aluminum percentage. These digits are the same as the two digits to the right of the decimal point in the minimum aluminum percentage when it is expressed to the nearest 0.01%. The second digit in the designation indicates modification in impurity lim-its. If the second digit in the designation is zero, it indi-cates unalloyed aluminum having natural impurity limits; integers 1 through 9, which are assigned consecutively as needed, indicate special control of one or more individual impurities or alloying elements.

3.2 Aluminum Alloys

In the alloy groups 2xxx through 8xxx, the last two of the four digits in the designation have no special significance but serve only to identify the different alloys in the group. The second digit in the alloy designation indicates alloy modifications. If the second digit in the designation is zero, it indicates the original alloy; integers 1 through 9, which are assigned consecutively, indicate alloy modifications.

3.3 Experimental Alloys

Experimental alloys are also designated in accordance with this system but they are indicated by the prefix X. The prefix is dropped when the alloy is no longer experimental.

During development and before they are designated as experimental, new alloys are identified by serial numbers assigned by their originators. Use of the serial number is discontinued when the X number is assigned.

3.4 National Variations

National variations of wrought aluminum and wrought aluminum alloys registered by another country in accor-dance with this system are identified by a serial letter fol-lowing the numerical designation. The serial letters are assigned internationally in alphabetical sequence starting with A but omitting I, O, and Q.

A national variation has composition limits which are similar but not identical to those registered by another country.

4.0 Cast Aluminum and Aluminum Alloy Designation System

Designation No.Aluminum, 99.00% and greater 1xx.xAluminum alloys grouped by major alloying elements Copper 2xx.x Silicon, with Copper

and/or Magnesium3xx.x

Silicon 4xx.x Magnesium 5xx.x Zinc 7xx.x Tin 8xx.x Other element 9xx.xUnused series 6xx.x

A system of four-digit numerical designations is used to identify aluminum and aluminum alloys in the form of castings and foundry ingot. The first digit indicates the alloy group. The second two digits identify the aluminum alloy or indicate the aluminum purity. The last digit, which is separated from the others by a decimal point, indicates the product form: i.e., casting or ingot. A modification of the original alloy or impurity limits is indicated by a serial letter before the numerical designation. The serial letters are assigned in alphabetical sequence starting with A but omitting I, O, Q, and X, the X being reserved for experi-mental alloys.

4.1 Aluminum Castings and Ingot

In the 1xx.x group for minimum aluminum purities of 99.00% and greater, the second two of the four digits in the designation indicate the minimum aluminum percentage.

These digits are the same as the two digits to the right of the decimal point in the minimum aluminum percentage when it is expressed to the nearest 0.01%. The last digit, which is to the right of the decimal point, indicates the product form: 1xx.0 indicates castings, and 1xx.1 indicates ingot.

4.2 Aluminum Alloy Castings and Ingot

In the 2xx.x through 9xx.x alloy groups the second two of the four digits in the designation have no special sig-nificance but serve only to identify the different aluminum alloys in the group. The last digit, which is to the right of the decimal point, indicates the product form: xxx.0 indi-cates castings, xxx.1 indicates ingot.

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4.3 Experimental Alloys

Experimental alloys are also designated in accordance with this system but they are indicated by the prefix X. The prefix is dropped when the alloy is no longer experimental.

During development and before they are designated as experimental, new alloys are identified by serial numbers assigned by their originators. Use of the serial number is discontinued when the X number is assigned.

5.0 Effect of Alloying Elements

1xxx series – Aluminum of 99% or higher purity has many applications, especially in the electrical and chemi-cal fields. These alloys are characterized by excellent corro-sion resistance, high thermal and electrical conductivity, low mechanical properties and excellent workability. Moderate increases in strength may be obtained by strain-hardening. Iron and silicon are the major impurities.

2xxx series – Copper is the principal alloying element in this group. These alloys require solution heat-treatment to obtain optimum properties. In the heat treated and natu-rally aged condition alloys have mechanical properties that are similar to, and sometimes exceed, those of mild steel. Artificial aging can be employed to further increase the mechanical properties. This treatment materially increases tensile yield strength, with attendant loss in elongation; its effect on tensile (ultimate) strength is not as great. 2xxx series alloys have been used extensively for aircraft com-ponents and for cryogenic tanks.

3xxx series – Manganese is the major alloying element of alloys in this group, which are generally non-heat-treatable. Because only a limited percentage of manganese, up to about 1.5%, can be effectively added to aluminum, it is used as a major element in only a few instances. One of these, however, is the popular alloy 3003, which is widely used as a general-purpose alloy for moderate strength applications requiring good workability. Alloy 3004 which contains magnesium as well as manganese for higher strength, is used widely for beverage container bodies.

4xxx series – The major alloying element of this group is silicon, which can be added in sufficient quantities to cause substantial lowering of the melting point without pro-ducing brittleness in the resulting alloys. For these reasons aluminum-silicon alloys are used in welding wire and as brazing alloys where a lower melting point than that of the parent metal is required. Most alloys in this series are non-heat-treatable. When used in welding heat-treatable alloys they will pick up some of the alloying constituents of the latter and respond to heat treatment to a limited extent.

5xxx series – Magnesium is one of the most effective and widely used alloying elements for aluminum. When it is used as the major alloying element or with manganese, the result is a moderate to high strength non-heat-treatable

alloy. Magnesium is considerable more effective than man-ganese as a hardener, about 0.8% magnesium being equal to 1.25% manganese, and it can be added in considerably higher quantities. Alloys in this series possess good welding characteristics and good resistance to corrosion in marine atmospheres. These alloys are used in cryogenic applica-tions. Certain limitations, however, should be placed on the amount of cold work and the safe operating temperature permissible for the higher magnesium content alloys (over about 3.0%) is about 150°F (66°C) to avoid susceptibility to intergranular forms of corrosion.

6xxx series – Alloys in this group contain silicon and magnesium in appropriate proportions to form magnesium silicide, thus making them heat-treatable. A major alloy in this series is 6061, one of the most versatile of the heat treatable alloys. Though less strong than most of the 2000 or 7000 alloys, the magnesium-silicon (or magnesium silicide) alloys possess good formability, weldability and corrosion resistance, with medium strength. Alloys in this heat-treatable group may be formed in the T4 temper (solu-tion heat-treated but not artificially aged) and then reach full T6 properties by artificial aging.

7xxx series – Zinc is the major alloying element and when coupled with a smaller percentage of magnesium, results in heat-treatable alloys of very high strength. Other elements such as copper and chromium may also be added. Alloys in this series include those used for automotive bumpers and bumper reinforcements and aircraft applica-tions. Alloys without copper are weldable and have been used for armor plate.

6.0 Temper Designation System⑥

The temper designation system is used for all forms of wrought and cast aluminum and aluminum alloys except ingot. It is based on the sequences of basic treatments used to produce the various tempers. The temper designation follows the alloy designation, the two being separated by a hyphen. Basic temper designations consist of letters. Sub-divisions of the basic tempers, where required, are indicated by one or more digits following the letter. These designate specific sequences of basic treatments, but only operations recognized as significantly influencing the characteristics of the product are indicated. Should some other variation of the same sequence of basic operations be applied to the same alloy, resulting in different characteristics, then addi-tional digits are added to the designation.

⑥ Temper designations conforming to this standard for wrought aluminum and wrought aluminum alloys, and aluminum alloy castings may be registered with the Aluminum Association provided: (1) the temper is used or is available for use by more than one user, (2) mechanical property limits are registered, (3) the characteristics of the temper are significantly different from those of all other tempers that have the same sequence of basic treatments and for which designations already have been assigned for the same alloy and product, and (4) the following are also registered if characteristics other than mechanical properties are considered significant: (a) test methods and limits for the char-acteristics or (b) the specific practices used to produce the temper.

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6.1 Basic Temper Designations

F as fabricated. Applies to the products of shaping pro-cesses in which no special control over thermal con-ditions or strain hardening is employed. For wrought products, there are no mechanical property limits.

O annealed. Applies to wrought products that are annealed to obtain the lowest strength temper, and to cast products that are annealed to improve ductility and dimensional stability. The O may be followed by a digit other than zero.

H strain-hardened (wrought products only). Applies to products that have their strength increased by strain-hardening, with or without supplementary thermal treat-ments to produce some reduction in strength. The H is always followed by two or more digits.

W solution heat-treated. An unstable temper appli-cable only to alloys that spontaneously age at room temperature after solution heat-treatment. This des-ignation is specific only when the period of natural aging is indicated; for example: W ½ hr.

T thermally treated to produce stable tempers other than F, O, or H. Applies to products that are ther-mally treated, with or without supplementary strain-hardening, to produce stable tempers. The T is always followed by one or more digits.

6.2 Subdivisions of Basic Tempers

6.2.1 Subdivision of H Temper: Strain-hardened

6.2.1.1 The first digit following the H indicates the spe-cific combination of basic operations, as follows:

H1 strain-hardened only. Applies to products that are strain-hardened to obtain the desired strength with-out supplementary thermal treatment. The number following this designation indicates the degree of strain-hardening.

H2 strain-hardened and partially annealed. Applies to products that are strain-hardened more than the desired final amount and then reduced in strength to the desired level by partial annealing. For alloys that age-soften at room temperature, the H2 tempers have the same minimum ultimate tensile strength as the corresponding H3 tempers. For other alloys, the H2 tempers have the same minimum ultimate tensile strength as the corresponding H1 tempers and slightly higher elongation. The number follow-ing this designation indicates the degree of strain-hardening remaining after the product has been partially annealed.

H3 strain-hardened and stabilized. Applies to products that are strain-hardened and whose mechanical prop-erties are stabilized either by a low temperature ther-mal treatment or as a result of heat introduced during fabrication. Stabilization usually improves ductility. This designation is applicable only to those alloys that, unless stabilized, gradually age-soften at room temperature. The number following this designation indicates the degree of strain-hardening remaining after the stabilization treatment.

H4 strain-hardened and lacquered or painted. Applies to products which are strain-hardened and which are subjected to some thermal operation during the sub-sequent painting or lacquering operation. The num-ber following this designation indicates the degree of strain-hardening remaining after the product has been thermally treated, as part of painting/lacquering cure operation. The corresponding H2X or H3X mechani-cal property limits apply.

6.2.1.2 The digit following the designation H1, H2, H3, and H4 indicates the degree of strain-hardening as identi-fied by the minimum value of the ultimate tensile strength. Numeral 8 has been assigned to the hardest tempers nor-mally produced. The minimum tensile strength of tempers HX8 may be determined from Table 1 and is based on the minimum tensile strength of the alloy in the annealed tem-per. However, temper registrations prior to 1992 that do not conform to the requirements of Table 1 shall not be revised and registrations of intermediate or modified tempers for such alloy/temper systems shall conform to the registration requirements that existed prior to 1992.

Table 1 Minimum tensile strength Increase in tensile strength in annealed temper to HX8 temper ksi ksi up to 6 8 7 to 9 9 10 to 12 10 13 to 15 11 16 to 18 12 19 to 24 13 25 to 30 14 31 to 36 15 37 to 42 16 43 and over 17

Tempers between O (annealed) and HX8 are designated by numerals 1 through 7.

—Numeral 4 designates tempers whose ultimate tensile strength is approximately midway between that of the O temper and that of the HX8 tempers;

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—Numeral 2 designates tempers whose ultimate tensile strength is approximately midway between that of the O temper and that of the HX4 tempers;

—Numeral 6 designates tempers whose ultimate tensile strength is approximately midway between that of the HX4 tempers and that of the HX8 tempers;

—Numerals 1, 3, 5 and 7 designate, similarly, tempers intermediate between those defined above.

—Numeral 9 designates tempers whose minimum ultimate tensile strength exceeds that of the HX8 tem-pers by 2 ksi or more.

The ultimate tensile strength of the odd numbered interme-diate (-HX1, -HX3, -HX5, and HX7) tempers, determined as described above, shall be rounded to the nearest multiple of 0.5 ksi.

6.2.1.3 The third digit,⑦ when used, indicates a variation of a two-digit temper. It is used when the degree of control of temper or the mechanical properties or both differ from, but are close to, that (or those) for the two-digit H tem-per designation to which it is added, or when some other characteristic is significantly affected. (See Appendix for assigned three-digit H tempers.) NOTE: The minimum ulti-mate tensile strength of a three-digit H temper must be at least as close to that of the corresponding two-digit H tem-per as it is to the adjacent two-digit H tempers. Products in the H temper whose mechanical properties are below H__1 shall be variations of H__1.

6.2.2 Subdivision of T Temper: Thermally Treated

6.2.2.1 Numerals 1 through 10 following the T indicate specific sequences of basic treatments, as follows:⑧

T1 cooled from an elevated temperature shaping process and naturally aged to a substantially sta-ble condition. Applies to products that are not cold worked after cooling from an elevated temperature shaping process, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits.

T2 cooled from an elevated temperature shaping pro-cess, cold worked, and naturally aged to a substan-tially stable condition. Applies to products that are cold worked to improve strength after cooling from an elevated temperature shaping process, or in which

the effect of cold work in flattening or straightening is recognized in mechanical property limits.

T3 solution heat-treated,⑨ cold worked, and natu-rally aged to a substantially stable condition. Applies to products that are cold worked to improve strength after solution heat-treatment, or in which the effect of cold work in flattening or straightening is recognized in mechanical property limits.

T4 solution heat-treated⑨ and naturally aged to a substantially stable condition. Applies to products that are not cold worked after solution heat-treatment, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits.

T5 cooled from an elevated temperature shaping pro-cess and then artificially aged. Applies to products that are not cold worked after cooling from an elevated temperature shaping process, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits.

T6 solution heat-treated⑨ and then artificially aged. Applies to products that are not cold worked after solution heat-treatment, or in which the effect of cold work in flattening or straightening may not be recog-nized in mechanical property limits.

T7 solution heat-treated⑨ and overaged/stabilized. Applies to wrought products that are artificially aged after solution heat-treatment to carry them beyond a point of maximum strength to provide control of some significant characteristic⑩. Applies to cast products that are artificially aged after solution heat-treatment to provide dimensional and strength stability.

T8 solution heat-treated,⑨ cold worked, and then artificially aged. Applies to products that are cold worked to improve strength, or in which the effect of cold work in flattening or straightening is recognized in mechanical property limits.

T9 solution heat-treated,⑨ artificially aged, and then cold worked. Applies to products that are cold worked to improve strength.

⑦ Numerals 1 through 9 may be arbitrarily assigned as the third digit and registered with the Aluminum Association for an alloy and product to indi-cate a variation of a two-digit H temper (see note ⑥).

⑧ A period of natural aging at room temperature may occur between or after the operations listed for the T tempers. Control of this period is exercised when it is metallurgically important.

⑨ Solution heat treatment is achieved by heating cast or wrought products to a suitable temperature, holding at that temperature long enough to allow constituents to enter into solid solution and cooling rapidly enough to hold the constituents in solution. Some 6xxx series alloys attain the same speci-fied mechanical properties whether furnace solution heat treated or cooled from an elevated temperature shaping process at a rate rapid enough to hold constituents in solution. In such cases the temper designations T3, T4, T6, T7, T8, and T9 are used to apply to either process and are ap-propriate designations.⑩ For this purpose, characteristic is something other than mechanical properties. The test method and limit used to evaluate material for this characteristic are specified at the time of the temper registration.

January 2005 IV-11

T10 cooled from an elevated temperature shaping process, cold worked, and then artificially aged. Applies to products that are cold worked to improve strength, or in which the effect of cold work in flat-tening or straightening is recognized in mechanical property limits.

6.2.2.2 Additional digits,⑪ the first of which shall not be zero, may be added to designations T1 through T10 to indicate a variation in treatment that significantly alters the product characteristics that are or would be obtained using the basic treatment. (See Appendix for specific additional digits for T tempers.)

6.3 Variations of O Temper: Annealed

6.3.1 A digit following the O, when used, indicates a prod-uct in the annealed condition having special characteristics. NOTE: As the O temper is not part of the strain-hardened (H) series, variations of O temper shall not apply to prod-ucts that are strain-hardened after annealing and in which the effect of strain-hardening is recognized in the mechani-cal properties or other characteristics.

APPENDIX

A1 Three-Digit H Tempers

A1.1 The following three-digit H temper designations have been assigned for wrought products in all alloys:

H_11 Applies to products that incur sufficient strain hardening after the final anneal that they fail to qualify as annealed but not so much or so consistent an amount of strain hardening that they qualify as H_1.

H112 Applies to products that may acquire some temper from work-ing at an elevated temperature and for which there are mechanical property limits.

A1.2 The following three-digit H temper designations have been assigned for

pattern orembossed fabricated fromsheet

H114 O temperH124, H224, H324 H11, H21, H31 temper, respectivelyH134, H234, H334 H12, H22, H32 temper, respectivelyH144, H244, H344 H13, H23, H33 temper, respectivelyH154, H254, H354 H14, H24, H34 temper, respectivelyH164, H264, H364 H15, H25, H35 temper, respectivelyH174, H274, H374 H16, H26, H36 temper, respectivelyH184, H284, H384 H17, H27, H37 temper, respectivelyH194, H294, H394 H18, H28, H38 temper, respectivelyH195, H295, H395 H19, H29, H39 temper, respectively

A1.3 The following three-digit H temper designations have been assigned only for wrought products in the 5xxx series, for which the magnesium content is 3% nominal or more:

H116 Applies to products manufactured from alloys in the 5xxx series, for which the magnesium content is 3% nominal or more. Prod-ucts are normally strain hardened at the last operation to specified stable tensile property limits and meet specified levels of corro-sion resistance in accelerated type corrosion tests. They are suit-able for continuous service at temperature no greater than 150o F. Corrosion tests include inter-granular and exfoliation

H321 Applies to products from alloys in the 5xxx series, for which the magnesium content is 3% nominal or more. Products are normally thermally stabilized at the last operation to specified stable tensile property limits and meet specified levels of corrosion resistance in accelerated type corrosion tests. They are suitable for continuous service at temperatures no greater than 150o F. Corrosion tests include inter-granular and exfoliation.

A2 Additional Digits for T Tempers

A2.1 The following specific additional digits have been assigned for stress-relieved tempers of wrought products:

Stress relieved by stretching.

T_51 Applies to plate and rolled or cold-finished rod or bar, die or ring forgings and rolled rings when stretched the indicated amounts after solution heat treatment or after cooling from an elevated tem-perature shaping process. The products receive no further straight-ening after stretching.

Plate . . . . . . . . . . . . . . . . . . . . . . . . . .1½% to 3% permanent set.Rolled orCold-FinishedRod and Bar . . . . . . . . . . . . . . . . . . . . 1% to 3% permanent set.Die or RingForgings andRolled Rings . . . . . . . . . . . . . . . . . . . . 1% to 5% permanent set.

T_510 Applies to extruded rod, bar, profiles (shapes) and tube and to drawn tube when stretched the indicated amounts after solution heat treat-ment or after cooling from an elevated temperature shaping process. These products receive no further straightening after stretching.

Extruded RodBar, Profiles (Shapes)and Tube . . . . . . . . . . . . . . . . . . . . . . . 1% to 3% permanent set.Drawn Tube . . . . . . . . . . . . . . . . . . . . .½% to 3% permanent set.

T_511 Applies to extruded rod, bar, profiles (shapes) and tube and to drawn tube when stretched the indicated amounts after solution heat treatment or after cooling from an elevated temperature shap-ing process. These products may receive minor straightening after stretching to comply with standard tolerances.

Extruded Rod,Bar, Profiles (Shapes)and Tube . . . . . . . . . . . . . . . . . . . . . . . 1% to 3% permanent set.Drawn Tube . . . . . . . . . . . . . . . . . . . . .½% to 3% permanent set.

Stress relieved by compressing.

T_52 Applies to products that are stress-relieved by compressing after solution heat treatment or cooling from an elevated tempera-ture shaping process to produce a permanent set of 1 percent to 5 percent.

Stress relieved by combined stretching and compressing.

⑪ Additional digits may be arbitrarily assigned and registered with The Aluminum Association for an alloy and product to indicate a variation of tempers T1 through T10 even though the temper representing the basic treatment has not been registered (see note ⑥). Variations in treatment that do not alter the characteristics of the product are considered alternate treatments for which additional digits are not assigned.

IV-12 January 2005

T_54 Applies to die forgings that are stress relieved by restriking cold in the finish die.

NOTE: The same digits (51, 510, 511, 52, 54) may be added to the designation W to indicate unstable solution heat-treated and stress-relieved tempers.

A2.2 Temper Designations for Producer/Sup-plier Laboratory Demonstration of Response to Heat-treatment:

The following temper designations have been assigned for wrought products test material, furnace heat-treated from annealed (O, O1, etc.) or F temper, to demonstrate response to heat-treatment.

T42 Solution heat-treated from annealed or F temper and naturally aged to a substantially stable condition.

T62 Solution heat-treated from annealed or F temper and artificially aged.

T7_2 Solution heat-treated from annealed or F temper and artificially overaged to meet the mechanical properties and corrosion resis-tance limits of the T7_ temper.

A2.3 Temper Designations for Producer/Supplier Demonstration of Response to Temper Conversion:

Temper designation T_2 shall be used to indicate wrought product test material, which has undergone furnace heat-treatment for capability demonstration of temper conver-sion. When the purchaser requires capability demonstra-tions from T-temper, the seller shall note “Capabilitiy Demonstration” adjacent to the specified and ending tem-pers. Some examples are:

• “-T3 to -T82 Capability Demonstration for response to aging”;

• “-T4 to -T62 Capability Demonstration for response to aging”;

• “-T4 to -T762 Capability Demonstration for response to overaging”;

• “-T6 to -T732 Capability Demonstration for response to overaging”;

• “-T351 to -T42 Capability Demonstration for response to re-solution heat-treatment”.

A2.4 Temper Designation for Purchaser/User Heat-treatment

Temper designation T_2 should also be applied to wrought products heat-treated by the purchaser/user, in accordance with the applicable heat treatment specification, to achieve the properties applicable to the final temper.

A3 Assigned O Temper Variations

A3.1 The following temper designation has been assigned for wrought products high temperature annealed to accentu-ate ultrasonic response and provide dimensional stability.

O1 Thermally treated at approximately same time and temperature required for solution heat treatment and slow cooled to room tem-perature. Applicable to products that are to be machined prior to solution heat treatment by the user. Mechanical property limits are not applicable.

A4 Designation of Unregistered Tempers

A4.1 The letter P has been assigned to denote H, T and O temper variations that are negotiated between manufacturer and purchaser. The letter P immediately follows the temper designation that most nearly pertains. Specific examples where such designation may be applied include the following:

A4.1.1 The use of the temper is sufficiently limited so as to preclude its registration. (Negotiated H temper variations were formerly indicated by the third digit zero.)

A4.1.2 The test conditions (sampling location, number of samples, test specimen configuration, etc.) are different from those required for registration with The Aluminum Association.

A4.1.3 The mechanical property limits are not established on the same basis as required for registration with The Alu-minum Association.

A4.1.4 For products such as Aluminum Metal Matrix Com-posites which are not included in any registration records.

January 2005 IV-13

SOME ALLOY AND TEMPER APPLICATIONS OF ALLOYS

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RESISTANCE TO

CORROSIONWELDABILITY ⑥

1060-O A A A E A A A B Chemical equipment, railroad tank cars H12 A A A E A A A A H14 A A A D A A A A H16 A A B D A A A A H18 A A B D A A A A

1100-O A A A E A A A B Sheet metal work, spun hollowware, H12 A A A E A A A A fin stock H14 A A A D A A A A H16 A A B D A A A A H18 A A C D A A A A

1350-O A A A E A A A B Electrical conductors H12, H111 A A A E A A A A H14, H24 A A A D A A A A H16, H26 A A B D A A A A H18 A A B D A A A A

2011-T3 D ③ D C A D D D D Screw machine products T4, T451 D ③ D B A D D D D T8 D B D A D D D D

2014-O . . . . . . D D D D B Truck frames, aircraft structures T3, T4, T451 D ③ C C B D D B B T6, T651, T6510, T6511 D C D B D D B B

2017-T4, T451 D ③ C C B D D B B Screw machine products, fittings

2018-T61 . . . . . . B D D C B Aircraft engine cylinders, heads and pistons

2024-O . . . . . . D D D D D Truck wheels, screw machine products, T4, T3, T351, T3510, T3511 D ③ C C B D C B B aircraft structures T361 D ③ C D B D D C B T6 D B C B D D C B T861, T81, T851, T8510, T8511 D B D B D D C B T72 . . . . . . B D D C B

2025-T6 D C . . B D D B B Forgings, aircraft propellers

2036-T4 C . . B C D C B B Auto body panel sheet

2117-T4 C A B C D D B B Rivets

2124-T851 D B D B D D C B Aircraft structures

2218-T61 D C . . . . D D C B Jet engine impellers and rings T72 D C . . B D D C B

2219-O . . . . . . . . D D A B Structural uses at high temperatures T31, T351, T3510, T3511 D ③ C C B D A A A (to 600°F) T37 D ③ C D B D A A A High strength weldments T81, T851, T8510, T8511 D B D B D A A A T87 D B D B D A A A

2618-T61 D C . . B D D C B Aircraft engines

3003-O A A A E A A A B Cooking utensils, chemical equipment, H12 A A A E A A A A pressure vessels, sheet metal work, H14 A A B D A A A A builder’s hardware, storage tanks H16 A A C D A A A A H18 A A C D A A A A H25 A A B D A A A A

3004-O A A A D B A A B Sheet metal work, storage tanks H32 A A B D B A A A H34 A A B C B A A A H36 A A C C B A A A H38 A A C C B A A A

3105-O A A A E A A A B Residential siding, mobile homes, rain H12 A A B E A A A A carrying goods, sheet metal work H14 A A B D A A A A H16 A A C D A A A A H18 A A C D A A A A H25 A A B D A A A A

Table 1COMPARATIVE CHARACTERISTICS AND APPLICATIONS

For all numbered footnotes, see page IV-15.

IV-14 January 2005

Table 1COMPARATIVE CHARACTERISTICS AND APPLICATIONS (Continued)

RESISTANCE TO

CORROSION SOME ALLOY AND TEMPER APPLICATIONS OF ALLOYS

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WELDABILITY ⑥


4032-T6 C B . . B D D B C Pistons

5005-O A A A E B A A B Appliances, utensils, architectural, H12 A A A E B A A A electrical conductor H14 A A B D B A A A H16 A A C D B A A A H18 A A C D B A A A H32 A A A E B A A A H34 A A B D B A A A H36 A A C D B A A A H38 A A C D B A A A

5050-O A A A E B A A B Builder’s hardware, refrigerator trim, H32 A A A D B A A A coiled tubes H34 A A B D B A A A H36 A A C C B A A A H38 A A C C B A A A

5052-O A A A D C A A B Sheet metal work, hydraulic tube, H32 A A B D C A A A appliances H34 A A B C C A A A H36 A A C C C A A A H38 A A C C C A A A

5056-O A ④ B ④ A D D C A B Cable sheathing, rivets for magnesium, H111 A ④ B ④ A D D C A A screen wire, zipper H12, H32 A ④ B ④ B D D C A A H14, H34 A ④ B ④ B C D C A A H18, H38 A ④ C ④ C C D C A A H192 B ④ D ④ D B D C A A H392 B ④ D ④ D B D C A A

5083-O A ④ A ④ B D D C A B H321 ⑧ A ④ A ④ C D D C A A H111 A ④ B ④ C D D C A A H116 ⑧ A ④ A ④ C D D C A A

5086-O A ④ A ④ A D D C A B Unfired, welded pressure vessels, H32 ⑧ A ④ A ④ B D D C A A marine, auto aircraft cryogenics, H34 A ④ B ④ B C D C A A TV towers, drilling rigs, transportation H36 A ④ B ④ C C D C A A equipment, missile components H38 A ④ B ④ C C D C A A H111 A ④ A ④ B D D C A A H116 ⑧ A ④ A ④ B D D C A A

5154-O A ④ A ④ A D D C A B Welded structures, storage tanks, H32 A ④ A ④ B D D C A A pressure vessels, salt water service H34 A ④ A ④ B C D C A A H36 A ④ A ④ C C D C A A H38 A ④ A ④ C C D C A A

5252-H24 A A B D C A A A Automotive and appliance trim H25 A A B C C A A A H28 A A C C C A A A

5254-O A ④ A ④ A D D C A B Hydrogen peroxide and chemical H32 A ④ A ④ B D D C A A storage vessels H34 A ④ A ④ B C D C A A H36 A ④ A ④ C C D C A A H38 A ④ A ④ C C D C A A

5454-O A A A D D C A B Welded structures, pressure vessels, H32 A A B D D C A A marine service H34 A A B C D C A A H111 A A B D D C A A

5456-O A ④ B ④ B D D C A B High strength welded structures, H321 ⑧ A ④ B ④ C D D C A A pressure vessels, marine applications, H116 ⑧ A ④ B ④ C D D C A A storage tanks

5457-O A A A E B A A B

5652-O A A A D C A A B Hydrogen peroxide and chemical H32 A A B D C A A A storage vessels H34 A A B C C A A A H36 A A C C C A A A H38 A A C C C A A A

January 2005 IV-15

SOME ALLOY AND TEMPER APPLICATIONS OF ALLOYS

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RESISTANCE TO

CORROSIONWELDABILITY ⑥


5657-H241 A A A D B A A A Anodized auto and appliance trim H25 A A B D B A A A H26 A A B D B A A A H28 A A C D B A A A

6005-T1, T5 . . . . . . . . A A A A

6053-O . . . . . . E B A A B Wire and rod for rivets T6, T61 A A . . C B A A A

6061-O B A A D A A A B Heavy-duty structures requiring good T4, T451, T4510, T4511 B B B C A A A A corrosion resistance, truck and marine, T6, T651, T652, T6510, T6511 B A C C A A A A railroad cars, furniture, pipelines

6063-T1 A A B D A A A A Pipe railing, furniture, architectural T4 A A B D A A A A extrusions T5, T452 A A B C A A A A T6 A A C C A A A A T83, T831, T832 A A C C A A A A

6066-O C A B D D D B B Forgings and extrusion for welded T4, T4510, T4511 C B C C D D B B structures T6, T6510, T6511 C B C B D D B B

6070-T4, T4511 B B B C D A A A Heavy duty welded structures, pipelines T6 B B C C D A A A

6101-T6, T63 A A C C A A A A High strength bus conductors T61, T64 A A B D A A A A

6151-T6, T652 . . . . . . . . B . . . . . . Moderate strength, intricate forgings for machine and auto parts

6201-T81 A A . . C A A A A High strength electric conductor wire

6262-T6, T651, T6510, T6511 B A C B B B B A Screw machine products T9 B A D B B B B A

6351-T1 . . . . C C C B A B Extruded shapes, structurals, pipe and T4 A . . C C C B A B tube T5 A . . C C C B A A T6 A . . C C C B A A

6463-T1 A A B D A A A A Extruded architectural and trim sections T5 A A B C A A A A T6 A A C C A A A A

6951-T42, T62 . . . . . . . . A A A A

7005-T53 . . . . . . . . B C A A

7049-T73, T7352 C B D B D D D B Aircraft forgings

7050-T73510, T73511 C B D B D D D B Aircraft and other structures T74 ⑦, T7451 ⑦, T74510 ⑦,

T74511 ⑦, T7452 ⑦, T7651, T76510, T76511

7075-O . . . . . . D D D D B Aircraft and other structures T6, T651, T652, T6510, T6511 C ③ C D B D D D B T73, T7351 C B D B D D D B

7175-T74, T7452, T7454 C B D B D D C B

7178-O . . . . . . . . D D D B Aircraft and other structures T6, T651, T6510, T6511 C ③ C D B D D D B

7475-O . . . . . . . . D D D B Shell Casings7475-T61, -T651 C C D B D D B B Aircraft & Other7475-T761, T7351 C B D B D D D B Structures

8017-H12, H22, H221 A A A D A A A A Electrical conductors

8030-H12, H221 A A A E A A A A Electrical conductors

8176-H14, H24 A A A D A A A A Electrical conductors

Table 1COMPARATIVE CHARACTERISTICS AND APPLICATIONS (Continued)

IV-16 January 2005

④ This rating may be different for material held at elevated temperature for long periods.⑤ Ratings A through D for Workability (cold), and A through E for Machin-ability, are relative ratings in decreasing order of merit.⑥ Ratings A through D for Weldability and Brazeability are relative ratings defined as follows:

A = Generally weldable by all commercial procedures and methods.B = Weldable with special techniques or for specific applications that jus-

tify preliminary trials or testing to develop welding procedure and weld performance.

C = Limited weldability because of crack sensitivity or loss in resistance to corrosion and mechanical properties.

D = No commonly used welding methods have been developed.⑦ T74 type tempers, although not previously registered, have appeared in various literature and specifications as T736 type tempers.⑧ 5xxx products in the -H116 and H32X tempers have similar mechanical properties; however, production methods and testing requirements differ, and these tempers are not interchangeable. The -H116 temper is typically used in marine and other applications requiring demonstration of exfoliation resistance.

Notes for Table 1① Ratings A through E are relative ratings in decreasing order of merit, based on exposures to sodium chloride solution by intermittent spraying or immer-sion. Alloys with A and B ratings can be used in industrial and seacoast atmospheres without protection. Alloys with C, D and E ratings generally should be protected at least on faying surfaces.② Stress-corrosion cracking ratings are based on service experience and on laboratory tests of specimens exposed to the 3.5% sodium chloride alternate immersion test.

A = No known instance of failure in service or in laboratory tests.B = No known instance of failure in service; limited failures in laboratory

tests of short transverse specimens.C = Service failures with sustained tension stress acting in short trans-

verse direction relative to grain structure; limited failures in laboratory tests of long transverse specimens.

D = Limited service failures with sustained longitudinal or long transverse areas.

These ratings are neither product specific nor test direction specific and therefore indicate only the general level of stress-corrosion cracking resis-tance. For more specific information on certain alloys, see ASTM G64.

③ In relatively thick sections the rating would be E.

January 2005 IV-17

Table 2HISTORICAL FOREIGN ALLOY DESIGNATIONS AND SIMILAR AA ALLOYS

Foreign Alloy Designating Equivalent or Designation Country Similar AA Alloy

E-A1995 ④ } 13503.0257 ⑤ AlCuBiPb ④ } 20113.1655 ⑤ AlCuMg0.5 ④ } 21173.1305 ⑤ AlCuMg1 ④ } 20173.1325 ⑤ AlCuMg2 ④ } 20243.1355 ⑤ AlCuSiMn ④ } Germany 20143.1255 ⑤ AlMg4.5Mn ④ } 50833.3547 ⑤ AlMgSi0.5 ④ } 60633.3206 ⑤ AlSi5 ④ } 40433.2245 ⑤ E-AlMgSi0.5 ④ } 61013.3207 ⑤ AlZnMgCu1.5 ④ } 70753.4365 ⑤

1E 135091E 6101H14 2017H19 6063H20 6061L.80, L.81 5052L.86 2117L.87 2117L.93, L.94 Great Britain 2014AL.95, L.96 (BS) ⑥ 7075L.97, L.98 20242L.55, 2L.56 50522L.58 50563L.44 50505L.37 20176L.25 2218N8 5083N21 4043

150A 2017324A 4032372B 6063717, 724, 731A } Great Britain } 745, 5014, 5084 (DTD) ⑦ 2618

5090 20245100 Alclad 2024


Al99 1200Al99,5 1050E-Al 1350AlCuMg1 2017AlCuMg2 Austria 2024AlCuMg0,5 (Önorm) ① 2117AlMg5 5056AlMgSi0,5 6063E-AlMgSi 6101AlZnMgCu1,5 7075

990C 1100CB60 2011CG30 2117CG42 2024CG42 Alclad Alclad 2024CM41 2017CN42 2018CS41N 2014CS41N Alclad Alclad 2014CS41P 2025GM31N 5454GM41 Canada 5083GM50P (CSA) ② 5356GM50R 5056GR20 5052GS10 6063GS11N 6061GS11P 6053MC10 3003S5 4043SG11P 6151SG121 4032ZG62 7075ZG62 Alclad Alclad 7075

A5/L 1350A45 1100A-G1 5050A-G0.6 5005A-G4MC 5086A-GS 6063A-GS/L 6101A-M1 3003A-M1G France 3004A-U4G (NF) ③ 2017A-U2G 2117A-U2GN 2618A-U4G1 2024A-U4N 2218A-U4SG 2014A-S12UN 4032A-Z5GU 7075

For all numbered footnotes, see next page.

IV-18 January 2005


Al-Mg-Si 6101Al1.5Mg 5050Al-Cu-Ni 2218Al3.5Cu0.5Mg Switzerland 2017Al4Cu1.2Mg (VSM) ⑩ 2027Al-Zn-Mg-Cu 7075Al-Zn-Mg-Cu-pl Alclad 7075

Al99.0Cu 1100AlCu2Mg 2117AlCu4Mg1 2024AlCu4SiMg 2014AlCu4MgSi 2017AlMg1 5005AlMg1.5 5050AlMg2.5 5052AlMg3.5 ISO ⑪ 5154AlMg4 5086AlMg5 5056AlMn1Cu 3003AlMg3Mn 5454AlMg4.5Mn 5083AlMgSi 6063AlMg1SiCu 6061AIZn6MgCu 7075

⑦ Directorate of Technical Development.⑧ Unificazione Nazionale Italiana.⑨ Una Norma Espanol.⑩ Verein Schweizerischer Maschinenindustrieller.⑪ International Organization for Standardization.


P-AlCu4MgMn 2017P-AlCu4.5MgMn 2024P-AlCu4.5MgMnplacc. Alclad 2024P-AlCu2.5MgSi 2117P-AlCu4.4SiMnMg Italy 2014P-AlCu4.4SiMnMgplacc. (UNI) ⑧ Alclad 2014P-AlMg0.9 5657P-AlMg1.5 5050P-AlMg2.5 5052P-AlSi0.4Mg 6063P-AlSi0.5Mg 6101

Al99.5E 1350L-313 2014L-314 Spain 2024L-315 (UNE) ⑨ 2218L-371 7075

① Austrian Standard M3430.② Canadian Standards Association.③ Normes Françaises.④ Deutsche Industrie-Norm.⑤ Werkstoff-Nr.⑥ British Standard.

Table 2HISTORICAL FOREIGN ALLOY DESIGNATIONS AND SIMILAR AA ALLOYS (Continued)


PART V

Material Properties



January 2005 V-3

VMaterial Properties

TABLE OF CONTENTS

1.0 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

2.0 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Table 1 Minimum Mechanical Properties for Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6Table 1M Minimum Mechanical Properties for Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8Table 2 Minimum Mechanical Properties for Welded Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10Table 2M Minimum Mechanical Properties for Welded Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11Table 3 Mechanical Property Limits for Aluminum Sand Casting Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12Table 3M Mechanical Property Limits for Aluminum Sand Casting Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13Table 4 Mechanical Property Limits for Aluminum Permanent Mold Casting Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14Table 4M Mechanical Property Limits for Aluminum Permanent Mold Casting Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15Table 5 Mechanical Property Limits of Fastener Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16Table 5M Mechanical Property Limits of Fastener Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16Table 6 Typical Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17Table 6M Typical Mechanical Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21Table 7 Typical Physical Properties-Thermal and Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25Table 7M Typical Physical Properties-Thermal and Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27Table 8 Typical Physical Properties-Density . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29Table 9 Typical Tensile Properties at Various Temperatures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30Table 9M Typical Tensile Properties at Various Temperatures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

January 2005 V-5

1.0 Introduction

The mechanical properties intended to be used for struc-tural design in accordance with the Design Guide and the Specification for Aluminum Structures included in this manual are listed in Tables 1 and 2 of this Part.

In Table 1, the tensile strength (Ftu) and tensile yield strength (Fty) are equal to specified minimum properties, and are based on producer analysis of data accumulated from standard procedures (Reference 1). The limits are established after sufficient test data have been accumu-lated to adequately determine the form of the frequency distribution curve and to provide a reliable estimate of the population mean and standard deviation. In most instances the distribution is normal in form and properties are based on the results of a minimum of 100 tests from at least 10 different lots of material. In some instances, however, limits may be derived through their known relationship with another limit or property having sufficient data and meeting the above data base criteria. The standard mechan-ical property limits are subsequently established at levels at which 99% of the material is expected to conform at a confidence level of 0.95.

The compressive yield strength (Fcy), and shear ulti-mate strength (Fsu) in Table 1 are “expected minimum” properties, strengths which 99% of the population would be expected, but are not guaranteed, to equal or exceed; individual lots of material may not be accepted or rejected based upon these properties. They are derived values estab-lished by multiplying values of these properties from tests of representative lots of material by the ratio of the speci-fied minimum tensile yield or ultimate strength to the ten-sile yield or ultimate strength of the lot tested. While every effort is made to base these values on test data for at least 5 to 10 lots of each alloy, temper and product, there are instances where insufficient data are available, and the derived properties are based on data for similar products.

Minimum mechanical properties for welded material are shown in Table 2. Values of tensile strength (Ftuw) are weld qualification properties required by AWS D1.2. For non-heat-treatable alloys, the values of tensile strength (Ftuw) are the minimum properties of the parent metal in the annealed (O) temper.

The tensile ultimate strengths (Ftuw) of heat-treatable alloys and the tensile yield strengths (Ftyw) of all the alloys listed are based, where possible, on the statistical analysis of test data. Minimum values are those that 99% of the population would be expected to equal or exceed with a confidence level of 0.75. There are instances where insuf-

ficient data are available, and in those cases the minimum properties are based on data for similar combinations of filler and parent material.

Generally, the compressive and shear properties in Table 2 are derived from the relationships among those proper-ties of the parent alloys and tempers. None of the mini-mum mechanical properties of welds are specified (guaran-teed) values upon which individual lots of material may be accepted or rejected. All values are based on the assumption that recommended weld procedures are employed, with the realization that variations in these procedures could alter the values obtained.

Tables 3 and 4 show minimum mechanical properties for aluminum sand and permanent mold casting alloys respectively. Table 5 has minimum mechanical properties of threaded fastener alloys.

As a resource for comparing alloys and tempers, Table 6 gives typical mechanical properties which include not only tensile ultimate and yield, but also hardness, shear, fatigue, and modulus. These typical properties are not guaranteed and are averages for various sizes, product forms, and methods of manufacture. The data should not be specified as engineering requirements or used for design purposes.

Table 7 similarly shows typical physical properties, both thermal and electrical and can be used as a basis for com-paring alloys and tempers. Densities for alloys are shown in Table 8, while Table 9 displays tensile properties at various temperatures. As stated earlier, properties shown in Tables 6 and 9 are not to be used for design purposes.

Other material properties and material properties of other alloys and tempers may be found in References 1 through 3.

2.0 References

1. Aluminum Association, Aluminum Standards and Data, The Aluminum Association, Washington, DC, 2003.

2. DOT/FAA/AR-MMPDS-01, Metallic Materials Prop-erties Development and Standardization (MMPDS), (formerly MIL Handbook 5) Chapter 3, January, 2003, U.S. Department of Transportation, Federal Aviation Administration, Washington, D.C. Copies available through the National Technical Information Service (NTIS), 5285 Port Royal Road, Springfield VA 22161-0001; www.ntis.gov or downloadable from http://www.tc.faa.gov/its/worldpac/techrpt/ar-mmpds-01.pdf

3. Bruhn, E.F., Analysis and Design of Flight Vehicle Structures, Tristate Offset Co., Cincinnati, OH, 1965.

V-6 January 2005

Table 1MINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS


RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi


E (ksi)1100-H12


AllAll

1416

1114

1013

910

10,10010,100

2014-T6-T651-T6, T6510, T6511-T6, T651


0.040 to 0.2490.250 to 2.000

AllAll

66676065

58595355

59585253

40403538

10,90010,90010,90010,900

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.025 to 0.0390.040 to 0.2490.250 to 0.499

636464

555757

565856

383939

10,80010,80010,800

3003-H12-H14-H16-H18-H12-H14-H16-H18


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.128

AllAllAllAll

1720242717202427

1217212412172124

1014182011161921

1112141511121415

10,10010,10010,10010,10010,10010,10010,10010,100

Alclad3003-H12

-H14-H16-H18-H14-H18


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.025 to 0.2590.010 to 0.500

161923261926

111620231623

91317191520

101214151215

10,10010,10010,10010,10010,10010,100

3004-H32-H34-H36-H38-H34-H36


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.006 to 0.1280.018 to 0.4500.018 to 0.450

283235383235

212528312528

182225292427

171920211920

10,10010,10010,10010,10010,10010,100

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361


0.017 to 0.2490.009 to 0.2490.006 to 0.1620.006 to 0.1280.024 to 0.0500.024 to 0.050

273134373134

202427302630

172124282228

161819211819

10,10010,10010,10010,10010,10010,100

3005-H25-H28

SheetSheet

0.013 to 0.0500.006 to 0.080

2631

2227

2025

1517

10,10010,100

3105-H25 Sheet 0.013 to 0.080 23 19 17 14 10,100

5005-H12-H14-H16-H32-H34-H36


0.017 to 2.0000.009 to 1.0000.006 to 0.1620.017 to 2.0000.009 to 1.0000.006 to 0.162

182124172023

141720121518

131518111416

111214111213

10,10010,10010,10010,10010,10010,100

5050-H32-H34-H32

-H34


0.017 to 2.0000.009 to 0.249

All

All

222522

25

162016

20

141815

19

141513

15

10,10010,10010,100

10,100


( )

January 2005 V-7

Table 1MINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS


RANGE in.

Ftu

ksiFty

ksiFcy ksi

Fsu

ksi


E (ksi)5052-O

-H32-H34-H36



0.006 to 0.162

253134

37

9.52326

29

9.52124

26

161920

22

10,20010,20010,200

10,2005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321



3940404044444141

1624241831312929

1621211826262424

2424232526262424

10,40010,40010,40010,40010,40010,40010,40010,400

5086-O-H111-H111 -O-H112-H112-H112-H116-H112-H32

-H34



AllAll

All

35363635363535344040

44

14212114181614142828

34

14181814171615152626

32

21212121222121212424

26

10,40010,40010,40010,40010,40010,40010,40010,40010,40010,400

10,400

5154-H38 Sheet 0.006 to 0.128 45 35 33 24 10,3005454-O

-H111-H111-H112-O-H32-H34



31333331313639

12191912122629

12161613122427

19201919192123

10,40010,40010,40010,40010,40010,40010,400

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321


0.051 to 1.5000.188 to 1.2500.188 to 1.2501.251 to 1.5001.251 to 1.5001.501 to 3.0001.501 to 3.000

42464644444141

19333331312929

19272725252525

26272725252525

10,40010,40010,40010,40010,40010,40010,400


-T6, T6510, T6511-T6, T651-T6-T6


0.010 to 4.000All

up thru 8.0000.025 to 0.500

All

4238424238

3535353535

3535353535

2724252724

10,10010,10010,10010,10010,100

6063-T5, -T52-T5-T6


up thru 0.500up thru 1.0000.500 to 1.000

All

22222130

16161525

16161525

13131219

10,10010,10010,10010,100


-T5-T6



3842

3537

3537

2427

10,10010,100




( )

V-8 January 2005

Table 1MMINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS


RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)1100-H12


AllAll

95110

75 95

70 90

62 70

69,60069,600

2014-T6-T651-T6, T6510, T6511-T6, T651


1.00 to 6.306.30 to 50.00

AllAll

455460415450

400405365380

405400360365

275275240260

75,20075,20075,20075,200

Alclad2014-T6

-T6-T651

SheetSheetPlate

0.63 to 1.001.00 to 6.30

6.30 to 12.50

435440440

380395395

385400385

260270270

74,50074,50074,500

3003-H12-H14-H16-H18-H12-H14-H16-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.20

AllAllAllAll

120140165185120140165185

85115145165 85115145165

70 95125140 75110130145

75 85 95105 75 85 95105

69,60069,60069,60069,60069,60069,60069,60069,600

Alclad3003-H12

-H14-H16-H18-H14-H18


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.63 to 6.300.25 to 12.50

115135160180135180

80110140160110160

62 90115130105140

70 85 95105 85105

69,60069,60069,60069,60069,60069,600

3004-H32-H34-H36-H38-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.000.15 to 3.200.45 to 11.500.45 to 11.50

190220240260220240

145170190215170190

125150170200165185

115130140145130140

69,60069,60069,60069,60069,60069,600

Alclad3004-H32

-H34-H36-H38-H131, H241, H341-H151, H261, H361


0.40 to 6.300.20 to 6.300.15 to 4.000.15 to 3.200.60 to 1.200.60 to 1.20

185215235255215235

140165185205180205

115145165195150195

110125130145125130

69,60069,60069,60069,60069,60069,600

3005-H25-H28

SheetSheet

0.32 to 1.200.15 to 2.00

180215

150185

140170

105115

69,60069,600

3105-H25 Sheet 0.32 to 2.00 160 130 115 95 69,600

5005-H12-H14-H16-H32-H34-H36


0.40 to 50.000.20 to 25.000.15 to 4.00

0.40 to 50.000.20 to 25.000.15 to 4.00

125145165120140160

95115135 85105125

90105125 75 95110

75 85 95 75 85 90

69,60069,60069,60069,60069,60069,600

5050-H32-H34-H32

-H34


0.40 to 6.300.20 to 6.30

All

All

150170150

170

110140110

140

95125105

130

95105 90

105

69,60069,60069,600

69,600


( )

January 2005 V-9

Table 1MMINIMUM MECHANICAL PROPERTIES FOR ALUMINUM ALLOYS


RANGE mm

Ftu

MPaFty

MPaFcy

MPaFsu

MPa


E (MPa)5052-O

-H32-H34

-H36


0.15 to 80.00AllAll

0.15 to 4.00

170215235

255

65160180

200

66145165

180

110130140

150

70,30070,30070,300

70,3005083-O

-H111-H111-O-H116-H32, H321-H116-H32, H321



12.70 to 130.001.20 to 6.30

4.00 to 40.004.00 to 40.0040.00 to 80.0040.00 to 80.00

270275275275305305285285

110165165125215215200200

110145145125180180165165

165165160170180180165165

71,70071,70071,70071,70071,70071,70071,70071,700

5086-O-H111-H111 -O-H112-H112-H112-H116-H32

-H34



12.70 to 130.000.50 to 50.004.00 to 12.5012.50 to 40.0040.00 to 80.001.60 to 50.00

All

All

240250250240250240235275275

300

95145145 95125105 95195195

235

95125125 95115110105180180

220

145145145145150145145165165

180

71,70071,70071,70071,70071,70071,70071,70071,70071,700

71,700

5154-H38 Sheet 0.15 to 3.20 310 240 230 165 71,7005454-O

-H111-H111-H112-O-H32-H34



12.70 to 130.00up thru 130.000.50 to 80.000.50 to 50.000.50 to 25.00

215230230215215250270

85130130 85 85180200

85110110 90 85165185

130140130130130145160

71,70071,70071,70071,70071,70071,70071,700

5456-O-H116-H32, H321-H116-H32, H321-H116-H32, H321


1.20 to 6.304.00 to 12.504.00 to 12.5012.50 to 40.0012.50 to 40.0040.00 to 80.0040.00 to 80.00

290315315305305285285

130230230215215200200

130185185170170170170

180185185170170170170

71,70071,70071,70071,70071,70071,70071,700


-T6, T6510, T6511-T6, T651-T6-T6


0.25 to 100.00All

up thru 2000.63 to 12.50

All

290260290290260

240240240240240

240240240240240

185165170185165

69,60069,60069,60069,60069,600

6063-T5, -T52-T5-T6


up thru 12.50up thru 25.0012.50 to 25.00

All

150150145205

110110105170

110110105170

90 90 85130

69,60069,60069,60069,600




( )

V-10 January 2005

Table 2MINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEin.


2

ksi

SHEARFsuw ksi

Ftuw1

ksiFtyw

2 ksi

1100-H12, H14 All 11 3.5 3.5 8

3003-H12, H14, H16, H18 All 14 5 5 10

Alclad 3003-

H12, H14, H16, H18

All

13

4.5

4.510

3004-H32, H34, H36, H38 All 22 8.5 8.5 14

Alclad 3004-

H32, H34, H36, H38

All

21

8

8

13

3005-H25 Sheet 17 6.5 6.5 12

5005-H12, H14, H32, H34 All 15 5 5 9

5050-H32, H34 All 18 6 6 12

5052-O, H32, H34 All 25 9.5 9.5 16

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321


0.188-1.5001.501-3.000

394039

161817

151817

232424

5086-5086-5086-

O, H111H112O, H32, H34, H116


0.250-2.000353535

141414

131414

212121

5154-H38 Sheet 30 11 11 19

5454-5454-5454-

O, H111H112O, H32, H34


313131

121212

111212

191919

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

0.188-1.5001.501-3.000

4241

1918

1817

2525


6061-6061-

T6, T651, T6510, T65113

T6, T651, T6510, T65114

AllAll over 0.375

2424

1511

1511

1515

6063-T5, T52, T6 All 17 8 8 11

6351-6351-

T5, T63

T5, T64


2424

1511

1511

1515

6463-T6 Extrusions 0.125-0.500 17 8 8 11






January 2005 V-11

Table 2MMINIMUM MECHANICAL PROPERTIES FOR WELDED ALUMINUM ALLOYS


RANGEmm

TENSION COMPRESSIONFcyw ‡MPa

SHEARFsuw MPa

Ftuw †MPa

Ftyw ‡ MPa

1100-H12, H14 All 75 25 25 55

3003-H12, H14, H16, H18 All 95 35 35 70

Alclad 3003-

H12, H14, H16, H18

All

90

30

30

70

3004-H32, H34, H36, H38 All 150 60 60 95

Alclad 3004-

H32, H34, H36, H38

All

145

55

55

90

3005-H25 Sheet 115 45 45 85

5005-H12, H14, H32, H34 All 105 35 35 62

5050-H32, H34 All 125 40 40 85

5052-O, H32, H34 All 170 65 65 110

5083-5083-5083-

O, H111O, H116, H32, H321O, H116, H32, H321


6.30-38.0038.00-80.00

270270270

110115115

110115115

160165165

5086-5086-5086-

O, H111H112O, H32, H34, H116


6.30-50.00240240240

95 95 95

85 95 95

145145145

5154-H38 Sheet 205 75 75 130

5454-5454-5454-

O, H111H112O, H32, H34


215215215

85 85 85

85 85 85

130130130

5456-5456-

O, H116, H32, H321O, H116, H32, H321

Sheet & PlatePlate

6.30-38.0038.00-80.00

285285

125125

125120

170170


6061-6061-

T6, T651, T6510, T6511*T6, T651, T6510, T6511**

AllAll over 9.50

165165

105 80

105 80

105105

6063-T5, T52, T6 All 115 55 55 75

6351-6351-

T5, T6*T5, T6**


165165

105 80

105 80

105105

6463-T6 Extrusions 3.20-12.50 115 55 55 75


† Filler wires are listed in Table 7.1-1. Values of Ftuw are AWS D1.2 weld qualification values.

‡ 0.2% offset in 50 mm gage length across a groove weld.

* Values when welded with 5183, 5356, or 5556 alloy filler wire, regardless of thickness. Values also apply to thicknesses less than or equal to 9.5 mm when welded with 4043, 5554, or 5654 alloy filler wire.

** Values when welded with 4043, 5554, or 5654 alloy filler wire.

V-12 January 2005

Table 3MECHANICAL PROPERTY LIMITS FOR ALUMINUM SAND CASTING ALLOYS

ALLOY TEMPER

MINIMUM TENSILE

ULTIMATE STRENGTH

(ksi)

MINIMUM TENSILE YIELD

STRENGTH (ksi)

MINIMUM % ELONGATION in 2 in. or 4D

TYPICAL BRINNELL HARDNESS

(500 kgf load 10 mm ball)

201.0 T7 60.0 50.0 3.0 –

204.0 T4 45.0 28.0 6.0 –

242.0 O 23.0 A A 70

242.0 T61 32.0 20.0 A 105

A242.0 T75 29.0 A 1.0 75

295.0 T4 29.0 13.0 6.0 60

295.0 T6 32.0 20.0 3.0 75

295.0 T62 36.0 28.0 A 95

295.0 T7 29.0 16.0 3.0 70

319.0 F 23.0 13.0 1.5 70

319.0 T5 25.0 A A 80

319.0 T6 31.0 20.0 1.5 80

355.0 T51 25.0 18.0 A 65

355.0 T6 32.0 20.0 2.0 80

355.0 T71 30.0 22.0 A 75

C355.0 T6 36.0 25.0 2.5 –

356.0 F 19.0 9.5 2.0 55

356.0 T51 23.0 16.0 A 60

356.0 T6 30.0 20.0 3.0 70

356.0 T7 31.0 A A 75

356.0 T71 25.0 18.0 3.0 60

A356.0 T6 34.0 24.0 3.5 80

A356.0 T61 35.0 26.0 1.0 –

443.0 F 17.0 7.0 3.0 40

B443.0 F 17.0 6.0 3.0 40

512.0 F 17.0 10.0 – 50

514.0 F 22.0 9.0 6.0 50

520.0 T4 42.0 22.0 12.0 75

535.0 F 35.0 18.0 9.0 70

705.0 T5 30.0 17.0 B 5.0 65

707.0 T7 37.0 30.0 B 1.0 80

710.0 T5 32.0 20.0 2.0 75

712.0 T5 34.0 25.0 B 4.0 75

713.0 T5 32.0 22.0 3.0 75

771.0 T5 42.0 38.0 1.5 100

771.0 T51 32.0 27.0 3.0 85

771.0 T52 36.0 30.0 1.5 85

771.0 T6 42.0 35.0 5.0 90

771.0 T71 48.0 45.0 2.0 120

850.0 T5 16.0 A 5.0 45

851.0 T5 17.0 A 3.0 45

852.0 T5 24.0 18.0 A 60

A = not required; B = to be determined only when specified by the purchaser

January 2005 V-13

Table 3MMECHANICAL PROPERTY LIMITS FOR ALUMINUM SAND CASTING ALLOYS

ALLOY TEMPER

MINIMUM TENSILE

ULTIMATE STRENGTH

(MPa)

MINIMUM TENSILE YIELD

STRENGTH (MPa)

MINIMUM % ELONGATION

in 5D

TYPICAL BRINNELL HARDNESS

(500 kgf load 10 mm ball)

201.0 T7 415 345 3.0 –

204.0 T4 310 195 6.0 –

242.0 O 160 A A 70

242.0 T61 220 140 A 105

A242.0 T75 200 A 1.0 75

295.0 T4 200 90 6.0 60

295.0 T6 220 140 3.0 75

295.0 T62 250 195 A 95

295.0 T7 200 110 3.0 70

319.0 F 160 90 1.5 70

319.0 T5 170 A A 80

319.0 T6 215 140 1.5 80

355.0 T51 170 125 A 65

355.0 T6 220 140 2.0 80

355.0 T71 205 150 A 75

C355.0 T6 250 170 2.5 –

356.0 F 130 65 2.0 55

356.0 T51 160 110 A 60

356.0 T6 205 140 3.0 70

356.0 T7 215 A A 75

356.0 T71 170 125 3.0 60

A356.0 T6 235 165 3.5 80

A356.0 T61 245 180 1.0 –

443.0 F 115 50 3.0 40

B443.0 F 115 40 3.0 40

512.0 F 115 70 – 50

514.0 F 150 60 6.0 50

520.0 T4 290 150 12.0 75

535.0 F 240 125 9.0 70

705.0 T5 205 115 B 5.0 65

707.0 T7 255 205 B 1.0 80

710.0 T5 220 140 2.0 75

712.0 T5 235 170 B

4.0 75

713.0 T5 220 150 3.0 75

771.0 T5 290 260 1.5 100

771.0 T51 220 185 3.0 85

771.0 T52 250 205 1.5 85

771.0 T6 290 240 5.0 90

771.0 T71 330 310 2.0 120

850.0 T5 110 A 5.0 45

851.0 T5 115 A 3.0 45

852.0 T5 165 125 A 60

V-14 January 2005

A = not required; B = to be determined only when specified by the purchaser

Table 4MECHANICAL PROPERTY LIMITS FOR ALUMINUM

PERMANENT MOLD CASTING ALLOYS

ALLOY TEMPER

MINIMUM TENSILE

ULTIMATE STRENGTH

(ksi)

MINIMUM TENSILE

YIELD STRENGTH

(ksi) B

MINIMUM % ELONGATION in

2 in. or 4D

TYPICAL BRINNELL HARDNESS(500 kgf load 10 mm ball)

204.0 T4 separately cast specimens 48.0 29.0 8.0 –242.0 T571 34.0 – A 105242.0 T61 40.0 – A 110319.0 F 27.0 14.0 2.5 95332.0 T5 31.0 – A 105333.0 F 28.0 – A 90333.0 T5 30.0 – A 100333.0 T6 35.0 – A 105333.0 T7 31.0 – A 90336.0 T551 31.0 – A 105336.0 T65 40.0 – A 125354.0 T61 separately cast specimens 48.0 37.0 3.0354.0 T61 castings, designated area 47.0 36.0 3.0354.0 T61 castings, no location designated 43.0 33.0 2.0354.0 T62 separately cast specimens 52.0 42.0 2.0354.0 T62 castings, designated area 50.0 42.0 2.0354.0 T62 castings, no location designated 43.0 33.0 2.0355.0 T51 27.0 – A 75355.0 T62 42.0 – A 105355.0 T7 36.0 – A 90355.0 T71 34.0 27.0 A 80

C355.0 T61 separately cast specimens 40.0 30.0 3.0 85 – 90C355.0 T61 castings, designated area 40.0 30.0 3.0C355.0 T61 castings, no location designated 37.0 30.0 1.0 85356.0 F 21.0 10.0 3.0356.0 T6 33.0 22.0 3.0 85356.0 T71 25.0 – 3.0 70

A356.0 T61 separately cast specimens 38.0 26.0 5.0 80 – 90A356.0 T61 castings, designated area 33.0 26.0 5.0A356.0 T61 castings, no location designated 28.0 26.0 3.0357.0 T6 45.0 – 3.0 –

A357.0 T61 separately cast specimens 45.0 36.0 3.0 100A357.0 T61 castings, designated area 46.0 36.0 3.0 –A357.0 T61 castings, no location designated 41.0 31.0 3.0 –359.0 T61 separately cast specimens 45.0 34.0 4.0 90359.0 T61 castings, designated area 45.0 34.0 4.0359.0 T61 castings, no location designated 40.0 30.0 3.0359.0 T62 separately cast specimens 47.0 38.0 3.0 100359.0 T62 castings, designated area 47.0 38.0 3.0359.0 T62 castings, no location designated 40.0 30.0 3.0443.0 F 21.0 7.0 2.0 45

B443.0 F 21.0 6.0 2.5 45A444.0 T4 separately cast specimens 20.0 – 20 –A444.0 T4 castings, designated area 20.0 – 20 –513.0 F 22.0 12.0 2.5 60535.0 F 35.0 18.0 8.0 –705.0 T1 or T5 37.0 17.0 10.0707.0 T1 42.0 25.0 4.0707.0 T7 45.0 35.0 3.0711.0 T1 28.0 18.0 7.0 70713.0 T1 or T5 32.0 22.0 4.0850.0 T5 18.0 – 8.0851.0 T5 17.0 – 3.0851.0 T6 18.0 – 8.0852.0 T5 27.0 – 3.0

A = not requiredB = to be determined only when specified by the purchaser

January 2005 V-15

Table 4MMECHANICAL PROPERTY LIMITS FOR ALUMINUM

PERMANENT MOLD CASTING ALLOYS

ALLOY TEMPER

MINIMUM TENSILE

ULTIMATE STRENGTH

(MPa)

MINIMUM TENSILE

YIELD STRENGTH

(MPa) B

MINIMUM % ELONGATION in

50 mm or 4D

TYPICAL BRINNELL HARDNESS(500 kgf load 10 mm ball)

204.0 T4 separately cast specimens 331 200 8.0 –242.0 T571 234 – A 105242.0 T61 276 – A 110319.0 F 186 97 2.5 95332.0 T5 214 – A 105333.0 F 193 – A 90333.0 T5 207 – A 100333.0 T6 241 – A 105333.0 T7 214 – A 90336.0 T551 214 – A 105336.0 T65 276 – A 125354.0 T61 separately cast specimens 331 255 3.0354.0 T61 castings, designated area 324 248 3.0354.0 T61 castings, no location designated 297 228 2.0354.0 T62 separately cast specimens 359 290 2.0354.0 T62 castings, designated area 344 290 2.0354.0 T62 castings, no location designated 297 228 2.0355.0 T51 186 – A 75355.0 T62 290 – A 105355.0 T7 248 – A 90355.0 T71 234 186 A 80

C355.0 T61 separately cast specimens 276 207 3.0 85 – 90C355.0 T61 castings, designated area 276 207 3.0C355.0 T61 castings, no location designated 255 207 1.0 85356.0 F 145 69 3.0356.0 T6 228 152 3.0 85356.0 T71 172 – 3.0 70

A356.0 T61 separately cast specimens 262 179 5.0 80 – 90A356.0 T61 castings, designated area 228 179 5.0A356.0 T61 castings, no location designated 193 179 3.0357.0 T6 310 – 3.0 –

A357.0 T61 separately cast specimens 310 248 3.0 100A357.0 T61 castings, designated area 317 248 3.0 –A357.0 T61 castings, no location designated 283 214 3.0 –359.0 T61 separately cast specimens 310 234 4.0 90359.0 T61 castings, designated area 310 234 4.0359.0 T61 castings, no location designated 276 207 3.0359.0 T62 separately cast specimens 324 262 3.0 100359.0 T62 castings, designated area 324 262 3.0359.0 T62 castings, no location designated 276 207 3.0443.0 F 145 49 2.0 45

B443.0 F 145 41 2.5 45A444.0 T4 separately cast specimens 138 – 20 –A444.0 T4 castings, designated area 138 – 20 –513.0 F 152 83 2.5 60535.0 F 241 124 8.0 –705.0 T1 or T5 255 117 10.0707.0 T1 290 173 4.0707.0 T7 310 241 3.0711.0 T1 193 124 7.0 70713.0 T1 or T5 221 152 4.0850.0 T5 124 – 8.0851.0 T5 117 – 3.0851.0 T6 124 – 8.0 852.0 T5 186 – 3.0

A = not requiredB = to be determined only when specified by the purchaser

V-16 January 2005

Table 5MECHANICAL PROPERTY LIMITS OF FASTENER ALLOYS ①

TENSILE STRENGTH ksi min.

ULTIMATE YIELD ②

2017-T4 0.063–1.000 55.0 32.0 12 33.02024-T42 0.063–0.124 62.0 . . . . 37.0 0.125–1.000 62.0 40.0 10 37.02117-T4 0.063–1.000 38.0 18.0 18 26.02219-T6 0.063–1.000 55.0 35.0 6 30.06053-T61 0.063–1.000 30.0 20.0 14 20.06061-T6 0.063–1.000 42.0 35.0 10 25.07050-T7 0.063–1.000 70.0 58.0 10 39.07075-T6 0.063–1.000 77.0 66.0 7 42.07075-T73 0.063–1.000 68.0 56.0 10 41.07178-T6 0.063–1.000 84.0 73.0 5 46.0

ALLOY AND TEMPER

SPECIFIED DIAMETER

in.

ELONGATION ② percent min. in.

2 in. or 4D ③

ULTIMATE SHEARING STRENGTH

ksi min.

① Rivet and cold heading wire and rod, and the fasteners produced from it, shall upon proper heat treatment (T4 and T42 tempers) or heat treatment and aging (T6, T61, T7 and T73 tempers) be capable of developing the properties presented in Table 5. Tensile tests are preferred for the rivet and cold heading wire and rod, and shear tests for the fasteners made from it.② The measurement of elongation and yield strength is not required for wire less than 0.125 inch in thickness or diameter.③ D represents specimen diameter.

Table 5MMECHANICAL PROPERTY LIMITS OF FASTENER ALLOYS ①

ALLOY AND TEMPER

SPECIFIED DIAMETER

mm

TENSILE STRENGTH MPa min

ELONGATION ② percent min


MPa minULTIMATE YIELD ② 50 mm 5D (5.65 √__ A )

2017-T42024-T42

2117-T42219-T66053-T616061-T67050-T77075-T67075-T737178-T6

1.60–25.001.60–3.153.15–25.001.60–25.001.60–25.001.60–25.001.60–25.001.60–25.001.60–25.001.60–25.001.60–25.00

380425425260380205290485530470580

220. .

255125240135240400455385500

12. .1018 6141010 710 5

10. . 916 512 9 9 6 9 4

225255255180205135170270290280315

① Rivet and cold heading wire and rod, and the fasteners produced from it, shall upon proper heat treatment (T4 and T42 tempers) or heat treatment and aging (T6, T61, T7 and T73 tempers) be capable of developing the properties presented in Table 5. Tensile tests are preferred for the rivet and cold heading wire and rod, and shear tests for the fasteners made from it.② The measurement of elongation and yield strength is not required for wire 3.2 mm and less in thickness or diameter.

January 2005 V-17

Table 6TYPICAL MECHANICAL PROPERTIES ① ②

lar product or size. These data are intended only as a basis for comparing alloys and tempers and should not be specifi ed as engineering requirements or used for design purposes.

The following typical properties are not guaranteed, since in most cases they are averages for various sizes, product forms and methods of manufacture and may not be exactly representative of any particu-

NOT FOR D

ESIGN

TENSION HARDNESS SHEAR FATIGUE MODULUS

STRENGTH ELONGATION BRINNELL ULTIMATE ENDURANCE ③ MODULUS ④ ksi percent in 2 in. NUMBER SHEARING Limit OF

1⁄16 in. 1⁄2 in. STRENGTH ELASTICITY

ULTIMATE YIELD Thick Diameter 500 kg load Specimen Specimen 10 mm ball ksi ksi ksi × 103

1060-O 10 4 43 . . 19 7 3 10.0 1060-H12 12 11 16 . . 23 8 4 10.0 1060-H14 14 13 12 . . 26 9 5 10.0 1060-H16 16 15 8 . . 30 10 6.5 10.0 1060-H18 19 18 6 . . 35 11 6.5 10.0

1100-O 13 5 35 45 23 9 5 10.0 1100-H12 16 15 12 25 28 10 6 10.0 1100-H14 18 17 9 20 32 11 7 10.0 1100-H16 21 20 6 17 38 12 9 10.0 1100-H18 24 22 5 15 44 13 9 10.0

1350-O 12 4 . . . . ⑤ . . 8 . . 10.0 1350-H12 14 12 . . . . . . 9 . . 10.0 1350-H14 16 14 . . . . . . 10 . . 10.0 1350-H16 18 16 . . . . . . 11 . . 10.0 1350-H19 27 24 . . . . ⑥ . . 15 7 10.0

2011-T3 55 43 . . 15 95 32 18 10.2 2011-T8 59 45 . . 12 100 35 18 10.2

2014-O 27 14 . . 18 45 18 13 10.6 2014-T4, T451 62 42 . . 20 105 38 20 10.6 2014-T6, T651 70 60 . . 13 135 42 18 10.6

Alclad 2014-O 25 10 21 . . . . 18 . . 10.5Alclad 2014-T3 63 40 20 . . . . 37 . . 10.5Alclad 2014-T4, T451 61 37 22 . . . . 37 . . 10.5Alclad 2014-T6, T651 68 60 10 . . . . 41 . . 10.5

2017-O 26 10 . . 22 45 18 13 10.5 2017-T4, T451 62 40 . . 22 105 38 18 10.5

2018-T61 61 46 . . 12 120 39 17 10.8

2024-O 27 11 20 22 47 18 13 10.6 2024-T3 70 50 18 . . 120 41 20 10.6 2024-T4, T351 68 47 20 19 120 41 20 10.6 2024-T361 ⑦ 72 57 13 . . 130 42 18 10.6

Alclad 2024-O 26 11 20 . . . . 18 . . 10.6Alclad 2024-T3 65 45 18 . . . . 40 . . 10.6Alclad 2024-T4, T351 64 42 19 . . . . 40 . . 10.6Alclad 2024-T361 ⑦ 67 63 11 . . . . 41 . . 10.6Alclad 2024-T81, T851 65 60 6 . . . . 40 . . 10.6Alclad 2024-T861 ⑦ 70 66 6 . . . . 42 . . 10.6

2025-T6 58 37 . . 19 110 35 18 10.4

2036-T4 49 28 24 . . . . . . 18 ⑨ 10.3

2117-T4 43 24 . . 27 70 28 14 10.3

2124-T851 70 64 . . 8 . . . . . . 10.6

2218-T72 48 37 . . 11 95 30 . . 10.8

2219-O 25 11 18 . . . . . . . . 10.6 2219-T42 52 27 20 . . . . . . . . 10.6 2219-T31, T351 52 36 17 . . . . . . . . 10.6 2219-T37 57 46 11 . . . . . . . . 10.6 2219-T62 60 42 10 . . . . . . 15 10.6 2219-T81, T851 66 51 10 . . . . . . 15 10.6 2219-T87 69 57 10 . . . . . . 15 10.6

2618-T61 64 54 . . 10 115 38 18 10.8

3003-O 16 6 30 40 28 11 7 10.0 3003-H12 19 18 10 20 35 12 8 10.0 3003-H14 22 21 8 16 40 14 9 10.0 3003-H16 26 25 5 14 47 15 10 10.0 3003-H18 29 27 4 10 55 16 10 10.0

For all numbered footnotes, see last page of this Table.

ALLOY AND

TEMPER

V-18 January 2005

Table 6TYPICAL MECHANICAL PROPERTIES ① ② (Continued)

Alclad 3003-O 16 6 30 40 . . 11 . . 10.0Alclad 3003-H12 19 18 10 20 . . 12 . . 10.0Alclad 3003-H14 22 21 8 16 . . 14 . . 10.0Alclad 3003-H16 26 25 5 14 . . 15 . . 10.0Alclad 3003-H18 29 27 4 10 . . 16 . . 10.0

3004-O 26 10 20 25 45 16 14 10.0 3004-H32 31 25 10 17 52 17 15 10.0 3004-H34 35 29 9 12 63 18 15 10.0 3004-H36 38 33 5 9 70 20 16 10.0 3004-H38 41 36 5 6 77 21 16 10.0

Alclad 3004-O 26 10 20 25 . . 16 . . 10.0Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

3105-O 17 8 24 . . . . 12 . . 10.0 3105-H12 22 19 7 . . . . 14 . . 10.0 3105-H14 25 22 5 . . . . 15 . . 10.0 3105-H16 28 25 4 . . . . 16 . . 10.0 3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0 3105-H25 26 23 8 . . . . 15 . . 10.0 3105-H26 24 24 9 . . . . 16 . . 10.0 3105-H28 26 26 8 . . . . 17 . . 10.0

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0 5005-H14 23 22 6 . . . . 14 . . 10.0 5005-H16 26 25 5 . . . . 15 . . 10.0 5005-H18 29 28 4 . . . . 16 . . 10.0 5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0 5005-H38 29 27 5 . . 51 16 . . 10.0

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0 5050-H38 32 29 6 . . 63 20 14 10.0

5052-O 28 13 25 30 47 18 16 10.2 5052-H32 33 28 12 18 60 20 17 10.2 5052-H34 38 31 10 14 68 21 18 10.2 5052-H36 40 35 8 10 73 23 19 10.2 5052-H38 42 37 7 8 77 24 20 10.2

5056-O 42 22 . . 35 65 26 20 10.3 5056-H18 63 59 . . 10 105 34 22 10.3 5056-H38 60 50 . . 15 100 32 22 10.3

5083-O 42 21 . . 22 . . 25 . . 10.3 5083-H116 ⑪ 46 33 . . 16 . . . . 23 10.3 5083-H321 46 33 . . 16 . . . . 23 10.3

5086-O 38 17 22 . . . . 23 . . 10.3 5086-H32 42 30 12 . . . . . . . . 10.3 5086-H116 ⑪ 42 30 12 . . . . . . . . 10.3 5086-H34 47 37 10 . . . . 27 . . 10.3 5086-H112 39 19 14 . . . . . . . . 10.3

5154-O 35 17 27 . . 58 22 17 10.2 5154-H32 39 30 15 . . 67 22 18 10.2 5154-H34 42 33 13 . . 73 24 19 10.2 5154-H36 45 36 12 . . 78 26 20 10.2 5154-H38 48 39 10 . . 80 28 21 10.2 5154-H112 35 17 25 . . 63 . . 17 10.2






ALLOY AND

TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

Alclad 3003-H18 29 27 4 10 . . 16 . . 10.0

NOT FOR D

ESIGN

Alclad 3003-H18 29 27 4 10 . . 16 . . 10.0

3004-O 26 10 20 25 45 16 14 10.0

NOT FOR D

ESIGN

3004-O 26 10 20 25 45 16 14 10.0 3004-H32 31 25 10 17 52 17 15 10.0

NOT FOR D

ESIGN 3004-H32 31 25 10 17 52 17 15 10.0

3004-H34 35 29 9 12 63 18 15 10.0

NOT FOR D

ESIGN 3004-H34 35 29 9 12 63 18 15 10.0

3004-H36 38 33 5 9 70 20 16 10.0

NOT FOR D

ESIGN 3004-H36 38 33 5 9 70 20 16 10.0

3004-H38 41 36 5 6 77 21 16 10.0

NOT FOR D

ESIGN 3004-H38 41 36 5 6 77 21 16 10.0

Alclad 3004-O 26 10 20 25 . . 16 . . 10.0

NOT FOR D

ESIGNAlclad 3004-O 26 10 20 25 . . 16 . . 10.0

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN 3004-H34 35 29 9 12 63 18 15 10.0

NOT FOR D

ESIGN 3004-H34 35 29 9 12 63 18 15 10.0

3004-H36 38 33 5 9 70 20 16 10.0

NOT FOR D

ESIGN 3004-H36 38 33 5 9 70 20 16 10.0

3004-H38 41 36 5 6 77 21 16 10.0

NOT FOR D

ESIGN 3004-H38 41 36 5 6 77 21 16 10.0

Alclad 3004-O 26 10 20 25 . . 16 . . 10.0

NOT FOR D

ESIGNAlclad 3004-O 26 10 20 25 . . 16 . . 10.0

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

3105-O 17 8 24 . . . . 12 . . 10.0

NOT FOR D

ESIGN

3105-O 17 8 24 . . . . 12 . . 10.0 3105-H12 22 19 7 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H12 22 19 7 . . . . 14 . . 10.0 3105-H14 25 22 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H14 25 22 5 . . . . 15 . . 10.0 3105-H16 28 25 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H16 28 25 4 . . . . 16 . . 10.0 3105-H18 31 28 3 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

3105-O 17 8 24 . . . . 12 . . 10.0

NOT FOR D

ESIGN

3105-O 17 8 24 . . . . 12 . . 10.0 3105-H12 22 19 7 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H12 22 19 7 . . . . 14 . . 10.0 3105-H14 25 22 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H14 25 22 5 . . . . 15 . . 10.0 3105-H16 28 25 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H16 28 25 4 . . . . 16 . . 10.0 3105-H18 31 28 3 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

3105-H24 26 22 10 15 . . 10.0 3105-H25 26 23 8 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H25 26 23 8 . . . . 15 . . 10.0 3105-H26 24 24 9 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H26 24 24 9 . . . . 16 . . 10.0 3105-H28 26 26 8 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H28 26 26 8 . . . . 17 . . 10.0

4032-T6 55 46 . . 9 120 38 16 11.4

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0

NOT FOR D

ESIGN

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

3105-H24 26 22 10 15 . . 10.0 3105-H25 26 23 8 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H25 26 23 8 . . . . 15 . . 10.0 3105-H26 24 24 9 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H26 24 24 9 . . . . 16 . . 10.0 3105-H28 26 26 8 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H28 26 26 8 . . . . 17 . . 10.0

4032-T6 55 46 . . 9 120 38 16 11.4

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0

NOT FOR D

ESIGN

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H12 20 19 10 . . . . 14 . . 10.0 5005-H14 23 22 6 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H14 23 22 6 . . . . 14 . . 10.0 5005-H16 26 25 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

5005-H16 26 25 5 . . . . 15 . . 10.0 5005-H18 29 28 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

5005-H18 29 28 4 . . . . 16 . . 10.0 5005-H32 20 17 11 . . 36 14 . . 10.0

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0

NOT FOR D

ESIGN

5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0

NOT FOR D

ESIGN

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H12 20 19 10 . . . . 14 . . 10.0 5005-H14 23 22 6 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H14 23 22 6 . . . . 14 . . 10.0 5005-H16 26 25 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

5005-H16 26 25 5 . . . . 15 . . 10.0 5005-H18 29 28 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

5005-H18 29 28 4 . . . . 16 . . 10.0 5005-H32 20 17 11 . . 36 14 . . 10.0

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0

NOT FOR D

ESIGN

5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

5005-H36 26 24 6 . . 46 15 . . 10.0 5005-H38 29 27 5 . . 51 16 . . 10.0

NOT FOR D

ESIGN

5005-H38 29 27 5 . . 51 16 . . 10.0

5050-O 21 8 24 . . 36 15 12 10.0

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0

NOT FOR D

ESIGN

5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0

NOT FOR D

ESIGN

5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0

NOT FOR D

ESIGN

5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

5005-H36 26 24 6 . . 46 15 . . 10.0 5005-H38 29 27 5 . . 51 16 . . 10.0

NOT FOR D

ESIGN

5005-H38 29 27 5 . . 51 16 . . 10.0

5050-O 21 8 24 . . 36 15 12 10.0

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0

NOT FOR D

ESIGN

5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0

NOT FOR D

ESIGN

5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

5050-H36 30 26 7 . . 58 19 14 10.0 5050-H38 32 29 6 . . 63 20 14 10.0

NOT FOR D

ESIGN

5050-H38 32 29 6 . . 63 20 14 10.0

5052-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5052-O 28 13 25 30 47 18 16 10.2 5052-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5052-H32 33 28 12 18 60 20 17 10.2 5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0

NOT FOR D

ESIGN

5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0

NOT FOR D

ESIGN

5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

5050-H36 30 26 7 . . 58 19 14 10.0 5050-H38 32 29 6 . . 63 20 14 10.0

NOT FOR D

ESIGN

5050-H38 32 29 6 . . 63 20 14 10.0

5052-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5052-O 28 13 25 30 47 18 16 10.2 5052-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5052-H32 33 28 12 18 60 20 17 10.2 5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5052-H34 38 31 10 14 68 21 18 10.2 5052-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5052-H36 40 35 8 10 73 23 19 10.2 5052-H38 42 37 7 8 77 24 20 10.2

NOT FOR D

ESIGN

5052-H38 42 37 7 8 77 24 20 10.2

5056-O 42 22 . . 35 65 26 20 10.3

NOT FOR D

ESIGN

5056-O 42 22 . . 35 65 26 20 10.3 5056-H18 63 59 . . 10 105 34 22 10.3

NOT FOR D

ESIGN

5056-H18 63 59 . . 10 105 34 22 10.3 5056-H38 60 50 . . 15 100 32 22 10.3NOT F

OR DESIG

N

5056-H38 60 50 . . 15 100 32 22 10.3

5083-O 42 21 . . 22 . . 25 . . 10.3NOT FOR D

ESIGN

5083-O 42 21 . . 22 . . 25 . . 10.3 5083-H116 NOT F

OR DESIG

N

5083-H116 ⑪NOT FOR D

ESIGN

⑪ 46 33 . . 16 . . . . 23 10.3NOT FOR D

ESIGN

46 33 . . 16 . . . . 23 10.3 5083-H321 46 33 . . 16 . . . . 23 10.3NOT F

OR DESIG

N

5083-H321 46 33 . . 16 . . . . 23 10.3NOT FOR D

ESIGN

5052-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5052-O 28 13 25 30 47 18 16 10.2 5052-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5052-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5052-H34 38 31 10 14 68 21 18 10.2 5052-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5052-H36 40 35 8 10 73 23 19 10.2 5052-H38 42 37 7 8 77 24 20 10.2

NOT FOR D

ESIGN

5052-H38 42 37 7 8 77 24 20 10.2

5056-O 42 22 . . 35 65 26 20 10.3

NOT FOR D

ESIGN

5056-O 42 22 . . 35 65 26 20 10.3 5056-H18 63 59 . . 10 105 34 22 10.3

NOT FOR D

ESIGN

5056-H18 63 59 . . 10 105 34 22 10.3 5056-H38 60 50 . . 15 100 32 22 10.3NOT F

OR DESIG

N

5056-H38 60 50 . . 15 100 32 22 10.3

5083-O 42 21 . . 22 . . 25 . . 10.3NOT FOR D

ESIGN

5083-O 42 21 . . 22 . . 25 . . 10.3NOT FOR D

ESIGN

NOT FOR D

ESIGN

5005-H18 29 28 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

5005-H18 29 28 4 . . . . 16 . . 10.0 5005-H32 20 17 11 . . 36 14 . . 10.0

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0

NOT FOR D

ESIGN

5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

5005-H36 26 24 6 . . 46 15 . . 10.0 5005-H38 29 27 5 . . 51 16 . . 10.0

NOT FOR D

ESIGN

5005-H38 29 27 5 . . 51 16 . . 10.0

5050-O 21 8 24 . . 36 15 12 10.0

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0

NOT FOR D

ESIGN

5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0

NOT FOR D

ESIGN

5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0

NOT FOR D

ESIGN

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H12 20 19 10 . . . . 14 . . 10.0 5005-H14 23 22 6 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H14 23 22 6 . . . . 14 . . 10.0 5005-H16 26 25 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

5005-H16 26 25 5 . . . . 15 . . 10.0 5005-H18 29 28 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

5005-H18 29 28 4 . . . . 16 . . 10.0 5005-H32 20 17 11 . . 36 14 . . 10.0

NOT FOR D

ESIGN

5005-H32 20 17 11 . . 36 14 . . 10.0 5005-H34 23 20 8 . . 41 14 . . 10.0

NOT FOR D

ESIGN

5005-H34 23 20 8 . . 41 14 . . 10.0 5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

5005-H36 26 24 6 . . 46 15 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0

NOT FOR D

ESIGN

5050-O 21 8 24 . . 36 15 12 10.0 5050-H32 25 21 9 . . 46 17 13 10.0

NOT FOR D

ESIGN

5050-H32 25 21 9 . . 46 17 13 10.0 5050-H34 28 24 8 . . 53 18 13 10.0

NOT FOR D

ESIGN

5050-H34 28 24 8 . . 53 18 13 10.0 5050-H36 30 26 7 . . 58 19 14 10.0

NOT FOR D

ESIGN

5050-H36 30 26 7 . . 58 19 14 10.0 5050-H38 32 29 6 . . 63 20 14 10.0

NOT FOR D

ESIGN

5050-H38 32 29 6 . . 63 20 14 10.0

5052-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5052-O 28 13 25 30 47 18 16 10.2 5052-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5052-H32 33 28 12 18 60 20 17 10.2 5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5052-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

3105-H24 26 22 10 15 . . 10.0 3105-H25 26 23 8 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H25 26 23 8 . . . . 15 . . 10.0 3105-H26 24 24 9 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H26 24 24 9 . . . . 16 . . 10.0 3105-H28 26 26 8 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H28 26 26 8 . . . . 17 . . 10.0

4032-T6 55 46 . . 9 120 38 16 11.4

NOT FOR D

ESIGN

4032-T6 55 46 . . 9 120 38 16 11.4

5005-O 18 6 25 . . 28 11 . . 10.0

NOT FOR D

ESIGN

5005-O 18 6 25 . . 28 11 . . 10.0 5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

5005-H12 20 19 10 . . . . 14 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

3105-O 17 8 24 . . . . 12 . . 10.0

NOT FOR D

ESIGN

3105-O 17 8 24 . . . . 12 . . 10.0 3105-H12 22 19 7 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H12 22 19 7 . . . . 14 . . 10.0 3105-H14 25 22 5 . . . . 15 . . 10.0

NOT FOR D

ESIGN

3105-H14 25 22 5 . . . . 15 . . 10.0 3105-H16 28 25 4 . . . . 16 . . 10.0

NOT FOR D

ESIGN

3105-H16 28 25 4 . . . . 16 . . 10.0 3105-H18 31 28 3 . . . . 17 . . 10.0

NOT FOR D

ESIGN

3105-H18 31 28 3 . . . . 17 . . 10.0 3105-H22 24 20 11 . . . . 14 . . 10.0

NOT FOR D

ESIGN

3105-H22 24 20 11 . . . . 14 . . 10.0 3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

3105-H24 26 22 10 15 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN 3004-H34 35 29 9 12 63 18 15 10.0

NOT FOR D

ESIGN 3004-H34 35 29 9 12 63 18 15 10.0

3004-H36 38 33 5 9 70 20 16 10.0

NOT FOR D

ESIGN 3004-H36 38 33 5 9 70 20 16 10.0

3004-H38 41 36 5 6 77 21 16 10.0

NOT FOR D

ESIGN 3004-H38 41 36 5 6 77 21 16 10.0

Alclad 3004-O 26 10 20 25 . . 16 . . 10.0

NOT FOR D

ESIGNAlclad 3004-O 26 10 20 25 . . 16 . . 10.0

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H32 31 25 10 17 . . 17 . . 10.0Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H34 35 29 9 12 . . 18 . . 10.0Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H36 38 33 5 9 . . 20 . . 10.0Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

NOT FOR D

ESIGN

Alclad 3004-H38 41 36 5 6 . . 21 . . 10.0

January 2005 V-19


5252-H25 34 25 11 . . 68 21 . . 10.0 5252-H38, H28 41 35 5 . . 75 23 . . 10.0

5254-O 35 17 27 . . 58 22 17 10.2 5254-H32 39 30 15 . . 67 22 18 10.2 5254-H34 42 33 13 . . 73 24 19 10.2 5254-H36 45 36 12 . . 78 26 20 10.2 5254-H38 48 39 10 . . 80 28 21 10.2 5254-H112 35 17 25 . . 63 . . 17 10.2

5454-O 36 17 22 . . 62 23 . . 10.2 5454-H32 40 30 10 . . 73 24 . . 10.2 5454-H34 44 35 10 . . 81 26 . . 10.2 5454-H111 38 26 14 . . 70 23 . . 10.2 5454-H112 36 18 18 . . 62 23 . . 10.2

5456-O 45 23 . . 24 . . . . . . 10.3 5456-H25 45 24 . . 22 . . . . . . 10.3 5456-H116 ⑪ 51 37 . . 16 90 30 . . 10.3 5456-H321 ⑪ 51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0 5457-H25 26 23 12 . . 48 16 . . 10.0 5457-H38, H28 30 27 6 . . 55 18 . . 10.0

5652-O 28 13 25 30 47 18 16 10.2 5652-H32 33 28 12 18 60 20 17 10.2 5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2 5652-H38 42 37 7 8 77 24 20 10.2

5657-H25 23 20 12 . . 40 12 . . 10.0 5657-H38, H28 28 24 7 . . 50 15 . . 10.0

6061-O 18 8 25 30 30 12 9 10.0 6061-T4, T451 35 21 22 25 65 24 14 10.0 6061-T6, T651 45 40 12 17 95 30 14 10.0

Alclad 6061-O 17 7 25 . . . . 11 . . 10.0Alclad 6061-T4, T451 33 19 22 . . . . 22 . . 10.0Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

6063-O 13 7 . . . . 25 10 8 10.0 6063-T1 22 13 20 . . 42 14 9 10.0 6063-T4 25 13 22 . . . . . . . . 10.0 6063-T5 27 21 12 . . 60 17 10 10.0 6063-T6 35 31 12 . . 73 22 10 10.0 6063-T83 37 35 9 . . 82 22 . . 10.0 6063-T831 30 27 10 . . 70 18 . . 10.0 6063-T832 42 39 12 . . 95 27 . . 10.0

6066-O 22 12 . . 18 43 14 . . 10.0 6066-T4, T451 52 30 . . 18 90 29 . . 10.0 6066-T6. T651 57 52 . . 12 120 34 16 10.0

6070-T6 55 51 10 . . . . 34 14 10.0

6101-H111 14 11 . . . . . . . . . . 10.0 6101-T6 32 28 15 ⑧ . . 71 20 . . 10.0

6262-T9 58 55 . . 10 120 35 13 10.0

6351-T4 36 22 20 . . . . . . . . 10.0 6351-T6 45 41 14 . . 95 29 13 10.0

6463-T1 22 13 20 . . 42 14 10 10.0 6463-T5 27 21 12 . . 60 17 10 10.0 6463-T6 35 31 12 . . 74 22 10 10.0

7049-T73 75 65 . . 12 135 44 . . 10.4 7049-T7352 75 63 . . 11 135 43 . . 10.4

7050-T73510, T73511 72 63 . . 12 . . . . . . 10.4 7050-T7451 ⑩ 76 68 . . 11 . . 44 . . 10.4 7050-T7651 80 71 . . 11 . . 47 . . 10.4

7075-O 33 15 17 16 60 22 . . 10.4 7075-T6, T651 83 73 11 11 150 48 23 10.4






ALLOY AND

TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5454-H32 40 30 10 . . 73 24 . . 10.2

NOT FOR D

ESIGN

5454-H32 40 30 10 . . 73 24 . . 10.2 5454-H34 44 35 10 . . 81 26 . . 10.2

NOT FOR D

ESIGN

5454-H34 44 35 10 . . 81 26 . . 10.2 5454-H111 38 26 14 . . 70 23 . . 10.2

NOT FOR D

ESIGN

5454-H111 38 26 14 . . 70 23 . . 10.2 5454-H112 36 18 18 . . 62 23 . . 10.2

NOT FOR D

ESIGN 5454-H112 36 18 18 . . 62 23 . . 10.2

5456-O 45 23 . . 24 . . . . . . 10.3

NOT FOR D

ESIGN 5456-O 45 23 . . 24 . . . . . . 10.3

5456-H25 45 24 . . 22 . . . . . . 10.3

NOT FOR D

ESIGN 5456-H25 45 24 . . 22 . . . . . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN 51 37 . . 16 90 30 . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5454-H34 44 35 10 . . 81 26 . . 10.2

NOT FOR D

ESIGN

5454-H34 44 35 10 . . 81 26 . . 10.2 5454-H111 38 26 14 . . 70 23 . . 10.2

NOT FOR D

ESIGN

5454-H111 38 26 14 . . 70 23 . . 10.2 5454-H112 36 18 18 . . 62 23 . . 10.2

NOT FOR D

ESIGN 5454-H112 36 18 18 . . 62 23 . . 10.2

5456-O 45 23 . . 24 . . . . . . 10.3

NOT FOR D

ESIGN 5456-O 45 23 . . 24 . . . . . . 10.3

5456-H25 45 24 . . 22 . . . . . . 10.3

NOT FOR D

ESIGN 5456-H25 45 24 . . 22 . . . . . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN 51 37 . . 16 90 30 . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

5457-O 19 7 22 . . 32 12 . . 10.0 5457-H25 26 23 12 . . 48 16 . . 10.0

NOT FOR D

ESIGN

5457-H25 26 23 12 . . 48 16 . . 10.0 5457-H38, H28 30 27 6 . . 55 18 . . 10.0

NOT FOR D

ESIGN

5457-H38, H28 30 27 6 . . 55 18 . . 10.0

5652-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5652-O 28 13 25 30 47 18 16 10.2 5652-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5652-H32 33 28 12 18 60 20 17 10.2 5652-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

5457-O 19 7 22 . . 32 12 . . 10.0 5457-H25 26 23 12 . . 48 16 . . 10.0

NOT FOR D

ESIGN

5457-H25 26 23 12 . . 48 16 . . 10.0 5457-H38, H28 30 27 6 . . 55 18 . . 10.0

NOT FOR D

ESIGN

5457-H38, H28 30 27 6 . . 55 18 . . 10.0

5652-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5652-O 28 13 25 30 47 18 16 10.2 5652-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5652-H32 33 28 12 18 60 20 17 10.2 5652-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5652-H36 40 35 8 10 73 23 19 10.2 5652-H38 42 37 7 8 77 24 20 10.2

NOT FOR D

ESIGN

5652-H38 42 37 7 8 77 24 20 10.2

5657-H25 23 20 12 . . 40 12 . . 10.0

NOT FOR D

ESIGN

5657-H25 23 20 12 . . 40 12 . . 10.0 5657-H38, H28 28 24 7 . . 50 15 . . 10.0

NOT FOR D

ESIGN

5657-H38, H28 28 24 7 . . 50 15 . . 10.0

6061-O 18 8 25 30 30 12 9 10.0

NOT FOR D

ESIGN

6061-O 18 8 25 30 30 12 9 10.0 6061-T4, T451 35 21 22 25 65 24 14 10.0

NOT FOR D

ESIGN

6061-T4, T451 35 21 22 25 65 24 14 10.0 6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5652-H36 40 35 8 10 73 23 19 10.2 5652-H38 42 37 7 8 77 24 20 10.2

NOT FOR D

ESIGN

5652-H38 42 37 7 8 77 24 20 10.2

5657-H25 23 20 12 . . 40 12 . . 10.0

NOT FOR D

ESIGN

5657-H25 23 20 12 . . 40 12 . . 10.0 5657-H38, H28 28 24 7 . . 50 15 . . 10.0

NOT FOR D

ESIGN

5657-H38, H28 28 24 7 . . 50 15 . . 10.0

6061-O 18 8 25 30 30 12 9 10.0

NOT FOR D

ESIGN

6061-O 18 8 25 30 30 12 9 10.0 6061-T4, T451 35 21 22 25 65 24 14 10.0

NOT FOR D

ESIGN

6061-T4, T451 35 21 22 25 65 24 14 10.0 6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

6061-T6, T651 45 40 12 17 95 30 14 10.0

Alclad 6061-O 17 7 25 . . . . 11 . . 10.0

NOT FOR D

ESIGN

Alclad 6061-O 17 7 25 . . . . 11 . . 10.0Alclad 6061-T4, T451 33 19 22 . . . . 22 . . 10.0

NOT FOR D

ESIGN

Alclad 6061-T4, T451 33 19 22 . . . . 22 . . 10.0Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

NOT FOR D

ESIGN

Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

6063-O 13 7 . . . . 25 10 8 10.0

NOT FOR D

ESIGN

6063-O 13 7 . . . . 25 10 8 10.0 6063-T1 22 13 20 . . 42 14 9 10.0

NOT FOR D

ESIGN

6063-T1 22 13 20 . . 42 14 9 10.0 6063-T4 25 13 22 . . . . . . . . 10.0

NOT FOR D

ESIGN

6063-T4 25 13 22 . . . . . . . . 10.0 6063-T5 27 21 12 . . 60 17 10 10.0

NOT FOR D

ESIGN

6063-T5 27 21 12 . . 60 17 10 10.0 6063-T6 35 31 12 . . 73 22 10 10.0

NOT FOR D

ESIGN

6063-T6 35 31 12 . . 73 22 10 10.0 6063-T83 37 35 9 . . 82 22 . . 10.0

NOT FOR D

ESIGN

6063-T83 37 35 9 . . 82 22 . . 10.0 6063-T831 30 27 10 . . 70 18 . . 10.0

NOT FOR D

ESIGN

6063-T831 30 27 10 . . 70 18 . . 10.0 6063-T832 42 39 12 . . 95 27 . . 10.0

NOT FOR D

ESIGN

6063-T832 42 39 12 . . 95 27 . . 10.0

6066-O 22 12 . . 18 43 14 . . 10.0

NOT FOR D

ESIGN

6066-O 22 12 . . 18 43 14 . . 10.0 6066-T4, T451 52 30 . . 18 90 29 . . 10.0

NOT FOR D

ESIGN

6066-T4, T451 52 30 . . 18 90 29 . . 10.0 6066-T6. T651 57 52 . . 12 120 34 16 10.0

NOT FOR D

ESIGN

6066-T6. T651 57 52 . . 12 120 34 16 10.0

6070-T6 55 51 10 . . . . 34 14 10.0

NOT FOR D

ESIGN

6070-T6 55 51 10 . . . . 34 14 10.0

6101-H111 14 11 . . . . . . . . . . 10.0

NOT FOR D

ESIGN

6101-H111 14 11 . . . . . . . . . . 10.0 6101-T6 32 28 15

NOT FOR D

ESIGN

6101-T6 32 28 15

6262-T9 58 55 . . 10 120 35 13 10.0

NOT FOR D

ESIGN

6262-T9 58 55 . . 10 120 35 13 10.0

6351-T4 36 22 20 . . . . . . . . 10.0

NOT FOR D

ESIGN

6351-T4 36 22 20 . . . . . . . . 10.0 6351-T6 45 41 14 . . 95 29 13 10.0

NOT FOR D

ESIGN

6351-T6 45 41 14 . . 95 29 13 10.0

6463-T1 22 13 20 . . 42 14 10 10.0NOT FOR D

ESIGN

6463-T1 22 13 20 . . 42 14 10 10.0 6463-T5 27 21 12 . . 60 17 10 10.0NOT F

OR DESIG

N

6463-T5 27 21 12 . . 60 17 10 10.0 6463-T6 35 31 12 . . 74 22 10 10.0NOT F

OR DESIG

N

6463-T6 35 31 12 . . 74 22 10 10.0

7049-T73 75 65 . . 12 135 44 . . 10.4NOT FOR D

ESIGN

7049-T73 75 65 . . 12 135 44 . . 10.4NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

6066-T4, T451 52 30 . . 18 90 29 . . 10.0

NOT FOR D

ESIGN

6066-T4, T451 52 30 . . 18 90 29 . . 10.0 6066-T6. T651 57 52 . . 12 120 34 16 10.0

NOT FOR D

ESIGN

6066-T6. T651 57 52 . . 12 120 34 16 10.0

6070-T6 55 51 10 . . . . 34 14 10.0

NOT FOR D

ESIGN

6070-T6 55 51 10 . . . . 34 14 10.0

6101-H111 14 11 . . . . . . . . . . 10.0

NOT FOR D

ESIGN

6101-H111 14 11 . . . . . . . . . . 10.0 6101-T6 32 28 15

NOT FOR D

ESIGN

6101-T6 32 28 15

6262-T9 58 55 . . 10 120 35 13 10.0

NOT FOR D

ESIGN

6262-T9 58 55 . . 10 120 35 13 10.0

6351-T4 36 22 20 . . . . . . . . 10.0

NOT FOR D

ESIGN

6351-T4 36 22 20 . . . . . . . . 10.0 6351-T6 45 41 14 . . 95 29 13 10.0

NOT FOR D

ESIGN

6351-T6 45 41 14 . . 95 29 13 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

NOT FOR D

ESIGN

Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

6063-O 13 7 . . . . 25 10 8 10.0

NOT FOR D

ESIGN

6063-O 13 7 . . . . 25 10 8 10.0 6063-T1 22 13 20 . . 42 14 9 10.0

NOT FOR D

ESIGN

6063-T1 22 13 20 . . 42 14 9 10.0 6063-T4 25 13 22 . . . . . . . . 10.0

NOT FOR D

ESIGN

6063-T4 25 13 22 . . . . . . . . 10.0 6063-T5 27 21 12 . . 60 17 10 10.0

NOT FOR D

ESIGN

6063-T5 27 21 12 . . 60 17 10 10.0 6063-T6 35 31 12 . . 73 22 10 10.0

NOT FOR D

ESIGN

6063-T6 35 31 12 . . 73 22 10 10.0 6063-T83 37 35 9 . . 82 22 . . 10.0

NOT FOR D

ESIGN

6063-T83 37 35 9 . . 82 22 . . 10.0 6063-T831 30 27 10 . . 70 18 . . 10.0

NOT FOR D

ESIGN

6063-T831 30 27 10 . . 70 18 . . 10.0 6063-T832 42 39 12 . . 95 27 . . 10.0

NOT FOR D

ESIGN

6063-T832 42 39 12 . . 95 27 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

6061-O 18 8 25 30 30 12 9 10.0

NOT FOR D

ESIGN

6061-O 18 8 25 30 30 12 9 10.0 6061-T4, T451 35 21 22 25 65 24 14 10.0

NOT FOR D

ESIGN

6061-T4, T451 35 21 22 25 65 24 14 10.0 6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

6061-T6, T651 45 40 12 17 95 30 14 10.0

Alclad 6061-O 17 7 25 . . . . 11 . . 10.0

NOT FOR D

ESIGN


NOT FOR D

ESIGN

Alclad 6061-T4, T451 33 19 22 . . . . 22 . . 10.0Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

NOT FOR D

ESIGN

Alclad 6061-T6, T651 42 37 12 . . . . 27 . . 10.0

6063-O 13 7 . . . . 25 10 8 10.0

NOT FOR D

ESIGN

6063-O 13 7 . . . . 25 10 8 10.0 6063-T1 22 13 20 . . 42 14 9 10.0

NOT FOR D

ESIGN

6063-T1 22 13 20 . . 42 14 9 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

6063-T6 35 31 12 . . 73 22 10 10.0

NOT FOR D

ESIGN

6063-T6 35 31 12 . . 73 22 10 10.0 6063-T83 37 35 9 . . 82 22 . . 10.0

NOT FOR D

ESIGN

6063-T83 37 35 9 . . 82 22 . . 10.0 6063-T831 30 27 10 . . 70 18 . . 10.0

NOT FOR D

ESIGN

6063-T831 30 27 10 . . 70 18 . . 10.0 6063-T832 42 39 12 . . 95 27 . . 10.0

NOT FOR D

ESIGN

6063-T832 42 39 12 . . 95 27 . . 10.0

6066-O 22 12 . . 18 43 14 . . 10.0

NOT FOR D

ESIGN

6066-O 22 12 . . 18 43 14 . . 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

6066-T4, T451 52 30 . . 18 90 29 . . 10.0

NOT FOR D

ESIGN

6066-T4, T451 52 30 . . 18 90 29 . . 10.0 6066-T6. T651 57 52 . . 12 120 34 16 10.0

NOT FOR D

ESIGN

6066-T6. T651 57 52 . . 12 120 34 16 10.0

6070-T6 55 51 10 . . . . 34 14 10.0

NOT FOR D

ESIGN

6070-T6 55 51 10 . . . . 34 14 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5652-H36 40 35 8 10 73 23 19 10.2 5652-H38 42 37 7 8 77 24 20 10.2

NOT FOR D

ESIGN

5652-H38 42 37 7 8 77 24 20 10.2

5657-H25 23 20 12 . . 40 12 . . 10.0

NOT FOR D

ESIGN

5657-H25 23 20 12 . . 40 12 . . 10.0 5657-H38, H28 28 24 7 . . 50 15 . . 10.0

NOT FOR D

ESIGN

5657-H38, H28 28 24 7 . . 50 15 . . 10.0

6061-O 18 8 25 30 30 12 9 10.0

NOT FOR D

ESIGN

6061-O 18 8 25 30 30 12 9 10.0 6061-T4, T451 35 21 22 25 65 24 14 10.0

NOT FOR D

ESIGN

6061-T4, T451 35 21 22 25 65 24 14 10.0 6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

6061-T6, T651 45 40 12 17 95 30 14 10.0

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

5457-O 19 7 22 . . 32 12 . . 10.0 5457-H25 26 23 12 . . 48 16 . . 10.0

NOT FOR D

ESIGN

5457-H25 26 23 12 . . 48 16 . . 10.0 5457-H38, H28 30 27 6 . . 55 18 . . 10.0

NOT FOR D

ESIGN

5457-H38, H28 30 27 6 . . 55 18 . . 10.0

5652-O 28 13 25 30 47 18 16 10.2

NOT FOR D

ESIGN

5652-O 28 13 25 30 47 18 16 10.2 5652-H32 33 28 12 18 60 20 17 10.2

NOT FOR D

ESIGN

5652-H32 33 28 12 18 60 20 17 10.2 5652-H34 38 31 10 14 68 21 18 10.2

NOT FOR D

ESIGN

5652-H34 38 31 10 14 68 21 18 10.2 5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

5652-H36 40 35 8 10 73 23 19 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5454-H34 44 35 10 . . 81 26 . . 10.2

NOT FOR D

ESIGN

5454-H34 44 35 10 . . 81 26 . . 10.2 5454-H111 38 26 14 . . 70 23 . . 10.2

NOT FOR D

ESIGN

5454-H111 38 26 14 . . 70 23 . . 10.2 5454-H112 36 18 18 . . 62 23 . . 10.2

NOT FOR D

ESIGN 5454-H112 36 18 18 . . 62 23 . . 10.2

5456-O 45 23 . . 24 . . . . . . 10.3

NOT FOR D

ESIGN 5456-O 45 23 . . 24 . . . . . . 10.3

5456-H25 45 24 . . 22 . . . . . . 10.3

NOT FOR D

ESIGN 5456-H25 45 24 . . 22 . . . . . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN 51 37 . . 16 90 30 . . 10.3

51 37 . . 16 90 30 . . 10.3

NOT FOR D

ESIGN

51 37 . . 16 90 30 . . 10.3

5457-O 19 7 22 . . 32 12 . . 10.0

NOT FOR D

ESIGN

5457-O 19 7 22 . . 32 12 . . 10.0

V-20 January 2005



7175-T74 76 66 . . 11 135 42 23 10.4

7178-O 33 15 15 16 . . . . . . 10.4 7178-T6, T651 88 78 10 11 . . . . . . 10.4 7178-T76, T7651 83 73 . . 11 . . . . . . 10.3

Alclad 7178-O 32 14 16 . . . . . . . . 10.4Alclad 7178-T6, T651 81 71 10 . . . . . . . . 10.4

7475-T61 82 71 11 . . . . . . . . 10.2 7475-T651 85 74 . . 13 . . . . . . 10.4 7475-T7351 72 61 . . 13 . . . . . . 10.4 7475-T761 75 65 12 . . . . . . . . 10.2 7475-T7651 77 67 . . 12 . . . . . . 10.4

Alclad 7475-T61 75 66 11 . . . . . . . . 10.2Alclad 7475-T761 71 61 12 . . . . . . . . 10.2

8176-H24 17 14 15 . . . . 10 . . 10.0





① The mechanical property limits are listed by major product in the “Stan-dards Section” of Aluminum Standards and Data 2003.② The indicated typical mechanical properties for all except O temper material are higher than the specifi ed minimum properties. For O temper products typical ultimate and yield values are slightly lower than specifi ed (maximum) values.③ Based on 500,000,000 cycles of completely reversed stress using the R.R. Moore type of machine and specimen.④ Average of tension and compression moduli. Compression modulus is about 2% greater than tension modulus.⑤ 1350-O wire will have an elongation of approximately 23% in 10 inches.⑥ 1350-H19 wire will have an elongation of approximately 1½% in 10 inches.

⑦ Tempers T361 and T861 were formerly designated T36 and T86, respectively.⑧ Based on ¼ in. thick specimen.⑨ Based on 107 cycles using fl exural type testing of sheet specimens.⑩ T7451, although not previously registered, has appeared in literature and in some specifi cations as T73651.⑪ 5xxx products in the -H116 and -H32X tempers have similar mechanical properties; however, production methods and testing requirements differ, and these tempers are not interchangeable. The -H116 temper is typically used in marine and other applications requiring demonstrations of exfolia-tion resistance.

ALLOY AND

TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

7475-T61 82 71 11 . . . . . . . . 10.2

NOT FOR D

ESIGN

7475-T61 82 71 11 . . . . . . . . 10.2 7475-T651 85 74 . . 13 . . . . . . 10.4

NOT FOR D

ESIGN

7475-T651 85 74 . . 13 . . . . . . 10.4 7475-T7351 72 61 . . 13 . . . . . . 10.4

NOT FOR D

ESIGN

7475-T7351 72 61 . . 13 . . . . . . 10.4 7475-T761 75 65 12 . . . . . . . . 10.2

NOT FOR D

ESIGN 7475-T761 75 65 12 . . . . . . . . 10.2

7475-T7651 77 67 . . 12 . . . . . . 10.4

NOT FOR D

ESIGN 7475-T7651 77 67 . . 12 . . . . . . 10.4

Alclad 7475-T61 75 66 11 . . . . . . . . 10.2

NOT FOR D

ESIGNAlclad 7475-T61 75 66 11 . . . . . . . . 10.2

Alclad 7475-T761 71 61 12 . . . . . . . . 10.2

NOT FOR D

ESIGNAlclad 7475-T761 71 61 12 . . . . . . . . 10.2

8176-H24 17 14 15 . . . . 10 . . 10.0

NOT FOR D

ESIGN

8176-H24 17 14 15 . . . . 10 . . 10.0

NOT FOR D

ESIGN 7475-T761 75 65 12 . . . . . . . . 10.2

NOT FOR D

ESIGN 7475-T761 75 65 12 . . . . . . . . 10.2

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN 7475-T7651 77 67 . . 12 . . . . . . 10.4

NOT FOR D

ESIGN 7475-T7651 77 67 . . 12 . . . . . . 10.4

Alclad 7475-T61 75 66 11 . . . . . . . . 10.2

NOT FOR D

ESIGNAlclad 7475-T61 75 66 11 . . . . . . . . 10.2

Alclad 7475-T761 71 61 12 . . . . . . . . 10.2

NOT FOR D

ESIGNAlclad 7475-T761 71 61 12 . . . . . . . . 10.2

8176-H24 17 14 15 . . . . 10 . . 10.0

NOT FOR D

ESIGN

8176-H24 17 14 15 . . . . 10 . . 10.0

Tempers T361 and T861 were formerly designated T36 and T86,

NOT FOR D

ESIGN

Tempers T361 and T861 were formerly designated T36 and T86,

NOT FOR D

ESIGN

1350-O wire will have an elongation of approximately 23% in 10 inches.

NOT FOR D

ESIGN

1350-O wire will have an elongation of approximately 23% in 10 inches. 1350-H19 wire will have an elongation of approximately 1½% in 10 inches.

NOT FOR D

ESIGN

1350-H19 wire will have an elongation of approximately 1½% in 10 inches.

Based on ¼ in. thick specimen.

NOT FOR D

ESIGN

Based on ¼ in. thick specimen. Based on 10

NOT FOR D

ESIGN

Based on 107

NOT FOR D

ESIGN

7 cycles using fl exural type testing of sheet specimens.

NOT FOR D

ESIGN

cycles using fl exural type testing of sheet specimens. T7451, although not previously registered, has appeared in literature and

NOT FOR D

ESIGN

T7451, although not previously registered, has appeared in literature and in some specifi cations as T73651.

NOT FOR D

ESIGN

in some specifi cations as T73651.⑪

NOT FOR D

ESIGN

⑪ 5xxx products in the -H116 and -H32X tempers have similar mechanical

NOT FOR D

ESIGN

5xxx products in the -H116 and -H32X tempers have similar mechanical properties; however, production methods and testing requirements differ,

NOT FOR D

ESIGN

properties; however, production methods and testing requirements differ, and these tempers are not interchangeable. The -H116 temper is typically

NOT FOR D

ESIGN

and these tempers are not interchangeable. The -H116 temper is typically used in marine and other applications requiring demonstrations of exfolia-

NOT FOR D

ESIGN

used in marine and other applications requiring demonstrations of exfolia-tion resistance.

NOT FOR D

ESIGN

tion resistance.

January 2005 V-21

Table 6MTYPICAL MECHANICAL PROPERTIES ① ②

ALLOY AND

TEMPER


STRENGTH MPa

ELONGATION percent BRINNELL

NUMBER

500 kgf load 10 mm ball


MPa

ENDURANCE ③ LIMIT

MPa

MODULUS ④ OF

ELASTICITY MPa × 103ULTIMATE YIELD

in 50 mm in 5D

1.60 mm Thick

Specimen

12.5 mm Diameter Specimen

1060-O1060-H121060-H141060-H161060-H18

7085

100115130

30 75 90105125

431612 8 6

. .

. .

. .

. .

. .

1923263035

5055607075

2030354545

6969696969

1100-O1100-H121100-H141100-H161100-H18

90110125145165

35105115140150

3512 9 6 5

4222181513

2328323844

6070758590

3540506060

6969696969

1350-O1350-H121350-H141350-H161350-H19

8595

110125185

308595

110165

. .

. .

. .

. .

. .

. .⑤. .. .. .

. .⑥

. .

. .

. .

. .

. .

55607075

105

. .

. .

. .

. .50

6969696969

2011-T32011-T8

380405

295310

. .

. .1310

95100

220240

125125

7070

2014-O2014-T4, T4512014-T6, T651

185425485

95290415

. .

. .

. .

161811

45105135

125260290

90140125

737373

Alclad 2014-OAlclad 2014-T3Alclad 2014-T4, T451Alclad 2014-T6, T651

170435421470

70275255415

21202210

. .

. .

. .

. .

. .

. .

. .

. .

125255255285

. .

. .

. .

. .

73737373

2017-O2017-T4, T451

180425

70275

. .

. .2020

45105

125260

90125

7373

2018-T61 420 315 . . 10 120 270 115 742024-O2024-T32024-T4, T3512024-T361 ⑦

185485472495

75345325395

20182013

20. .17. .

47120120130

125285285290

90140140125

73737373

Alclad 2024-OAlclad 2024-T3Alclad 2024-T4, T351Alclad 2024-T361 ⑦Alclad 2024-T81, T851Alclad 2024-T861 ⑦

180450440460450485

75310290365415455

20181911 6 6

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

125275275285275290

. .

. .

. .

. .

. .

. .

737373737373

2025-T6 400 255 . . 17 110 240 125 72

2036-T4 340 195 24 . . . . 205 125 ⑨ 71

2117-T4 295 165 . . 24 70 195 95 712124-T851 485 440 . . 8 . . . . . . 732218-T72 330 255 . . 9 95 205 . . 742219-O2219-T422219-T31, T3512219-T372219-T622219-T81, T8512219-T87

170360360395415455475

75185250315290350395

18201711101010

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .105105105

73737373737373

2618-T61 440 370 . . 10 115 260 90 73

3003-O3003-H123003-H143003-H163003-H18

110130150175200

40125145170185

3010854

37181412 9

2835404755

75 8595

105110

5055607070

6969696969


NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN75

NOT FOR D

ESIGN75

85

NOT FOR D

ESIGN85

90

NOT FOR D

ESIGN90

35

NOT FOR D

ESIGN

3540

NOT FOR D

ESIGN40

50

NOT FOR D

ESIGN50

60

NOT FOR D

ESIGN60

60

NOT FOR D

ESIGN60

. .

NOT FOR D

ESIGN

. .

55

NOT FOR D

ESIGN55

60

NOT FOR D

ESIGN

6070

NOT FOR D

ESIGN

7075

NOT FOR D

ESIGN

75105

NOT FOR D

ESIGN

105

95

NOT FOR D

ESIGN

95100

NOT FOR D

ESIGN

100220

NOT FOR D

ESIGN

220240

NOT FOR D

ESIGN

240 45

NOT FOR D

ESIGN

45105

NOT FOR D

ESIGN

105135

NOT FOR D

ESIGN

135. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .20

NOT FOR D

ESIGN

2020

NOT FOR D

ESIGN

20. .

NOT FOR D

ESIGN

. . 10

NOT FOR D

ESIGN

10

395

NOT FOR D

ESIGN

395

20

NOT FOR D

ESIGN

2018

NOT FOR D

ESIGN

1820

NOT FOR D

ESIGN

2013

NOT FOR D

ESIGN

13

20

NOT FOR D

ESIGN

20

450

NOT FOR D

ESIGN

450485

NOT FOR D

ESIGN

485

75

NOT FOR D

ESIGN

75310

NOT FOR D

ESIGN

310290

NOT FOR D

ESIGN

290365

NOT FOR D

ESIGN

365415

NOT FOR D

ESIGN

415455

NOT FOR D

ESIGN

455

20

NOT FOR D

ESIGN

2018

NOT FOR D

ESIGN

1819

NOT FOR D

ESIGN

19

400

NOT FOR D

ESIGN

400 255

NOT FOR D

ESIGN

255

340

NOT FOR D

ESIGN

340 195

NOT FOR D

ESIGN

195

295

NOT FOR D

ESIGN

2952124-T851

NOT FOR D

ESIGN

2124-T851 485

NOT FOR D

ESIGN

4852218-T72

NOT FOR D

ESIGN

2218-T72 330

NOT FOR D

ESIGN

3302219-O

NOT FOR D

ESIGN

2219-O2219-T42

NOT FOR D

ESIGN

2219-T422219-T31, T351NOT F

OR DESIG

N

2219-T31, T3512219-T37NOT F

OR DESIG

N

2219-T372219-T62NOT F

OR DESIG

N

2219-T62NOT FOR D

ESIGN

2219-T81, T851NOT FOR D

ESIGN

2219-T81, T8512219-T87NOT F

OR DESIG

N

2219-T87

170

NOT FOR D

ESIGN

170

V-22 January 2005

Table 6MTYPICAL MECHANICAL PROPERTIES ① ② (Continued)

ALLOY AND

TEMPER


STRENGTH MPa

ELONGATION percent BRINNELL

NUMBER



MPa

ENDURANCE ③ LIMIT

MPa

MODULUS ④ OF


in 50 mm in 5D

1.60 mm Thick

Specimen

12.5 mm Diameter Specimen

Alclad 3003-OAlclad 3003-H12Alclad 3003-H14Alclad 3003-H16Alclad 3003-H18

110130150175200

40125145170185

3010854

371814129

. .

. .

. .

. .

. .

758595

105110

. .

. .

. .

. .

. .

6969696969

3004-O3004-H323004-H343004-H363004-H38

180215240260285

70170200230250

2010955

22151085

4552637077

110115125140145

95105105110110

6969696969

Alclad 3004-OAlclad 3004-H32Alclad 3004-H34Alclad 3004-H36Alclad 3004-H38

180215240260285

70170200230250

2010955

22151085

. .

. .

. .

. .

. .

110115125140145

. .

. .

. .

. .

. .

6969696969

3105-O3105-H123105-H143105-H163105-H183105-H223105-H243105-H253105-H263105-H28

115150170195215165180185195205

55130150170195140150160165180

247543

1110998

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

8595

10511011595

105105110115

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

69696969696969696969

4032-T6 380 315 . . 9 120 260 110 79

5005-O5005-H125005-H145005-H165005-H185005-H325005-H345005-H365005-H38

125140160180200140160180200

40130150170195115140165185

2510654

11865

. .

. .

. .

. .

. .

. .

. .

. .

. .

28. .. .. .. .

36414651

759595

1051109595

105110

. .

. .

. .

. .

. .

. .

. .

. .

. .

696969696969696969

5050-O5050-H325050-H345050-H365050-H38

145170190205220

55145165180200

249876

. .

. .

. .

. .

. .

3646535863

105115125130140

8590909595

6969696969

5052-O5052-H325052-H345052-H365052-H38

195230260275290

90195215240255

25121087

27161297

4760687377

125140145160165

110115125130140

7070707070

5056-O5056-H185056-H38

290435415

150405345

. .

. .

. .

329

13

65105100

180235220

140150150

717171

5083-O5083-H116 ⑪5083-H321

290315315

145230230

. .

. .

. .

201414

. .

. .

. .

170. .. .

. .160160

717171

5086-O5086-H325086-H116 ⑪5086-H345086-H112

260290290325270

115205205255130

2212121014

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

165. .. .

185. .

. .

. .

. .

. .

. .

7171717171


NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN145

NOT FOR D

ESIGN145

95

NOT FOR D

ESIGN

95105

NOT FOR D

ESIGN105105

NOT FOR D

ESIGN105110

NOT FOR D

ESIGN110110

NOT FOR D

ESIGN110

110

NOT FOR D

ESIGN110

115

NOT FOR D

ESIGN

115125

NOT FOR D

ESIGN

125140

NOT FOR D

ESIGN

140145

NOT FOR D

ESIGN

145

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

85

NOT FOR D

ESIGN

8595

NOT FOR D

ESIGN

95105

NOT FOR D

ESIGN

105

9

NOT FOR D

ESIGN

9

115

NOT FOR D

ESIGN

115140

NOT FOR D

ESIGN

140165

NOT FOR D

ESIGN

165185

NOT FOR D

ESIGN

185

25

NOT FOR D

ESIGN

2510

NOT FOR D

ESIGN

106

NOT FOR D

ESIGN

65

NOT FOR D

ESIGN

54

NOT FOR D

ESIGN

411

NOT FOR D

ESIGN

118

NOT FOR D

ESIGN

86

NOT FOR D

ESIGN

65

NOT FOR D

ESIGN

5

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

170

NOT FOR D

ESIGN

170190

NOT FOR D

ESIGN

190205

NOT FOR D

ESIGN

205220

NOT FOR D

ESIGN

220

55

NOT FOR D

ESIGN

55145

NOT FOR D

ESIGN

145165

NOT FOR D

ESIGN

165180

NOT FOR D

ESIGN

180200

NOT FOR D

ESIGN

200

24

NOT FOR D

ESIGN

24

5052-H34

NOT FOR D

ESIGN

5052-H345052-H36

NOT FOR D

ESIGN

5052-H365052-H38

NOT FOR D

ESIGN

5052-H38

195

NOT FOR D

ESIGN

195230

NOT FOR D

ESIGN

230260

NOT FOR D

ESIGN

260275

NOT FOR D

ESIGN

275290

NOT FOR D

ESIGN

290

5056-O NOT FOR D

ESIGN

5056-O5056-H18NOT F

OR DESIG

N

5056-H185056-H38NOT F

OR DESIG

N

5056-H38

290NOT FOR D

ESIGN

290

5083-H116 NOT FOR D

ESIGN

5083-H116 ⑪NOT FOR D

ESIGN

⑪

January 2005 V-23


ALLOY AND

TEMPER


STRENGTH ksi

ELONGATION percent in 2 in. BRINNELL

NUMBER


ULTIMATESHEARING STRENGTH

MPa

ENDURANCE ③LIMIT

MPa

MODULUS ④OF


in 50 mm in 5D

1.60 mm Thick

Specimen

12.5 mmDiameter Specimen

5154-O5154-H325154-H345154-H365154-H385154-H112

240270290310330240

115205230250270115

271513121025

. .

. .

. .

. .

. .

. .

58 67 73 78 80 63

150150165180195. .

115125130140145115

707070707070

5252-H255252-H38, H28

235285

170240

11 5

. .

. . 68 75

145160

. .

. .6969

5254-O5254-H325254-H345254-H365254-H385254-H112

240270290310330240

115205230250270115

271513121025

. .

. .

. .

. .

. .

. .

58 67 73 78 80 63

150150165180195. .

115125130140145115

707070707070

5454-O5454-H325454-H345454-H1115454-H112

250275305260250

115205240180125

2210101418

. .

. .

. .

. .

. .

62 73 81 70 62

160165180160160

. .

. .

. .

. .

. .

7070707070

5456-O5456-H255456-H321, H116

310310350

160165255

. .

. .

. .

222014

. .

. . 90

. .

. .205

. .

. .

. .

717171

5457-O5457-H255457-H38, H28

130180205

50160185

2212 6

. .

. .

. .

32 48 55

85110125

. .

. .

. .

696969

5652-O5652-H325652-H345652-H365652-H38

195230260275290

90195215240255

251210 8 7

271612 9 7

47 60 68 73 77

125140145160165

110115125130140

7070707070

5657-H255657-H38, H28

160195

140165

12 7

. .

. . 40 50

95105

. .

. .6969

6061-O6061-T4, T4516061-T6, T651

125240310

55145275

252212

272215

30 65 95

85165205

60 95 95

696969

Alclad 6061-OAlclad 6061-T4, T451Alclad 6061-T6, T651

115230290

50130255

252212

. .

. .

. .

. .

. .

. .

75150185

. .

. .

. .

696969

6063-O6063-T16063-T46063-T56063-T66063-T836063-T8316063-T832

90150170185240255205290

50 90 90145215240185270

. .20221212 91012

. .

. .

. .

. .

. .

. .

. .

. .

25 42. .

60 73 82 70 95

70 95. .

115150150125185

55 60. .

70 70. .. .. .

6969696969696969

6066-O6066-T4, T4516066-T6. T651

150360395

85205360

. .

. .

. .

161610

43 90120

95200235

. .

. .110

696969

6070-T6 380 350 10 . . . . 235 95 696101-H1116101-T6

95220

75195

. . 15 ⑧

. .

. .. .

71. .

140. .. .

6969

6262-T9 400 380 . . 9 120 240 90 696351-T46351-T6

250310

150285

2014

. .

. .. .

95. .

200. .

906969

6463-T16463-T56463-T6

150185240

90145215

201212

. .

. .

. .

42 60 74

95115150

70 70 70

696969


NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

115

NOT FOR D

ESIGN

115. .

NOT FOR D

ESIGN. .

. .

NOT FOR D

ESIGN. .

150

NOT FOR D

ESIGN150

150

NOT FOR D

ESIGN150

165

NOT FOR D

ESIGN165

180

NOT FOR D

ESIGN

180195

NOT FOR D

ESIGN

195. .

NOT FOR D

ESIGN

. .

115

NOT FOR D

ESIGN115

125

NOT FOR D

ESIGN125

62

NOT FOR D

ESIGN

62 73

NOT FOR D

ESIGN

73 81

NOT FOR D

ESIGN

81 70

NOT FOR D

ESIGN

70 62

NOT FOR D

ESIGN

62

160

NOT FOR D

ESIGN

160165

NOT FOR D

ESIGN

165180

NOT FOR D

ESIGN

180

20

NOT FOR D

ESIGN

2014

NOT FOR D

ESIGN

14

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. . 90

NOT FOR D

ESIGN

90

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .25

NOT FOR D

ESIGN

2512

NOT FOR D

ESIGN

1210

NOT FOR D

ESIGN

10 8

NOT FOR D

ESIGN

8 7

NOT FOR D

ESIGN

7

27

NOT FOR D

ESIGN

2716

NOT FOR D

ESIGN

1612

NOT FOR D

ESIGN

12

140

NOT FOR D

ESIGN

140165

NOT FOR D

ESIGN

16512

NOT FOR D

ESIGN

12 7

NOT FOR D

ESIGN

7 55

NOT FOR D

ESIGN

55145

NOT FOR D

ESIGN

145275

NOT FOR D

ESIGN

275

25

NOT FOR D

ESIGN

2522

NOT FOR D

ESIGN

22

115

NOT FOR D

ESIGN

115230

NOT FOR D

ESIGN

230290

NOT FOR D

ESIGN

290

50

NOT FOR D

ESIGN

50130

NOT FOR D

ESIGN

130255

NOT FOR D

ESIGN

255

6063-T5

NOT FOR D

ESIGN

6063-T56063-T6

NOT FOR D

ESIGN

6063-T66063-T83

NOT FOR D

ESIGN

6063-T836063-T831

NOT FOR D

ESIGN

6063-T8316063-T832NOT F

OR DESIG

N

6063-T832

90

NOT FOR D

ESIGN

90150

NOT FOR D

ESIGN

150170

NOT FOR D

ESIGN

170185

NOT FOR D

ESIGN

185240

NOT FOR D

ESIGN

240255

NOT FOR D

ESIGN

255

NOT FOR D

ESIGN

50

NOT FOR D

ESIGN

50

6066-ONOT FOR D

ESIGN

6066-O6066-T4, T451NOT F

OR DESIG

N

6066-T4, T4516066-T6. T651NOT F

OR DESIG

N

6066-T6. T651

V-24 January 2005


ALLOY AND

TEMPER


STRENGTH MPa

ELONGATION percent in 2 in. BRINNELL

NUMBER

500 kgf load10 mm ball

ULTIMATESHEARINGSTRENGTH

MPa

ENDURANCE ③LIMIT

MPa

MODULUS ④OF

ELASTICITYMPa × 103ULTIMATE YIELD

in 50 mm in 5D

1.60 mmThick

Specimen

12.5DiameterSpecimen

7049-T737049-T7352

515515

450435

. .

. .10 9

135135

305295

. .

. .7272

7050-T73510,T735117050-T7451 ⑩7050-T7651

495525550

435470490

. .

. .

. .

111010

. .

. .

. .

. .305325

. .

. .

. .

727272

7075-O7075-T6, T651

230570

105505

1711

14 9

60150

150330

. .160

7272

Alclad 7075-OAlclad 7075-T6, T651

220525

95460

1711

. .

. .. .. .

150315

. .

. .7272

7175-T74 525 455 . . 10 135 290 160 72

7178-O7178-T6, T6517178-T76, T7651

230605570

105540505

1510. .

14 9 9

. .

. .

. .

. .

. .

. .

. .

. .

. .

727271

Alclad 7178-OAlclad 7178-T6, T651

220560

95460

1610

. .

. .. .. .

. .

. .. .. .

7272

7475-T617475-T6517475-T73517475-T7617475-T7651

565585495515530

490510420450460

11. .. .12. .

. .1313. .12

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

7072727072

Alclad 7475-T61Alclad 7475-T761

515490

455420

1112

. .

. .. .. .

. .

. .. .. .

7070

8176-H24 160 95 15 . . . . 70 . . 69

① The mechanical property limits are listed by major product in the “Stan-dards Section” of Aluminum Standards and Data, 2003.② The indicated typical mechanical properties for all except O temper material are higher than the specifi ed minimum properties. For O temper products typical ultimate and yield values are slightly lower than specifi ed (maximum) values.③ Based on 500,000,000 cycles of completely reversed stress using the R.R. Moore type of machine and specimen.④ Average of tension and compression moduli. Compression modulus is about 2% greater than tension modulus.⑤ 1350-O wire will have an elongation of approximately 23% in 250 mm.⑥ 1350-H19 wire will have an elongation of approximately 1½% in 250 mm.

⑦ Tempers T361 and T861 were formerly designated T36 and T86, respec-tively.⑧ Based on 6.3 mm. thick specimen.⑨ Based on 107 cycles using fl exural type testing of sheet specimens.⑩ T7451, although not previously registered, has appeared in literature and in some specifi cations as T73651.⑪ 5xxx products in the -H116 and -H32X tempers have similar mechanical properties; however, production methods and testing requirements differ, and these tempers are not interchangeable. The -H116 temper is typically used in marine and other applications requiring demonstrations of exfolia-tion resistance.

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN. .

NOT FOR D

ESIGN. .

. .

NOT FOR D

ESIGN. .160

NOT FOR D

ESIGN160

150

NOT FOR D

ESIGN150

315

NOT FOR D

ESIGN315. .

NOT FOR D

ESIGN. .. .

NOT FOR D

ESIGN. .

290

NOT FOR D

ESIGN

290 160

NOT FOR D

ESIGN160

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

12

NOT FOR D

ESIGN

12

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

NOT FOR D

ESIGN

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

The mechanical property limits are listed by major product in the “Stan-

NOT FOR D

ESIGN

The mechanical property limits are listed by major product in the “Stan-

The indicated typical mechanical properties for all except O temper

NOT FOR D

ESIGN

The indicated typical mechanical properties for all except O temper material are higher than the specifi ed minimum properties. For O temper

NOT FOR D

ESIGN

material are higher than the specifi ed minimum properties. For O temper products typical ultimate and yield values are slightly lower than specifi ed

NOT FOR D

ESIGN

products typical ultimate and yield values are slightly lower than specifi ed

Based on 500,000,000 cycles of completely reversed stress using the

NOT FOR D

ESIGN

Based on 500,000,000 cycles of completely reversed stress using the R.R. Moore type of machine and specimen.

NOT FOR D

ESIGN

R.R. Moore type of machine and specimen.

NOT FOR D

ESIGN

Average of tension and compression moduli. Compression modulus is

NOT FOR D

ESIGN

Average of tension and compression moduli. Compression modulus is about 2% greater than tension modulus.

NOT FOR D

ESIGN

about 2% greater than tension modulus.1350-O wire will have an elongation of approximately 23% in 250 mm.

NOT FOR D

ESIGN

1350-O wire will have an elongation of approximately 23% in 250 mm.1350-H19 wire will have an elongation of approximately 1½% in 250 mm.

NOT FOR D

ESIGN

1350-H19 wire will have an elongation of approximately 1½% in 250 mm.

⑦

NOT FOR D

ESIGN

⑦

January 2005 V-25

ALLOY TEMPER

68° TO 212°F English Equal Equal Ohm—Cir. per °F °F Units ④ Volume Weight Mil/Foot

1060 13.1 1195–1215 O 1625 62 204 17 H18 1600 61 201 171100 13.1 1190–1215 O 1540 59 194 18 H18 1510 57 187 181350 13.2 1195–1215 All 1625 62 204 17

2011 12.7 1005–1190 ⑥ T3 1050 39 123 27 T8 1190 45 142 232014 12.8 945–1180 ⑤ O 1340 50 159 21 T4 930 34 108 31 T6 1070 40 127 262017 13.1 955–1185 ⑤ O 1340 50 159 21 T4 930 34 108 31

2018 12.4 945–1180 ⑥ T61 1070 40 127 262024 12.9 935–1180 ⑤ O 1340 50 160 21 T3, T4, T361 840 30 96 35 T6, T81, T861 1050 38 122 272025 12.6 970–1185 ⑤ T6 1070 40 128 262036 13.0 1030–1200 ⑥ T4 1100 41 135 25

2117 13.2 1030–1200 ⑥ T4 1070 40 130 262124 12.7 935–1180 ⑤ T851 1055 38 122 272218 12.4 940–1175 ⑤ T72 1070 40 126 262219 12.4 1010–1190 ⑤ O 1190 44 138 24 T31, T37 780 28 88 37 T6, T81, T87 840 30 94 35

2618 12.4 1020–1180 T6 1020 37 120 283003 12.9 1190–1210 O 1340 50 163 21 H12 1130 42 137 25 H14 1100 41 134 25 H18 1070 40 130 263004 13.3 1165–1210 All 1130 42 137 25

3105 13.1 1175–1210 All 1190 45 148 23

4032 10.8 990–1060 ⑤ O 1070 40 132 26 T6 960 35 116 304043 12.3 1065–1170 O 1130 42 140 254045 11.7 1065–1110 All 1190 45 151 23

4343 12.0 1070–1135 All 1250 47 158 25

5005 13.2 1170–1210 All 1390 52 172 205050 13.2 1155–1205 All 1340 50 165 215052 13.2 1125–1200 All 960 35 116 305056 13.4 1055–1180 O 810 29 98 36 H38 750 27 91 38

5083 13.2 1095–1180 O 810 29 98 365086 13.2 1085–1185 All 870 31 104 33

5154 13.3 1100–1190 All 870 32 107 325252 13.2 1125–1200 All 960 35 116 305254 13.3 1100–1190 All 870 32 107 325356 13.4 1060–1175 O 810 29 98 36

5454 13.1 1115–1195 O 930 34 113 31 H38 930 34 113 315456 13.3 1055–1180 O 810 29 98 365457 13.2 1165–1210 All 1220 46 153 235652 13.2 1125–1200 All 960 35 116 305657 13.2 1180–1215 All 1420 54 180 19

6005 13.0 1125–1210 ⑥ T1 1250 47 155 22 T5 1310 49 161 21


AVERAGE ① COEFFICIENT OF THERMAL EXPANSION

MELTING RANGE ② ③

APPROX.

THERMAL CONDUCTIVITY

AT 77°F

ELECTRICAL CONDUCTIVITY

AT 68°F Percent of International

Annealed Copper Standard

ELECTRICAL RESISTIVITY

AT 68°F

Table 7TYPICAL PHYSICAL PROPERTIES —

THERMAL AND ELECTRICAL



NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

1350 13.2 1195–1215 All 1625 62 204 17

NOT FOR D

ESIGN

1350 13.2 1195–1215 All 1625 62 204 17

T3 1050 39 123 27

NOT FOR D

ESIGN

T3 1050 39 123 27 T8 1190 45 142 23

NOT FOR D

ESIGN

T8 1190 45 142 23 O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T6 1070 40 127 26

NOT FOR D

ESIGN T6 1070 40 127 26

O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T61 1070 40 127 26

NOT FOR D

ESIGN

T61 1070 40 127 26 O 1340 50 160 21

NOT FOR D

ESIGN

O 1340 50 160 21 T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T6 1070 40 127 26

NOT FOR D

ESIGN T6 1070 40 127 26

O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T61 1070 40 127 26

NOT FOR D

ESIGN

T61 1070 40 127 26 O 1340 50 160 21

NOT FOR D

ESIGN

O 1340 50 160 21 T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35 T6, T81, T861 1050 38 122 27

NOT FOR D

ESIGN

T6, T81, T861 1050 38 122 27 T6 1070 40 128 26

NOT FOR D

ESIGN

T6 1070 40 128 26 T4 1100 41 135 25

NOT FOR D

ESIGN

T4 1100 41 135 25

T4 1070 40 130 26

NOT FOR D

ESIGN

T4 1070 40 130 26 T851 1055 38 122 27

NOT FOR D

ESIGN

T851 1055 38 122 27 T72 1070 40 126 26

NOT FOR D

ESIGN

T72 1070 40 126 26 O 1190 44 138 24

NOT FOR D

ESIGN

O 1190 44 138 24

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35 T6, T81, T861 1050 38 122 27

NOT FOR D

ESIGN

T6, T81, T861 1050 38 122 27 T6 1070 40 128 26

NOT FOR D

ESIGN

T6 1070 40 128 26 T4 1100 41 135 25

NOT FOR D

ESIGN

T4 1100 41 135 25

T4 1070 40 130 26

NOT FOR D

ESIGN

T4 1070 40 130 26 T851 1055 38 122 27

NOT FOR D

ESIGN

T851 1055 38 122 27 T72 1070 40 126 26

NOT FOR D

ESIGN

T72 1070 40 126 26 O 1190 44 138 24

NOT FOR D

ESIGN

O 1190 44 138 24 T31, T37 780 28 88 37

NOT FOR D

ESIGN

T31, T37 780 28 88 37 T6, T81, T87 840 30 94 35

NOT FOR D

ESIGN

T6, T81, T87 840 30 94 35

2618 12.4 1020–1180 T6 1020 37 120 28

NOT FOR D

ESIGN

2618 12.4 1020–1180 T6 1020 37 120 283003 12.9 1190–1210 O 1340 50 163 21

NOT FOR D

ESIGN

3003 12.9 1190–1210 O 1340 50 163 21 H12 1130 42 137 25

NOT FOR D

ESIGN

H12 1130 42 137 25 H14 1100 41 134 25

NOT FOR D

ESIGN

H14 1100 41 134 25 H18 1070 40 130 26

NOT FOR D

ESIGN

H18 1070 40 130 263004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T31, T37 780 28 88 37

NOT FOR D

ESIGN

T31, T37 780 28 88 37 T6, T81, T87 840 30 94 35

NOT FOR D

ESIGN

T6, T81, T87 840 30 94 35

2618 12.4 1020–1180 T6 1020 37 120 28

NOT FOR D

ESIGN

2618 12.4 1020–1180 T6 1020 37 120 283003 12.9 1190–1210 O 1340 50 163 21

NOT FOR D

ESIGN

3003 12.9 1190–1210 O 1340 50 163 21 H12 1130 42 137 25

NOT FOR D

ESIGN

H12 1130 42 137 25 H14 1100 41 134 25

NOT FOR D

ESIGN

H14 1100 41 134 25 H18 1070 40 130 26

NOT FOR D

ESIGN

H18 1070 40 130 263004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

3105 13.1 1175–1210 All 1190 45 148 23

NOT FOR D

ESIGN

3105 13.1 1175–1210 All 1190 45 148 23

O 1070 40 132 26

NOT FOR D

ESIGN

O 1070 40 132 26 T6 960 35 116 30

NOT FOR D

ESIGN

T6 960 35 116 304043 12.3 1065–1170 O 1130 42 140 25

NOT FOR D

ESIGN

4043 12.3 1065–1170 O 1130 42 140 254045 11.7 1065–1110 All 1190 45 151 23

NOT FOR D

ESIGN

4045 11.7 1065–1110 All 1190 45 151 23

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

3105 13.1 1175–1210 All 1190 45 148 23

NOT FOR D

ESIGN

3105 13.1 1175–1210 All 1190 45 148 23

4032 10.8 990–1060

NOT FOR D

ESIGN

4032 10.8 990–1060 ⑤

NOT FOR D

ESIGN

⑤ O 1070 40 132 26

NOT FOR D

ESIGN

O 1070 40 132 26 T6 960 35 116 30

NOT FOR D

ESIGN

T6 960 35 116 304043 12.3 1065–1170 O 1130 42 140 25

NOT FOR D

ESIGN

4043 12.3 1065–1170 O 1130 42 140 254045 11.7 1065–1110 All 1190 45 151 23

NOT FOR D

ESIGN

4045 11.7 1065–1110 All 1190 45 151 23

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

5005 13.2 1170–1210 All 1390 52 172 20

NOT FOR D

ESIGN

5005 13.2 1170–1210 All 1390 52 172 205050 13.2 1155–1205 All 1340 50 165 21

NOT FOR D

ESIGN

5050 13.2 1155–1205 All 1340 50 165 215052 13.2 1125–1200 All 960 35 116 30

NOT FOR D

ESIGN

5052 13.2 1125–1200 All 960 35 116 305056 13.4 1055–1180 O 810 29 98 36

NOT FOR D

ESIGN

5056 13.4 1055–1180 O 810 29 98 36 H38 750 27 91 38

NOT FOR D

ESIGN

H38 750 27 91 38

5083 13.2 1095–1180 O 810 29 98 36

NOT FOR D

ESIGN

5083 13.2 1095–1180 O 810 29 98 365086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

5086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

5005 13.2 1170–1210 All 1390 52 172 20

NOT FOR D

ESIGN

5005 13.2 1170–1210 All 1390 52 172 205050 13.2 1155–1205 All 1340 50 165 21

NOT FOR D

ESIGN

5050 13.2 1155–1205 All 1340 50 165 215052 13.2 1125–1200 All 960 35 116 30

NOT FOR D

ESIGN

5052 13.2 1125–1200 All 960 35 116 305056 13.4 1055–1180 O 810 29 98 36

NOT FOR D

ESIGN

5056 13.4 1055–1180 O 810 29 98 36 H38 750 27 91 38

NOT FOR D

ESIGN

H38 750 27 91 38

5083 13.2 1095–1180 O 810 29 98 36

NOT FOR D

ESIGN

5083 13.2 1095–1180 O 810 29 98 365086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

5086 13.2 1085–1185 All 870 31 104 33

5154 13.3 1100–1190 All 870 32 107 32

NOT FOR D

ESIGN

5154 13.3 1100–1190 All 870 32 107 325252 13.2 1125–1200 All 960 35 116 30NOT F

OR DESIG

N

5252 13.2 1125–1200 All 960 35 116 305254 13.3 1100–1190 All 870 32 107 32NOT F

OR DESIG

N

5254 13.3 1100–1190 All 870 32 107 325356 13.4 1060–1175 O 810 29 98 36NOT F

OR DESIG

N

5356 13.4 1060–1175 O 810 29 98 36

5454 13.1 1115–1195 O 930 34 113 31NOT FOR D

ESIGN

5454 13.1 1115–1195 O 930 34 113 31NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

5086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

5086 13.2 1085–1185 All 870 31 104 33

5154 13.3 1100–1190 All 870 32 107 32

NOT FOR D

ESIGN

5154 13.3 1100–1190 All 870 32 107 325252 13.2 1125–1200 All 960 35 116 30NOT F

OR DESIG

N

5252 13.2 1125–1200 All 960 35 116 30NOT FOR D

ESIGN

5254 13.3 1100–1190 All 870 32 107 32NOT FOR D

ESIGN

5254 13.3 1100–1190 All 870 32 107 325356 13.4 1060–1175 O 810 29 98 36NOT F

OR DESIG

N

5356 13.4 1060–1175 O 810 29 98 36NOT FOR D

ESIGN

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

5005 13.2 1170–1210 All 1390 52 172 20

NOT FOR D

ESIGN

5005 13.2 1170–1210 All 1390 52 172 205050 13.2 1155–1205 All 1340 50 165 21

NOT FOR D

ESIGN

5050 13.2 1155–1205 All 1340 50 165 215052 13.2 1125–1200 All 960 35 116 30

NOT FOR D

ESIGN

5052 13.2 1125–1200 All 960 35 116 305056 13.4 1055–1180 O 810 29 98 36

NOT FOR D

ESIGN

5056 13.4 1055–1180 O 810 29 98 36 H38 750 27 91 38

NOT FOR D

ESIGN

H38 750 27 91 38

5083 13.2 1095–1180 O 810 29 98 36

NOT FOR D

ESIGN

5083 13.2 1095–1180 O 810 29 98 365086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

5086 13.2 1085–1185 All 870 31 104 33

NOT FOR D

ESIGN

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

3105 13.1 1175–1210 All 1190 45 148 23

NOT FOR D

ESIGN

3105 13.1 1175–1210 All 1190 45 148 23

O 1070 40 132 26

NOT FOR D

ESIGN

O 1070 40 132 26 T6 960 35 116 30

NOT FOR D

ESIGN

T6 960 35 116 304043 12.3 1065–1170 O 1130 42 140 25

NOT FOR D

ESIGN

4043 12.3 1065–1170 O 1130 42 140 254045 11.7 1065–1110 All 1190 45 151 23

NOT FOR D

ESIGN

4045 11.7 1065–1110 All 1190 45 151 23

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

4343 12.0 1070–1135 All 1250 47 158 25

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T31, T37 780 28 88 37

NOT FOR D

ESIGN

T31, T37 780 28 88 37 T6, T81, T87 840 30 94 35

NOT FOR D

ESIGN

T6, T81, T87 840 30 94 35

2618 12.4 1020–1180 T6 1020 37 120 28

NOT FOR D

ESIGN

2618 12.4 1020–1180 T6 1020 37 120 283003 12.9 1190–1210 O 1340 50 163 21

NOT FOR D

ESIGN

3003 12.9 1190–1210 O 1340 50 163 21 H12 1130 42 137 25

NOT FOR D

ESIGN

H12 1130 42 137 25 H14 1100 41 134 25

NOT FOR D

ESIGN

H14 1100 41 134 25 H18 1070 40 130 26

NOT FOR D

ESIGN

H18 1070 40 130 263004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

3004 13.3 1165–1210 All 1130 42 137 25

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35 T6, T81, T861 1050 38 122 27

NOT FOR D

ESIGN

T6, T81, T861 1050 38 122 27 T6 1070 40 128 26

NOT FOR D

ESIGN

T6 1070 40 128 26 T4 1100 41 135 25

NOT FOR D

ESIGN

T4 1100 41 135 25

T4 1070 40 130 26

NOT FOR D

ESIGN

T4 1070 40 130 26 T851 1055 38 122 27

NOT FOR D

ESIGN

T851 1055 38 122 27 T72 1070 40 126 26

NOT FOR D

ESIGN

T72 1070 40 126 26 O 1190 44 138 24

NOT FOR D

ESIGN

O 1190 44 138 24

NOT FOR D

ESIGN T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

NOT FOR D

ESIGN

NOT FOR D

ESIGN O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T6 1070 40 127 26

NOT FOR D

ESIGN T6 1070 40 127 26

O 1340 50 159 21

NOT FOR D

ESIGN O 1340 50 159 21

T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

T61 1070 40 127 26

NOT FOR D

ESIGN

T61 1070 40 127 26 O 1340 50 160 21

NOT FOR D

ESIGN

O 1340 50 160 21 T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN

T3, T4, T361 840 30 96 35

NOT FOR D

ESIGN T4 930 34 108 31

NOT FOR D

ESIGN T4 930 34 108 31

V-26 January 2005

Table 7TYPICAL PHYSICAL PROPERTIES —

THERMAL AND ELECTRICAL (Continued)

ALLOY TEMPER

68° TO 212°F English Equal Equal Ohm—Cir. per °F °F Units ④ Volume Weight Mil/Foot



APPROX.


AT 77°F


AT 68°F Percent of International

Annealed Copper Standard


AT 68°F

6053 12.8 1070–1205 ⑥ O 1190 45 148 23 T4 1070 40 132 26 T6 1130 42 139 25

6061 13.1 1080–1205 ⑥ O 1250 47 155 22 T4 1070 40 132 26 T6 1160 43 142 24

6063 13.0 1140–1210 O 1510 58 191 18 T1 1340 50 165 21 T5 1450 55 181 19 T6, T83 1390 53 175 20

6066 12.9 1045–1195 ⑤ O 1070 40 132 26 T6 1020 37 122 286070 . . 1050–1200 ⑤ T6 1190 44 145 24

6101 13.0 1150–1210 T6 1510 57 188 18 T61 1540 59 194 18 T63 1510 58 191 18 T64 1570 60 198 17 T65 1510 58 191 18

6105 13.0 1110–1200 ⑥ T1 1220 46 151 23 T5 1340 50 165 216151 12.9 1090–1200 ⑥ O 1420 54 178 19 T4 1130 42 138 25 T6 1190 45 148 23

6201 13.0 1125–1210 ⑥ T81 1420 54 180 196262 13.0 1080–1205 ⑥ T9 1190 44 145 246351 13.0 1030–1200 T6 1220 46 151 23

6463 13.0 1140–1210 T1 1340 50 165 21 T5 1450 55 181 19 T6 1390 53 175 206951 13.0 1140–1210 O 1480 56 186 19 T6 1370 52 172 20

7049 13.0 890–1175 T73 1070 40 132 267050 12.8 910–1165 T74 ⑧ 1090 41 135 257072 13.1 1185–1215 O 1540 59 193 187075 13.1 890–1175 ⑦ T6 900 33 105 31

7175 13.0 890–1175 ⑦ T74 1080 39 124 267178 13.0 890–1165 ⑦ T6 870 31 98 337475 12.9 890–1175 T61, T651 960 35 116 30 T76, T761 1020 40 132 26 T7351 1130 42 139 25

8017 13.1 1190–1215 H12, H22 . . 59 193 18 H212 . . 61 200 178030 13.1 1190–1215 H221 1600 61 201 178176 13.1 1190–1215 H24 61 201 17

① Coeffi cient to be multiplied by 10−6. Example: 12.2 × 10−6 = 0.0000122.② Melting ranges shown apply to wrought products of ¼ inch thickness or greater.③ Based on typical composition of the indicated alloys.④ English units = btu-in./ft2hr°F.⑤ Eutectic melting is not eliminated by homogenization.

⑥ Eutectic melting can be completely eliminated by homogenization.⑦ Homogenization may raise eutectic melting temperature 20–40°F but usually does not eliminate eutectic melting.⑧ Although not formerly registered, the literature and some specifi cations have used T736 as the designation for this temper.

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

O 1250 47 155 22

NOT FOR D

ESIGN

O 1250 47 155 22 T4 1070 40 132 26

NOT FOR D

ESIGN

T4 1070 40 132 26 T6 1160 43 142 24

NOT FOR D

ESIGN

T6 1160 43 142 24

6063 13.0 1140–1210 O 1510 58 191 18

NOT FOR D

ESIGN6063 13.0 1140–1210 O 1510 58 191 186063 13.0 1140–1210 O 1510 58 191 18

NOT FOR D

ESIGN6063 13.0 1140–1210 O 1510 58 191 18

T1 1340 50 165 21

NOT FOR D

ESIGN T1 1340 50 165 21 T1 1340 50 165 21

NOT FOR D

ESIGN T1 1340 50 165 21

T5 1450 55 181 19

NOT FOR D

ESIGN T5 1450 55 181 19 T5 1450 55 181 19

NOT FOR D

ESIGN T5 1450 55 181 19

T6, T83 1390 53 175 20

NOT FOR D

ESIGN T6, T83 1390 53 175 20 T6, T83 1390 53 175 20

NOT FOR D

ESIGN T6, T83 1390 53 175 20

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

O 1070 40 132 26

NOT FOR D

ESIGN

O 1070 40 132 26 O 1070 40 132 26

NOT FOR D

ESIGN

O 1070 40 132 26 T6 1020 37 122 28

NOT FOR D

ESIGN

T6 1020 37 122 28 T6 1020 37 122 28

NOT FOR D

ESIGN

T6 1020 37 122 28 T6 1190 44 145 24

NOT FOR D

ESIGN

T6 1190 44 145 24 T6 1190 44 145 24

NOT FOR D

ESIGN

T6 1190 44 145 24 T6 1190 44 145 24

NOT FOR D

ESIGN

T6 1190 44 145 24

6101 13.0 1150–1210 T6 1510 57 188 18

NOT FOR D

ESIGN

6101 13.0 1150–1210 T6 1510 57 188 186101 13.0 1150–1210 T6 1510 57 188 18

NOT FOR D

ESIGN

6101 13.0 1150–1210 T6 1510 57 188 18 T61 1540 59 194 18

NOT FOR D

ESIGN

T61 1540 59 194 18 T61 1540 59 194 18

NOT FOR D

ESIGN

T61 1540 59 194 18 T63 1510 58 191 18

NOT FOR D

ESIGN

T63 1510 58 191 18 T63 1510 58 191 18

NOT FOR D

ESIGN

T63 1510 58 191 18 T64 1570 60 198 17

NOT FOR D

ESIGN

T64 1570 60 198 17 T64 1570 60 198 17

NOT FOR D

ESIGN

T64 1570 60 198 17 T65 1510 58 191 18

NOT FOR D

ESIGN

T65 1510 58 191 18 T65 1510 58 191 18

NOT FOR D

ESIGN

T65 1510 58 191 18

T1 1220 46 151 23

NOT FOR D

ESIGN

T1 1220 46 151 23 T1 1220 46 151 23

NOT FOR D

ESIGN

T1 1220 46 151 23 T5 1340 50 165 21

NOT FOR D

ESIGN

T5 1340 50 165 21 O 1420 54 178 19

NOT FOR D

ESIGN

O 1420 54 178 19 O 1420 54 178 19

NOT FOR D

ESIGN

O 1420 54 178 19 T4 1130 42 138 25

NOT FOR D

ESIGN

T4 1130 42 138 25 T4 1130 42 138 25

NOT FOR D

ESIGN

T4 1130 42 138 25 T6 1190 45 148 23

NOT FOR D

ESIGN

T6 1190 45 148 23 T6 1190 45 148 23

NOT FOR D

ESIGN

T6 1190 45 148 23

T81 1420 54 180 19

NOT FOR D

ESIGN

T81 1420 54 180 19 T81 1420 54 180 19

NOT FOR D

ESIGN

T81 1420 54 180 19 T9 1190 44 145 24

NOT FOR D

ESIGN

T9 1190 44 145 24 T9 1190 44 145 24

NOT FOR D

ESIGN

T9 1190 44 145 246351 13.0 1030–1200 T6 1220 46 151 23

NOT FOR D

ESIGN

6351 13.0 1030–1200 T6 1220 46 151 236351 13.0 1030–1200 T6 1220 46 151 23

NOT FOR D

ESIGN

6351 13.0 1030–1200 T6 1220 46 151 23

6463 13.0 1140–1210 T1 1340 50 165 21

NOT FOR D

ESIGN

6463 13.0 1140–1210 T1 1340 50 165 216463 13.0 1140–1210 T1 1340 50 165 21

NOT FOR D

ESIGN

6463 13.0 1140–1210 T1 1340 50 165 216463 13.0 1140–1210 T1 1340 50 165 21

NOT FOR D

ESIGN

6463 13.0 1140–1210 T1 1340 50 165 21 T5 1450 55 181 19

NOT FOR D

ESIGN

T5 1450 55 181 19 T5 1450 55 181 19

NOT FOR D

ESIGN

T5 1450 55 181 19 T5 1450 55 181 19

NOT FOR D

ESIGN

T5 1450 55 181 19 T6 1390 53 175 20

NOT FOR D

ESIGN

T6 1390 53 175 20 T6 1390 53 175 20

NOT FOR D

ESIGN

T6 1390 53 175 206951 13.0 1140–1210 O 1480 56 186 19

NOT FOR D

ESIGN

6951 13.0 1140–1210 O 1480 56 186 196951 13.0 1140–1210 O 1480 56 186 19

NOT FOR D

ESIGN

6951 13.0 1140–1210 O 1480 56 186 19 T6 1370 52 172 20

NOT FOR D

ESIGN

T6 1370 52 172 20 T6 1370 52 172 20

NOT FOR D

ESIGN

T6 1370 52 172 20

7049 13.0 890–1175 T73 1070 40 132 26

NOT FOR D

ESIGN

7049 13.0 890–1175 T73 1070 40 132 267049 13.0 890–1175 T73 1070 40 132 26

NOT FOR D

ESIGN

7049 13.0 890–1175 T73 1070 40 132 267050 12.8 910–1165 T74

NOT FOR D

ESIGN

7050 12.8 910–1165 T74 7050 12.8 910–1165 T74

NOT FOR D

ESIGN

7050 12.8 910–1165 T74 7072 13.1 1185–1215 O 1540 59 193 18

NOT FOR D

ESIGN

7072 13.1 1185–1215 O 1540 59 193 187072 13.1 1185–1215 O 1540 59 193 18

NOT FOR D

ESIGN

7072 13.1 1185–1215 O 1540 59 193 187072 13.1 1185–1215 O 1540 59 193 18

NOT FOR D

ESIGN

7072 13.1 1185–1215 O 1540 59 193 187075 13.1 890–1175

NOT FOR D

ESIGN

7075 13.1 890–1175 7075 13.1 890–1175

NOT FOR D

ESIGN

7075 13.1 890–1175 ⑦

NOT FOR D

ESIGN

⑦ T6 900 33 105 31

NOT FOR D

ESIGN

T6 900 33 105 31

7175 13.0 890–1175

NOT FOR D

ESIGN

7175 13.0 890–1175 7175 13.0 890–1175

NOT FOR D

ESIGN

7175 13.0 890–1175 ⑦

NOT FOR D

ESIGN

⑦

7178 13.0 890–1165

NOT FOR D

ESIGN

7178 13.0 890–1165 7178 13.0 890–1165

NOT FOR D

ESIGN

7178 13.0 890–1165 7475 12.9 890–1175 T61, T651 960 35 116 30

NOT FOR D

ESIGN

7475 12.9 890–1175 T61, T651 960 35 116 307475 12.9 890–1175 T61, T651 960 35 116 30

NOT FOR D

ESIGN

7475 12.9 890–1175 T61, T651 960 35 116 30 T76, T761 1020 40 132 26

NOT FOR D

ESIGN

T76, T761 1020 40 132 26 T76, T761 1020 40 132 26

NOT FOR D

ESIGN

T76, T761 1020 40 132 26

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T7351 1130 42 139 25

NOT FOR D

ESIGN

T7351 1130 42 139 25 T7351 1130 42 139 25

NOT FOR D

ESIGN

T7351 1130 42 139 25

8017 13.1 1190–1215 H12, H22 . . 59 193 18

NOT FOR D

ESIGN

8017 13.1 1190–1215 H12, H22 . . 59 193 188017 13.1 1190–1215 H12, H22 . . 59 193 18

NOT FOR D

ESIGN

8017 13.1 1190–1215 H12, H22 . . 59 193 188017 13.1 1190–1215 H12, H22 . . 59 193 18

NOT FOR D

ESIGN

8017 13.1 1190–1215 H12, H22 . . 59 193 18 H212 . . 61 200 17

NOT FOR D

ESIGN

H212 . . 61 200 17 H212 . . 61 200 17

NOT FOR D

ESIGN

H212 . . 61 200 178030 13.1 1190–1215 H221 1600 61 201 17

NOT FOR D

ESIGN

8030 13.1 1190–1215 H221 1600 61 201 178030 13.1 1190–1215 H221 1600 61 201 17

NOT FOR D

ESIGN

8030 13.1 1190–1215 H221 1600 61 201 17

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

8176 13.1 1190–1215 H24 61 201 17

NOT FOR D

ESIGN

8176 13.1 1190–1215 H24 61 201 178176 13.1 1190–1215 H24 61 201 17

NOT FOR D

ESIGN

8176 13.1 1190–1215 H24 61 201 17

Coeffi cient to be multiplied by 10NOT FOR D

ESIGN

Coeffi cient to be multiplied by 10NOT FOR D

ESIGN

Melting ranges shown apply to wrought products of ¼ inch thickness or NOT FOR D

ESIGN

Melting ranges shown apply to wrought products of ¼ inch thickness or

January 2005 V-27

Table 7MTYPICAL PHYSICAL PROPERTIES—

THERMAL AND ELECTRICAL



ALLOY



APPROX. TEMPER


AT 25°C


AT 20°C MS/m ⑧


AT 20°C

20° TO 100°C per °C °C W/m •K Equal

VolumeEqual Mass Ohm • mm2/m

1060

1100

1350

23.6

23.6

23.6

645–655

640–655

645–655

OH18OH18All

234230222218234

3635343336

118117113108118

0.0280.0290.0290.0300.028

2011

2014

2017

22.9

23.0

23.6

540–645 ⑤

505–635 ④

510–640 ④

T3T8OT4T6OT4

151172193134155193134

23262920232920

71829263749263

0.0430.0380.0340.0500.0430.0340.050

20182024

20252036

22.323.2

22.723.4

505–640 ⑤500–635 ④

520–640 ④555–650 ⑤

T61OT3, T4, T361T6, T81, T861T6T4

155193121151155159

232917222324

749356717478

0.0430.0340.0590.0450.0430.042

2117212422182219

23.822.922.322.3

550–650 ⑤500–635 ④505–635 ④545–645 ④

T4T851T72OT31, T37T6, T81, T87

155152155172113121

232223261617

757173805758

0.0430.0450.0430.0380.0620.059

26183003

3004

3105

22.323.2

23.9

23.6

550–640640–655

630–655

635–655

T6OH12H14H18All

All

146193163159155163

172

212924242324

26

709278787479

86

0.0480.0340.0420.0420.0430.042

0.038

4032

40434045

4343

19.4

22.021.1

21.6

530–570 ④

575–630575–600

575–615

OT6OAll

All

155138163171

180

23202426

27

77678188

92

0.0430.0500.0410.038

0.037

5005505050525056

50835086

23.823.823.824.1

23.823.8

630–655625–650605–650565–640

580–640585–640

AllAllAllOH38

OAll

201193138117109

117126

3029201716

1718

10096675753

5760

0.0330.0340.0500.0590.062

0.0590.056

5154525252545356

23.923.823.924.1

590–645605–650590–645575–635

AllAllAllO

126138126117

19201917

62676257

0.0530.0500.0530.059

5454

5456545756525657

23.6

23.923.823.823.8

600–645

570–640630–655605–650635–655

OH38OAllAllAll

134134117176138205

202017272031

6666578969

104

0.0500.0500.0590.0370.0500.032

6005 23.6 605–655 ⑤ T1T5

180188

2728

9093

0.0370.036


NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN20

NOT FOR D

ESIGN20

82

NOT FOR D

ESIGN8292

NOT FOR D

ESIGN9263

NOT FOR D

ESIGN6374

NOT FOR D

ESIGN7492

NOT FOR D

ESIGN9263

NOT FOR D

ESIGN63

23

NOT FOR D

ESIGN23

29

NOT FOR D

ESIGN

2917

NOT FOR D

ESIGN

1722

NOT FOR D

ESIGN

2223

NOT FOR D

ESIGN

2324

NOT FOR D

ESIGN

24

74

NOT FOR D

ESIGN74

155

NOT FOR D

ESIGN

155152

NOT FOR D

ESIGN

152155

NOT FOR D

ESIGN

155172

NOT FOR D

ESIGN

172113

NOT FOR D

ESIGN

113121

NOT FOR D

ESIGN

121

23

NOT FOR D

ESIGN

2322

NOT FOR D

ESIGN

22

H14

NOT FOR D

ESIGN

H14H18

NOT FOR D

ESIGN

H18All

NOT FOR D

ESIGN

All

All

NOT FOR D

ESIGN

All

146

NOT FOR D

ESIGN

146193

NOT FOR D

ESIGN

193163

NOT FOR D

ESIGN

163159

NOT FOR D

ESIGN

159

530–570

NOT FOR D

ESIGN

530–570 ④

NOT FOR D

ESIGN

④

575–630

NOT FOR D

ESIGN

575–630575–600

NOT FOR D

ESIGN

575–600

575–615

NOT FOR D

ESIGN

575–615

O

NOT FOR D

ESIGN

OT6

NOT FOR D

ESIGN

T6O

NOT FOR D

ESIGN

OAll

NOT FOR D

ESIGN

All

23.8

NOT FOR D

ESIGN

23.823.8

NOT FOR D

ESIGN

23.824.1

NOT FOR D

ESIGN

24.1

23.8

NOT FOR D

ESIGN

23.823.8

NOT FOR D

ESIGN

23.8

630–655

NOT FOR D

ESIGN

630–655625–650

NOT FOR D

ESIGN

625–650605–650

NOT FOR D

ESIGN

605–650565–640

NOT FOR D

ESIGN

565–640

5154

NOT FOR D

ESIGN

51545252 NOT F

OR DESIG

N

52525254 NOT F

OR DESIG

N

5254

23.9

NOT FOR D

ESIGN

23.923.8NOT F

OR DESIG

N

23.823.9NOT F

OR DESIG

N

23.9

V-28 January 2005

Table 7MTYPICAL PHYSICAL PROPERTIES—

THERMAL AND ELECTRICAL (Continued)

ALLOY



APPROX. TEMPER


AT 25°C


AT 20°C MS/m ⑧


AT 20°C

20° TO 100°C per °C °C W/m • K Equal

VolumeEqual Mass Ohm • mm2/m

6053 23.0 575–650 ⑤ OT4T6

172155167

262324

867781

0.0380.0420.041

6061 23.6 580–650 ⑤ OT4T6

180155167

272325

907782

0.0370.0430.040

6063 23.4 615–655 OT1T5T6, T83

218193209201

34293231

11196

105102

0.0290.0340.0310.032

6066

6070

23.2

. .

560–645 ④

565–650 ④

OT6T6

155146172

232126

777184

0.0430.0480.038

6101 23.4 620–655 T6T61T63T64T65

218222218226218

3334343534

109113111115111

0.0300.0290.0290.0290.029

6105

6151

23.4

23.2

600–650 ⑥

590–650 ⑤

T1T5OT4T6

176193205163172

2729312426

8896

1038086

0.0370.0340.0320.0420.038

620162626351

23.423.423.4

610–655 ⑤580–650 ⑤555–650

T81T9T6

205172176

312627

1048488

0.0320.0380.038

6463

6951

23.4

23.4

615–655 ⑤

615–655

T1T5T6OT6

193209201213197

2932313230

96105102108100

0.0340.0310.0320.0310.033

7049705070727075

23.423.023.623.6

475–635490–630640–655475–635 ⑥

T73T74 ⑦OT6

155157222130

23243419

7778

11261

0.0430.0420.0290.053

717571787475

23.423.423.2

475–635 ⑥475–630 ⑥475–635

T74T6T61, T651T76, T761T7351

157126138146163

2318202324

7257697781

0.0430.0560.0500.0430.041

8017

80308176

23.6

23.623.6

645–655

645–655645–655

H12, H22H212H221H24

. .

. .230230

34353535

113117117117

0.0290.0290.0290.029

① Coeffi cient to be multiplied by 10–6. Example: 23.6 × 10–6 = 0.0000236.② Melting ranges shown apply to wrought products of 6 mm thickness or greater.③ Based on typical composition of the indicated alloys.④ Eutectic melting is not eliminated by homogenization.⑤ Eutectic melting can be completely eliminated by homogenization.

⑥ Homogenization may raise eutectic melting temperature 10–20°C but usually does not eliminate eutectic melting.⑦ Although not formerly registered, the literature and some specifi cations have used T736 as the designation for this temper.⑧ MS/m = 0.58 × % IACS.NOT F

OR DESIG

N

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

111

NOT FOR D

ESIGN

11196

NOT FOR D

ESIGN

96105

NOT FOR D

ESIGN105

102

NOT FOR D

ESIGN102

23

NOT FOR D

ESIGN23

21

NOT FOR D

ESIGN21

26

NOT FOR D

ESIGN

26

77

NOT FOR D

ESIGN77

226

NOT FOR D

ESIGN

226218

NOT FOR D

ESIGN

218

33

NOT FOR D

ESIGN

3334

NOT FOR D

ESIGN

3434

NOT FOR D

ESIGN

3435

NOT FOR D

ESIGN

3534

NOT FOR D

ESIGN

34

176

NOT FOR D

ESIGN

176193

NOT FOR D

ESIGN

193205

NOT FOR D

ESIGN

205163

NOT FOR D

ESIGN

163172

NOT FOR D

ESIGN

172

205

NOT FOR D

ESIGN

205172

NOT FOR D

ESIGN

172176

NOT FOR D

ESIGN

176

T1

NOT FOR D

ESIGN

T1T5

NOT FOR D

ESIGN

T5T6

NOT FOR D

ESIGN

T6O

NOT FOR D

ESIGN

OT6

NOT FOR D

ESIGN

T6

475–635

NOT FOR D

ESIGN

475–635490–630

NOT FOR D

ESIGN

490–630640–655

NOT FOR D

ESIGN

640–655475–635

NOT FOR D

ESIGN

475–635 ⑥

NOT FOR D

ESIGN

⑥

T73

NOT FOR D

ESIGN

T73T74

NOT FOR D

ESIGN

T74 ⑦

NOT FOR D

ESIGN

⑦

O

NOT FOR D

ESIGN

O

23.2

NOT FOR D

ESIGN

23.2

475–635

NOT FOR D

ESIGN

475–635 ⑥

NOT FOR D

ESIGN

⑥

475–630

NOT FOR D

ESIGN

475–630 ⑥

NOT FOR D

ESIGN

⑥

475–635

NOT FOR D

ESIGN

475–635

23.6

NOT FOR D

ESIGN

23.6

NOT FOR D

ESIGN

23.6

NOT FOR D

ESIGN

23.623.6

NOT FOR D

ESIGN

23.6

645–655

NOT FOR D

ESIGN

645–655

Coeffi cient to be multiplied by 10

NOT FOR D

ESIGN

Coeffi cient to be multiplied by 10 Melting ranges shown apply to wrought products of 6 mm thickness or NOT F

OR DESIG

N

Melting ranges shown apply to wrought products of 6 mm thickness or

Based on typical composition of the indicated alloys.NOT FOR D

ESIGN

Based on typical composition of the indicated alloys. Eutectic melting is not eliminated by homogenization.NOT F

OR DESIG

N

Eutectic melting is not eliminated by homogenization. Eutectic melting can be completely eliminated by homogenization.NOT F

OR DESIG

N

Eutectic melting can be completely eliminated by homogenization.

January 2005 V-29

Table 8TYPICAL PHYSICAL PROPERTIES—DENSITY

Density and specific gravity are dependent upon composition, and variations are discernible from one cast to another for most alloys. The nominal values shown below should not be specified as engineering requirements but are used in calculating typical val-ues for weight per unit length, weight per unit area,

covering area, etc. The density values are derived from the metric and subsequently rounded. These values are not to be converted to the metric. X.XXX0 and X.XXX5 density values and X.XX0 and X.XX5 specific gravity values are limited to 99.35 percent or higher purity aluminum.

Density Specific Alloy (lbs/cu. in.) Gravity

1050 .0975 2.705 1060 .0975 2.705 1100 .098 2.71 1145 .0975 2.700 1175 .0975 2.700 1200 .098 2.70 1230 .098 2.70 1235 .0975 2.705 1345 .0975 2.705 1350 .0975 2.705 2011 .102 2.83 2014 .101 2.80 2017 .101 2.79 2018 .102 2.82 2024 .100 2.78 2025 .101 2.81 2036 .100 2.75 2117 .099 2.75 2124 .100 2.78 2218 .101 2.81 2219 .103 2.84 2618 .100 2.76 3003 .099 2.73 3004 .098 2.72 3005 .098 2.73 3105 .098 2.72 4032 .097 2.68 4043 .097 2.69 4045 .096 2.67 4047 .096 2.66 4145 .099 2.74 4343 .097 2.68 4643 .097 2.69 5005 .098 2.70 5050 .097 2.69 5052 .097 2.68 5056 .095 2.64 5083 .096 2.66 5086 .096 2.66 5154 .096 2.66 5183 .096 2.66

Density Specific Alloy (lbs/cu. in.) Gravity

5252 .096 2.67 5254 .096 2.66 5356 .096 2.64 5454 .097 2.69 5456 .096 2.66 5457 .097 2.69 5554 .097 2.69 5556 .096 2.66 5652 .097 2.67 5654 .096 2.66 5657 .097 2.69 6003 .097 2.70 6005 .097 2.70 6053 .097 2.69 6061 .098 2.70 6063 .097 2.70 6066 .098 2.72 6070 .098 2.71 6101 .097 2.70 6105 .097 2.69 6151 .098 2.71 6162 .097 2.70 6201 .097 2.69 6262 .098 2.72 6351 .098 2.71 6463 .097 2.69 6951 .098 2.70 7005 .100 2.78 7008 .100 2.78 7049 .103 2.84 7050 .102 2.83 7072 .098 2.72 7075 .101 2.81 7175 .101 2.80 7178 .102 2.83 7475 .101 2.81 8017 .098 2.71 8030 .098 2.71 8176 .098 2.71 8177 .098 2.70

V-30 January 2005

Table 9TYPICAL TENSILE PROPERTIES AT VARIOUS TEMPERATURES ①



ELONGATION IN 2 IN.,

PERCENT

TENSILE STRENGTH, TEMP. ksi

°F ULTIMATE YIELD ②

1100-O –320 25 6 50 –112 15 5.5 43 –18 14 5 40 75 13 5 40 212 10 4.6 45 300 8 4.2 55 400 6 3.5 65 500 4 2.6 75 600 2.9 2 80 700 2.1 1.6 85

1100-H14 –320 30 20 45 –112 20 18 24 –18 19 17 20 75 18 17 20 212 16 15 20 300 14 12 23 400 10 7.5 26 500 4 2.6 75 600 2.9 2 80 700 2.1 1.6 85

1100-H18 –320 34 26 30 –112 26 23 16 –118 25 23 15 75 24 22 15 212 21 19 15 300 18 14 20 400 6 3.5 65 500 4 2.6 75 600 2.9 2 80 700 2.1 1.6 85

2011-T3 75 55 43 15 212 47 34 16 300 28 19 25 400 16 11 35 500 6.5 3.8 45 600 3.1 1.8 90 700 2.3 1.4 125

2014-T6, T651 –320 84 72 14 –112 74 65 13 –18 72 62 13 75 70 60 13 212 63 57 15 300 40 35 20 400 16 13 38 500 9.5 7.5 52 600 6.5 5 65 700 4.3 3.5 72

2017-T4, T451 –320 80 53 28 –112 65 42 24 –18 64 41 23 75 62 40 22 212 57 39 18 300 40 30 15 400 16 13 35 500 9 7.5 45 600 6 5 65 700 4.3 3.5 70




PERCENT

ALLOY AND TEMPER

2024-T3 –320 85 62 18(Sheet) –112 73 52 17 –18 72 51 17 75 70 50 17 212 66 48 16 300 55 45 11 400 27 20 23 500 11 9 55 600 7.5 6 75 700 5 4 100

2024-T4, T351 –320 84 61 19(plate) –112 71 49 19 –18 69 47 19 75 68 47 19 212 63 45 19 300 45 36 17 400 26 19 27 500 11 9 55 600 7.5 6 75 700 5 4 100

2024-T6, T651 –320 84 68 11 –112 72 59 10 –18 70 58 10 75 69 57 10 212 65 54 10 300 45 36 17 400 26 19 27 500 11 9 55 600 7.5 6 75 700 5 4 100

2024-T81, T851 –320 85 78 8 –112 74 69 7 –18 73 68 7 75 70 65 7 212 66 62 8 300 55 49 11 400 27 20 23 500 11 9 55 600 7.5 6 75 700 5 4 100

2024-T861 –320 92 85 5 –112 81 77 5 –18 78 74 5 75 75 71 5 212 70 67 6 300 54 48 11 400 21 17 28 500 11 9 55 600 7.5 6 75 700 5 4 100

2117-T4 –320 56 33 30 –112 45 25 29 –18 44 24 28 75 43 24 27 212 36 21 16 300 30 17 20 400 16 12 35 500 7.5 5.5 55 600 4.7 3.3 80 700 2.9 2 110

ALLOY AND TEMPER

NOT FOR D

ESIGN

600 2.9 2 80

NOT FOR D

ESIGN

600 2.9 2 80 700 2.1 1.6 85

NOT FOR D

ESIGN

700 2.1 1.6 85

2011-T3 75 55 43 15

NOT FOR D

ESIGN

2011-T3 75 55 43 15 212 47 34 16

NOT FOR D

ESIGN

212 47 34 16 300 28 19 25

NOT FOR D

ESIGN

300 28 19 25 400 16 11 35

NOT FOR D

ESIGN

400 16 11 35 500 6.5 3.8 45

NOT FOR D

ESIGN

500 6.5 3.8 45 600 3.1 1.8 90

NOT FOR D

ESIGN

600 3.1 1.8 90 700 2.3 1.4 125

NOT FOR D

ESIGN

700 2.3 1.4 125

2014-T6, T651 –320 84 72 14

NOT FOR D

ESIGN

2014-T6, T651 –320 84 72 14 –112 74 65 13

NOT FOR D

ESIGN

–112 74 65 13 –18 72 62 13

NOT FOR D

ESIGN

–18 72 62 13 75 70 60 13

NOT FOR D

ESIGN

75 70 60 13 212 63 57 15

NOT FOR D

ESIGN

212 63 57 15 300 40 35 20

NOT FOR D

ESIGN

300 40 35 20 400 16 13 38

NOT FOR D

ESIGN

400 16 13 38 500 9.5 7.5 52

NOT FOR D

ESIGN

500 9.5 7.5 52 600 6.5 5 65

NOT FOR D

ESIGN

600 6.5 5 65 700 4.3 3.5 72

NOT FOR D

ESIGN

700 4.3 3.5 72

2017-T4, T451 –320 80 53 28

NOT FOR D

ESIGN

2017-T4, T451 –320 80 53 28 –112 65 42 24

NOT FOR D

ESIGN

–112 65 42 24 –18 64 41 23NOT F

OR DESIG

N

–18 64 41 23 75 62 40 22NOT F

OR DESIG

N

75 62 40 22 212 57 39 18NOT F

OR DESIG

N

212 57 39 18 300 40 30 15NOT F

OR DESIG

N

300 40 30 15NOT FOR D

ESIGN

212 63 57 15

NOT FOR D

ESIGN

212 63 57 15 300 40 35 20

NOT FOR D

ESIGN

300 40 35 20

NOT FOR D

ESIGN

400 16 13 38

NOT FOR D

ESIGN

400 16 13 38 500 9.5 7.5 52

NOT FOR D

ESIGN

500 9.5 7.5 52 600 6.5 5 65

NOT FOR D

ESIGN

600 6.5 5 65 700 4.3 3.5 72

NOT FOR D

ESIGN

700 4.3 3.5 72

2017-T4, T451 –320 80 53 28

NOT FOR D

ESIGN

2017-T4, T451 –320 80 53 28 –112 65 42 24

NOT FOR D

ESIGN

–112 65 42 24

NOT FOR D

ESIGN

600 6.5 5 65

NOT FOR D

ESIGN

600 6.5 5 65 700 4.3 3.5 72

NOT FOR D

ESIGN

700 4.3 3.5 72

2017-T4, T451 –320 80 53 28

NOT FOR D

ESIGN

2017-T4, T451 –320 80 53 28 –112 65 42 24

NOT FOR D

ESIGN

–112 65 42 24 –18 64 41 23NOT F

OR DESIG

N

–18 64 41 23 75 62 40 22NOT F

OR DESIG

N

75 62 40 22NOT FOR D

ESIGN

212 57 39 18NOT FOR D

ESIGN

212 57 39 18 300 40 30 15NOT F

OR DESIG

N

300 40 30 15NOT FOR D

ESIGN

212 47 34 16

NOT FOR D

ESIGN

212 47 34 16 300 28 19 25

NOT FOR D

ESIGN

300 28 19 25 400 16 11 35

NOT FOR D

ESIGN

400 16 11 35 500 6.5 3.8 45

NOT FOR D

ESIGN

500 6.5 3.8 45 600 3.1 1.8 90

NOT FOR D

ESIGN

600 3.1 1.8 90 700 2.3 1.4 125

NOT FOR D

ESIGN

700 2.3 1.4 125

2014-T6, T651 –320 84 72 14

NOT FOR D

ESIGN

2014-T6, T651 –320 84 72 14 –112 74 65 13

NOT FOR D

ESIGN

–112 74 65 13

NOT FOR D

ESIGN

700 2.3 1.4 125

NOT FOR D

ESIGN

700 2.3 1.4 125

2014-T6, T651 –320 84 72 14

NOT FOR D

ESIGN

2014-T6, T651 –320 84 72 14 –112 74 65 13

NOT FOR D

ESIGN

–112 74 65 13 –18 72 62 13

NOT FOR D

ESIGN

–18 72 62 13 75 70 60 13

NOT FOR D

ESIGN

75 70 60 13 212 63 57 15

NOT FOR D

ESIGN

212 63 57 15 300 40 35 20

NOT FOR D

ESIGN

300 40 35 20 400 16 13 38

NOT FOR D

ESIGN

400 16 13 38

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

600 7.5 6 75

NOT FOR D

ESIGN

600 7.5 6 75 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100

2024-T4, T351 –320 84 61 19

NOT FOR D

ESIGN2024-T4, T351 –320 84 61 192024-T4, T351 –320 84 61 19

NOT FOR D

ESIGN2024-T4, T351 –320 84 61 19

(plate) –112 71 49 19

NOT FOR D

ESIGN(plate) –112 71 49 19(plate) –112 71 49 19

NOT FOR D

ESIGN(plate) –112 71 49 19(plate) –112 71 49 19

NOT FOR D

ESIGN(plate) –112 71 49 19

–18 69 47 19

NOT FOR D

ESIGN –18 69 47 19 –18 69 47 19

NOT FOR D

ESIGN –18 69 47 19 –18 69 47 19

NOT FOR D

ESIGN –18 69 47 19

75 68 47 19

NOT FOR D

ESIGN 75 68 47 19 75 68 47 19

NOT FOR D

ESIGN 75 68 47 19 75 68 47 19

NOT FOR D

ESIGN 75 68 47 19

212 63 45 19

NOT FOR D

ESIGN 212 63 45 19 212 63 45 19

NOT FOR D

ESIGN 212 63 45 19 212 63 45 19

NOT FOR D

ESIGN 212 63 45 19

300 45 36 17

NOT FOR D

ESIGN

300 45 36 17 300 45 36 17

NOT FOR D

ESIGN

300 45 36 17 400 26 19 27

NOT FOR D

ESIGN

400 26 19 27 400 26 19 27

NOT FOR D

ESIGN

400 26 19 27 400 26 19 27

NOT FOR D

ESIGN

400 26 19 27 500 11 9 55

NOT FOR D

ESIGN

500 11 9 55 500 11 9 55

NOT FOR D

ESIGN

500 11 9 55 500 11 9 55

NOT FOR D

ESIGN

500 11 9 55 600 7.5 6 75

NOT FOR D

ESIGN

600 7.5 6 75 600 7.5 6 75

NOT FOR D

ESIGN

600 7.5 6 75 600 7.5 6 75

NOT FOR D

ESIGN

600 7.5 6 75 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100

2024-T6, T651 –320 84 68 11

NOT FOR D

ESIGN

2024-T6, T651 –320 84 68 112024-T6, T651 –320 84 68 11

NOT FOR D

ESIGN

2024-T6, T651 –320 84 68 11 –112 72 59 10

NOT FOR D

ESIGN

–112 72 59 10 –112 72 59 10

NOT FOR D

ESIGN

–112 72 59 10 –18 70 58 10

NOT FOR D

ESIGN

–18 70 58 10 –18 70 58 10

NOT FOR D

ESIGN

–18 70 58 10 75 69 57 10

NOT FOR D

ESIGN

75 69 57 10 75 69 57 10

NOT FOR D

ESIGN

75 69 57 10 212 65 54 10

NOT FOR D

ESIGN

212 65 54 10 300 45 36 17

NOT FOR D

ESIGN

300 45 36 17 400 26 19 27

NOT FOR D

ESIGN

400 26 19 27 500 11 9 55

NOT FOR D

ESIGN

500 11 9 55 600 7.5 6 75

NOT FOR D

ESIGN

600 7.5 6 75 700 5 4 100

NOT FOR D

ESIGN

700 5 4 100

For all numbered footnotes, see last page of table.

January 2005 V-31

Table 9TYPICAL TENSILE PROPERTIES AT VARIOUS TEMPERATURES ① (Continued)



3003-H14 –320 35 25 30 –112 24 22 18 –18 22 21 16 75 22 21 16 212 21 19 16 300 18 16 16 400 14 9 20 500 7.5 4 60 600 4 2.4 70 700 2.8 1.8 70

3003-H18 –320 41 33 23 –112 32 29 11 –18 30 28 10 75 29 27 10 212 26 21 10 300 23 16 11 400 14 9 18 500 7.5 4 60 600 4 2.4 70 700 2.8 1.8 70

3004-O –320 42 13 38 –112 28 11 30 –18 26 10 26 75 26 10 25 212 26 10 25 300 22 10 35 400 14 9.5 55 500 10 7.5 70 600 7.5 5 80 700 5 3 90

3004-H34 –320 52 34 26 –112 38 30 16 –18 36 29 13 75 35 29 12 212 34 29 13 300 28 25 22 400 21 15 35 500 14 7.5 55 600 7.5 5 80 700 5 3 90

3004-H38 –320 58 43 20 –112 44 38 10 –18 42 36 7 75 41 36 6 212 40 36 7 300 31 27 15 400 22 15 30 500 12 7.5 50 600 7.5 5 80 700 5 3 90

4032-T6 –320 66 48 11 –112 58 46 10 –18 56 46 9 75 55 46 9 212 50 44 9 300 37 33 9 400 13 9 30 500 8 5.5 50 600 5 3.2 70 700 3.4 2 90

2124-T851 –452 102 90 10 –320 86 79 9 –112 76 71 8 –18 73 68 8 75 70 64 9 212 66 61 9 300 54 49 13 400 27 20 28 500 11 8 60 600 7.5 6 75 700 5.5 4.1 100

2218-T61 –320 72 52 15 –112 61 45 14 –18 59 44 13 75 59 44 13 212 56 42 15 300 41 35 17 400 22 16 30 500 10 6 70 600 5.5 3 85 700 4 2.5 100

2219-T62 –320 73 49 16 –112 63 44 13 –18 60 42 12 75 58 40 12 212 54 37 14 300 45 33 17 400 34 25 20 500 27 20 21 600 10 8 40 700 4.4 3.7 75

2219-T81, T851 –320 83 61 15 –112 71 54 13 –18 69 52 12 75 66 50 12 212 60 47 15 300 49 40 17 400 36 29 20 500 29 23 21 600 7 6 55 700 4.4 3.7 75

2618-T61 –320 78 61 12 –12 67 55 11 –18 64 54 10 75 64 54 10 212 62 54 10 300 50 44 14 400 32 26 24 500 13 9 50 600 7.5 4.5 80 700 5 3.5 120

3003-O –320 33 8.5 46 –112 20 7 42 –18 17 6.5 41 75 16 6 40 212 13 5.5 43 300 11 5 47 400 8.5 4.3 60 500 6 3.4 65 600 4 2.4 70 700 2.8 1.8 70




PERCENT

ALLOY AND TEMPER




PERCENT

ALLOY AND TEMPER

NOT FOR D

ESIGN

600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3003-H18 –320 41 33 23

NOT FOR D

ESIGN3003-H18 –320 41 33 23

–112 32 29 11

NOT FOR D

ESIGN –112 32 29 11

–18 30 28 10

NOT FOR D

ESIGN –18 30 28 10

75 29 27 10

NOT FOR D

ESIGN 75 29 27 10

212 26 21 10

NOT FOR D

ESIGN 212 26 21 10

300 23 16 11

NOT FOR D

ESIGN

300 23 16 11 400 14 9 18

NOT FOR D

ESIGN

400 14 9 18 500 7.5 4 60

NOT FOR D

ESIGN

500 7.5 4 60 600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

NOT FOR D

ESIGN 75 29 27 10

NOT FOR D

ESIGN 75 29 27 10

212 26 21 10

NOT FOR D

ESIGN 212 26 21 10

300 23 16 11

NOT FOR D

ESIGN

300 23 16 11 400 14 9 18

NOT FOR D

ESIGN

400 14 9 18 500 7.5 4 60

NOT FOR D

ESIGN

500 7.5 4 60 600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3004-O –320 42 13 38

NOT FOR D

ESIGN

3004-O –320 42 13 38 –112 28 11 30

NOT FOR D

ESIGN

–112 28 11 30 –18 26 10 26

NOT FOR D

ESIGN

–18 26 10 26 75 26 10 25

NOT FOR D

ESIGN

75 26 10 25 212 26 10 25

NOT FOR D

ESIGN

212 26 10 25

NOT FOR D

ESIGN

500 7.5 4 60

NOT FOR D

ESIGN

500 7.5 4 60 600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3004-O –320 42 13 38

NOT FOR D

ESIGN

3004-O –320 42 13 38 –112 28 11 30

NOT FOR D

ESIGN

–112 28 11 30 –18 26 10 26

NOT FOR D

ESIGN

–18 26 10 26 75 26 10 25

NOT FOR D

ESIGN

75 26 10 25 212 26 10 25

NOT FOR D

ESIGN

212 26 10 25 300 22 10 35

NOT FOR D

ESIGN

300 22 10 35 400 14 9.5 55

NOT FOR D

ESIGN

400 14 9.5 55 500 10 7.5 70

NOT FOR D

ESIGN

500 10 7.5 70 600 7.5 5 80

NOT FOR D

ESIGN

600 7.5 5 80 700 5 3 90

NOT FOR D

ESIGN

700 5 3 90

3004-H34 –320 52 34 26

NOT FOR D

ESIGN

3004-H34 –320 52 34 26

600 10 8 40

NOT FOR D

ESIGN

600 10 8 40 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

2219-T81, T851 –320 83 61 15

NOT FOR D

ESIGN

2219-T81, T851 –320 83 61 15 –112 71 54 13

NOT FOR D

ESIGN

–112 71 54 13 –18 69 52 12

NOT FOR D

ESIGN

–18 69 52 12 75 66 50 12

NOT FOR D

ESIGN

75 66 50 12 212 60 47 15

NOT FOR D

ESIGN

212 60 47 15 300 49 40 17

NOT FOR D

ESIGN

300 49 40 17

NOT FOR D

ESIGN

400 36 29 20

NOT FOR D

ESIGN

400 36 29 20 500 29 23 21

NOT FOR D

ESIGN

500 29 23 21 600 7 6 55

NOT FOR D

ESIGN

600 7 6 55 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

NOT FOR D

ESIGN

–112 71 54 13

NOT FOR D

ESIGN

–112 71 54 13 –18 69 52 12

NOT FOR D

ESIGN

–18 69 52 12 75 66 50 12

NOT FOR D

ESIGN

75 66 50 12 212 60 47 15

NOT FOR D

ESIGN

212 60 47 15 300 49 40 17

NOT FOR D

ESIGN

300 49 40 17

NOT FOR D

ESIGN

400 36 29 20

NOT FOR D

ESIGN

400 36 29 20 500 29 23 21

NOT FOR D

ESIGN

500 29 23 21 600 7 6 55

NOT FOR D

ESIGN

600 7 6 55 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

2618-T61 –320 78 61 12

NOT FOR D

ESIGN

2618-T61 –320 78 61 12 –12 67 55 11

NOT FOR D

ESIGN

–12 67 55 11 –18 64 54 10

NOT FOR D

ESIGN

–18 64 54 10 75 64 54 10

NOT FOR D

ESIGN

75 64 54 10

NOT FOR D

ESIGN

400 36 29 20

NOT FOR D

ESIGN

400 36 29 20 500 29 23 21

NOT FOR D

ESIGN

500 29 23 21 600 7 6 55

NOT FOR D

ESIGN

600 7 6 55 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

2618-T61 –320 78 61 12

NOT FOR D

ESIGN

2618-T61 –320 78 61 12 –12 67 55 11

NOT FOR D

ESIGN

–12 67 55 11 –18 64 54 10

NOT FOR D

ESIGN

–18 64 54 10 75 64 54 10

NOT FOR D

ESIGN

75 64 54 10 212 62 54 10

NOT FOR D

ESIGN

212 62 54 10 300 50 44 14

NOT FOR D

ESIGN

300 50 44 14 400 32 26 24

NOT FOR D

ESIGN

400 32 26 24 500 13 9 50

NOT FOR D

ESIGN

500 13 9 50 600 7.5 4.5 80NOT F

OR DESIG

N

600 7.5 4.5 80 700 5 3.5 120NOT F

OR DESIG

N

700 5 3.5 120NOT FOR D

ESIGN

–12 67 55 11

NOT FOR D

ESIGN

–12 67 55 11 –18 64 54 10

NOT FOR D

ESIGN

–18 64 54 10 75 64 54 10

NOT FOR D

ESIGN

75 64 54 10 212 62 54 10

NOT FOR D

ESIGN

212 62 54 10 300 50 44 14

NOT FOR D

ESIGN

300 50 44 14 400 32 26 24

NOT FOR D

ESIGN

400 32 26 24 500 13 9 50

NOT FOR D

ESIGN

500 13 9 50 600 7.5 4.5 80NOT F

OR DESIG

N

600 7.5 4.5 80 700 5 3.5 120NOT F

OR DESIG

N

700 5 3.5 120

3003-O –320 33 8.5 46NOT FOR D

ESIGN

3003-O –320 33 8.5 46 –112 20 7 42NOT F

OR DESIG

N

–112 20 7 42NOT FOR D

ESIGN

300 50 44 14

NOT FOR D

ESIGN

300 50 44 14 400 32 26 24

NOT FOR D

ESIGN

400 32 26 24 500 13 9 50

NOT FOR D

ESIGN

500 13 9 50 600 7.5 4.5 80NOT F

OR DESIG

N

600 7.5 4.5 80 700 5 3.5 120NOT F

OR DESIG

N

700 5 3.5 120

3003-O –320 33 8.5 46NOT FOR D

ESIGN

3003-O –320 33 8.5 46 –112 20 7 42NOT F

OR DESIG

N

–112 20 7 42NOT FOR D

ESIGN

–12 67 55 11

NOT FOR D

ESIGN

–12 67 55 11 –18 64 54 10

NOT FOR D

ESIGN

–18 64 54 10 75 64 54 10

NOT FOR D

ESIGN

75 64 54 10 212 62 54 10

NOT FOR D

ESIGN

212 62 54 10 300 50 44 14

NOT FOR D

ESIGN

300 50 44 14 400 32 26 24

NOT FOR D

ESIGN

400 32 26 24 500 13 9 50

NOT FOR D

ESIGN

500 13 9 50 600 7.5 4.5 80NOT F

OR DESIG

N

600 7.5 4.5 80 700 5 3.5 120NOT F

OR DESIG

N

700 5 3.5 120NOT FOR D

ESIGN

300 50 44 14

NOT FOR D

ESIGN

300 50 44 14 400 32 26 24

NOT FOR D

ESIGN

400 32 26 24 500 13 9 50

NOT FOR D

ESIGN

500 13 9 50 600 7.5 4.5 80NOT F

OR DESIG

N

600 7.5 4.5 80 700 5 3.5 120NOT F

OR DESIG

N

700 5 3.5 120

3003-O –320 33 8.5 46NOT FOR D

ESIGN

3003-O –320 33 8.5 46 –112 20 7 42NOT F

OR DESIG

N

–112 20 7 42NOT FOR D

ESIGN

–112 71 54 13

NOT FOR D

ESIGN

–112 71 54 13 –18 69 52 12

NOT FOR D

ESIGN

–18 69 52 12 75 66 50 12

NOT FOR D

ESIGN

75 66 50 12 212 60 47 15

NOT FOR D

ESIGN

212 60 47 15 300 49 40 17

NOT FOR D

ESIGN

300 49 40 17

NOT FOR D

ESIGN

400 36 29 20

NOT FOR D

ESIGN

400 36 29 20 500 29 23 21

NOT FOR D

ESIGN

500 29 23 21 600 7 6 55

NOT FOR D

ESIGN

600 7 6 55 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

NOT FOR D

ESIGN

400 36 29 20

NOT FOR D

ESIGN

400 36 29 20 500 29 23 21

NOT FOR D

ESIGN

500 29 23 21 600 7 6 55

NOT FOR D

ESIGN

600 7 6 55 700 4.4 3.7 75

NOT FOR D

ESIGN

700 4.4 3.7 75

2618-T61 –320 78 61 12

NOT FOR D

ESIGN

2618-T61 –320 78 61 12 –12 67 55 11

NOT FOR D

ESIGN

–12 67 55 11 –18 64 54 10

NOT FOR D

ESIGN

–18 64 54 10 75 64 54 10

NOT FOR D

ESIGN

75 64 54 10

NOT FOR D

ESIGN 75 29 27 10

NOT FOR D

ESIGN 75 29 27 10

212 26 21 10

NOT FOR D

ESIGN 212 26 21 10

300 23 16 11

NOT FOR D

ESIGN

300 23 16 11 400 14 9 18

NOT FOR D

ESIGN

400 14 9 18 500 7.5 4 60

NOT FOR D

ESIGN

500 7.5 4 60 600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3004-O –320 42 13 38

NOT FOR D

ESIGN

3004-O –320 42 13 38

NOT FOR D

ESIGN

500 7.5 4 60

NOT FOR D

ESIGN

500 7.5 4 60 600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3004-O –320 42 13 38

NOT FOR D

ESIGN

3004-O –320 42 13 38 –112 28 11 30

NOT FOR D

ESIGN

–112 28 11 30 –18 26 10 26

NOT FOR D

ESIGN

–18 26 10 26 75 26 10 25

NOT FOR D

ESIGN

75 26 10 25 212 26 10 25

NOT FOR D

ESIGN

212 26 10 25

NOT FOR D

ESIGN

600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3003-H18 –320 41 33 23

NOT FOR D

ESIGN3003-H18 –320 41 33 23

–112 32 29 11

NOT FOR D

ESIGN –112 32 29 11

–18 30 28 10

NOT FOR D

ESIGN –18 30 28 10

75 29 27 10

NOT FOR D

ESIGN 75 29 27 10

212 26 21 10

NOT FOR D

ESIGN 212 26 21 10

300 23 16 11

NOT FOR D

ESIGN

300 23 16 11

NOT FOR D

ESIGN

600 4 2.4 70

NOT FOR D

ESIGN

600 4 2.4 70 700 2.8 1.8 70

NOT FOR D

ESIGN

700 2.8 1.8 70

3003-H18 –320 41 33 23

NOT FOR D

ESIGN3003-H18 –320 41 33 23

–112 32 29 11

NOT FOR D

ESIGN –112 32 29 11

–18 30 28 10

NOT FOR D

ESIGN –18 30 28 10

75 29 27 10

NOT FOR D

ESIGN 75 29 27 10

212 26 21 10

NOT FOR D

ESIGN 212 26 21 10

300 23 16 11

NOT FOR D

ESIGN

300 23 16 11


V-32 January 2005







PERCENT




PERCENT

5050-O –320 37 10 . . –112 22 8.5 . . –18 21 8 . . 75 21 8 . . 212 21 8 . . 300 19 8 . . 400 14 7.5 . . 500 9 6 . . 600 6 4.2 . . 700 3.9 2.6 . .

5050-H34 –320 44 30 . . –112 30 25 . . –18 28 24 . . 75 28 24 . . 212 28 24 . . 300 25 22 . . 400 14 7.5 . . 500 9 6 . . 600 6 4.2 . . 700 3.9 2.6 . .

5050-H38 –320 46 36 . . –112 34 30 . . –18 32 29 . . 75 32 29 . . 212 31 29 . . 300 27 25 . . 400 14 7.5 . . 500 9 6 . . 600 6 4.2 . . 700 3.9 2.6 . .

5052-O –320 44 16 46 –112 29 13 35 –18 28 13 32 75 28 13 30 212 28 13 36 300 23 13 50 400 17 11 60 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

5052-H34 –320 55 36 28 –112 40 32 21 –18 38 31 18 75 38 31 16 212 38 31 18 300 30 27 27 400 24 15 45 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

5052-H38 –320 60 44 25 –112 44 38 18 –18 42 37 15 75 42 37 14 212 40 36 16 300 34 28 24 400 25 15 45 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

5083-O –320 59 24 36 –112 43 21 30 –18 42 21 27 75 42 21 25 212 40 21 36 300 31 19 50 400 22 17 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5086-O –320 55 19 46 –112 39 17 35 –18 38 17 32 75 38 17 30 212 38 17 36 300 29 16 50 400 22 15 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5154-O –320 52 19 46 –112 36 17 35 –18 35 17 32 75 35 17 30 212 35 17 36 300 29 16 50 400 22 15 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5254-O –320 52 19 46 –112 36 17 35 –18 35 17 32 75 35 17 30 212 35 17 36 300 29 16 50 400 22 15 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5454-O –320 54 19 39 –112 37 17 30 –18 36 17 27 75 36 17 25 212 36 17 31 300 29 16 50 400 22 15 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5454-H32 –320 59 36 32 –112 42 31 23 –18 41 30 20 75 40 30 18 212 39 29 20 300 32 26 37 400 25 19 45 500 17 11 80 600 11 7.5 110 700 6 4.2 130

ALLOY AND TEMPER

ALLOY AND TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

600 6 4.2 . .

NOT FOR D

ESIGN

600 6 4.2 . . 700 3.9 2.6 . .

NOT FOR D

ESIGN

700 3.9 2.6 . .

5052-O –320 44 16 46

NOT FOR D

ESIGN

5052-O –320 44 16 46 –112 29 13 35

NOT FOR D

ESIGN

–112 29 13 35 –112 29 13 35

NOT FOR D

ESIGN

–112 29 13 35 –18 28 13 32

NOT FOR D

ESIGN

–18 28 13 32 –18 28 13 32

NOT FOR D

ESIGN

–18 28 13 32 75 28 13 30

NOT FOR D

ESIGN

75 28 13 30 75 28 13 30

NOT FOR D

ESIGN

75 28 13 30 212 28 13 36

NOT FOR D

ESIGN

212 28 13 36 212 28 13 36

NOT FOR D

ESIGN

212 28 13 36 300 23 13 50

NOT FOR D

ESIGN

300 23 13 50 300 23 13 50

NOT FOR D

ESIGN

300 23 13 50

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

400 17 11 60

NOT FOR D

ESIGN

400 17 11 60 400 17 11 60

NOT FOR D

ESIGN

400 17 11 60 400 17 11 60

NOT FOR D

ESIGN

400 17 11 60 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130

5052-H34 –320 55 36 28

NOT FOR D

ESIGN

5052-H34 –320 55 36 285052-H34 –320 55 36 28

NOT FOR D

ESIGN

5052-H34 –320 55 36 28 –112 40 32 21

NOT FOR D

ESIGN

–112 40 32 21 –112 40 32 21

NOT FOR D

ESIGN

–112 40 32 21 –112 40 32 21

NOT FOR D

ESIGN

–112 40 32 21 –18 38 31 18

NOT FOR D

ESIGN

–18 38 31 18 –18 38 31 18

NOT FOR D

ESIGN

–18 38 31 18 –18 38 31 18

NOT FOR D

ESIGN

–18 38 31 18 75 38 31 16

NOT FOR D

ESIGN

75 38 31 16 75 38 31 16

NOT FOR D

ESIGN

75 38 31 16 75 38 31 16

NOT FOR D

ESIGN

75 38 31 16 212 38 31 18

NOT FOR D

ESIGN

212 38 31 18 212 38 31 18

NOT FOR D

ESIGN

212 38 31 18 300 30 27 27

NOT FOR D

ESIGN

300 30 27 27 300 30 27 27

NOT FOR D

ESIGN

300 30 27 27 300 30 27 27

NOT FOR D

ESIGN

300 30 27 27 400 24 15 45

NOT FOR D

ESIGN

400 24 15 45 400 24 15 45

NOT FOR D

ESIGN

400 24 15 45 400 24 15 45

NOT FOR D

ESIGN

400 24 15 45 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 700 5 3.1 130NOT F

OR DESIG

N

700 5 3.1 130 700 5 3.1 130NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130NOT FOR D

ESIGN

700 5 3.1 130

5052-H38 –320 60 44 25NOT FOR D

ESIGN

5052-H38 –320 60 44 255052-H38 –320 60 44 25NOT FOR D

ESIGN

5052-H38 –320 60 44 25 –112 44 38 18NOT F

OR DESIG

N

–112 44 38 18 –112 44 38 18NOT FOR D

ESIGN

–112 44 38 18 –18 42 37 15NOT F

OR DESIG

N

–18 42 37 15 –18 42 37 15NOT FOR D

ESIGN

–18 42 37 15

600 11 7.5 110

NOT FOR D

ESIGN

600 11 7.5 110 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130

5086-O –320 55 19 46

NOT FOR D

ESIGN5086-O –320 55 19 465086-O –320 55 19 46

NOT FOR D

ESIGN5086-O –320 55 19 46

–112 39 17 35

NOT FOR D

ESIGN –112 39 17 35 –112 39 17 35

NOT FOR D

ESIGN –112 39 17 35

–18 38 17 32

NOT FOR D

ESIGN –18 38 17 32 –18 38 17 32

NOT FOR D

ESIGN –18 38 17 32 –18 38 17 32

NOT FOR D

ESIGN –18 38 17 32

75 38 17 30

NOT FOR D

ESIGN 75 38 17 30 75 38 17 30

NOT FOR D

ESIGN 75 38 17 30 75 38 17 30

NOT FOR D

ESIGN 75 38 17 30

212 38 17 36

NOT FOR D

ESIGN 212 38 17 36 212 38 17 36

NOT FOR D

ESIGN 212 38 17 36 212 38 17 36

NOT FOR D

ESIGN 212 38 17 36

300 29 16 50

NOT FOR D

ESIGN

300 29 16 50 300 29 16 50

NOT FOR D

ESIGN

300 29 16 50 400 22 15 60

NOT FOR D

ESIGN

400 22 15 60 400 22 15 60

NOT FOR D

ESIGN

400 22 15 60 400 22 15 60

NOT FOR D

ESIGN

400 22 15 60 500 17 11 80

NOT FOR D

ESIGN

500 17 11 80 500 17 11 80

NOT FOR D

ESIGN

500 17 11 80 500 17 11 80

NOT FOR D

ESIGN

500 17 11 80 600 11 7.5 110

NOT FOR D

ESIGN

600 11 7.5 110 600 11 7.5 110

NOT FOR D

ESIGN

600 11 7.5 110 600 11 7.5 110

NOT FOR D

ESIGN

600 11 7.5 110 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130

5154-O –320 52 19 46

NOT FOR D

ESIGN

5154-O –320 52 19 465154-O –320 52 19 46

NOT FOR D

ESIGN

5154-O –320 52 19 46 –112 36 17 35

NOT FOR D

ESIGN

–112 36 17 35 –112 36 17 35

NOT FOR D

ESIGN

–112 36 17 35 –18 35 17 32

NOT FOR D

ESIGN

–18 35 17 32 –18 35 17 32

NOT FOR D

ESIGN

–18 35 17 32 75 35 17 30

NOT FOR D

ESIGN

75 35 17 30 75 35 17 30

NOT FOR D

ESIGN

75 35 17 30 212 35 17 36

NOT FOR D

ESIGN

212 35 17 36 300 29 16 50

NOT FOR D

ESIGN

300 29 16 50 400 22 15 60

NOT FOR D

ESIGN

400 22 15 60 500 17 11 80

NOT FOR D

ESIGN

500 17 11 80 600 11 7.5 110

NOT FOR D

ESIGN

600 11 7.5 110 700 6 4.2 130

NOT FOR D

ESIGN

700 6 4.2 130


January 2005 V-33







PERCENT




PERCENT

5454-H34 –320 63 41 30 –112 46 36 21 –18 44 35 18 75 44 35 16 212 43 34 18 300 34 28 32 400 26 19 45 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5456-O –320 62 26 32 –112 46 23 25 –18 45 23 22 75 45 23 20 212 42 22 31 300 31 20 50 400 22 17 60 500 17 11 80 600 11 7.5 110 700 6 4.2 130

5652-O –320 44 16 46 –112 29 13 35 –18 28 13 32 75 28 13 30 212 28 13 30 300 23 13 50 400 17 11 60 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

5652-H34 –320 55 36 28 –112 40 32 21 –18 38 31 18 75 38 31 16 212 38 31 18 300 30 27 27 400 24 15 45 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

5652-H38 –320 60 44 25 –112 44 38 18 –18 42 37 15 75 42 37 14 212 40 36 16 300 34 28 24 400 25 15 45 500 12 7.5 80 600 7.5 5.5 110 700 5 3.1 130

6053-T6, T651 75 37 32 13 212 32 28 13 300 25 24 13 400 13 12 25 500 5.5 4 70 600 4 2.7 80 700 2.9 2 90

6061-T6, T651 –320 60 47 22 –112 49 42 18 –18 47 41 17 75 45 40 17 212 42 38 18 300 34 31 20 400 19 15 28 500 7.5 5 60 600 4.6 2.7 85 700 3 1.8 95

6063-T1 –320 34 16 44 –112 26 15 36 –18 24 14 34 75 22 13 33 212 22 14 18 300 21 15 20 400 9 6.5 40 500 4.5 3.5 75 600 3.2 2.5 80 700 2.3 2 105

6063-T5 –320 37 24 28 –112 29 22 24 –18 28 22 23 75 27 21 22 212 24 20 18 300 20 18 20 400 9 6.5 40 500 4.5 3.5 75 600 3.2 2.5 80 700 2.3 2 105

6063-T6 –320 47 36 24 –112 38 33 20 –18 36 32 19 75 35 31 18 212 31 28 15 300 21 20 20 400 9 6.5 40 500 4.5 3.5 75 600 3.3 2.5 80 700 2.3 2 105

6101-T6 –320 43 33 24 –112 36 30 20 –18 34 29 19 75 32 28 19 212 28 25 20 300 21 19 20 400 10 7 40 500 4.8 3.3 80 600 3 2.3 100 700 2.5 1.8 105

6151-T6 –320 57 50 20 –112 50 46 17 –18 49 45 17 75 48 43 17 212 43 40 17 300 28 27 20 400 14 12 30 500 6.5 5 50 600 5 3.9 43 700 4 3.2 35

ALLOY AND TEMPER

ALLOY AND TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130

5652-H34 –320 55 36 28

NOT FOR D

ESIGN

5652-H34 –320 55 36 28 –112 40 32 21

NOT FOR D

ESIGN

–112 40 32 21 –18 38 31 18

NOT FOR D

ESIGN

–18 38 31 18 –18 38 31 18

NOT FOR D

ESIGN

–18 38 31 18 75 38 31 16

NOT FOR D

ESIGN

75 38 31 16 75 38 31 16

NOT FOR D

ESIGN

75 38 31 16 212 38 31 18

NOT FOR D

ESIGN

212 38 31 18 212 38 31 18

NOT FOR D

ESIGN

212 38 31 18 300 30 27 27

NOT FOR D

ESIGN

300 30 27 27 300 30 27 27

NOT FOR D

ESIGN

300 30 27 27 400 24 15 45

NOT FOR D

ESIGN

400 24 15 45 400 24 15 45

NOT FOR D

ESIGN

400 24 15 45

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130

NOT FOR D

ESIGN

700 5 3.1 130

5652-H38 –320 60 44 25

NOT FOR D

ESIGN

5652-H38 –320 60 44 255652-H38 –320 60 44 25

NOT FOR D

ESIGN

5652-H38 –320 60 44 25 –112 44 38 18

NOT FOR D

ESIGN

–112 44 38 18 –112 44 38 18

NOT FOR D

ESIGN

–112 44 38 18 –18 42 37 15

NOT FOR D

ESIGN

–18 42 37 15 –18 42 37 15

NOT FOR D

ESIGN

–18 42 37 15 –18 42 37 15

NOT FOR D

ESIGN

–18 42 37 15 75 42 37 14

NOT FOR D

ESIGN

75 42 37 14 75 42 37 14

NOT FOR D

ESIGN

75 42 37 14 75 42 37 14

NOT FOR D

ESIGN

75 42 37 14 212 40 36 16

NOT FOR D

ESIGN

212 40 36 16 212 40 36 16

NOT FOR D

ESIGN

212 40 36 16 212 40 36 16

NOT FOR D

ESIGN

212 40 36 16 300 34 28 24

NOT FOR D

ESIGN

300 34 28 24 300 34 28 24

NOT FOR D

ESIGN

300 34 28 24 400 25 15 45

NOT FOR D

ESIGN

400 25 15 45 400 25 15 45

NOT FOR D

ESIGN

400 25 15 45 400 25 15 45

NOT FOR D

ESIGN

400 25 15 45 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 500 12 7.5 80

NOT FOR D

ESIGN

500 12 7.5 80 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 600 7.5 5.5 110

NOT FOR D

ESIGN

600 7.5 5.5 110 700 5 3.1 130NOT F

OR DESIG

N

700 5 3.1 130 700 5 3.1 130NOT FOR D

ESIGN

700 5 3.1 130 700 5 3.1 130NOT FOR D

ESIGN

700 5 3.1 130

6053-T6, T651 75 37 32 13NOT FOR D

ESIGN

6053-T6, T651 75 37 32 136053-T6, T651 75 37 32 13NOT FOR D

ESIGN

6053-T6, T651 75 37 32 13 212 32 28 13NOT F

OR DESIG

N

212 32 28 13 212 32 28 13NOT FOR D

ESIGN

212 32 28 13 300 25 24 13NOT F

OR DESIG

N

300 25 24 13 300 25 24 13NOT FOR D

ESIGN

300 25 24 13

600 4.6 2.7 85

NOT FOR D

ESIGN

600 4.6 2.7 85 600 4.6 2.7 85

NOT FOR D

ESIGN

600 4.6 2.7 85 700 3 1.8 95

NOT FOR D

ESIGN

700 3 1.8 95 700 3 1.8 95

NOT FOR D

ESIGN

700 3 1.8 95

6063-T1 –320 34 16 44

NOT FOR D

ESIGN6063-T1 –320 34 16 446063-T1 –320 34 16 44

NOT FOR D

ESIGN6063-T1 –320 34 16 44

–112 26 15 36

NOT FOR D

ESIGN –112 26 15 36 –112 26 15 36

NOT FOR D

ESIGN –112 26 15 36

–18 24 14 34

NOT FOR D

ESIGN –18 24 14 34 –18 24 14 34

NOT FOR D

ESIGN –18 24 14 34

75 22 13 33

NOT FOR D

ESIGN 75 22 13 33 75 22 13 33

NOT FOR D

ESIGN 75 22 13 33 75 22 13 33

NOT FOR D

ESIGN 75 22 13 33

212 22 14 18

NOT FOR D

ESIGN 212 22 14 18 212 22 14 18

NOT FOR D

ESIGN 212 22 14 18 212 22 14 18

NOT FOR D

ESIGN 212 22 14 18

300 21 15 20

NOT FOR D

ESIGN

300 21 15 20 300 21 15 20

NOT FOR D

ESIGN

300 21 15 20 300 21 15 20

NOT FOR D

ESIGN

300 21 15 20 400 9 6.5 40

NOT FOR D

ESIGN

400 9 6.5 40 400 9 6.5 40

NOT FOR D

ESIGN

400 9 6.5 40 500 4.5 3.5 75

NOT FOR D

ESIGN

500 4.5 3.5 75 500 4.5 3.5 75

NOT FOR D

ESIGN

500 4.5 3.5 75 500 4.5 3.5 75

NOT FOR D

ESIGN

500 4.5 3.5 75 600 3.2 2.5 80

NOT FOR D

ESIGN

600 3.2 2.5 80 600 3.2 2.5 80

NOT FOR D

ESIGN

600 3.2 2.5 80 600 3.2 2.5 80

NOT FOR D

ESIGN

600 3.2 2.5 80 700 2.3 2 105

NOT FOR D

ESIGN

700 2.3 2 105 700 2.3 2 105

NOT FOR D

ESIGN

700 2.3 2 105 700 2.3 2 105

NOT FOR D

ESIGN

700 2.3 2 105

6063-T5 –320 37 24 28

NOT FOR D

ESIGN

6063-T5 –320 37 24 286063-T5 –320 37 24 28

NOT FOR D

ESIGN

6063-T5 –320 37 24 286063-T5 –320 37 24 28

NOT FOR D

ESIGN

6063-T5 –320 37 24 28 –112 29 22 24

NOT FOR D

ESIGN

–112 29 22 24 –112 29 22 24

NOT FOR D

ESIGN

–112 29 22 24 –18 28 22 23

NOT FOR D

ESIGN

–18 28 22 23 –18 28 22 23

NOT FOR D

ESIGN

–18 28 22 23 75 27 21 22

NOT FOR D

ESIGN

75 27 21 22 75 27 21 22

NOT FOR D

ESIGN

75 27 21 22 212 24 20 18

NOT FOR D

ESIGN

212 24 20 18 212 24 20 18

NOT FOR D

ESIGN

212 24 20 18 300 20 18 20

NOT FOR D

ESIGN

300 20 18 20 400 9 6.5 40

NOT FOR D

ESIGN

400 9 6.5 40 500 4.5 3.5 75

NOT FOR D

ESIGN

500 4.5 3.5 75 600 3.2 2.5 80

NOT FOR D

ESIGN

600 3.2 2.5 80 700 2.3 2 105

NOT FOR D

ESIGN

700 2.3 2 105

6063-T6 –320 47 36 24

NOT FOR D

ESIGN

6063-T6 –320 47 36 24


V-34 January 2005




TENSILE STRENGTH,

TEMP. ksi



PERCENT

TENSILE STRENGTH,

TEMP. ksi



PERCENT

ALLOY AND TEMPER

6262-T651 –320 60 47 22 –112 49 42 18 –18 47 41 17 75 45 40 17 212 42 38 18 300 34 31 20

6262-T9 –320 74 67 14 –112 62 58 10 –18 60 56 10 75 58 55 10 212 53 52 10 300 38 37 14 400 15 13 34 500 8.5 6 48 600 4.6 2.7 85 700 3 1.8 95

7075-T6, –320 102 92 9T651 –112 90 79 11 –18 86 75 11 75 83 73 11 212 70 65 14 300 31 27 30 400 16 13 55 500 11 9 65 600 8 6.5 70 700 6 4.6 70

7075-T73, –320 92 72 14T7351 –112 79 67 14 –18 76 65 13 75 73 63 13 212 63 58 15 300 31 27 30 400 16 13 55 500 11 9 65 600 8 6.5 70 700 6 4.6 70

7175-T74 –320 106 98 13 –112 90 83 14 –18 87 80 16 75 80 73 14 212 72 69 17 300 35 31 30 400 18 13 65

7178-T6, T651 –320 106 94 5 –112 94 84 8 –18 91 81 9 75 88 78 11 212 73 68 14 300 31 27 40 400 15 12 70 500 11 9 76 600 8.5 7 80 700 6.5 5.5 80

7178-T76, –320 106 89 10T7651 –112 91 78 10 –18 88 76 10 75 83 73 11 212 69 64 17 300 31 27 40 400 15 12 70 500 11 9 76 600 8.5 7 80 700 6.5 5.5 80

7475-T61 Sheet –320 99 87 10 –112 88 79 12 –18 84 75 12 75 80 72 12 212 70 65 14 300 30 26 28 400 14 11 55 500 9.5 7 70 600 6.5 5.5 80 700 5 3.8 85

7475-T761 –320 95 82 11 –112 84 73 12 –18 80 70 12 75 76 67 12 212 64 61 14 300 30 26 38 400 14 11 55 500 9.5 7 70 600 6.5 5.5 80 700 5 3.8 85

① These data are based on a limited amount of testing and represent the lowest strength during 10,000 hours of exposure at testing temperature under no load; stress applied at 5,000 psi/min to yield strength and then at strain rate of 0.05 in./in./min to failure. Under some conditions of tem-

perature and time, the application of heat will adversely affect certain other properties of some alloys.② Offset equals 0.2 percent.

ALLOY AND TEMPER

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

T7351 –112 79 67 14

NOT FOR D

ESIGN

T7351 –112 79 67 14 –18 76 65 13

NOT FOR D

ESIGN

–18 76 65 13 75 73 63 13

NOT FOR D

ESIGN

75 73 63 13 212 63 58 15

NOT FOR D

ESIGN

212 63 58 15 300 31 27 30

NOT FOR D

ESIGN

300 31 27 30 300 31 27 30

NOT FOR D

ESIGN

300 31 27 30 400 16 13 55

NOT FOR D

ESIGN

400 16 13 55 400 16 13 55

NOT FOR D

ESIGN

400 16 13 55 500 11 9 65

NOT FOR D

ESIGN

500 11 9 65 500 11 9 65

NOT FOR D

ESIGN

500 11 9 65 600 8 6.5 70

NOT FOR D

ESIGN

600 8 6.5 70 600 8 6.5 70

NOT FOR D

ESIGN

600 8 6.5 70

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

700 6 4.6 70

NOT FOR D

ESIGN

700 6 4.6 70 700 6 4.6 70

NOT FOR D

ESIGN

700 6 4.6 70

7175-T74 –320 106 98 13

NOT FOR D

ESIGN

7175-T74 –320 106 98 137175-T74 –320 106 98 13

NOT FOR D

ESIGN

7175-T74 –320 106 98 137175-T74 –320 106 98 13

NOT FOR D

ESIGN

7175-T74 –320 106 98 13 –112 90 83 14

NOT FOR D

ESIGN

–112 90 83 14 –112 90 83 14

NOT FOR D

ESIGN

–112 90 83 14 –112 90 83 14

NOT FOR D

ESIGN

–112 90 83 14 –18 87 80 16

NOT FOR D

ESIGN

–18 87 80 16 –18 87 80 16

NOT FOR D

ESIGN

–18 87 80 16 –18 87 80 16

NOT FOR D

ESIGN

–18 87 80 16 75 80 73 14

NOT FOR D

ESIGN

75 80 73 14 75 80 73 14

NOT FOR D

ESIGN

75 80 73 14 212 72 69 17

NOT FOR D

ESIGN

212 72 69 17 212 72 69 17

NOT FOR D

ESIGN

212 72 69 17 300 35 31 30

NOT FOR D

ESIGN

300 35 31 30 300 35 31 30

NOT FOR D

ESIGN

300 35 31 30 300 35 31 30

NOT FOR D

ESIGN

300 35 31 30 400 18 13 65

NOT FOR D

ESIGN

400 18 13 65 400 18 13 65

NOT FOR D

ESIGN

400 18 13 65 400 18 13 65

NOT FOR D

ESIGN

400 18 13 65

600 8.5 7 80

NOT FOR D

ESIGN

600 8.5 7 80 700 6.5 5.5 80

NOT FOR D

ESIGN

700 6.5 5.5 80 700 6.5 5.5 80

NOT FOR D

ESIGN

700 6.5 5.5 80

7178-T76, –320 106 89 10

NOT FOR D

ESIGN7178-T76, –320 106 89 107178-T76, –320 106 89 10

NOT FOR D

ESIGN7178-T76, –320 106 89 10

T7651 –112 91 78 10

NOT FOR D

ESIGNT7651 –112 91 78 10T7651 –112 91 78 10

NOT FOR D

ESIGNT7651 –112 91 78 10

–18 88 76 10

NOT FOR D

ESIGN –18 88 76 10 –18 88 76 10

NOT FOR D

ESIGN –18 88 76 10 –18 88 76 10

NOT FOR D

ESIGN –18 88 76 10

75 83 73 11

NOT FOR D

ESIGN 75 83 73 11 75 83 73 11

NOT FOR D

ESIGN 75 83 73 11 75 83 73 11

NOT FOR D

ESIGN 75 83 73 11

212 69 64 17

NOT FOR D

ESIGN 212 69 64 17 212 69 64 17

NOT FOR D

ESIGN 212 69 64 17 212 69 64 17

NOT FOR D

ESIGN 212 69 64 17

300 31 27 40

NOT FOR D

ESIGN

300 31 27 40 300 31 27 40

NOT FOR D

ESIGN

300 31 27 40 300 31 27 40

NOT FOR D

ESIGN

300 31 27 40 400 15 12 70

NOT FOR D

ESIGN

400 15 12 70 400 15 12 70

NOT FOR D

ESIGN

400 15 12 70 400 15 12 70

NOT FOR D

ESIGN

400 15 12 70 500 11 9 76

NOT FOR D

ESIGN

500 11 9 76 500 11 9 76

NOT FOR D

ESIGN

500 11 9 76 500 11 9 76

NOT FOR D

ESIGN

500 11 9 76 600 8.5 7 80

NOT FOR D

ESIGN

600 8.5 7 80 600 8.5 7 80

NOT FOR D

ESIGN

600 8.5 7 80 600 8.5 7 80

NOT FOR D

ESIGN

600 8.5 7 80 700 6.5 5.5 80

NOT FOR D

ESIGN

700 6.5 5.5 80 700 6.5 5.5 80

NOT FOR D

ESIGN

700 6.5 5.5 80 700 6.5 5.5 80

NOT FOR D

ESIGN

700 6.5 5.5 80

7475-T61 Sheet –320 99 87 10

NOT FOR D

ESIGN

7475-T61 Sheet –320 99 87 107475-T61 Sheet –320 99 87 10

NOT FOR D

ESIGN

7475-T61 Sheet –320 99 87 10 –112 88 79 12

NOT FOR D

ESIGN

–112 88 79 12 –112 88 79 12

NOT FOR D

ESIGN

–112 88 79 12 –18 84 75 12

NOT FOR D

ESIGN

–18 84 75 12 –18 84 75 12

NOT FOR D

ESIGN

–18 84 75 12 75 80 72 12

NOT FOR D

ESIGN

75 80 72 12 212 70 65 14

NOT FOR D

ESIGN

212 70 65 14 300 30 26 28

NOT FOR D

ESIGN

300 30 26 28 400 14 11 55

NOT FOR D

ESIGN

400 14 11 55 500 9.5 7 70

NOT FOR D

ESIGN

500 9.5 7 70 600 6.5 5.5 80

NOT FOR D

ESIGN

600 6.5 5.5 80 700 5 3.8 85

NOT FOR D

ESIGN

700 5 3.8 85

These data are based on a limited amount of

NOT FOR D

ESIGN

These data are based on a limited amount of lowest strength during 10,000 hours of exposure at testing temperature

NOT FOR D

ESIGN

lowest strength during 10,000 hours of exposure at testing temperature

NOT FOR D

ESIGN

under no load; stress applied at 5,000 psi/min to yield strength and then

NOT FOR D

ESIGN

under no load; stress applied at 5,000 psi/min to yield strength and then at strain rate of 0.05 in./in./min to failure. Under some conditions of tem-

NOT FOR D

ESIGN

at strain rate of 0.05 in./in./min to failure. Under some conditions of tem-

January 2005 V-35

Table 9MTYPICAL TENSILE PROPERTIES AT VARIOUS TEMPERATURES ①



ALLOY AND

TEMPER

TEMP. TENSILE STRENGTH, MPa

ELONGATION IN 50 mm PERCENT°C ULTIMATE YIELD ②

1100-O –195–80–3025

100150205260315370

1701059590705541282014

41383434322924181411

50434040455565758085

1100-H14 –195–80–3025

100150205260315370

2051401301251109570282014

1401251151151058550181411

45242020202326758085

1100-H18 –195–80–3025

100150205260315370

23518017016514512541282014

1801601601501309524181411

30161515152065758085

2011-T3 25100150205260315370

380325195110452116

29523513075261210

151625354590

125

2014-T6, T651 –195–80–3025

100150205260315370

580510495485435275110654530

49545042541539524090503424

14131313152038526572

2017-T4, T451 –195–80–3025

100150205260315370

550450440425395275110604130

36529028527527020590503424

28242322181535456570


ALLOY AND

TEMPER

TEMP. TENSILE STRENGTH, MPa


2024-T3(Sheet)

–195–80–3025

100150205260315370

585505495485455380185755034

425360350345330310140604128

181717171611235575

100

2024-T4, T351(plate)

–195–80–3025

100150205260315370

580490475470435310180755034

420340325325310250130604128

191919191917275575

100

2024-T6, T651 –195–80–3025

100150205260315370

580495485475450310180755034

470405400395370250130604128

111010101017275575

100

2024-T81, T851 –195–80–3025

100150205260315370

585510505485455380185755034

540475470450425340140604128

87778

11235575

100

2024-T861 –195–80–3025

100150205260315370

635560540515485370145755034

585530510490460330115604128

55556

11285575

100

2117-T4 –195–80–3025

100150205260315370

385310305295250205110503220

23017016516514511585382314

302928271620355580

110

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

80

NOT FOR D

ESIGN

8085

NOT FOR D

ESIGN

85

130

NOT FOR D

ESIGN

13075

NOT FOR D

ESIGN

7526

NOT FOR D

ESIGN

2612

NOT FOR D

ESIGN

1210

NOT FOR D

ESIGN

10

15

NOT FOR D

ESIGN

1516

NOT FOR D

ESIGN

1625

NOT FOR D

ESIGN

2535

NOT FOR D

ESIGN

3545

NOT FOR D

ESIGN

4590

NOT FOR D

ESIGN

90125

NOT FOR D

ESIGN

125

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

580

NOT FOR D

ESIGN

580510

NOT FOR D

ESIGN

510495

NOT FOR D

ESIGN

495485

NOT FOR D

ESIGN

485435

NOT FOR D

ESIGN

435275

NOT FOR D

ESIGN

275110

NOT FOR D

ESIGN

11065

NOT FOR D

ESIGN

6545

NOT FOR D

ESIGN

45

495

NOT FOR D

ESIGN

495450

NOT FOR D

ESIGN

450425

NOT FOR D

ESIGN

425415

NOT FOR D

ESIGN

415

2017-T4, T451

NOT FOR D

ESIGN

2017-T4, T451 –195

NOT FOR D

ESIGN

–195–80NOT F

OR DESIG

N

–80–30NOT F

OR DESIG

N

–30NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

34

NOT FOR D

ESIGN

34

25

NOT FOR D

ESIGN25

100

NOT FOR D

ESIGN100

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

580

NOT FOR D

ESIGN580

490

NOT FOR D

ESIGN490

475

NOT FOR D

ESIGN475

470

NOT FOR D

ESIGN470

435

NOT FOR D

ESIGN435

310

NOT FOR D

ESIGN

310180

NOT FOR D

ESIGN

180

340

NOT FOR D

ESIGN340

2024-T6, T651

NOT FOR D

ESIGN

2024-T6, T651 –195

NOT FOR D

ESIGN

–195–80

NOT FOR D

ESIGN

–80

V-36 January 2005

Table 9MTYPICAL TENSILE PROPERTIES AT VARIOUS TEMPERATURES ① (Continued)



ALLOY AND

TEMPER

TEMP. TENSILE STRENGTH,MPa


2124-T851 –268–195–80–3025

100150205260315370

705595525505485455370185755038

620545490470440420340140554128

1098899

13286075

100

2218-T61 –195–80–3025

100150205260315370

495420405405385285150703828

360310305305290240110412117

151413131517307085

100

2219-T62 –195–80–3025

100150205260315370

5054354154003703102351857030

3403052902752552301701405526

16131212141720214075

2219-T81, T851 –195–80–3025

100150205160315370

5704904754554153402502004830

4203703603453252752001604126

15131212151720215575

2618-T61 –195–80–3025

100150205260315370

540460440440425345220905034

420380370370370305180603124

121110101014245080

120

3003-O –195–80–3025

100150205260315370

230140115110907560412819

60504541383430231712

46424140434760657070


ALLOY AND

TEMPER



3003-H14 –195–80–3025

100150205260315370

24016515015014512595502819

17015014514513011060281712

30181616161620607070

3003-H18 –195–80–3025

100150205260315370

28522020520018016095502819

23020019518514511060281712

23111010101118607070

3004-O –195–80–3025

100150205260315370

29019518018018015095705034

90757070707065503421

38302625253555708090

3004-H34 –195–80–3025

100150205260315370

360260250240235195145955034

235205200200200170105503421

26161312132235558090

3004-H38 –195–80–3025

100150205260315370

400305290285275215150855034

295260250250250185105503421

2010767

1530508090

4032-T6 –195–80–3025

100150205260315370

45540038538034525590553423

33031531531530523060382214

11109999

30507090

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

40

NOT FOR D

ESIGN

4075

NOT FOR D

ESIGN

75

48

NOT FOR D

ESIGN

4830

NOT FOR D

ESIGN

30

360

NOT FOR D

ESIGN

360345

NOT FOR D

ESIGN

345325

NOT FOR D

ESIGN

325275

NOT FOR D

ESIGN

275200

NOT FOR D

ESIGN

200160

NOT FOR D

ESIGN

16041

NOT FOR D

ESIGN

4126

NOT FOR D

ESIGN

26

15

NOT FOR D

ESIGN

1513

NOT FOR D

ESIGN

1312

NOT FOR D

ESIGN

1212

NOT FOR D

ESIGN

1215

NOT FOR D

ESIGN

1517

NOT FOR D

ESIGN

17

–30

NOT FOR D

ESIGN

–3025

NOT FOR D

ESIGN

25100

NOT FOR D

ESIGN

100150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315NOT F

OR DESIG

N

315370NOT F

OR DESIG

N

370

540

NOT FOR D

ESIGN

540460

NOT FOR D

ESIGN

460440

NOT FOR D

ESIGN

440440

NOT FOR D

ESIGN

440425

NOT FOR D

ESIGN

425345

NOT FOR D

ESIGN

345220

NOT FOR D

ESIGN

220

420

NOT FOR D

ESIGN

420

–195NOT FOR D

ESIGN

–195NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN100

NOT FOR D

ESIGN100

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

285

NOT FOR D

ESIGN285

220

NOT FOR D

ESIGN220

205

NOT FOR D

ESIGN205

200

NOT FOR D

ESIGN200

180

NOT FOR D

ESIGN180

160

NOT FOR D

ESIGN

16095

NOT FOR D

ESIGN

9550

NOT FOR D

ESIGN

5028

NOT FOR D

ESIGN

28

230

NOT FOR D

ESIGN230

200

NOT FOR D

ESIGN200

195

NOT FOR D

ESIGN195

3004-O

NOT FOR D

ESIGN

3004-O –195

NOT FOR D

ESIGN

–195–80

NOT FOR D

ESIGN

–80–30

NOT FOR D

ESIGN

–30

3004-H34

NOT FOR D

ESIGN

3004-H34

January 2005 V-37




ALLOY AND

TEMPER



5050-O –195–80–3025

100150205260315370

25515014514514513095604127

70605555555550412918

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

5050-H34 –195–80–3025

100150205260315370

30520519519519517095604127

20517016516516515050412918

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

5050-H38 –195–80–3025

100150205260315370

31523522022021518595604127

25020520020020017050412918

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

5052-O –195–80–3025

100150205260315370

305200195195195160115855034

110909090909075503821

4635323036506080

110130

5052-H34 –195–80–3025

100150205260315370

380275260260260205165855034

250220215215215185105503821

2821181618274580

110130

5052-H38 –195–80–3025

100150205260315370

415305290290275235170855034

305260255255250195105503821

2518151416244580

110130


ALLOY AND

TEMPER



5083-O –195–80–3025

100150205260315370

4052952902902752151501157541

165145145145145130115755029

3630272536506080

110130

5086-O –195–80–3025

100150205260315370

3802702602602602001501157541

130115115115115110105755029

4635323036506080

110130

5154-O –195–80–3025

100150205260315370

3602502402402402001501157541

130115115115115110105755029

4635323036506080

110130

5254-O –195–80–3025

100150205260315370

3602502402402402001501157541

130115115115115110105755029

4635323036506080

110130

5454-O –195–80–3025

100150205260315370

3702552502502502001501157541

130115115115115110105755029

3930272531506080

110130

5454-H32 –195–80–3025

100150205260315370

4052902852752702201701157541

250215205205200180130755029

3223201820374580

110130

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

. .

NOT FOR D

ESIGN

. .

. .

NOT FOR D

ESIGN

. .

50

NOT FOR D

ESIGN

5034

NOT FOR D

ESIGN

34

90

NOT FOR D

ESIGN

9090

NOT FOR D

ESIGN

9090

NOT FOR D

ESIGN

9090

NOT FOR D

ESIGN

9075

NOT FOR D

ESIGN

7550

NOT FOR D

ESIGN

5038

NOT FOR D

ESIGN

3821

NOT FOR D

ESIGN

21

46

NOT FOR D

ESIGN

4635

NOT FOR D

ESIGN

3532

NOT FOR D

ESIGN

3230

NOT FOR D

ESIGN

3036

NOT FOR D

ESIGN

3650

NOT FOR D

ESIGN

50

–30

NOT FOR D

ESIGN

–3025

NOT FOR D

ESIGN

25100

NOT FOR D

ESIGN

100150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370NOT F

OR DESIG

N

370

380

NOT FOR D

ESIGN

380275

NOT FOR D

ESIGN

275260

NOT FOR D

ESIGN

260260

NOT FOR D

ESIGN

260260

NOT FOR D

ESIGN

260205

NOT FOR D

ESIGN

205165

NOT FOR D

ESIGN

165

250

NOT FOR D

ESIGN

250

–195NOT FOR D

ESIGN

–195NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

41

NOT FOR D

ESIGN

41

25

NOT FOR D

ESIGN25

100

NOT FOR D

ESIGN100

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

380

NOT FOR D

ESIGN380

270

NOT FOR D

ESIGN270

260

NOT FOR D

ESIGN260

260

NOT FOR D

ESIGN260

260

NOT FOR D

ESIGN260

200

NOT FOR D

ESIGN

200150

NOT FOR D

ESIGN

150115

NOT FOR D

ESIGN

115

115

NOT FOR D

ESIGN115

5154-O

NOT FOR D

ESIGN

5154-O –195

NOT FOR D

ESIGN

–195–80

NOT FOR D

ESIGN

–80

V-38 January 2005

ALLOY AND

TEMPER



5454-H34 –195–80–3025

100150205260315370

4353153053052952351801157541

285250240240235195130755029

3021181618324580

110130

5456-O –195–80–3025

100150205260315370

4253153103102902151501157541

180160160160150140115755029

3225222031506080

110130

5652-O –195–80–3025

100150205260315370

305200195195195160115855034

110909090909075503821

4635323030506080

110130

5652-H34 –195–80–3025

100150205260315370

380275260260260205165855034

250220215215215185105503821

2821181618274580

110130

5652-H38 –195–80–3025

100150205260315370

415305290290275235170855034

305260255255250195105503821

2518151416244580

110130

6053-T6, T651 25100150205260315370

25522017090382820

22019516585281914

13131325708090


ALLOY AND

TEMPER



6061-T6, T651 –195–80–3025

100150205260315370

415340325310290235130503221

325290285275260215105341912

22181717182028608595

6063-T1 –195–80–3025

100150205260315370

23518016515015014560312216

110105959095

10545241714

443634331820407580

105

6063-T5 –195–80–3025

100150205260315370

25520019518516514060312216

16515015014514012545241714

282423221820407580

105

6063-T6 –195–80–3025

100150205260315370

32526025024021514560312316

25023022021519514045241714

242019181520407580

105

6101-T6 –195–80–3025

100150205260315370

29525023522019514570332117

23020520019517013048231612

2420191920204080

100105

6151-T6 –195–80–3025

100150205260315370

39534534033029519595453428

34531531029527518585342722

20171717172030504335




NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

130

NOT FOR D

ESIGN

130

34

NOT FOR D

ESIGN

34

215

NOT FOR D

ESIGN

215215

NOT FOR D

ESIGN

215185

NOT FOR D

ESIGN

185105

NOT FOR D

ESIGN

10550

NOT FOR D

ESIGN

5038

NOT FOR D

ESIGN

3821

NOT FOR D

ESIGN

21

28

NOT FOR D

ESIGN

2821

NOT FOR D

ESIGN

2118

NOT FOR D

ESIGN

1816

NOT FOR D

ESIGN

1618

NOT FOR D

ESIGN

1827

NOT FOR D

ESIGN

2745

NOT FOR D

ESIGN

45

25

NOT FOR D

ESIGN

25100

NOT FOR D

ESIGN

100150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370NOT F

OR DESIG

N

370

415

NOT FOR D

ESIGN

415305

NOT FOR D

ESIGN

305290

NOT FOR D

ESIGN

290290

NOT FOR D

ESIGN

290275

NOT FOR D

ESIGN

275235

NOT FOR D

ESIGN

235170

NOT FOR D

ESIGN

170

305

NOT FOR D

ESIGN

305260

NOT FOR D

ESIGN

260

6053-T6, T651 NOT FOR D

ESIGN

6053-T6, T651 25NOT FOR D

ESIGN

25100NOT F

OR DESIG

N

100NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN100

NOT FOR D

ESIGN100

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

235

NOT FOR D

ESIGN235

180

NOT FOR D

ESIGN180

165

NOT FOR D

ESIGN165

150

NOT FOR D

ESIGN150

150

NOT FOR D

ESIGN150

145

NOT FOR D

ESIGN

14560

NOT FOR D

ESIGN

6031

NOT FOR D

ESIGN

3122

NOT FOR D

ESIGN

22

110

NOT FOR D

ESIGN110

105

NOT FOR D

ESIGN105

95

NOT FOR D

ESIGN95

6063-T5

NOT FOR D

ESIGN

6063-T5 –195

NOT FOR D

ESIGN

–195–80

NOT FOR D

ESIGN

–80–30

NOT FOR D

ESIGN

–30

6063-T6

NOT FOR D

ESIGN

6063-T6

January 2005 V-39




ALLOY AND

TEMPER



6262-T651 –195–80–3025

100150

415340325310290235

325290285275260215

221817171820

6262-T9 –195–80–3025

100150205260315370

510425415400365260105603221

46040038538036025590411912

14101010101434488595

7075-T6,T651

–195–80–3025

100150205260315370

705620595570485215110755541

63554551550545018590604532

9111111143055657070

7075-T73,T7351

–195–80–3025

100150205260315370

635545525505435215110755541

49546045043540018590604532

14141313153055657070

7175-T74 –195–80–3025

100150205

730620600550495240125

67557055050547521590

13141614173065

① These data are based on a limited amount of testing and represent the lowest strength during 10,000 hours of exposure at testing tempera-ture under no load; stress applied at approximately 0.58 MPa/s in to yield strength and then at strain rate of approximately 0.001mm/mm/s in to failure.

ALLOY AND

TEMPER



7178-T6, T651 –195–80–3025

100150205260315370

730650625605505215105756045

65058056054047018585604838

589

11144070768080

7178-T76,T7651

–195–80–3025

100150205260315370

730625605570475215105756045

61554052550544018585604838

10101011174070768080

7475-T61 Sheet –195–80–3025

100150205260315370

68560558055048520595654534

60054551549545018075503826

10121212142855708085

7475-T761 Sheet –195–80–3025

100150205260315370

65558055052544020595654534

56550548546042018075503826

11121212143855708085

Under some conditions of temperature and time, the application of heat will adversely affect certain other properties of some alloys.② Offset equals 0.2 percent.

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

90

NOT FOR D

ESIGN

9060

NOT FOR D

ESIGN

6045

NOT FOR D

ESIGN

4532

NOT FOR D

ESIGN

32

14

NOT FOR D

ESIGN

1413

NOT FOR D

ESIGN

1313

NOT FOR D

ESIGN

1315

NOT FOR D

ESIGN

1530

NOT FOR D

ESIGN

3055

NOT FOR D

ESIGN

5565

NOT FOR D

ESIGN

6570

NOT FOR D

ESIGN

7070

NOT FOR D

ESIGN

70

205

NOT FOR D

ESIGN

205

620

NOT FOR D

ESIGN

620600

NOT FOR D

ESIGN

600550

NOT FOR D

ESIGN

550495

NOT FOR D

ESIGN

495240

NOT FOR D

ESIGN

240125

NOT FOR D

ESIGN

125

675

NOT FOR D

ESIGN

675570

NOT FOR D

ESIGN

570550

NOT FOR D

ESIGN

550505

NOT FOR D

ESIGN

505475

NOT FOR D

ESIGN

475

These data are based on a limited amount of testing and represent

NOT FOR D

ESIGN

These data are based on a limited amount of testing and represent the lowest strength during 10,000 hours of exposure at testing tempera-

NOT FOR D

ESIGN

the lowest strength during 10,000 hours of exposure at testing tempera-ture under no load; stress applied at approximately 0.58 MPa/s in to yield

NOT FOR D

ESIGN

ture under no load; stress applied at approximately 0.58 MPa/s in to yield strength and then at strain rate of approximately 0.001mm/mm/s in to failure.

NOT FOR D

ESIGN

strength and then at strain rate of approximately 0.001mm/mm/s in to failure.

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

NOT FOR D

ESIGN

45

NOT FOR D

ESIGN

45

25

NOT FOR D

ESIGN25

100

NOT FOR D

ESIGN100

150

NOT FOR D

ESIGN

150205

NOT FOR D

ESIGN

205260

NOT FOR D

ESIGN

260315

NOT FOR D

ESIGN

315370

NOT FOR D

ESIGN

370

730

NOT FOR D

ESIGN730

625

NOT FOR D

ESIGN625

605

NOT FOR D

ESIGN605

570

NOT FOR D

ESIGN570

475

NOT FOR D

ESIGN475

215

NOT FOR D

ESIGN

215105

NOT FOR D

ESIGN

105

540

NOT FOR D

ESIGN540

7475-T61 Sheet

NOT FOR D

ESIGN

7475-T61 Sheet –195

NOT FOR D

ESIGN

–195–80

NOT FOR D

ESIGN

–80


PART VI

Section Properties




PART VI

Section Properties



January 2005 VI-3

VISection Properties

TABLE OF CONTENTS

Table 1 Nomenclature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4Table 2 Section Designations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5Table 3 Weights Per Square Foot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6Table 4 Aluminum Association Standard Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7Table 5 American Standard Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8Table 6 Car and Ship Building Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10Table 7 Canadian Channels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11Table 8 Aluminum Association Standard I Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12Table 9 Wide Flange Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13Table 10 Army-Navy Wide Flange Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14Table 11 American Standard I Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15Table 12 Canadian I Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16Table 13 Canadian Wide Flange Beams . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17Table 14 Angles – Equal Legs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18Table 15 Square End Angles – Equal Legs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20Table 16 Angles – Unequal Legs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21Table 17 Square End Angles – Unequal Legs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24Table 18 Tees . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25Table 19 Army-Navy and Special Tees . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26Table 20 Zees . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27Table 21 Round Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28Table 22 Pipes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32Table 23 Square Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34Table 24 Rectangular Tubes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36Table 25 Roofing And Siding – Dimensions and Weights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38Table 26 Roofing and Siding – Section Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39Table 27 Decimal Equivalents in Inches of Sheet Metal and Wire Gauges . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40Table 28 Geometric Shapes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

VI-4 January 2005

TABLE 1 – NOMENCLATURE

Symbol Property Units

A Area in2

b width in.

Cw warping constant in6

d depth in.

I moment of inertia in4

J torsion constant in4

r radius of gyration in.

r0 polar radius of gyration about the shear center in.

R fillet radius in.

Rb mid-thickness radius of a pipe or tube in.

S section modulus in3

t thickness in.

tf flange thickness in.

tw web thickness in.

Wt weight per length lb/ft

x location of the y axis in.

x0 x coordinate of shear center in.

y location of the x axis in.

x and y subscripts denote the axis about which the property is taken.The x axis is the major axis. The y axis is the minor axis.

January 2005 VI-5

TABLE 2 – SECTION DESIGNATIONS

Section Designation Example Description

Channels CS Depth × Wt CS 4 × 2.33 C shapes with flat flanges; includes Canadian Channels

Car and Ship Building Channels

CS Depth × Wt CS 3 × 2.23 C shapes; some have a slope on the inner surface of the flanges

American Standard Channels

C Depth × Wt C 2 × 1.22 C shapes with flanges with a 1:6 slope on the inner surface

I-Beams I Depth × Wt I 12 × 11.7 I shapes with flat flanges; includes Canadian I-Beams

American Standard I-Beams

S Depth × Wt S 10 × 12.1 I shapes with flanges with a 1:6 slope on the inner surface

Wide Flange Beams WF Nominal Depth × Wt WF 12 × 13.8

I shapes with a flange width approximately equal to the depth

Army-Navy Wide Flange Beams

WF(A-N) Depth × Wt WF(A-N) 4 × 4.14 I shapes with flat flanges and a radius on the inside corner of the flanges

Angles L long leg × short leg × thickness

L 3 × 2 × ¼ L shaped product with a fillet at the junction of the legs and radii on the inside tips of the legs

Square End Angles LS long leg × short leg × thickness

LS 3 × 3 × 1/8 L shaped product with small radii at the corners

Tees T Depth × Width × Wt T 2.50 × 2.50 × 1.91 T shapes

Zees Z Depth × Width × Wt Z 4.00 × 3.19 × 4.32 Z shapes

Plates PL Thickness × Width PL 0.375 × 60 Rolled product with a rectangular cross section at least 0.25 in. thick

Rods RD Diameter RD 0.500 Solid product with a circular cross section at least 0.375 in. in diameter

Square Bars SQ Side dimension SQ 4 Solid product with a square cross section at least 0.375 in. on a side

Pipes NPS size × SCH schedule no.

NPS 4 × SCH 40 Tube in standardized outside diameters and wall thicknesses

Round Tubes Outside diameter OD × wall thickness WALL

4 OD × 0.125 WALL Hollow product with a circular cross section

Rectangular Tubes RT short side × long side × wall thickness

RT 4 × 6 × ¼ Hollow product with a rectangular cross section (including square tube)

VI-6 January 2005

TABLE 3 – WEIGHTS PER SQUARE FOOT

The weight per square foot for an alloy with density of 0.100 lb/in3 is shown for each thickness. The weights for other alloys can be calculated using the density given in Part V Table 8.

Commonly used thicknesses are shown BOLD.

Thickness – in.Weight (lb/ft2)

Decimal Fraction

.006

.007

.008

.009

.010

0.0860.1010.1150.1300.144

.011

.012

.013

.014

.016 1/64

0.1580.1730.1870.2020.230

.018

.019

.020

.021

.022

0.2590.2740.2880.3020.317

.024

.025

.026

.028

.030

0.3460.3600.3740.4030.432

.032

.034

.036

.038

.040

0.4610.4900.5180.5470.576

.042

.045

.048

.050

.053

0.6050.6480.6910.7200.763

.056

.060

.063

.067

.071

1/16

08060.8640.9070.9651.02

.075

.080

.085

.090

.095

1.081.151.221.301.37

.100

.106

.112

.118

.125 1/8

1.441.531.611.701.80

.132

.140

.150

.160

.170

1.902.022.162.302.45

.180

.1875

.190

.200

.212

.224

3/162.592.702.742.883.053.23

Thickness – in.Weight (lb/ft2)

Decimal Fraction

.236

.250

.266

.281

.297

¼17/649/3219/64

3.403.603.834.054.28

.313

.328

.344

.359

.375

5/1621/6411/3223/643/8

4.514.724.955.175.40

.391

.406

.422

.438

.453

25/6413/3227/647/16

29/64

5.635.856.086.316.52

.469

.484

.500

.531

.562

15/3231/64

½17/329/16

6.756.977.207.658.09

.594

.625

.656

.688

.719

19/325/8

21/3211/1623/32

8.559.009.459.91

10.35

.750

.812

.875

.9381.000

¾13/167/8

15/161

10.8011.6912.6013.5114.40

1.1251.2501.3751.5001.625

1 1/81 ¼1 3/81 ½1 5/8

16.2018.0019.8021.6023.40

1.7501.8752.0002.1252.250

1 ¾1 7/8

22 1/82 ¼

25.2027.0028.8030.6032.40

2.3752.5002.6252.7502.875

2 3/82 ½2 5/82 ¾2 7/8

34.2036.0037.8039.6041.40

3.0003.2503.5003.7504.000

33 ¼3 ½3 ¾4

43.2046.8050.4054.0057.60

4.2504.5004.7505.0005.250

4 ¼4 ½4 ¾5

5 ¼

61.2064.8068.4072.0075.60

5.5005.7506.000

5 ½5 ¾6

79.2082.8086.40

January 2005 VI-7

TAB

LE

4 –

AL

UM

INU

M A

SS

OC

IAT

ION

STA

ND

AR

D C

HA

NN

EL

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Thi

ck-

ness

t f in.

Web

Thi

ck-

ness t w in.

Fill

etR

adiu

sR in

.

Are

aA in

2

Axi

s x-

xA

xis

y-y

x o in.

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

x in.

CS

2 ×

0.5

772.

000

1.00

00.

130

0.13

00.

100

0.49

00.

288

0.28

80.

766

0.04

500.

0639

0.30

30.

296

0.62

60.

0324

0.00

274

1.03

CS

2 ×

1.0

72.

000

1.25

00.

260

0.17

00.

150

0.91

10.

546

0.54

60.

774

0.13

90.

178

0.39

00.

471

0.90

40.

0894

0.01

711.

25

CS

3 ×

1.1

43.

000

1.50

00.

200

0.13

00.

250

0.96

51.

410.

940

1.21

0.21

70.

215

0.47

40.

494

1.02

0.33

20.

0099

01.

65

CS

3 ×

1.6

03.

000

1.75

00.

260

0.17

00.

250

1.36

1.97

1.31

1.20

0.41

70.

368

0.55

40.

617

1.25

0.62

60.

0246

1.82

CS

4 ×

1.7

44.

000

2.00

00.

230

0.15

00.

250

1.48

3.91

1.95

1.63

0.60

10.

446

0.63

80.

653

1.38

1.65

0.02

022.

22

CS

4 ×

2.3

34.

000

2.25

00.

290

0.19

00.

250

1.98

5.21

2.60

1.62

1.02

0.69

20.

717

0.77

51.

602.

760.

0444

2.39

CS

5 ×

2.2

15.

000

2.25

00.

260

0.15

00.

300

1.88

7.88

3.15

2.05

0.97

50.

642

0.72

00.

731

1.54

4.17

0.03

142.

66

CS

5 ×

3.0

95.

000

2.75

00.

320

0.19

00.

300

2.63

11.1

4.45

2.06

2.05

1.14

0.88

40.

955

1.98

8.70

0.07

002.

99

CS

6 ×

2.8

36.

000

2.50

00.

290

0.17

00.

300

2.41

14.4

4.78

2.44

1.53

0.89

60.

798

0.78

81.

679.

520.

0495

3.06

CS

6 ×

4.0

36.

000

3.25

00.

350

0.21

00.

300

3.43

21.0

7.01

2.48

3.76

1.76

1.05

1.12

2.34

23.1

0.10

93.

57

CS

7 ×

3.2

17.

000

2.75

00.

290

0.17

00.

300

2.73

22.1

6.31

2.85

2.10

1.10

0.87

80.

842

1.81

17.8

0.05

523.

49

CS

7 ×

4.7

27.

000

3.50

00.

380

0.21

00.

300

4.01

33.8

9.65

2.90

5.13

2.23

1.13

1.20

2.52

43.0

0.14

74.

01

CS

8 ×

4.1

58.

000

3.00

00.

350

0.19

00.

300

3.53

37.4

9.35

3.26

3.25

1.57

0.95

90.

934

1.99

36.0

0.10

23.

94

CS

8 ×

5.7

98.

000

3.75

00.

410

0.25

00.

350

4.92

52.7

13.2

3.27

7.12

2.82

1.20

1.22

2.59

78.5

0.21

04.

34

CS

9 ×

4.9

89.

000

3.25

00.

350

0.23

00.

350

4.24

54.4

12.1

3.58

4.40

1.89

1.02

0.92

82.

0262

.80.

127

4.24

CS

9 ×

6.9

79.

000

4.00

00.

440

0.29

00.

350

5.93

78.3

17.4

3.63

9.60

3.49

1.27

1.25

2.68

135

0.29

34.

69

CS

10

× 6

.14

10.0

003.

500

0.41

00.

250

0.35

05.

2283

.216

.63.

996.

332.

551.

101.

022.

2011

10.

209

4.69

CS

10

× 8

.36

10.0

004.

250

0.50

00.

310

0.40

07.

1111

623

.24.

0413

.04.

461.

351.

342.

8422

60.

444

5.12

CS

12

× 8

.27

12.0

004.

000

0.47

00.

290

0.40

07.

0416

026

.64.

7711

.03.

851.

251.

142.

4728

10.

367

5.51

CS

12

× 1

1.8

12.0

005.

000

0.62

00.

350

0.45

010

.124

039

.94.

8825

.77.

591.

601.

613.

4063

90.

948

6.16

CS

14

× 1

3.91

14.0

006.

000

0.64

00.

320

0.45

011

.840

157

.35.

8244

.711

.21.

942.

004.

2515

101.

197.

46

1. N

ew s

hape

; che

ck a

vaila

bilit

y w

ith s

uppl

iers

.2.

Tol

eran

ces

for

extr

uded

sha

pes

are

give

n in

Alu

min

um S

tand

ard

s an

d D

ata.

VI-8 January 2005

TAB

LE

5 –

AM

ER

ICA

N S

TAN

DA

RD

CH

AN

NE

LS

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Tip

T

hick

ness

t f in.

Ave

rage

F

lang

e T

hick

ness

t in.

Web

T

hick

ness

t w in.

Fill

et

Rad

ius

R1

in.

Tip

R

adiu

sR

2

in.

d1

in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

y-ax

is

Loca

tion

x in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

C 2

× 1

.22

C 3

× 1

.42

C 3

× 1

.73

C 3

× 2

.07

C 4

× 1

.85

C 4

× 2

.16

C 4

× 2

.50

C 5

× 2

.32

C 5

× 3

.11

C 5

× 3

.97

C 6

× 2

.83

C 6

× 3

.00

C 6

× 3

.63

C 6

× 4

.50

C 7

× 3

.54

C 7

× 4

.23

C 7

× 5

.10

C 7

× 5

.96

2.00

0

3.00

03.

000

3.00

0

4.00

04.

000

4.00

0

5.00

05.

000

5.00

0

6.00

06.

000

6.00

06.

000

7.00

07.

000

7.00

07.

000

1.41

0

1.41

01.

498

1.59

6

1.58

01.

647

1.72

0

1.75

01.

885

2.03

2

1.92

01.

945

2.03

42.

157

2.11

02.

194

2.29

92.

404

0.17

0

0.17

00.

170

0.17

0

0.18

00.

180

0.18

0

0.19

00.

190

0.19

0

0.20

00.

200

0.20

00.

200

0.21

00.

210

0.21

00.

210

0.27

3

0.27

30.

273

0.27

3

0.29

70.

297

0.29

7

0.32

00.

320

0.32

0

0.34

30.

343

0.34

30.

343

0.36

70.

367

0.36

70.

367

0.17

0

0.17

00.

258

0.35

6

0.18

00.

247

0.32

0

0.19

00.

325

0.47

2

0.20

00.

225

0.31

40.

438

0.23

00.

314

0.41

90.

524

0.27

0

0.27

00.

270

0.27

0

0.28

00.

280

0.28

0

0.29

00.

290

0.29

0

0.30

00.

300

0.30

00.

300

0.31

00.

310

0.31

00.

310

0.10

0

0.10

00.

100

0.10

0

0.11

00.

110

0.11

0

0.11

00.

110

0.11

0

0.12

00.

120

0.12

00.

120

0.13

00.

130

0.13

00.

130

0.75

1.75

1.75

1.75

2.75

2.75

2.75

3.75

3.75

3.75

4.50

4.50

4.50

4.50

5.50

5.50

5.50

5.50

1.0

4

1.2

1 1

.47

1.7

6

1.5

7 1

.84

2.1

3

1.9

7 2

.64

3.3

8

2.4

0 2

.55

3.0

9 3

.83

3.0

1 3

.60

4.3

3 5

.07

0.6

22

1.6

6 1

.85

2.0

7

3.8

3 4

.19

4.5

8

7.4

9 8

.90

10.4

13.1

13.6

15.2

17.4

21.8

24.2

27.2

30.3

0.62

2

1.10

1.24

1.38

1.92

2.10

2.29

3.00

3.56

4.17

4.37

4.52

5.06

5.80

6.24

6.93

7.78

8.64

0.77

4

1.17

1.12

1.08

1.56

1.51

1.47

1.95

1.83

1.76

2.34

2.31

2.22

2.13

2.69

2.60

2.51

2.44

0.1

72

0.2

0 0

.21

0.3

1

0.3

2 0

.37

0.4

3

0.4

8 0

.63

0.8

1

0.6

9 0

.73

0.8

7 1

.05

1.0

1 1

.17

1.3

8 1

.59

0.18

8

0.20

0.21

0.27

0.28

0.31

0.34

0.38

0.45

0.53

0.49

0.51

0.56

0.64

0.64

0.70

0.78

0.86

0.40

7

0.40

0.41

0.42

0.45

0.45

0.45

0.49

0.49

0.49

0.54

0.54

0.50

0.52

0.58

0.57

0.56

0.56

0.49

0.44

0.44

0.46

0.46

0.45

0.46

0.48

0.48

0.51

0.51

0.51

0.50

0.51

0.54

0.52

0.53

0.55

January 2005 VI-9

C 8

× 4

.25

C 8

× 4

.75

C 8

× 5

.62

C 8

× 6

.48

C 9

× 4

.60

C 9

× 5

.19

C 9

× 6

.91

C 9

× 8

.65

C 1

0 ×

5.2

8C

10

× 6

.91

C 1

0 ×

8.6

4C

10

× 1

0.4

C 1

2 ×

7.4

1C

12

× 8

.64

C 1

2 ×

10.

4C

12

× 1

2.1

C 1

5 ×

11.

7C

15

× 1

7.3

8.00

08.

000

8.00

08.

000

9.00

09.

000

9.00

09.

000

10.0

0010

.000

10.0

0010

.000

12.0

0012

.000

12.0

0012

.000

15.0

0015

.000

2.29

02.

343

2.43

52.

527

2.43

02.

485

2.64

82.

812

2.60

02.

739

2.88

63.

033

2.96

03.

047

3.17

03.

292

3.40

03.

716

0.22

00.

220

0.22

00.

220

0.23

00.

230

0.23

00.

230

0.24

00.

240

0.24

00.

240

0.28

00.

280

0.28

00.

280

0.40

00.

400

0.39

00.

390

0.39

00.

390

0.41

30.

413

0.41

30.

413

0.43

70.

437

0.43

70.

437

0.50

20.

502

0.50

20.

502

0.65

00.

650

0.25

00.

303

0.39

50.

487

0.23

00.

285

0.44

80.

612

0.24

00.

379

0.52

60.

673

0.30

00.

387

0.51

00.

632

0.40

00.

716

0.32

00.

320

0.32

00.

320

0.33

00.

330

0.33

00.

330

0.34

00.

340

0.34

00.

340

0.38

00.

380

0.38

00.

380

0.50

00.

500

0.13

00.

130

0.13

00.

130

0.14

00.

140

0.14

00.

140

0.14

00.

140

0.14

00.

140

0.17

00.

170

0.17

00.

170

0.24

00.

240

6.25

6.25

6.25

6.25

7.25

7.25

7.25

7.25

8.25

8.25

8.25

8.25

10.0

10.0

10.0

10.0

12.4

12.4

3.6

2 4

.04

4.7

8 5

.51

3.9

1 4

.41

5.8

8 7

.35

4.4

9 5

.88

7.3

5 8

.82

6.3

0 7

.35

8.8

210

.3

9.9

614

.7

33.9

36.1

40.0

44.0

47.7

51.0

60.9

70.9

67.4

79.0

91.2

104

132

144

162

180

315

404

8.4

6 9

.03

10.0

11.0

10.6

11.3

13.5

15.8

13.5

15.8

18.2

20.7

22.0

24.1

27.0

29.9

42.0

53.8

3.06

2.99

2.90

2.82

3.49

3.40

3.22

3.11

3.87

3.66

3.52

3.43

4.57

4.43

4.29

4.18

5.62

5.24

1.4

0 1

.53

1.7

5 1

.98

1.7

5 1

.93

2.4

2 2

.94

2.2

8 2

.81

3.3

6 3

.95

3.9

9 4

.47

5.1

4 5

.82

8.1

311

.0

0.81

0.85

0.93

1.01

0.96

1.01

1.17

1.34

1.16

1.32

1.48

1.66

1.76

1.89

2.06

2.24

3.11

3.78

0.62

0.61

0.61

0.60

0.67

0.66

0.64

0.63

0.71

0.69

0.68

0.67

0.80

0.78

0.76

0.75

0.90

0.87

0.56

0.55

0.55

0.57

0.60

0.59

0.58

0.61

0.63

0.61

0.62

0.65

0.69

0.67

0.67

0.69

0.79

0.80

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-10 January 2005

TAB

LE

6 –

CA

R A

ND

SH

IP B

UIL

DIN

G C

HA

NN

EL

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Avg

Fla

nge

Thi

ckne

ss

t f in.

Web

T

hick

ness

t w in

.F

lang

e S

lope

Fill

et

Rad

ius

R1

in.

Tip

R

adiu

sR

2

in.

d1

in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

I x in.4

Sx

in.3

r x in.

I y in.4

Sy

in.3

r y in.

x in.

CS

3 ×

2.2

3C

S 3

× 2

.70

3.0

00 3

.000

2.00

02.

000

0.32

00.

375

0.25

00.

375

1:12

.10

0.25

00.

188

0 0.37

51.

750.

875

1.90

2.30

2.6

1 2

.89

1.7

4 1

.92

1.17

1.12

0.68

0.78

0.52

0.59

0.60

0.58

0.68

0.67

CS

4 ×

3.3

2C

S 5

× 5

.82

4.0

00 5

.000

2.50

02.

875

0.34

40.

562

0.31

80.

438

1:34

.91:

9.8

0.37

50.

250

0.12

50.

094

2.38

3.00

2.82

4.95

6.8

418

.1 3

.42

7.2

51.

561.

911.

623.

570.

951.

870.

760.

850.

810.

96

CS

6 ×

5.7

7C

S 6

× 5

.93

6.0

00 6

.000

3.00

03.

500

0.37

50.

442

0.50

00.

375

0 1:49

.60.

375

0.48

00.

250

0.42

04.

504.

004.

915.

0424

.128

.2 8

.02

9.4

12.

212.

373.

525.

581.

612.

310.

851.

050.

811.

09

CS

8 ×

6.5

9C

S 8

× 7

.86

8.0

00 8

.000

3.00

03.

500

0.46

80.

524

0.38

00.

425

1:14

.43

1:28

.50.

550

0.52

50.

220

0.37

55.

755.

755.

606.

6854

.263

.813

.515

.93.

113.

094.

107.

061.

882.

840.

861.

030.

811.

01

CS

10 ×

8.5

8C

S 1

0 ×

9.3

2C

S 1

0 ×

10.

1

10.0

0010

.000

10.0

00

3.50

03.

563

3.62

5

0.54

40.

544

0.54

4

0.37

50.

438

0.50

0

1:9

1:9

1:9

0.62

50.

625

0.62

5

0.18

80.

188

0.18

8

7.50

7.50

7.50

7.30

7.93

8.55

110

115

120

21.9

24.0

24.0

3.88

3.81

3.75

7.19

7.73

8.25

2.80

2.93

3.04

0.99

0.99

0.98

0.93

0.92

0.91

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a.

January 2005 VI-11

TAB

LE

7 –

CA

NA

DIA

N C

HA

NN

EL

S

Des

igna

tion

Dep

thd in

.

Wid

th

b in.

Fla

nge

Thi

ckne

sst f in.

Web

T

hick

ness

t w in

.

Fill

et

Rad

ius

R in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

x o in.

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

x in.

CS

2 ×

0.7

06C

S 2

.25

× 0

.86

2.00

02.

250

1.50

01.

000

0.12

50.

188

0.12

50.

188

0.12

50.

062

0.60

00.

730

0.39

10.

505

0.39

10.

449

0.80

70.

832

0.13

70.

062

0.13

60.

090

0.47

70.

292

0.49

30.

303

1.06

0.60

5 0

.093

8 0

.058

90.

0031

0.00

861.

421.

07

CS

3 ×

1.4

8C

S 3

× 1

.85

CS

3 ×

2.1

8

3.00

03.

000

3.00

0

1.50

01.

500

2.00

0

0.25

00.

312

0.31

2

0.18

80.

250

0.25

0

0.31

20.

312

0.18

8

1.26

1.57

1.86

1.72

2.03

2.56

1.15

1.35

1.71

1.17

1.14

1.17

0.26

80.

321

0.73

0

0.26

50.

322

0.56

8

0.46

10.

452

0.62

7

0.48

90.

502

0.71

4

0.98

10.

971

1.44

0.4

15 0

.501

1.0

9

0.02

10.

043

0.05

3

1.59

1.56

1.96

CS

4 ×

1.9

0C

S 4

× 2

.24

CS

4 ×

2.0

2C

S 4

× 2

.53

CS

4 ×

2.9

0

4.00

04.

000

4.00

04.

000

4.00

0

1.62

01.

750

2.00

02.

000

2.50

0

0.28

10.

281

0.25

00.

312

0.31

2

0.18

80.

250

0.18

80.

250

0.25

0

0.37

50.

375

0.37

50.

375

0.37

5

1.62

1.90

1.72

2.15

2.46

3.95

4.41

4.36

5.21

6.27

1.98

2.21

2.18

2.60

3.14

1.56

1.52

1.59

1.56

1.60

0.39

60.

514

0.66

70.

810

1.52

0.35

50.

417

0.48

60.

595

0.91

9

0.49

50.

520

0.62

30.

613

0.78

6

0.50

40.

519

0.62

70.

638

0.84

2

1.01

1.05

1.31

1.30

1.74

1.1

1 1

.49

1.8

4 2

.25

4.1

3

0.03

20.

044

0.02

90.

058

0.06

8

1.92

1.92

2.15

2.12

2.49

CS

5 ×

2.5

1C

S 5

× 3

.11

CS

5 ×

3.0

5C

S 5

× 3

.55

5.00

05.

000

5.00

05.

000

2.00

02.

000

2.50

02.

500

0.31

20.

343

0.31

20.

375

0.18

80.

281

0.21

80.

250

0.37

50.

375

0.43

70.

437

2.13

2.64

2.60

3.02

8.45

9.59

10.5

12.0

3.38

3.84

4.18

4.79

1.99

1.90

2.01

1.99

0.83

20.

942

1.60

1.86

0.60

70.

669

0.94

41.

11

0.62

50.

597

0.78

60.

784

0.63

00.

592

0.80

10.

830

1.29

1.20

1.67

1.69

3.5

9 4

.27

6.8

6 7

.89

0.05

00.

086

0.06

60.

110

2.45

2.33

2.73

2.73

CS

6 ×

3.6

0C

S 6

× 3

.51

CS

6 ×

6.4

2

6.00

06.

000

6.00

0

2.00

02.

500

3.50

0

0.37

50.

312

0.50

0

0.28

10.

250

0.37

5

0.43

70.

437

0.43

7

3.06

2.99

5.46

15.8

16.4

30.9

5.26

5.47

10.3

2.27

2.34

2.38

1.06

1.74

6.62

0.74

00.

978

2.87

0.58

80.

764

1.10

0.56

90.

719

1.19

1.13

1.52

2.44

7.0

411

.240

.3

0.10

90.

079

0.38

0

2.61

2.90

3.58

CS

7 ×

3.9

0C

S 7

× 4

.61

7.0

00

7.0

00

2.50

03.

000

0.37

50.

375

0.21

80.

250

0.43

70.

500

3.32

3.92

25.8

30.8

7.37

8.79

2.79

2.80

2.02

3.47

1.16

1.67

0.78

10.

941

0.75

90.

921

1.57

1.94

17.3

29.5

0.10

90.

138

3.29

3.53

CS

8 ×

4.6

5C

S 8

× 5

.56

8.00

08.

000

2.75

03.

000

0.37

50.

437

0.25

00.

281

0.43

70.

500

3.96

4.73

39.0

47.3

9.74

11.8

3.14

3.16

2.83

4.10

1.44

1.95

0.84

60.

931

0.78

10.

900

1.65

1.87

32.2

46.1

0.13

40.

220

3.65

3.79

CS

10

× 6

.23

CS

10

× 7

.58

CS

10

× 1

9.0

10.0

0010

.000

10.0

00

3.00

03.

500

4.00

0

0.43

70.

500

1.25

0

0.28

10.

312

0.81

2

0.50

00.

562

0.50

0

5.29

6.44

16.2

79.9

101

223

16.0

20.1

44.5

3.89

3.95

3.71

4.3

9 7

.59

23.3

2.01

3.07

8.94

0.91

11.

091.

20

0.81

91.

031.

39

1.73

2.15

2.49

79.3

134

402

0.23

40.

383

6.54

7

4.35

4.63

4.62

CS

12

× 1

0.3

12.0

004.

000

0.56

20.

375

0.62

58.

7419

232

.04.

6913

.14.

561.

221.

132.

3833

80.

665

5.40

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-12 January 2005

TAB

LE

8 –

AL

UM

INU

M A

SS

OC

IAT

ION

STA

ND

AR

D I-

BE

AM

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Thi

ckne

sst f in.

Web

T

hick

ness

t w in.

Fill

et

Rad

ius

R in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

I 3 ×

1.6

4I 3

× 2

.03

I 4 ×

2.3

1I 4

× 2

.79

3.00

03.

000

4.00

04.

000

2.50

02.

500

3.00

03.

000

0.20

00.

260

0.23

00.

290

0.13

00.

150

0.15

00.

170

0.25

00.

250

0.25

00.

250

1.3

9 1

.73

1.9

6 2

.38

2.24

2.71

5.62

6.71

1.4

9 1

.81

2.8

1 3

.36

1.27

1.25

1.69

1.68

0.5

22 0

.679

1.0

4 1

.31

0.4

18 0

.543

0.6

91 0

.872

0.61

30.

627

0.72

70.

742

1.

02

1.27

3.

68

4.50

0.01

920.

0374

0.03

330.

0608

1.41

1.40

1.84

1.84

I 5 ×

3.7

0I 6

× 4

.03

I 6 ×

4.6

9I 7

× 5

.80

5.00

06.

000

6.00

07.

000

3.50

04.

000

4.00

04.

500

0.32

00.

290

0.35

00.

380

0.19

00.

190

0.21

00.

230

0.30

00.

300

0.30

00.

300

3.1

5 3

.43

3.9

9 4

.93

13.9

22.0

25.5

42.9

5.5

8 7

.33

8.5

012

.3

2.11

2.53

2.53

2.95

2.2

9 3

.10

3.7

4 5

.78

1.3

1 1

.55

1.8

7 2

.57

0.85

30.

951

0.96

81.

08

12.5

25.3

29.8

63.3

0.09

840.

0888

0.14

50.

206

2.27

2.71

2.71

3.14

I 8 ×

6.1

8I 8

× 7

.02

I 9 ×

8.3

6

8.00

08.

000

9.00

0

5.00

05.

000

5.50

0

0.35

00.

410

0.44

0

0.23

00.

250

0.27

0

0.30

00.

300

0.30

0

5.2

6 5

.97

7.1

1

59.7

67.8

102

14.9

16.9

22.7

3.37

3.37

3.79

7.3

0 8

.55

12.2

2.9

2 3

.42

4.4

4

1.18

1.20

1.31

107

123

224

0.18

80.

286

0.38

6

3.57

3.57

4.01

I 10

× 8

.65

I 10

× 1

0.3

I 12

× 1

1.7

I 12

× 1

4.3

10.0

0010

.000

12.0

0012

.000

6.00

06.

000

7.00

07.

000

0.41

00.

500

0.47

00.

620

0.25

00.

290

0.29

00.

310

0.40

00.

400

0.40

00.

400

7.3

5 8

.75

9.9

212

.2

132

156

256

317

26.4

31.2

42.6

52.9

4.24

4.22

5.07

5.11

14.8

18.0

26.9

35.5

4.9

3 6

.01

7.6

910

.1

1.42

1.44

1.65

1.71

340

407

894

1149

0.36

00.

620

0.62

11.

26

4.47

4.46

5.33

5.39

I 14

× 1

6.01

14.0

008.

000

0.60

00.

300

0.40

014

.248

969

.96.

0051

.212

.81.

9423

001.

316.

31

1. N

ew s

hape

; che

ck a

vaila

bilit

y w

ith s

uppl

iers

.2.

Tol

eran

ces

for

extr

uded

sha

pes

are

give

n in

Alu

min

um S

tand

ard

s an

d D

ata .

January 2005 VI-13

TAB

LE

9 –

WID

E F

LA

NG

E B

EA

MS

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Avg

Fla

nge

Thi

ckne

sst f in.

Web

T

hick

ness

t w in

.F

lang

e S

lope

Fill

et

Rad

ius

R1

in.

Tip

Rad

ius

R2

in.

d1

in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

I x in.4

Sx

in.3

r x in.

I y in.4

Sy

in.3

r y in.

WF

2 ×

1.4

3W

F 4

× 4

.76

WF

5 ×

6.4

9

2.00

04.

000

5.00

0

2.0

00 4

.000

5.0

00

0.23

20.

370

0.41

5

0.18

80.

313

0.31

3

1:11

.41:

11.3

1:13

.6

0.18

80.

313

0.31

3

0.09

40.

145

0.16

5

1.13

2.38

3.38

1.2

2 4

.05

5.5

2

0.7

8210

.823

.9

0.7

825.

409.

58

0.80

1.63

2.08

0.2

75 3

.52

7.7

3

0.2

75 1

.76

3.0

9

0.47

0.93

1.18

WF

6 ×

4.1

6W

F 6

× 5

.40

WF

6 ×

7.8

5W

F 6

× 8

.30

WF

6 ×

9.1

8

6.00

06.

000

6.00

06.

000

6.00

0

4.0

00 6

.000

5.9

30 6

.000

6.1

30

0.27

90.

269

0.45

10.

451

0.45

1

0.23

00.

240

0.25

00.

313

0.43

8

0 0 1:15

.61:

15.6

1:15

.6

0.25

00.

250

0.31

30.

313

0.31

3

0 0 0.18

00.

180

0.18

0

4.88

4.88

4.38

4.38

4.38

3.5

4 4

.59

6.6

8 7

.06

7.8

1

21.8

30.2

44.3

45.4

47.6

7.25

10.1

14.8

15.1

15.9

2.48

2.56

2.57

2.54

2.47

2.9

8 9

.69

14.0

14.5

15.5

1.4

9 3

.23

4.6

7 4

.83

5.1

6

0.92

1.45

1.45

1.43

1.41

WF

8 ×

5.9

0W

F 8

× 8

.32

WF

8 ×

10.

7W

F 8

× 1

1.2

WF

8 ×

11.

8W

F 8

× 1

3.0

8.00

08.

000

8.00

08.

000

8.00

08.

000

5.2

50 6

.500

8.0

00 7

.940

8.0

00 8

.130

0.30

80.

398

0.43

30.

458

0.45

80.

458

0.23

00.

245

0.28

80.

313

0.37

50.

500

0 0 0 1:18

.91:

18.9

1:18

.9

0.32

00.

400

0.40

00.

313

0.31

30.

313

0 0 0 0.17

90.

179

0.17

9

6.75

6.38

6.38

6.25

6.25

6.25

5.0

2 7

.08

9.1

2 9

.55

10.1

11.1

56.7

84.2

110

113

116

121

14.2

21.0

27.4

28.3

29.0

30.3

3.36

3.44

3.47

3.45

3.40

3.31

7.4

418

.237

.033

.934

.736

.5

2.8

3 5

.61

9.2

4 8

.47

8.6

8 9

.13

1.22

1.61

2.01

1.88

1.86

1.82

WF

10 ×

11.

4W

F 1

0 ×

7.3

09.

750

9.90

0 7

.964

5.7

500.

433

0.34

00.

292

0.24

00 0

0.50

00.

312

0 07.

888.

56 9

.71

6.2

117

110

735

.121

.64.

204.

1536

.510

.8 9

.16

3.7

51.

941.

32

WF

12 ×

13.

8W

F 1

2 ×

18.

311

.940

12.0

60 8

.000

10.0

000.

516

0.57

60.

294

0.34

50 0

0.60

00.

600

0 09.

699.

6911

.815

.631

042

651

.970

.75.

135.

2344

.196

.111

.019

.21.

942.

48

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-14 January 2005

TAB

LE

10

– A

RM

Y-N

AV

Y W

IDE

FL

AN

GE

BE

AM

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Thi

ck-

ness t f in.

Web

T

hick

-ne

ss t w in.

Fill

et

Rad

ius

R1

in.

Tip

R

adiu

sR

2

in.

d1

in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

WF

(A-N

) 2

× 0

.928

WF

(A-N

) 3

× 0

.769

WF

(A-N

) 3

× 1

.00

WF

(A-N

) 4

× 1

.14

WF

(A-N

) 4

× 1

.79

WF

(A-N

) 4

× 2

.35

WF

(A-N

) 4

× 3

.06

WF

(A-N

) 4

× 4

.14

WF

(A-N

) 5

× 5

.36

2.50

03.

000

3.00

04.

000

4.00

04.

000

4.00

04.

000

5.00

0

2.00

02.

000

2.00

02.

000

3.00

03.

500

3.50

04.

000

5.00

0

0.12

50.

094

0.12

50.

125

0.15

60.

188

0.25

00.

312

0.31

2

0.12

50.

094

0.12

50.

125

0.15

60.

188

0.25

00.

312

0.31

2

0.15

60.

156

0.15

60.

125

0.18

80.

188

0.18

80.

250

0.31

2

0.12

50.

094

0.12

50.

125

0.15

60.

188

0.25

00.

312

0.12

5

2.00

2.

50

2.50

3.

50

3.25

3.

25

3.00

2.

75

3.75

0.78

90.

654

0.85

10.

969

1.52

2.00

2.60

3.52

4.56

0.83

10.

992

1.26

2.42

4.14

5.52

6.97

9.39

19.7

0.66

50.

661

0.84

11.

212.

072.

763.

484.

707.

86

1.03

1.23

1.22

1.58

1.65

1.66

1.64

1.63

2.08

0.15

50.

118

0.15

50.

155

0.65

91.

261.

643.

036.

43

0.15

50.

118

0.15

50.

155

0.43

90.

719

0.93

61.

512.

57

0.44

30.

426

0.42

60.

400

0.65

80.

793

0.79

30.

927

1.19

0.2

35 0

.265

0.3

44 0

.626

2.5

9 4

.88

6.2

811

.335

.7

0.00

407

0.00

189

0.00

439

0.00

505

0.01

230.

0235

0.05

470.

115

0.14

6

1.12

1.30

1.29

1.63

1.78

1.84

1.82

1.88

2.39

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

January 2005 VI-15

TAB

LE

11

– A

ME

RIC

AN

STA

ND

AR

D I-

BE

AM

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Tip

T

hick

ness

t f in.

Avg

F

lang

e T

hick

ness

t in.

Web

T

hick

ness

t w in.

Fill

et

Rad

ius

R1

in.

Tip

Rad

ius

R2

in.

d1

in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

S 3

× 1

.96

S 3

× 2

.59

3.00

03.

000

2.33

02.

509

0.17

00.

170

0.26

00.

260

0.17

00.

349

0.27

00.

270

0.10

00.

100

1.75

1.75

1.6

7 2

.21

2.

52

2.93

1.6

8 1

.95

1.23

1.15

0.4

6 0

.59

0.39

0.47

0.52

0.52

S 4

× 2

.64

S 4

× 3

.28

4.00

04.

000

2.66

02.

796

0.19

00.

190

0.29

30.

293

0.19

00.

326

0.29

00.

290

0.11

00.

110

2.75

2.75

2.2

5 2

.79

6.

06

6.79

3.0

3 3

.39

1.64

1.56

0.7

6 0

.90

0.57

0.65

0.58

0.57

S 5

× 3

.43

S 5

× 4

.23

S 5

× 5

.10

5.00

05.

000

5.00

0

3.00

03.

137

3.28

4

0.21

00.

210

0.21

0

0.32

60.

326

0.32

6

0.21

00.

347

0.49

4

0.31

00.

310

0.31

0

0.13

00.

130

0.13

0

3.50

3.50

3.50

2.9

2 3

.60

4.3

4

12.3

13.7

15.2

4.9

0 5

.48

6.0

9

2.05

1.95

1.87

1.2

1 1

.41

1.6

6

0.81

0.90

1.01

0.64

0.63

0.62

S 6

× 4

.30

S 6

× 5

.10

S 6

× 5

.96

6.00

06.

000

6.00

0

3.33

03.

443

3.56

5

0.23

00.

230

0.23

0

0.35

90.

359

0.35

9

0.23

00.

343

0.46

5

0.33

00.

330

0.33

0

0.14

00.

140

0.14

0

4.50

4.50

4.50

3.6

6 4

.34

5.0

7

22.1

24.1

26.3

7.3

6 8

.04

8.7

7

2.46

2.36

2.28

1.8

2 2

.04

2.3

1

1.09

1.19

1.30

0.71

0.69

0.68

S 7

× 6

.05

7.00

03.

755

0.25

00.

392

0.34

50.

350

0.15

05.

25 5

.15

39.4

11.3

2.77

2.8

81.

530.

75

S 8

× 6

.35

S 8

× 7

.96

S 8

× 8

.81

8.00

08.

000

8.00

0

4.00

04.

171

4.26

2

0.27

00.

270

0.27

0

0.42

50.

425

0.42

5

0.27

00.

441

0.53

2

0.37

00.

370

0.37

0

0.16

00.

160

0.16

0

6.25

6.25

6.25

5.4

0 6

.77

7.4

9

57.6

64.9

68.7

14.4

16.2

17.2

3.27

3.10

3.03

3.7

3 4

.31

4.6

6

1.86

2.07

2.19

0.83

0.80

0.79

S 9

× 7

.51

9.00

04.

330

0.29

00.

458

0.29

00.

390

0.17

07.

00 6

.38

85.9

19.1

3.67

5.0

92.

350.

89

S 1

0 ×

8.7

6S

10

× 1

0.4

S 1

0 ×

12.

1

10.0

0010

.000

10.0

00

4.66

04.

797

4.94

4

0.31

00.

310

0.31

0

0.49

10.

491

0.49

1

0.31

00.

447

0.59

4

0.41

00.

410

0.41

0

0.19

00.

190

0.19

0

8.00

8.00

8.00

7.4

5 8

.82

10.3

123

135

147

24.5

27.0

29.4

4.07

3.91

3.78

6.7

8 7

.50

8.3

6

2.91

3.13

3.38

0.95

0.92

0.90

S 1

2 ×

11.

0S

12

× 1

2.1

S 1

2 ×

14.

1S

12

× 1

5.6

S 1

2 ×

17.

3

12.0

0012

.000

12.0

0012

.000

12.0

00

5.00

05.

078

5.25

05.

355

5.47

7

0.35

00.

350

0.46

00.

460

0.46

0

0.54

40.

544

0.66

00.

660

0.66

0

0.35

00.

428

0.46

00.

565

0.68

7

0.45

00.

450

0.56

00.

560

0.56

0

0.21

00.

210

0.28

00.

280

0.28

0

9.75

9.75

9.25

9.25

9.25

9.3

510

.312

.013

.214

.7

218

229

272

287

305

36.4

38.2

45.4

47.9

50.8

4.83

4.72

4.77

4.66

4.56

9.3

5 9

.87

13.5

14.5

15.7

3.74

3.89

5.16

5.42

5.74

1.00

0.98

1.06

1.05

1.03

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-16 January 2005

TAB

LE

12

– C

AN

AD

IAN

I-B

EA

MS

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Thi

ckne

ss

t f in.

Web

T

hick

ness

t w in

.

Fill

et

Rad

ius

R in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

I 3 ×

2.1

6 3

.000

2.50

00.

250

0.18

80.

375

1.

84

2.78

1.

851.

23 0

.657

0.52

50.

597

1.2

40.

017

1.37

I 4 ×

2.6

8 4

.000

3.00

00.

250

0.18

80.

375

2.

28

6.28

3.

141.

66 1

.13

0.75

40.

705

3.9

80.

017

1.80

I 5 ×

4.0

5 5

.000

3.50

00.

312

0.25

00.

437

3.

4414

.5

5.79

2.05

2.2

41.

280.

808

12.3

0.03

62.

20

I 6 ×

3.9

2I 6

× 4

.82

I 6 ×

5.4

6

6.0

00 6

.000

6.0

00

3.00

03.

500

4.00

0

0.31

20.

375

0.37

5

0.25

00.

250

0.28

1

0.37

50.

438

0.43

7

3.

34

4.10

4.

64

19.2

24.9

28.2

6.

40

8.28

9.

40

2.40

2.46

2.47

1.4

2 2

.70

4.0

2

0.94

51.

542.

01

0.65

20.

811

0.93

1

11.5

21.3

31.8

0.02

60.

043

0.04

8

2.49

2.59

2.64

I 7 ×

5.7

9 7

.000

4.00

00.

375

0.28

10.

438

4.

9240

.211

.52.

86 4

.02

2.01

0.90

444

.10.

048

3.00

I 8 ×

6.1

2I 8

× 8

.77

8.0

00 8

.000

4.00

05.

000

0.37

50.

500

0.28

10.

312

0.43

70.

562

5.

20

7.46

54.6

82.4

13.6

20.6

3.24

3.32

4.0

210

.52.

014.

180.

880

1.18

58.5

147

0.04

80.

116

3.36

3.53

I 10

× 9

.83

I 10

× 1

1.3

10.0

0010

.000

5.00

06.

000

0.50

00.

500

0.34

30.

375

0.56

20.

562

8.

36

9.65

139

163

27.8

32.7

4.08

4.12

10.5

18.1

4.19

6.02

1.12

1.37

236

408

0.12

70.

140

4.23

4.34

I 12

× 1

2.5

I 12

× 1

5.5

12.0

0012

.000

5.50

06.

500

0.56

20.

625

0.37

50.

437

0.62

50.

625

10.6

13.2

252

317

42.0

52.9

4.88

4.91

15.7

28.7

5.70

8.84

1.22

1.48

513

929

0.19

30.

245

5.03

5.13

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

January 2005 VI-17

TAB

LE

13

– C

AN

AD

IAN

WID

E F

LA

NG

E B

EA

MS

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Fla

nge

Thi

ckne

ss

t f in.

Web

T

hick

ness

t w in

.

Fill

et

Rad

ius

R in.

Are

aA in

2

Axi

s x-

xA

xis

y-y

Cw

in6

J in4

r 0 in.

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

WF

4 ×

4.1

24.

000

4.00

00.

312

0.25

00.

437

3.

50

9.72

4.

861.

67

3.34

1.6

70.

977

11.4

0.03

61.

93

WF

6 ×

7.6

1W

F 6

× 9

.66

6.00

06.

000

6.00

06.

000

0.37

50.

500

0.31

20.

375

0.62

50.

625

6.

47

8.21

41.5

51.2

13.8

17.1

2.53

2.50

13.5

18.1

4.5

2 6

.02

1.45

1.48

107

137

0.11

70.

176

2.91

2.91

WF

8 ×

13.

18.

000

8.00

00.

500

0.37

50.

750

11.1

129

32.2

3.40

42.8

10.7

1.96

601

0.26

73.

93

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a.

VI-18 January 2005

TAB

LE

14

– A

NG

LE

S –

EQ

UA

L L

EG

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Thi

ckne

sst in.

Fill

et

Rad

ius

R1

in.

Tip

Rad

ius

R2

in.

Wei

ght

lb/ft

Are

aA in

2

Axi

s x-

x, y

-yA

xis

z-z

I x ,

I yin

4

Sx ,

Sy

in3

r x ,

r yin

.x,

y in.

I z in4

r z in.

L 1

1/2

× 1

1/2

× 1

/8L

1 1/

2 ×

1 1

/2 ×

1/4

1.50

01.

500

1.50

01.

500

0.12

50.

250

0.18

80.

188

0.12

50.

125

0.4

2 0

.81

0.3

60 0

.688

0.0

745

0.1

35 0

.068

4 0

.130

0.45

50.

444

0.41

10.

461

0.0

282

0.0

556

0.28

00.

284

L 1

3/4

× 1

3/4

× 1

/8L

1 3/

4 ×

1 3

/4 ×

1/4

L 1

3/4

× 1

3/4

× 3

/8

1.75

01.

750

1.75

0

1.75

01.

750

1.75

0

0.12

50.

250

0.37

5

0.18

80.

188

0.18

8

0.12

50.

125

0.12

5

0.5

0 0

.96

1.3

8

0.4

23 0

.813

1.1

7

0.1

21 0

.223

0.3

06

0.0

948

0.1

82 0

.259

0.53

50.

523

0.51

1

0.47

30.

524

0.57

0

0.0

462

0.0

904

0.1

32

0.33

00.

333

0.33

6

L 2

× 2

× 1

/8L

2 ×

2 ×

3/1

6L

2 ×

2 ×

1/4

L 2

× 2

× 5

/16

L 2

× 2

× 3

/8

2.00

02.

000

2.00

02.

000

2.00

0

2.00

02.

000

2.00

02.

000

2.00

0

0.12

50.

188

0.25

00.

312

0.37

5

0.25

00.

250

0.25

00.

250

0.25

0

0.12

50.

125

0.12

50.

125

0.12

5

0.5

8 0

.85

1.1

1 1

.36

1.6

1

0.4

91 0

.723

0.9

44 1

.16

1.3

7

0.1

85 0

.268

0.3

42 0

.410

0.4

74

0.1

26 0

.186

0.2

42 0

.295

0.3

46

0.61

30.

608

0.60

20.

595

0.58

9

0.53

10.

560

0.58

50.

609

0.63

2

0.0

71 0

.106

0.1

38 0

.169

0.2

01

0.38

10.

382

0.38

20.

383

0.38

3

L 2

1/2

× 2

1/2

× 1

/8L

2 1/

2 ×

2 1

/2 ×

3/1

6L

2 1/

2 ×

2 1

/2 ×

1/4

L 2

1/2

× 2

1/2

× 5

/16

L 2

1/2

× 2

1/2

× 3

/8L

2 1/

2 ×

2 1

/2 ×

1/2

2.50

02.

500

2.50

02.

500

2.50

02.

500

2.50

02.

500

2.50

02.

500

2.50

02.

500

0.12

50.

188

0.25

00.

312

0.37

50.

500

0.25

00.

250

0.25

00.

250

0.25

00.

250

0.12

50.

125

0.12

50.

125

0.12

50.

125

0.7

2 1

.07

1.4

0 1

.73

2.0

5 2

.65

0.6

16 0

.911

1.1

9 1

.47

1.7

4 2

.26

0.3

69 0

.539

0.6

95 0

.839

0.9

76 1

.22

0.2

00 0

.297

0.3

88 0

.475

0.5

60 0

.718

0.77

40.

769

0.76

30.

756

0.74

90.

735

0.65

50.

684

0.71

00.

734

0.75

70.

802

0.1

43 0

.213

0.2

78 0

.341

0.4

03 0

.525

0.48

30.

484

0.48

30.

482

0.48

10.

482

L 3

× 3

× 3

/16

L 3

× 3

× 1

/4L

3 ×

3 ×

5/1

6L

3 ×

3 ×

3/8

L 3

× 3

× 1

/2

3.00

03.

000

3.00

03.

000

3.00

0

3.00

03.

000

3.00

03.

000

3.00

0

0.18

80.

250

0.31

20.

375

0.50

0

0.31

20.

312

0.31

20.

312

0.31

2

0.25

00.

250

0.25

00.

250

0.25

0

1.2

8 1

.68

2.0

8 2

.47

3.2

3

1.0

9 1

.43

1.7

7 2

.10

2.7

4

0.9

08 1

.19

1.4

5 1

.71

2.1

7

0.4

12 0

.547

0.6

77 0

.804

1.0

4

0.91

40.

912

0.90

70.

901

0.88

9

0.79

70.

826

0.85

20.

877

0.92

4

0.3

32 0

.450

0.5

63 0

.674

0.8

88

0.55

30.

560

0.56

40.

566

0.56

9

L 3

1/2

× 3

1/2

× 1

/4L

3 1/

2 ×

3 1

/2 ×

5/1

6L

3 1/

2 ×

3 1

/2 ×

3/8

L 3

1/2

× 3

1/2

× 1

/2

3.50

03.

500

3.50

03.

500

3.50

03.

500

3.50

03.

500

0.25

00.

313

0.37

50.

500

0.37

50.

375

0.37

50.

375

0.25

00.

250

0.25

00.

250

1.9

9 2

.47

2.9

3 3

.83

1.6

9 2

.10

2.4

9 3

.25

1.9

4 2

.38

2.7

9 3

.57

0.7

58 0

.942

1.1

2 1

.45

1.07

1.07

1.06

1.05

0.94

70.

974

1.00

1.05

0.7

39 0

.924

1.1

0 1

.45

0.66

10.

664

0.66

50.

667

January 2005 VI-19

L 4

× 4

× 1

/4L

4 ×

4 ×

5/1

6L

4 ×

4 ×

3/8

L 4

× 4

× 7

/16

L 4

× 4

× 1

/2L

4 ×

4 ×

9/1

6L

4 ×

4 ×

5/8

L 4

× 4

× 1

1/16

L 4

× 4

× 3

/4

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

0

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

0

0.25

00.

313

0.37

50.

438

0.50

00.

563

0.62

50.

688

0.75

0

0.37

50.

375

0.37

50.

375

0.37

50.

375

0.37

50.

375

0.37

5

0.25

00.

250

0.25

00.

250

0.25

00.

250

0.25

00.

250

0.25

0

2.2

8 2

.83

3.3

7 3

.90

4.4

1 4

.93

5.4

2 5

.92

6.4

0

1.9

4 2

.41

2.8

6 3

.32

3.7

5 4

.19

4.6

1 5

.03

5.4

4

2.9

4 3

.62

4.2

6 4

.89

5.4

7 6

.04

6.5

7 7

.09

7.5

8

1.0

0 1

.25

1.4

8 1

.71

1.9

3 2

.15

2.3

6 2

.57

2.7

7

1.23

1.23

1.22

1.21

1.21

1.20

1.19

1.19

1.18

1.07

1.10

1.12

1.15

1.17

1.20

1.22

1.24

1.27

1.1

3 1

.41

1.6

8 1

.95

2.2

0 2

.46

2.7

1 2

.96

3.2

1

0.76

20.

765

0.76

60.

766

0.76

60.

766

0.76

60.

767

0.76

8

L 5

× 5

× 3

/8L

5 ×

5 ×

7/1

6L

5 ×

5 ×

1/2

L 5

× 5

× 9

/16

L 5

× 5

× 5

/8L

5 ×

5 ×

3/4

5.00

05.

000

5.00

05.

000

5.00

05.

000

5.00

05.

000

5.00

05.

000

5.00

05.

000

0.37

50.

438

0.50

00.

563

0.62

50.

750

0.50

00.

500

0.50

00.

500

0.50

00.

500

0.37

50.

375

0.37

50.

375

0.37

50.

375

4.2

4 4

.92

5.5

8 6

.24

6.8

8 8

.15

3.6

0 4

.18

4.7

4 5

.31

5.8

5 6

.93

8.4

0 9

.69

10.9

12.1

13.3

15.4

2.3

1 2

.68

3.0

4 3

.40

3.7

5 4

.42

1.53

1.52

1.52

1.51

1.50

1.49

1.36

1.39

1.41

1.44

1.46

1.51

3.1

9 3

.73

4.2

5 4

.77

5.2

8 6

.27

0.94

10.

945

0.94

70.

948

0.94

90.

951

L 6

× 6

× 3

/8L

6 ×

6 ×

7/1

6L

6 ×

6 ×

1/2

L 6

× 6

× 5

/8L

6 ×

6 ×

3/4

6.00

06.

000

6.00

06.

000

6.00

0

6.00

06.

000

6.00

06.

000

6.00

0

0.37

50.

438

0.50

00.

625

0.75

0

0.50

00.

500

0.50

00.

500

0.50

0

0.37

50.

375

0.37

50.

375

0.37

5

5.1

2 5

.95

6.7

5 8

.35

9.9

1

4.3

5 5

.06

5.7

4 7

.10

8.4

3

14.9

17.2

19.4

23.7

27.7

3.3

9 3

.94

4.4

8 5

.52

6.5

3

1.85

1.84

1.84

1.83

1.81

1.61

1.64

1.66

1.71

1.76

5.6

9 6

.65

7.5

8 9

.39

11.1

1.14

1.15

1.15

1.15

1.15

L 8

× 8

× 1

/2L

8 ×

8 ×

5/8

L 8

× 8

× 3

/4L

8 ×

8 ×

1

8.00

08.

000

8.00

08.

000

8.00

08.

000

8.00

08.

000

0.50

00.

625

0.75

01.

000

0.62

50.

625

0.62

50.

625

0.37

50.

375

0.37

50.

375

9.1

411

.313

.517

.7

7.7

7 9

.63

11.5

15.0

47.8

58.6

68.9

88.2

8.1

810

.112

.015

.6

2.48

2.47

2.45

2.42

2.16

2.21

2.26

2.35

18.8

23.2

27.5

35.9

1.55

1.55

1.55

1.55

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-20 January 2005

TABLE 15 – SQUARE END ANGLES – EQUAL LEGS

Designation

Depthdin.

Widthbin.

Thicknesst

in.

Weightlb/ft

AreaAin2

Axis x-x, y-y Axis z-z

Ix , Iyin4

Sx , Sy

in3

rx , ry

in.x, yin.

Izin4

rz

in.

LS 1 × 1 × 1/8LS 1 × 1 × 3/16LS 1 × 1 × 1/4

1.0001.0001.000

1.0001.0001.000

0.1250.1880.250

0.280.400.51

0.2340.3410.438

0.02170.03000.0369

0.03090.04400.0558

0.3040.2970.290

0.2960.3180.339

0.008960.01290.0168

0.1960.1950.196

LS 1 1/4 × 1 1/4 × 1/8LS 1 1/4 × 1 1/4 × 3/16LS 1 1/4 × 1 1/4 × 1/4

1.2501.2501.250

1.2501.2501.250

0.1250.1880.250

0.350.510.66

0.2970.4350.563

0.04390.06160.0767

0.04930.07090.0905

0.3850.3770.369

0.3590.3810.403

0.01790.02580.0333

0.2460.2440.243

LS 1 1/2 × 1 1/2 × 1/8LS 1 1/2 × 1 1/2 × 3/16LS 1 1/2 × 1 1/2 × 1/4

1.5001.5001.500

1.5001.5001.500

0.1250.1880.250

0.420.620.81

0.3590.5290.688

0.07780.1100.139

0.07210.1040.134

0.4650.4570.449

0.4210.4440.466

0.03150.04550.0586

0.2960.2930.292

LS 1 3/4 × 1 3/4 × 1/8LS 1 3/4 × 1 3/4 × 3/16LS 1 3/4 × 1 3/4 × 1/4

1.7501.7501.750

1.7501.7501.750

0.1250.1880.250

0.500.730.96

0.4220.6230.813

0.1260.1790.227

0.0990.1440.186

0.5460.5370.529

0.4840.5070.529

0.05070.07340.0947

0.3470.3430.341

LS 2 × 2 × 1/8LS 2 × 2 × 3/16LS 2 × 2 × 1/4

2.0002.0002.000

2.0002.0002.000

0.1250.1880.250

0.570.841.10

0.4840.7170.938

0.1900.2730.348

0.1310.1910.247

0.6260.6170.609

0.5460.5690.592

0.07660.1110.143

0.3980.3940.391

LS 2 1/2 × 2 1/2 × 1/8LS 2 1/2 × 2 1/2 × 3/16LS 2 1/2 × 2 1/2 × 1/4LS 2 1/2 × 2 1/2 × 5/16

2.5002.5002.5002.500

2.5002.5002.5002.500

0.1250.1880.2500.312

0.721.061.401.72

0.6090.9051.191.46

0.3780.5480.7030.847

0.2070.3030.3940.481

0.7870.7780.7690.761

0.6710.6950.7170.739

0.1520.2220.2870.350

0.4990.4950.4910.489

LS 3 × 3 × 1/8LS 3 × 3 × 3/16LS 3 × 3 × 1/4LS 3 × 3 × 5/16

3.0003.0003.0003.000

3.0003.0003.0003.000

0.1250.1880.2500.312

0.861.281.692.09

0.7341.091.441.77

0.6610.9641.241.51

0.3000.4420.5770.706

0.9490.9390.9300.922

0.7970.8200.8420.865

0.2650.3880.5040.616

0.6010.5960.5920.589

LS 3 1/2 × 3 1/2 × 1/8 3.500 3.500 0.125 1.01 0.859 1.06 0.411 1.11 0.922 0.425 0.703

LS 4 × 4 × 1/8LS 4 × 4 × 1/4

4.0004.000

4.0004.000

0.1250.250

1.162.28

0.9841.94

1.593.04

0.5391.05

1.271.25

1.051.09

0.6381.22

0.8050.795

1. Users are encouraged to check availability with suppliers.2. Tolerances for extruded shapes are given in Aluminum Standards and Data.

January 2005 VI-21

TAB

LE

16

– A

NG

LE

S –

UN

EQ

UA

L L

EG

S

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Thi

ck-

ness t in.

Fill

et

Rad

ius

R1

in.

Tip

R

adiu

sR

2

in.

Wei

ght

lb/ft

Are

aA in

2

Axi

s x-

xA

xis

y-y

Axi

s z-

z

I x in4

Sx

in3

r x in.

y in.

I y in4

Sy

in3

r y in.

x in.

I z in4

r z in.

α(d

eg)

L 1

3/4

× 1

1/4

× 1

/8L

1 3/

4 ×

1 1

/4 ×

3/1

6L

1 3/

4 ×

1 1

/4 ×

1/4

1.75

01.

750

1.75

0

1.25

01.

250

1.25

0

0.12

50.

188

0.25

0

0.18

80.

188

0.18

8

0.12

50.

125

0.12

5

0.42

0.62

0.81

0.36

00.

530

0.68

8

0.10

90.

157

0.19

9

0.09

010.

133

0.17

2

0.54

90.

544

0.53

7

0.30

00.

326

0.34

9

0.04

600.

0659

0.08

30

0.04

840.

0713

0.09

21

0.35

70.

353

0.34

7

0.54

40.

572

0.59

6

0.02

380.

0355

0.04

65

0.25

70.

259

0.26

0

27.1

226

.61

26.0

9

L 2

× 1

× 3

/16

2.00

01.

000

0.18

80.

188

0.12

50.

620.

530

0.21

10.

166

0.63

10.

236

0.03

510.

0459

0.25

70.

728

0.02

230.

205

14.6

2

L 2

× 1

1/4

× 1

/8L

2 ×

1 1

/4 ×

1/4

2.00

02.

000

1.25

01.

250

0.12

50.

250

0.18

80.

188

0.12

50.

125

0.46

0.88

0.39

20.

751

0.15

80.

291

0.11

70.

224

0.63

50.

623

0.28

10.

330

0.04

770.

0862

0.04

920.

0937

0.34

90.

339

0.64

90.

702

0.02

650.

0515

0.26

00.

262

21.8

720

.83

L 2

× 1

1/2

× 1

/8L

2 ×

1 1

/2 ×

3/1

6L

2 ×

1 1

/2 ×

1/4

L 2

× 1

1/2

× 3

/8

2.00

02.

000

2.00

02.

000

1.50

01.

500

1.50

01.

500

0.12

50.

188

0.25

00.

375

0.18

80.

188

0.18

80.

188

0.12

50.

125

0.12

50.

125

0.50

0.73

0.96

1.38

0.42

30.

624

0.81

31.

17

0.16

80.

243

0.31

10.

428

0.12

00.

178

0.23

10.

330

0.63

00.

625

0.61

80.

604

0.36

00.

386

0.41

00.

455

0.08

100.

117

0.14

80.

202

0.07

100.

105

0.13

60.

193

0.43

80.

433

0.42

70.

415

0.60

50.

633

0.65

70.

704

0.04

070.

0606

0.07

920.

116

0.31

00.

312

0.31

20.

314

29.3

829

.00

28.6

227

.74

L 2

× 1

3/4

× 1

/42.

000

1.75

00.

250

0.25

00.

125

1.04

0.88

20.

328

0.23

70.

610

0.49

40.

233

0.18

50.

514

0.61

70.

109

0.35

236

.91

L 2

1/4

× 1

1/2

× 1

/42.

250

1.50

00.

250

0.25

00.

125

1.04

0.88

20.

435

0.29

20.

702

0.38

90.

153

0.13

80.

417

0.75

80.

0877

0.31

523

.46

L 2

1/2

× 1

1/4

× 1

/82.

500

1.25

00.

125

0.18

80.

094

0.54

0.45

70.

298

0.18

20.

807

0.25

20.

0515

0.05

160.

336

0.86

70.

0320

0.26

515

.16

L 2

1/2

× 1

1/2

× 1

/8L

2 1/

2 ×

1 1

/2 ×

3/1

6L

2 1/

2 ×

1 1

/2 ×

1/4

L 2

1/2

× 1

1/2

× 5

/16

L 2

1/2

× 1

1/2

× 3

/8

2.50

02.

500

2.50

02.

500

2.50

0

1.50

01.

500

1.50

01.

500

1.50

0

0.12

50.

188

0.25

00.

312

0.37

5

0.25

00.

250

0.25

00.

250

0.25

0

0.12

50.

125

0.12

50.

125

0.12

5

0.58

0.85

1.11

1.36

1.61

0.49

10.

723

0.94

41.

161.

37

0.31

40.

457

0.58

60.

705

0.81

6

0.18

60.

275

0.35

80.

437

0.51

4

0.80

00.

794

0.78

70.

780

0.77

3

0.32

00.

347

0.37

20.

395

0.41

9

0.08

600.

124

0.15

80.

188

0.21

6

0.07

280.

108

0.14

00.

170

0.20

0

0.41

80.

414

0.40

80.

403

0.39

8

0.80

60.

838

0.86

40.

889

0.91

4

0.04

920.

0727

0.09

460.

116

0.13

7

0.31

60.

317

0.31

60.

316

0.31

6

20.4

320

.07

19.7

019

.29

18.8

4

L 2

1/2

× 2

× 1

/8L

2 1/

2 ×

2 ×

3/1

6L

2 1/

2 ×

2 ×

1/4

L 2

1/2

× 2

× 5

/16

L 2

1/2

× 2

× 3

/8

2.50

02.

500

2.50

02.

500

2.50

0

2.00

02.

000

2.00

02.

000

2.00

0

0.12

50.

188

0.25

00.

312

0.37

5

0.25

00.

250

0.25

00.

250

0.25

0

0.12

50.

125

0.12

50.

125

0.12

5

0.65

0.96

1.26

1.54

1.83

0.55

40.

817

1.07

1.31

1.55

0.34

50.

503

0.64

60.

780

0.90

5

0.19

40.

288

0.37

50.

459

0.54

1

0.78

90.

784

0.77

80.

770

0.76

3

0.47

80.

506

0.53

10.

555

0.57

8

0.19

70.

286

0.36

60.

440

0.50

9

0.12

90.

191

0.24

90.

304

0.35

8

0.59

60.

592

0.58

50.

579

0.57

2

0.72

20.

752

0.77

80.

802

0.82

6

0.09

550.

142

0.18

50.

226

0.26

7

0.41

50.

416

0.41

60.

415

0.41

5

32.5

132

.30

32.0

931

.85

31.5

9

L 3

× 1

1/2

× 1

/43.

000

1.50

00.

250

0.31

20.

125

1.27

1.08

0.98

00.

510

0.95

40.

343

0.16

50.

142

0.39

11.

080.

106

0.31

314

.59

L 3

× 2

× 3

/16

L 3

× 2

× 1

/4L

3 ×

2 ×

5/1

6L

3 ×

2 ×

3/8

L 3

× 2

× 1

/2

3.00

03.

000

3.00

03.

000

3.00

0

2.00

02.

000

2.00

02.

000

2.00

0

0.18

80.

250

0.31

20.

375

0.50

0

0.31

20.

312

0.31

20.

312

0.31

2

0.18

80.

188

0.18

80.

188

0.18

8

1.07

1.40

1.73

2.05

2.65

0.91

01.

191.

471.

742.

26

0.82

11.

061.

291.

511.

90

0.40

00.

526

0.64

70.

765

0.98

7

0.94

90.

944

0.93

80.

931

0.91

8

0.45

90.

485

0.51

00.

534

0.58

0

0.29

20.

377

0.45

60.

529

0.65

9

0.19

00.

249

0.30

60.

361

0.46

4

0.56

70.

562

0.55

70.

551

0.54

1

0.94

70.

976

1.00

1.03

1.08

0.15

80.

209

0.25

70.

305

0.39

9

0.41

60.

418

0.41

90.

419

0.42

1

24.2

523

.95

23.6

423

.32

22.6

1

VI-22 January 2005

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Thi

ck-

ness t in.

Fill

et

Rad

ius

R1

in.

Tip

R

adiu

sR

2

in.

Wei

ght

lb/ft

Are

aA in

2

Axi

s x-

xA

xis

y-y

Axi

s z-

z

I x in4

Sx

in3

r x in.

y in.

I y in4

Sy

in3

r y in.

x in.

I z in4

r z in.

α(d

eg)

L 3

× 2

1/2

× 1

/4L

3 ×

2 1

/2 ×

5/1

6L

3 ×

2 1

/2 ×

3/8

3.00

03.

000

3.00

0

2.50

02.

500

2.50

0

0.25

00.

312

0.37

5

0.31

20.

312

0.31

2

0.25

00.

250

0.25

0

1.54

1.90

2.25

1.31

1.61

1.92

1.12

1.37

1.61

0.53

20.

659

0.78

2

0.92

70.

922

0.91

6

0.64

70.

672

0.69

7

0.70

40.

859

1.01

0.38

00.

470

0.55

7

0.73

40.

730

0.72

4

0.89

30.

919

0.94

4

0.32

30.

404

0.48

4

0.49

70.

500

0.50

3

34.6

534

.45

34.2

5

L 3

1/2

× 3

× 1

/4L

3 1/

2 ×

3 ×

5/1

6L

3 1/

2 ×

3 ×

3/8

L 3

1/2

× 3

× 1

/2

3.50

03.

500

3.50

03.

500

3.00

03.

000

3.00

03.

000

0.25

00.

312

0.37

50.

500

0.37

50.

375

0.37

50.

375

0.25

00.

250

0.25

00.

250

1.8

4 2

.27

2.7

1 3

.53

1.57

1.93

2.30

3.00

1.8

5 2

.26

2.6

6 3

.39

0.74

20.

918

1.09

1.42

1.09

1.08

1.08

1.06

0.76

70.

793

0.81

90.

867

1.25

1.53

1.79

2.28

0.55

90.

692

0.82

21.

07

0.89

30.

888

0.88

30.

871

1.01

1.04

1.07

1.11

0.5

62 0

.701

0.8

38 1

.10

0.59

90.

602

0.60

30.

605

36.1

736

.04

35.9

035

.63

L 4

× 3

× 1

/4L

4 ×

3 ×

5/1

6L

4 ×

3 ×

3/8

L 4

× 3

× 7

/16

L 4

× 3

× 1

/2L

4 ×

3 ×

5/8

4.00

04.

000

4.00

04.

000

4.00

04.

000

3.00

03.

000

3.00

03.

000

3.00

03.

000

0.25

00.

312

0.37

50.

438

0.50

00.

625

0.37

50.

375

0.37

50.

375

0.37

50.

375

0.25

00.

250

0.25

00.

250

0.25

00.

250

1.9

9 2

.46

2.9

3 3

.38

3.8

3 4

.69

1.69

2.09

2.49

2.88

3.25

3.99

2.6

9 3

.29

3.8

8 4

.44

4.9

7 5

.96

0.96

31.

191.

421.

641.

852.

26

1.26

1.26

1.25

1.24

1.24

1.22

0.71

90.

746

0.77

10.

796

0.81

90.

866

1.30

1.59

1.86

2.13

2.37

2.82

0.56

80.

703

0.83

60.

964

1.09

1.32

0.87

50.

871

0.86

50.

859

0.85

30.

841

1.21

1.24

1.27

1.29

1.31

1.36

0.6

51 0

.810

0.9

67 1

.12

1.2

7 1

.56

0.62

00.

623

0.62

40.

624

0.62

40.

625

29.3

929

.19

29.0

028

.81

28.6

228

.20

L 4

× 3

1/2

× 5

/16

L 4

× 3

1/2

× 3

/8L

4 ×

3 1

/2 ×

1/2

4.00

04.

000

4.00

0

3.50

03.

500

3.50

0

0.31

20.

375

0.50

0

0.37

50.

375

0.37

5

0.31

20.

312

0.31

2

2.6

2 3

.13

4.1

0

2.23

2.66

3.49

3.4

1 4

.03

5.1

8

1.20

1.43

1.88

1.24

1.23

1.22

0.91

30.

940

0.98

9

2.43

2.87

3.68

0.93

81.

121.

46

1.04

1.04

1.03

1.16

1.19

1.24

1.0

6 1

.28

1.7

0

0.69

10.

694

0.69

8

37.3

337

.22

37.0

0

L 5

× 3

× 1

/4L

5 ×

3 ×

5/1

6L

5 ×

3 ×

3/8

L 5

× 3

× 1

/2

5.00

05.

000

5.00

05.

000

3.00

03.

000

3.00

03.

000

0.25

00.

312

0.37

50.

500

0.37

50.

375

0.37

50.

375

0.31

20.

312

0.31

20.

312

2.2

6 2

.81

3.3

5 4

.40

1.93

2.39

2.85

3.74

4.9

0 6

.05

7.1

7 9

.26

1.45

1.81

2.16

2.83

1.60

1.59

1.59

1.57

0.63

90.

666

0.69

20.

742

1.34

1.65

1.95

2.49

0.56

70.

706

0.84

31.

10

0.83

40.

831

0.82

70.

816

1.62

1.65

1.68

1.73

0.7

39 0

.930

1.1

2 1

.47

0.62

00.

624

0.62

60.

628

20.7

920

.54

20.3

119

.86

TAB

LE

16

– A

NG

LE

S –

UN

EQ

UA

L L

EG

S (

Co

nti

nu

ed)

January 2005 VI-23

L 5

× 3

1/2

× 5

/16

L 5

× 3

1/2

× 3

/8L

5 ×

3 1

/2 ×

1/2

L 5

× 3

1/2

× 5

/8

5.00

05.

000

5.00

05.

000

3.50

03.

500

3.50

03.

500

0.31

20.

375

0.50

00.

625

0.43

80.

438

0.43

80.

438

0.31

20.

312

0.31

20.

312

3.0

0 3

.58

4.7

0 5

.79

2.55

3.05

4.00

4.92

6.3

9 7

.58

9.7

911

.8

1.86

2.22

2.91

3.57

1.58

1.58

1.56

1.55

0.81

90.

846

0.89

50.

943

2.59

3.06

3.93

4.72

0.96

51.

151.

511.

84

1.01

1.00

0.99

10.

979

1.56

1.59

1.64

1.69

1.3

5 1

.63

2.1

4 2

.64

0.72

80.

731

0.73

20.

733

26.3

226

.13

25.7

825

.41

L 6

× 3

x 3

/86.

000

3.00

00.

375

0.50

00.

375

3.8

03.

2311

.83.

031.

910.

630

1.99

0.84

20.

786

2.11

1.2

10.

612

15.2

4

L 6

× 3

1/2

× 5

/16

L 6

× 3

1/2

× 3

/8L

6 ×

3 1

/2 ×

1/2

L 6

× 3

1/2

× 5

/8

6.00

06.

000

6.00

06.

000

3.50

03.

500

3.50

03.

500

0.31

20.

375

0.50

00.

625

0.50

00.

500

0.50

00.

500

0.31

20.

312

0.31

20.

312

3.3

9 4

.04

5.3

1 6

.54

2.88

3.43

4.51

5.56

10.6

12.6

16.4

19.8

2.64

3.16

4.15

5.10

1.92

1.92

1.90

1.89

0.74

60.

773

0.82

30.

872

2.71

3.21

4.12

4.96

0.98

51.

181.

541.

89

0.97

10.

967

0.95

60.

944

1.97

2.00

2.06

2.11

1.5

6 1

.87

2.4

6 3

.02

0.73

60.

738

0.73

80.

737

19.6

119

.43

19.1

018

.75

L 6

× 4

× 3

/8L

6 ×

4 ×

7/1

6L

6 ×

4 ×

1/2

L 6

× 4

× 5

/8L

6 ×

4 ×

3/4

6.00

06.

000

6.00

06.

000

6.00

0

4.00

04.

000

4.00

04.

000

4.00

0

0.37

50.

438

0.50

00.

625

0.75

0

0.50

00.

500

0.50

00.

500

0.50

0

0.37

50.

375

0.37

50.

375

0.37

5

4.2

4 4

.92

5.5

8 6

.88

8.1

5

3.60

4.18

4.74

5.85

6.93

13.0

15.1

17.0

20.7

24.1

3.19

3.70

4.20

5.18

6.12

1.90

1.90

1.89

1.88

1.87

0.92

00.

947

0.97

21.

021.

07

4.66

5.37

6.03

7.30

8.46

1.51

1.76

1.99

2.45

2.89

1.14

1.13

1.13

1.12

1.10

1.91

1.93

1.96

2.01

2.06

2.5

0 2

.92

3.3

3 4

.12

4.8

8

0.83

40.

836

0.83

80.

839

0.83

9

24.3

324

.16

24.0

023

.68

23.3

5

L 7

× 4

× 1

/27.

000

4.00

00.

500

0.50

00.

375

6.1

75.

2426

.15.

662.

230.

903

6.28

2.03

1.09

2.39

3.7

10.

842

18.7

0

L 8

× 6

× 5

/8L

8 ×

6 ×

11/

16L

8 ×

6 ×

3/4

8.00

08.

000

8.00

0

6.00

06.

000

6.00

0

0.62

50.

688

0.75

0

0.50

00.

500

0.50

0

0.31

20.

375

0.37

5

9.8

410

.811

.7

8.37

9.15

9.93

53.6

58.1

62.6

9.74

10.6

11.5

2.53

2.52

2.51

1.51

1.53

1.55

26.0

28.`

030

.2

5.78

6.27

6.79

1.76

1.75

1.74

2.50

2.52

2.55

13.6

14.7

15.9

1.27

51.

266

1.26

5

29.0

729

.03

28.9

4

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-24 January 2005

TAB

LE

17

– S

QU

AR

E E

ND

AN

GL

ES

– U

NE

QU

AL

LE

GS

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Thi

ck-

ness t in.

Wei

ght

lb/ft

Are

aA in

2

Axi

s x-

xA

xis

y-y

Axi

s z-

z

I x in4

Sx

in3

r x in.

y in.

I y in4

Sy

in3

r y in.

x in.

I z in4

r z in.

α(d

eg)

LS 1

× 3

/4 ×

1/8

1.00

00.

750

0.12

50.

240.

203

0.01

970.

0295

0.31

20.

332

0.00

947

0.01

740.

216

0.20

70.

0051

90.

160

28.4

9

LS 1

1/4

× 1

× 1

/81.

250

1.00

00.

125

0.31

0.26

60.

0408

0.04

770.

392

0.39

30.

0233

0.03

180.

296

0.26

80.

0119

0.21

232

.05

LS 1

1/2

× 3

/4 ×

1/8

LS 1

1/2

× 1

× 1

/8LS

1 1

/2 ×

1 ×

3/1

6LS

1 1

/2 ×

1 1

/4 ×

1/8

1.50

01.

500

1.50

01.

500

0.75

01.

000

1.00

01.

250

0.12

50.

125

0.18

80.

125

0.31

0.35

0.51

0.39

0.26

60.

297

0.43

50.

328

0.06

130.

0679

0.09

590.

0733

0.06

440.

0677

0.09

790.

0702

0.48

00.

478

0.47

00.

473

0.54

80.

497

0.52

00.

455

0.01

050.

0245

0.03

400.

0465

0.01

830.

0325

0.04

650.

0505

0.19

90.

287

0.28

00.

376

0.17

30.

247

0.27

00.

330

0.00

683

0.01

400.

0201

0.02

28

0.16

00.

217

0.21

50.

264

14.6

223

.77

23.1

834

.37

LS 1

3/4

× 1

× 1

/81.

750

1.00

00.

125

0.39

0.32

80.

104

0.09

090.

563

0.60

40.

0255

0.03

310.

279

0.22

90.

0156

0.21

818

.50

LS 2

× 1

× 1

/8LS

2 ×

1 ×

3/1

6LS

2 ×

1 1

/2 ×

1/8

LS 2

× 1

1/2

× 3

/16

2.00

02.

000

2.00

02.

000

1.00

01.

000

1.50

01.

500

0.12

50.

188

0.12

50.

188

0.42

0.62

0.50

0.73

0.35

90.

529

0.42

20.

623

0.15

00.

215

0.17

30.

248

0.11

70.

170

0.12

50.

183

0.64

70.

638

0.64

10.

632

0.71

50.

738

0.61

80.

641

0.02

630.

0366

0.08

470.

120

0.03

350.

0481

0.07

480.

108

0.27

10.

263

0.44

80.

439

0.21

50.

238

0.36

80.

391

0.01

680.

0240

0.04

470.

0645

0.21

60.

213

0.32

60.

322

14.9

514

.45

29.1

628

.84

LS 2

1/2

× 1

× 1

/8LS

2 1

/2 ×

1 1

/2 ×

1/8

LS 2

1/2

× 2

× 1

/8LS

2 1

/2 ×

2 ×

3/1

6

2.50

02.

500

2.50

02.

500

1.00

01.

500

2.00

02.

000

0.12

50.

125

0.12

50.

188

0.50

0.57

0.64

0.95

0.42

20.

484

0.54

70.

811

0.27

70.

319

0.35

20.

510

0.17

80.

191

0.20

00.

294

0.81

10.

812

0.80

20.

793

0.94

20.

829

0.74

10.

764

0.02

760.

0899

0.20

30.

292

0.03

420.

0767

0.13

50.

197

0.25

60.

431

0.60

90.

600

0.19

20.

329

0.49

10.

514

0.01

870.

0532

0.10

20.

148

0.21

00.

331

0.43

20.

427

10.5

420

.36

32.4

632

.26

LS 3

× 1

× 1

/8LS

3 ×

2 ×

1/8

LS 3

× 2

× 1

/4LS

3 ×

2 ×

3/8

LS 3

× 2

1/2

× 1

/4

3.00

03.

000

3.00

03.

000

3.00

0

1.00

02.

000

2.00

02.

000

2.50

0

0.12

50.

125

0.25

00.

375

0.25

0

0.57

0.72

1.40

2.04

1.54

0.48

40.

609

1.19

1.73

1.31

0.45

60.

580

1.09

1.53

1.17

0.25

00.

282

0.54

20.

781

0.56

1

0.97

10.

975

0.95

70.

940

0.94

5

1.18

0.94

70.

993

1.04

0.91

1

0.02

860.

213

0.39

20.

543

0.74

3

0.03

470.

137

0.26

00.

371

0.40

4

0.24

30.

592

0.57

40.

559

0.75

3

0.17

50.

447

0.49

30.

539

0.66

1

0.02

010.

120

0.22

50.

320

0.36

6

0.20

40.

444

0.43

50.

430

0.52

8

7.9

424

.28

23.7

723

.18

34.3

7

LS 3

1/2

× 1

1/4

× 1

/83.

500

1.25

00.

125

0.68

0.57

80.

750

0.34

71.

141.

340.

0570

0.05

500.

314

0.21

50.

0392

0.26

1 8

.98

LS 4

× 2

× 1

/8LS

4 ×

2 ×

1/4

LS 4

× 3

× 1

/8

4.00

04.

000

4.00

0

2.00

02.

000

3.00

0

0.12

50.

250

0.12

5

0.86

1.69

1.01

0.73

41.

440.

859

1.27

2.41

1.45

0.48

40.

936

0.51

7

1.31

1.29

1.30

1.38

1.43

1.19

0.22

90.

421

0.71

9

0.14

10.

268

0.31

1

0.55

80.

541

0.91

4

0.38

20.

429

0.69

0

0.14

40.

269

0.37

6

0.44

20.

432

0.66

1

15.4

014

.95

29.4

5

LS 5

× 3

× 1

/8LS

5 ×

3 ×

1/4

LS 5

× 4

× 1

/8

5.00

05.

000

5.00

0

3.00

03.

000

4.00

0

0.12

50.

250

0.12

5

1.16

2.28

1.30

0.98

41.

941.

11

2.66

5.11

2.92

0.78

41.

530.

820

1.64

1.62

1.62

1.61

1.66

1.44

0.76

21.

441.

70

0.31

90.

614

0.55

4

0.88

00.

861

1.24

0.61

00.

657

0.93

6

0.44

70.

851

0.84

7

0.67

40.

663

0.87

4

20.6

720

.36

32.6

3

LS 5

¼ ×

2 ¼

× 1

/85.

250

2.25

00.

125

1.08

0.92

22.

750.

817

1.73

1.89

0.34

00.

183

0.60

70.

387

0.22

30.

491

12.1

7

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

January 2005 VI-25

TABLE 18 – TEES

DesignationTd × b × Wt

in. in. lb/ft

Thickness t

in.t1 in.

t2 in.

R1 in.

Area A in2

Axis x-x Axis y-y

Ix in4

Sx in3

rx in.

y in.

Iy in4

Sy in3

ry in.

T 1.00 × 1.00 × 0.31T 1.25 × 1.50 × 0.44T 1.25 × 1.50 × 0.62T 1.50 × 1.50 × 0.68T 1.50 × 1.50 × 0.87T 2.00 × 1.50 × 0.86

0.1250.1250.1880.1880.250.188

0.1560.1560.2190.2190.2810.25

0.1560.1560.2190.2190.2810.25

0.1250.1250.1250.1880.1880.188

0.270.370.520.580.740.73

0.0230.0490.0670.1140.1420.269

0.0320.0530.0750.1080.1370.195

0.2930.3630.3590.4330.4380.606

0.2920.3260.3520.4370.4640.624

0.0110.0380.0560.0560.0750.060

0.0230.0510.0750.0750.1000.080

0.2060.3190.3280.3120.3190.286

T 2.00 × 2.00 × 1.26T 2.00 × 2.00 × 1.50T 2.25 × 2.25 × 1.42T 1.25 × 2.50 × 1.00T 2.25 × 2.50 × 1.91

0.250.3130.250.1880.313

0.3130.3750.3130.3130.375

0.3130.3750.3130.2180.375

0.250.250.250.1880.25

1.071.281.210.851.62

0.370.430.530.080.89

0.260.310.330.090.50

0.590.580.660.310.74

0.580.610.640.300.73

0.180.230.260.2850.44

0.180.230.230.220.35

0.410.420.460.570.52

T 3.00 × 2.50 × 2.11T 2.50 × 3.00 × 2.13T 3.00 × 3.00 × 2.72T 2.00 × 4.00 × 2.70T 3.00 × 4.00 × 2.76

0.3130.3130.3750.3750.313

0.3750.3750.4380.4380.375

0.3750.3750.4380.4380.375

0.250.3130.3130.250.375

1.801.812.312.302.34

1.490.941.830.601.72

0.720.510.860.400.77

0.910.720.890.510.86

0.920.680.880.480.75

0.440.750.902.101.77

0.350.500.601.050.89

0.500.650.630.960.87

T 4.00 × 4.00 × 3.74T 5.00 × 4.00 × 4.22T 5.00 × 4.00 × 5.41T 3.00 × 4.50 × 2.96T 3.00 × 5.00 × 4.02

0.3750.3750.50.3130.375

0.4380.4380.5630.3750.625

0.4380.4380.5630.3750.438

0.50.50.50.3750.375

3.183.594.602.523.42

4.568.5610.81.782.37

1.582.433.140.781.06

1.201.541.540.840.83

1.111.481.540.710.76

2.122.132.832.524.13

1.061.061.421.121.65

0.820.770.791.001.10

T 1.13 × 1.00 × 0.16T 1.50 × 1.13 × 0.19T 1.50 × 1.50 × 0.063T 1.75 × 1.25 × 0.37

0.0630.0620.1870.109

0.0630.0620.1870.109

0.0630.0620.1870.109

0.0940.0620.1870.062

0.130.160.540.32

0.0130.0180.110.043

0.0170.0210.100.045

0.310.340.450.37

0.250.260.440.30

0.0070.0170.0540.049

0.0130.0230.0720.056

0.240.330.320.39

T 2.00 × 3.00 × 0.55T 2.00 × 1.50 × 0.75T 2.00 × 2.00 × 1.13T 2.50 × 2.50 × 1.77

0.0940.1870.2500.312

0.0940.1870.2500.312

0.0940.1870.2500.312

0.1570.1870.2500.312

0.470.640.961.51

0.450.120.350.86

0.220.110.250.49

0.980.440.600.76

0.920.390.590.74

0.0630.130.170.42

0.0630.130.170.33

0.370.450.420.53

T 3.00 × 3.00 × 2.55T 4.00 × 2.50 × 2.32T 4.00 × 4.00 × 3.43T 5.00 × 3.00 × 3.43

0.3750.3120.3750.375

0.3750.3120.3750.375

0.3750.3120.3750.375

0.3750.3120.3750.375

2.171.982.922.92

1.780.934.402.06

0.840.491.540.90

0.910.691.230.84

0.890.601.140.72

0.861.682.033.93

0.580.841.011.57

0.630.920.831.16

T 6.50 × 10.00 × 10.5(1) 0.500 0.625 0.500 0.625 8.92 89.7 12.7 3.17 2.95 14.4 4.44 1.27

1. t = 0.625 for flange and t = 0.500 for web2. Users are encouraged to check availability with suppliers.3. Tolerances for extruded shapes are given in Aluminum Standards and Data.

VI-26 January 2005

TABLE 19 – ARMY – NAVY AND SPECIAL TEES

Designation T(A-N) d × b × Wt

in. in. lb/ft

Stem Thickness

ts in.

Flange Thickness

tf in.

Area A in2

R1 in.

Axis x-x Axis y-y

Ix

in4

Sx in3

rx

in.y in.

Iy in4

Sy in3

ry in.

T(A-N) 1.25 × 1.50 × 0.384T(A-N) 1.63 × 1.75 × 0.476T(A-N) 1.00 × 2.00 × 0.421T(A-N) 1.75 × 2.00 × 0.531T(A-N) 1.25 × 2.50 × 0.652T(A-N) 2.00 × 2.50 × 0.789

0.1250.1250.1250.1250.1560.156

0.1250.1250.1250.1250.1560.156

0.326 0.405 0.358 0.451 0.554 0.671

0.1250.1250.1250.1250.1250.125

0.045 0.100 0.025 0.128 0.062 0.241

0.0490.830.0320.0980.0630.161

0.3710.4960.2660.5320.3330.599

0.3270.4340.2120.4510.2650.500

0.032 0.052 0.078 0.078 0.188 0.189

0.0430.0590.0780.0780.1510.151

0.3140.3570.4660.4150.5830.530

T(A-N) 2.00 × 3.00 × 0.881T(A-N) 2.50 × 3.00 × 1.17T(A-N) 3.00 × 4.00 × 1.50T(A-N) 4.00 × 4.00 × 2.27T(A-N) 5.00 × 4.00 × 2.57

0.1560.1880.1880.2500.250

0.1560.1880.1880.2500.250

0.749 0.995 1.28 1.93 2.18

0.1250.1880.1880.2500.250

0.254 0.565 1.03 2.98 5.54

0.1640.3020.4481.021.57

0.5820.7530.8971.241.59

0.4560.6320.7081.081.47

0.330 0.393 0.947 1.24 1.24

0.2200.2620.4740.6190.620

0.6630.6290.8610.8010.754

T(A-N) 3.00 × 6.00 × 3.24T(A-N) 4.00 × 6.00 × 3.88T(A-N) 4.00 × 6.00 × 4.79T(A-N) 7.50 × 7.50 × 9.46T(A-N) 7.50 × 7.50 × 14.4T(A-N) 6.00 × 8.00 × 11.2

0.3121

0.3751

0.3751

0. 5001

1.131

0.5001

0.3120.3130.4500.7500.7500.860

2.75 3.30 4.07 8.0412.3 9.56

0.3121

0.3131

0.3121

0.6251

0.6251

0.5001

1.83 4.78 5.0240.369.322.9

0.771.591.617.2814.54.82

0.811.201.112.242.381.55

0.621.000.881.962.711.24

5.63 5.65 8.1213.614.436.8

1.881.882.714.534.809.19

1.431.311.411.301.081.96

1. Both Flange and stem of these shapes have square ends. Fillet radius R1 applies only to juncture of stem and flange.2. Users are encouraged to check availability with suppliers.3. Tolerances for extruded shapes are given in Aluminum Standards and Data.

January 2005 VI-27

TAB

LE

20

– Z

EE

S

Des

igna

tion

Dep

th

d

in.

Wid

th

b

in.

Thi

ckne

ss

t in.

Fill

et

Rad

ius

R

1

in.

Tip

R

adiu

s

R2

in

.

Are

a

A

in2

Axi

s x-

xA

xis

y-y

Axi

s z-

z

l x

in4

Sx

in

3

r x

in.

l y

in4

Sy

in

3

r y

in.

l z

in4

r z

in.

α

deg

Z 1

3/4

× 1

3/4

× 1

.09

1.75

01.

750

0.18

80.

188

0.12

50.

925

0.4

470.

511

0.69

50.

553

0.33

40.

773

0.10

10.

330

48.8

2

Z 2

× 1

.25

× 0

.922

Z 2

3/8

× 1

1/4

× 1

.00

2.00

02.

375

1.25

01.

250

0.18

80.

188

0.18

80.

188

0.12

50.

125

0.78

40.

854

0.4

59 0

.695

0.45

90.

586

0.76

50.

902

0.18

60.

187

0.16

10.

161

0.48

80.

467

0.06

300.

0820

0.28

40.

310

29.2

023

.20

Z 3

× 2

11/

16 ×

2.3

3Z

3 ×

2 1

1/16

× 3

.38

3.00

03.

000

2.68

82.

688

0.25

00.

375

0.31

20.

312

0.25

00.

250

1.98

2.87

2.8

9 3

.86

1.92

2.57

1.21

1.16

2.64

3.76

1.03

1.50

1.15

1.14

0.59

00.

820

0.54

50.

534

43.4

044

.52

Z 4

× 3

1/1

6 ×

2.8

5Z

4 1

/16

× 3

1/8

× 3

.57

Z 4

1/8

× 3

3/1

6 ×

4.3

2Z

4 ×

3 1

/16

× 4

.78

Z 4

1/8

× 3

3/1

6 ×

6.2

2

4.00

04.

062

4.12

54.

000

4.12

5

3.06

23.

125

3.18

83.

062

3.18

8

0.25

00.

312

0.37

50.

438

0.56

3

0.31

20.

312

0.31

20.

312

0.31

2

0.25

00.

250

0.25

00.

250

0.25

0

2.42

3.04

3.67

4.07

5.29

6.3

1 7

.96

9.6

6 9

.69

12.8

3.16

3.92

4.69

4.84

6.19

1.61

1.62

1.62

1.54

1.55

4.01

5.23

6.54

6.53

9.06

1.36

1.76

2.18

2.30

3.12

1.29

1.31

1.33

1.27

1.31

1.08

1.39

1.72

1.74

2.41

0.66

80.

676

0.68

40.

654

0.67

5

36.7

837

.40

37.9

237

.83

38.6

8

Z 5

× 3

1/4

× 4

.01

Z 5

1/1

6 ×

3 5

/16

× 4

.84

Z 5

× 3

1/4

× 6

.19

5.00

05.

062

5.00

0

3.25

03.

312

3.25

0

0.31

20.

375

0.50

0

0.31

20.

312

0.31

2

0.25

00.

250

0.25

0

3.41

4.12

5.26

13.4

16.2

19.2

5.36

6.41

7.69

1.98

1.99

1.91

5.93

7.40

8.82

1.92

2.37

2.94

1.32

1.34

1.29

1.89

2.33

2.82

0.74

50.

752

0.73

2

30.6

731

.13

31.1

5

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

2. T

oler

ance

s fo

r ex

trud

ed s

hape

s ar

e gi

ven

in A

lum

inum

Sta

ndar

ds

and

Dat

a .

VI-28 January 2005

TABLE 21 – ROUND TUBES

Designation

Inside Diameter

in.Weight

lb/ft

Area A in2

Iin4

Sin3

rin.

Jin4 Rb /t

1.5001.5001.5001.5001.5001.5001.500

OD × 0.062OD × 0.094OD × 0.125OD × 0.156OD × 0.188OD × 0.250OD × 0.375

WALLWALLWALLWALLWALLWALLWALL

1.3761.3121.2501.1881.1241.0000.750

0.3290.4880.6350.7750.9111.151.56

0.2800.4150.5400.6590.7750.9821.33

0.07250.1030.1290.1510.1700.1990.233

0.0970.1370.1720.2010.2270.2660.311

0.5090.4980.4880.4780.4690.4510.419

0.1450.2050.2550.2970.3330.3830.419

11.67.55.54.33.52.51.5

1.6251.6251.625

OD × 0.125OD × 0.188OD × 0.250

WALLWALLWALL

1.3751.2491.125

0.6930.9981.27

0.5890.8491.08

0.1670.2230.264

0.2050.2740.324

0.5320.5120.494

0.3310.4380.510

6.03.82.8

1.7501.7501.7501.750

OD × 0.125OD × 0.188OD × 0.250OD × 0.375

WALLWALLWALLWALL

1.5001.3741.2501.000

0.7501.081.391.90

0.6380.9231.181.62

0.2120.2850.3410.411

0.2420.3260.3890.470

0.5760.5560.5380.504

0.4210.5630.6630.766

6.54.23.01.8

1.8751.8751.8751.875

OD × 0.125OD × 0.188OD × 0.250OD × 0.375

WALLWALLWALLWALL

1.6251.4991.3751.125

0.8081.171.502.08

0.6870.9961.281.77

0.2640.3590.4310.528

0.2820.3830.4600.563

0.6200.6000.5810.547

0.5260.7090.8430.994

7.04.53.32.0

2.0002.0002.0002.0002.0002.000

OD × 0.125OD × 0.188OD × 0.250OD × 0.312OD × 0.375OD × 0.500

WALLWALLWALLWALLWALLWALL

1.7501.6241.5001.3761.2501.000

0.8661.261.621.952.252.77

0.7361.071.371.651.912.36

0.3250.4440.5370.6090.6660.736

0.3250.4440.5370.6090.6660.736

0.6640.6440.6250.6070.5900.559

0.6470.8781.051.181.261.33

7.54.83.52.72.21.5

2.2502.2502.2502.2502.2502.250

OD × 0.125OD × 0.188OD × 0.250OD × 0.312OD × 0.375OD × 0.500


2.0001.8741.7501.6261.5001.250

0.9811.431.852.232.603.23

0.8341.221.571.902.212.75

0.4730.6530.7980.9151.011.14

0.4200.5800.7090.8130.8971.01

0.7530.7320.7130.6940.6760.643

0.9421.291.571.781.942.10

8.55.54.03.12.51.8

2.3752.3752.3752.375

OD × 0.188OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALLWALL

1.9991.8751.6251.375

1.521.962.773.46

1.291.672.362.95

0.7780.9551.221.39

0.6550.8041.031.17

0.7760.7560.7190.686

1.541.882.362.59

5.84.32.71.9

2.5002.5002.5002.5002.5002.5002.5002.500

OD × 0.125OD × 0.188OD × 0.250OD × 0.312OD × 0.375OD × 0.500OD × 0.625OD × 0.750

WALLWALLWALLWALLWALLWALLWALLWALL

2.2502.1242.0001.8761.7501.5001.2501.000

1.101.612.082.522.943.694.334.85

0.9331.371.772.142.503.143.684.12

0.6590.9181.131.311.461.671.801.87

0.5280.7350.9061.051.171.341.441.49

0.8410.8200.8000.7810.7630.7290.6990.673

1.321.822.242.572.833.143.243.16

9.56.14.53.52.82.01.51.2

2.625 OD × 0.250 WALL 2.125 2.19 1.87 1.33 1.01 0.844 2.63 4.8

January 2005 VI-29

TABLE 21 – ROUND TUBES (Continued)

Designation

Inside Diameter

in.Weight

lb/ft

Area A in2

Iin4

Sin3

rin.

Jin4 Rb /t

2.7502.7502.7502.7502.7502.7502.7502.750



2.5002.3742.2502.1262.0001.7501.5001.250

1.211.782.312.813.294.164.915.54

1.031.511.962.392.803.534.174.71

0.890 1.25 1.55 1.80 2.02 2.35 2.56 2.69

0.647 0.908

1.131.311.471.711.861.95

0.9290.9080.8880.8690.8500.8150.7830.755

1.78 2.48 3.07 3.55 3.95 4.47 4.71 4.71

10.5 6.8 5.0 3.9 3.2 2.3 1.7 1.3

2.8752.875

OD × 0.250OD × 0.500

WALLWALL

2.3751.875

2.424.39

2.063.73

1.79 2.75

1.251.91

0.9320.858

3.55 5.26

5.3 2.4

3.0003.0003.0003.0003.0003.0003.0003.000



2.7502.6242.5002.2502.0001.7501.5001.000

1.331.952.543.644.625.486.237.39

1.131.662.163.093.934.665.306.28

1.17 1.65 2.06 2.72 3.19 3.52 3.73 3.93

0.7791.101.371.812.132.342.492.62

1.020.9960.9760.9380.9010.8680.8390.791

2.33 3.28 4.08 5.33 6.14 6.58 6.71 6.28

11.5 7.5 5.5 3.5 2.5 1.9 1.5 1.0

3.2503.2503.250

OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALL

2.7502.5002.250

2.773.985.08

2.363.394.32

2.67 3.56 4.22

1.642.192.60

1.061.030.988

5.30 7.00 8.17

6.0 3.8 2.8

3.5003.5003.5003.5003.5003.5003.500

OD × 0.125OD × 0.188OD × 0.250OD × 0.312OD × 0.375OD × 0.500OD × 0.750


3.2503.1243.0002.8762.7502.5002.000

1.562.303.003.674.335.547.62

1.331.962.553.123.684.716.48

1.89 2.69 3.39 4.01 4.56 5.45 6.58

1.081.541.942.292.613.113.76

1.191.171.151.131.111.081.01

3.77 5.36 6.74 7.94 8.9910.612.3

13.5 8.8 6.5 5.1 4.2 3.0 1.8

3.7503.7503.7503.7503.750

OD × 0.125OD × 0.188OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALLWALLWALL

3.5003.3743.2503.0002.750

1.672.473.234.686.00

1.422.102.753.985.11

2.34 3.35 4.23 5.73 6.90

1.251.782.263.063.68

1.281.261.241.201.16

4.68 6.67 8.4211.313.5

14.5 9.5 7.0 4.5 3.3

4.0004.0004.0004.0004.0004.0004.0004.000



3.7503.6243.5003.3763.2503.0002.7502.500

1.792.653.464.255.026.477.799.01

1.522.252.953.614.275.506.637.66

2.86 4.10 5.20 6.19 7.09 8.59 9.7610.6

1.432.052.603.093.544.304.885.32

1.371.351.331.311.291.251.211.18

5.71 8.1810.412.314.016.818.920.2

15.510.1 7.5 5.9 4.8 3.5 2.7 2.2

4.2504.2504.2504.250

OD × 0.125OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALLWALL

4.0003.7503.5003.250

1.903.695.376.93

1.623.144.575.89

3.45 6.31 8.6510.5

1.622.974.074.96

1.461.421.381.34

6.8912.617.120.7

16.5 8.0 5.2 3.8

VI-30 January 2005

Designation

Inside Diameter

in.Weight

lb/ft

Area A in2

Iin4

Sin3

rin.

Jin4 Rb /t

4.5004.5004.5004.5004.5004.5004.5004.5004.500

OD × 0.125OD × 0.188OD × 0.250OD × 0.312OD × 0.375OD × 0.500OD × 0.625OD × 0.750OD × 1.000

WALLWALLWALLWALLWALLWALLWALLWALLWALL

4.2504.1244.0003.8763.7503.5003.2503.0002.500

2.02 2.99 3.93 4.83 5.71 7.39 8.9510.412.9

1.72 2.55 3.34 4.10 4.86 6.28 7.61 8.8411.0

4.11 5.93 7.56 9.0510.412.814.716.218.2

1.83 2.64 3.36 4.02 4.63 5.67 6.51 7.18 8.09

1.551.531.511.481.461.431.391.351.29

8.2211.815.118.020.725.128.631.133.7

17.511.5 8.5 6.7 5.5 4.0 3.1 2.5 1.8

4.7504.7504.7504.7504.750

OD × 0.125OD × 0.188OD × 0.250OD × 0.375OD × 0.500


4.5004.3744.2504.0003.750

2.14 3.17 4.16 6.06 7.85

1.82 2.69 3.53 5.15 6.68

4.86 7.02 8.9712.415.3

2.05 2.96 3.78 5.23 6.43

1.641.611.591.551.51

9.7114.017.924.730.1

18.512.1 9.0 5.8 4.3

5.0005.0005.0005.0005.0005.0005.0005.0005.000



4.7504.6244.5004.3764.2504.0003.7503.5003.000

2.25 3.34 4.39 5.40 6.41 8.3110.111.814.8

1.91 2.84 3.73 4.60 5.45 7.07 8.5910.012.6

5.69 8.2410.612.714.718.121.023.326.7

2.28 3.30 4.22 5.07 5.87 7.25 8.39 9.3310.7

1.721.701.681.661.641.601.561.531.46

11.416.521.025.229.135.841.145.250.3

19.512.8 9.5 7.5 6.2 4.5 3.5 2.8 2.0

5.5005.5005.5005.5005.5005.5005.500

OD × 0.125OD × 0.188OD × 0.250OD × 0.375OD × 0.500OD × 0.750OD × 1.000


5.2505.1245.0004.7504.5004.0003.500

2.48 3.69 4.85 7.10 9.2413.216.6

2.11 3.14 4.12 6.04 7.8511.214.1

7.6311.114.219.924.832.437.6

2.77 4.03 5.18 7.25 9.0111.813.7

1.901.881.861.821.781.701.63

15.222.128.439.649.163.171.6

21.514.110.5 6.8 5.0 3.2 2.3

6.0006.0006.0006.0006.0006.0006.0006.0006.000



5.7505.6245.5005.3765.2505.0004.7504.5004.000

2.71 4.04 5.31 6.56 7.7910.212.414.518.5

2.31 3.43 4.52 5.58 6.63 8.6410.612.415.7

9.9614.518.722.626.332.938.643.551.1

3.32 4.84 6.23 7.54 8.7811.012.914.517.0

2.082.062.032.011.991.951.911.881.80

19.929.037.345.152.465.376.285.298.2

23.515.511.5 9.1 7.5 5.5 4.3 3.5 2.5

6.5006.5006.5006.500

OD × 0.250OD × 0.375OD × 0.500OD × 0.750

WALLWALLWALLWALL

6.0005.7505.5005.000

5.77 8.4911.115.9

4.91 7.22 9.4213.5

24.034.042.756.9

7.3910.513.117.5

2.212.172.132.05

47.967.784.8112

12.5 8.2 6.0 3.8

6.7506.750

OD × 0.500OD × 0.750

WALLWALL

5.7505.250

11.516.6

9.8214.1

48.264.6

14.319.1

2.222.14

95.9127

6.3 4.0


January 2005 VI-31

Designation

Inside Diameter

in.Weight

lb/ft

Area A in2

Iin4

Sin3

rin.

Jin4 Rb /t

7.0007.0007.0007.0007.000

OD × 0.250OD × 0.375OD × 0.500OD × 0.750OD × 1.000


6.5006.2506.0005.5005.000

6.23 9.1812.017.322.2

5.30 7.8010.214.718.8

30.243.054.272.987.2

8.6412.315.520.824.9

2.392.352.302.232.15

60.4 85.6 108 144 170

13.5 8.8 6.5 4.2 3.0

7.5007.5007.500

OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALL

7.0006.7506.500

6.70 9.8712.9

5.69 8.3911.0

37.553.467.7

9.9914.218.1

2.562.522.48

74.8 107 135

14.59.5 7.0

8.0008.0008.0008.0008.0008.0008.000

OD × 0.125OD × 0.250OD × 0.375OD × 0.500OD × 0.625OD × 0.750OD × 1.000


7.7507.5007.2507.0006.7506.5006.000

3.64 7.1610.613.917.020.125.9

3.09 6.09 8.9811.814.517.122.0

24.045.765.483.299.2113137

5.9911.416.420.824.828.434.4

2.782.742.702.662.622.582.50

47.9 91.4 131 166 197 224 269

31.515.510.2 7.5 5.9 4.8 3.5

8.500 OD × 0.250 WALL 8.000 7.62 6.48 55.2 13.0 2.92 110 16.5

9.0009.0009.000

OD × 0.250OD × 0.375OD × 0.500

WALLWALLWALL

8.5008.2508.000

8.0811.915.7

6.8710.213.4

65.894.7121

14.621.026.9

3.093.053.01

132 189 241

17.511.5 8.5

10.00010.00010.00010.00010.00010.000

OD × 0.250OD × 0.375OD × 0.500OD × 0.625OD × 0.750OD × 1.000


9.5009.2509.0008.7508.5008.000

9.0113.317.521.625.633.3

7.6611.314.918.421.828.3

91.1132169203235290

18.226.333.840.646.958.0

3.453.413.363.323.283.20

182 263 337 404 466 573

19.512.8 9.5 7.5 6.2 4.5

10.50010.50010.50010.500

OD × 0.250OD × 0.375OD × 0.500OD × 0.750

WALLWALLWALLWALL

10.0009.7509.5009.000

9.4714.018.527.0

8.0511.915.723.0

106153197275

20.129.237.552.3

3.633.583.543.46

211 306 393 546

20.513.510.0 6.5

11.00011.00011.00011.000

OD × 0.375OD × 0.500OD × 0.750OD × 1.000

WALLWALLWALLWALL

10.25010.0009.5009.000

14.719.428.436.9

12.516.524.231.4

177228319397

32.241.458.072.1

3.763.723.633.55

353 455 634 785

14.210.5 6.8 5.0

12.00012.00012.00012.00012.000

OD × 0.250OD × 0.375OD × 0.500OD × 0.750OD × 1.000


11.50011.25011.00010.50010.000

10.916.121.231.240.6

9.2313.718.126.534.6

159232299421527

26.638.649.970.287.8

4.164.114.073.993.91

319 463 597 8391045

23.515.511.5 7.5 5.5

1. Tube can be produced by different methods. Seamless tube is usually required for applications with internal pressure.2. Users are encouraged to check availability with suppliers. Additional sizes and shapes may be available from suppliers.3. Tolerances for extruded shapes are given in Aluminum Standards and Data.


VI-32 January 2005

TABLE 22 – PIPES

NominalPipeSize

Schedule No.

OutsideDiameter

ODin.

InsideDiameter

IDin.

Wall Thickness

tin.

Weight2

lb/ft

AreaAin2

Iin4

Sin3

rin. Rb /t

1 1/2 5104080160

1.9001.9001.9001.9001.900

1.7701.6821.6101.5001.338

0.0650.1090.1450.2000.281

0.441 0.721 0.940 1.26 1.68

0.375 0.613 0.799 1.07 1.43

0.158 0.247 0.310 0.391 0.482

0.166 0.260 0.326 0.412 0.508

0.6490.6340.6230.6050.581

14.1 8.2 6.1 4.3 2.9

2 5104080160

2.3752.3752.3752.3752.375

2.2452.1572.0671.9391.687

0.0650.1090.1540.2180.344

0.555 0.913 1.26 1.74 2.58

0.472 0.776 1.07 1.48 2.19

0.315 0.499 0.666 0.868 1.16

0.265 0.420 0.561 0.731 0.980

0.8170.8020.7870.7660.728

17.810.4 7.2 4.9 3.0

2 1/2 5104080160

2.8752.8752.8752.8752.875

2.7092.6352.4692.3232.125

0.0830.1200.2030.2760.375

0.856 1.22 2.00 2.65 3.46

0.728 1.04 1.70 2.25 2.95

0.710 0.987 1.53 1.92 2.35

0.494 0.687 1.06 1.34 1.64

0.9880.9750.9470.9240.894

16.811.5 6.6 4.7 3.3

3 5104080160

3.5003.5003.5003.5003.500

3.3343.2603.0682.9002.624

0.0830.1200.2160.3000.438

1.05 1.50 2.62 3.55 4.95

0.891 1.27 2.23 3.02 4.21

1.30 1.82 3.02 3.89 5.04

0.744 1.04 1.72 2.23 2.88

1.211.201.161.141.09

20.614.1 7.6 5.3 3.5

3 1/2 5104080

4.0004.0004.0004.000

3.8343.7603.5483.364

0.0830.1200.2260.318

1.20 1.72 3.15 4.33

1.02 1.46 2.68 3.68

1.96 2.76 4.79 6.28

0.98 1.38 2.39 3.14

1.391.371.341.31

23.616.2 8.3 5.8

4 5104080120

4.5004.5004.5004.5004.500

4.3344.2604.0263.8263.624

0.0830.1200.2370.3370.438

1.35 1.94 3.73 5.18 6.57

1.15 1.65 3.17 4.41 5.59

2.81 3.96 7.23 9.6111.7

1.25 1.76 3.21 4.27 5.18

1.561.551.511.481.44

26.618.3 9.0 6.2 4.6

160 4.500 3.438 0.531 7.79 6.62 13.3 5.90 1.42 3.75 5

104080120160

5.5635.5635.5635.5635.5635.563

5.3455.2955.0474.8134.5634.313

0.1090.1340.2580.3750.5000.625

2.20 2.69 5.06 7.19 9.3511.4

1.87 2.29 4.30 6.11 7.95 9.70

6.95 8.4315.220.725.730.0

2.50 3.03 5.45 7.43 9.2510.8

1.931.921.881.841.801.76

25.020.310.3 6.9 5.1 4.0

6 5104080120160

6.6256.6256.6256.6256.6256.625

6.4076.3576.0655.7615.5015.187

0.1090.1340.2800.4320.5620.719

2.62 3.21 6.56 9.8812.615.7

2.23 2.73 5.58 8.4010.713.3

11.814.428.140.549.659.0

3.58 4.35 8.5012.215.017.8

2.302.302.252.192.152.10

29.924.211.3 7.2 5.4 4.1

January 2005 VI-33

NominalPipeSize

Schedule No.

OutsideDiameter

ODin.

InsideDiameter

IDin.

Wall Thickness

tin.

Weight2

lb/ft

AreaAin2

Iin4

Sin3

rin.

Rb /t

8 5102030406080100120140160

8.625 8.625 8.625 8.625 8.625 8.625 8.625 8.625 8.625 8.625 8.625

8.407 8.329 8.125 8.071 7.981 7.813 7.625 7.437 7.187 7.001 6.813

0.1090.1480.2500.2770.3220.4060.5000.5940.7190.8120.906

3.43 4.64 7.74 8.54 9.8812.315.017.621.023.425.8

2.92 3.94 6.58 7.26 8.4010.512.815.017.919.922.0

26.435.457.763.472.588.7106121141154166

6.13 8.2113.414.716.820.624.528.232.635.638.5

3.013.002.962.952.942.912.882.852.812.782.75

39.128.616.815.112.910.1 8.1 6.8 5.5 4.8 4.3

10 5 10.750 10.482 0.134 5.26 4.47 63.0 11.7 3.75 39.61020

10.75010.750

10.42010.250

0.1650.250

6.45 9.70

5.49 8.25

76.9114

14.321.2

3.743.71

32.121.0

30 10.750 10.136 0.307 11.8 10.1 137 25.6 3.69 17.0406080100

10.75010.75010.75010.750

10.020 9.750 9.562 9.312

0.3650.5000.5940.719

14.018.922.326.6

11.916.119.022.7

161212245286

29.939.445.653.3

3.673.633.603.56

14.210.3 8.5 7.0

12 5 12.750 12.438 0.156 7.26 6.17 122 19.2 4.45 40.4102030406080

12.75012.75012.75012.75012.75012.750

12.39012.25012.09011.93811.62611.374

0.1800.2500.3300.4060.5620.688

8.3611.515.118.525.330.7

7.11 9.8212.915.721.526.1

140192248300400476

22.030.139.047.162.874.6

4.444.424.394.374.314.27

34.925.018.815.210.8 8.8

1. Sizes are In accordance with ASME Standards B36.10M and B36.19M 2. Weights are for 6061, with a density of 0.098 lb/in3

3. Check availability of shaded sizes with suppliers before using. Additional sizes and shapes may be available from suppliers.4. Tolerances for extruded shapes are given in Aluminum Standards and Data.

TABLE 22 – PIPES (Continued)

VI-34 January 2005

TABLE 23 – SQUARE TUBES

Designation

Depth width d in.

Thickness t

in.Weight

lb/ft

AreaAin2

Axis x-x, y-y

Jin4

Ix , Iyin4

Sx , Sy

in3

rx , ry

in.

RT 1 × 1 × .065 RT 1 × 1 × .095RT 1 × 1 × .125

1.0001.0001.000

0.0650.0950.125

0.2860.4040.515

0.2430.3440.438

0.0356 0.0475 0.0570

0.07120.09490.114

0.3830.3710.361

0.0531 0.0704 0.0837

RT 1.25 × 1.25 × .065 RT 1.25 × 1.25 × .095RT 1.25 × 1.25 × .125

1.2501.2501.250

0.0650.0950.125

0.3620.5160.662

0.3080.4390.563

0.0723 0.0982 0.120

0.1160.1570.192

0.4850.4730.462

0.108 0.146 0.178

RT 1.375 × 1.375 × .125 1.375 0.125 0.735 0.625 0.164 0.239 0.513 0.244

RT 1.5 × 1.5 × .065 RT 1.5 × 1.5 × .078RT 1.5 × 1.5 × .095RT 1.5 × 1.5 × .125RT 1.5 × 1.5 × .250

1.5001.5001.5001.5001.500

0.0650.0780.0950.1250.250

0.4390.5220.6280.8091.47

0.3730.4440.5340.6881.25

0.128 0.150 0.176 0.218 0.339

0.1710.2000.2350.2910.451

0.5860.5810.5750.5640.520

0.192 0.224 0.263 0.325 0.488

RT 1.75 × 1.75 × .125 1.750 0.125 0.956 0.813 0.360 0.411 0.665 0.536

RT 2 × 2 × .095 RT 2 × 2 × .125RT 2 × 2 × .156RT 2 × 2 × .188RT 2 × 2 × .250

2.0002.0002.0002.0002.000

0.0950.1250.1560.1880.250

0.8511.101.351.602.06

0.7240.9381.151.361.75

0.439 0.552 0.657 0.754 0.911

0.4390.5520.6570.7540.911

0.7790.7670.7550.7440.722

0.657 0.824 0.978 1.12 1.34

RT 2.25 × 2.25 × .125 2.250 0.125 1.25 1.06 0.802 0.713 0.869 1.20

RT 2.5 × 2.5 × .125 RT 2.5 × 2.5 × .188RT 2.5 × 2.5 × .250

2.5002.5002.500

0.1250.1880.250

1.402.042.65

1.191.742.25

1.12 1.56 1.92

0.8961.251.54

0.9710.9470.924

1.67 2.32 2.85

RT 2.75 × 2.75 × .125RT 2.75 × 2.75 × .188

2.7502.750

0.1250.188

1.542.27

1.311.93

1.51 2.12

1.101.54

1.071.05

2.26 3.16

RT 3 × 3 × .095 RT 3 × 3 × .125RT 3 × 3 × .188RT 3 × 3 × .250RT 3 × 3 × .375

3.0003.0003.0003.0003.000

0.0950.1250.1880.2500.375

1.301.692.493.234.63

1.101.442.112.753.94

1.55 1.98 2.80 3.49 4.61

1.041.321.872.333.08

1.191.171.151.131.08

2.33 2.97 4.18 5.20 6.78

RT 3.5 × 3.5 × .125 RT 3.5 × 3.5 × .250RT 3.5 × 3.5 × .375

3.5003.5003.500

0.1250.2500.375

1.983.825.51

1.693.254.69

3.21 5.76 7.74

1.833.294.42

1.381.331.28

4.81 8.5811.4

RT 4 × 4 × .125 RT 4 × 4 × .188RT 4 × 4 × .250RT 4 × 4 × .375RT 4 × 4 × .500

4.0004.0004.0004.0004.000

0.1250.1880.2500.3750.500

2.283.374.416.398.23

1.942.873.755.447.00

4.85 6.96 8.8312.014.6

2.433.484.416.027.29

1.581.561.531.491.44

7.2710.413.217.921.4

January 2005 VI-35

TABLE 23 – SQUARE TUBES (Continued)

Designation

Depth width d in.

Thickness t

in.Weight

lb/ft

AreaAin2

Axis x-x, y-y

Jin4

Ix , Iyin4

Sx , Sy

in3

rx , ry

in.

RT 6 × 6 × .125 RT 6 × 6 × .188RT 6 × 6 × .250RT 6 × 6 × .375RT 6 × 6 × .500

6.0006.0006.0006.0006.000

0.1250.1880.2500.3750.500

3.45 5.14 6.76 9.9212.9

2.94 4.37 5.75 8.4411.0

16.9 24.6 31.7 44.7 55.9

5.64 8.2110.614.918.6

2.402.372.352.302.25

25.3 36.9 47.5 66.7 83.2

RT 8 × 8 × .188 RT 8 × 8 × .250RT 8 × 8 × .375RT 8 × 8 × .500

8.0008.0008.0008.000

0.1880.2500.3750.500

6.91 9.1113.517.6

5.87 7.7511.415.0

59.8 77.7111141

14.919.427.835.3

3.193.173.123.07

89.6116166211

1. Users are encouraged to check availability with suppliers. Additional sizes and shapes may be available from suppliers.

2. Tolerances for extruded shapes are given in Aluminum Standards and Data.

VI-36 January 2005

TAB

LE

24

– R

EC

TAN

GU

LA

R T

UB

ES

Des

igna

tion

Dep

thd in

.

Wid

thb in

.

Thi

ckne

sst in.

Wei

ght

lb/ft

Are

aA in

2

Axi

s x-

xA

xis

y-y

J in4

I x in4

Sx

in3

r x in.

I y in4

Sy

in3

r y in.

RT

1 ×

1 1

/2 ×

1/8

RT

1 ×

2 ×

1/8

RT

1 ×

2 1

/2 ×

1/8

RT

1 ×

3 ×

1/8

RT

1 ×

4 ×

1/8

1.00

01.

000

1.00

01.

000

1.00

0

1.50

02.

000

2.50

03.

000

4.00

0

0.12

50.

125

0.12

50.

125

0.12

5

0.6

62 0

.809

0.9

56 1

.10

1.4

0

0.5

63 0

.688

0.8

13 0

.938

1.1

9

0.0

811

0.1

05 0

.129

0.1

53 0

.201

0.1

62 0

.210

0.2

58 0

.307

0.4

03

0.38

00.

391

0.39

90.

404

0.41

2

0.1

59 0

.332

0.5

90 0

.950

2.0

4

0.2

12 0

.332

0.4

72 0

.633

1.0

2

0.53

20.

695

0.85

21.

011.

31

0.1

61 0

.245

0.3

32 0

.422

0.6

05

RT

1 1

/4 ×

2 ×

1/8

RT

1 1

/4 ×

2 1

/2 ×

1/8

RT

1 1

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3 ×

1/8

1.25

01.

250

1.25

0

2.00

02.

500

3.00

0

0.12

50.

125

0.12

5

0.8

82 1

.03

1.1

8

0.7

50 0

.875

1.0

0

0.1

80 0

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0.2

59

0.2

88 0

.351

0.4

15

0.48

90.

501

0.50

9

0.3

87 0

.678

1.0

8

0.3

87 0

.543

0.7

20

0.71

80.

881

1.04

0.3

71 0

.510

0.6

54

RT

1 1

/2 ×

1 3

/4 ×

1/8

RT

1 1

/2 ×

2 ×

1/8

RT

1 1

/2 ×

2 ×

1/4

RT

1 1

/2 ×

2 1

/2 ×

1/8

RT

1 1

/2 ×

3 ×

1/8

RT

1 1

/2 ×

3 ×

3/1

6R

T 1

1/2

× 4

× 1

/8R

T 1

1/2

× 6

× 1

/8

1.50

01.

500

1.50

01.

500

1.50

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500

1.50

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500

1.75

02.

000

2.00

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500

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000

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000

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125

0.25

00.

125

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188

0.12

50.

125

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1.2

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1.5

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0.7

50 0

.813

1.5

0 0

.938

1.0

6 1

.55

1.3

1 1

.81

0.2

48 0

.278

0.4

38 0

.337

0.3

96 0

.533

0.5

15 0

.752

0.3

31 0

.370

0.5

83 0

.449

0.5

28 0

.711

0.6

86 1

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0.57

50.

585

0.54

00.

599

0.61

10.

586

0.62

60.

644

0.3

18 0

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0.7

19 0

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1.2

1 1

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2.5

1 7

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0.3

64 0

.442

0.7

19 0

.613

0.8

06 1

.12

1.2

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.40

0.65

20.

737

0.69

20.

904

1.07

1.04

1.38

1.99

0.4

16 0

.511

0.7

98 0

.711

0.9

19 1

.24

1.3

5 2

.25

RT

1 3

/4 ×

2 ×

1/8

RT

1 3

/4 ×

2 1

/4 ×

1/8

RT

1 3

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2 1

/2 ×

1/8

RT

1 3

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2 3

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1/8

RT

1 3

/4 ×

3 ×

1/8

RT

1 3

/4 ×

3 1

/2 ×

1/8

RT

1 3

/4 ×

4 ×

1/8

RT

1 3

/4 ×

4 1

/2 ×

1/8

RT

1 3

/4 ×

5 ×

1/8

RT

1 3

/4 ×

5 ×

3/1

6R

T 1

3/4

× 6

× 1

/8

1.75

01.

750

1.75

01.

750

1.75

01.

750

1.75

01.

750

1.75

01.

750

1.75

0

2.00

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250

2.50

02.

750

3.00

03.

500

4.00

04.

500

5.00

05.

000

6.00

0

0.12

50.

125

0.12

50.

125

0.12

50.

125

0.12

50.

125

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50.

188

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5

1.0

3 1

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1.1

8 1

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2 1

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1.6

2 1

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1.9

1 2

.82

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1

0.8

75 0

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0 1

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8

0.4

01 0

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0.5

66 0

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0.7

32 0

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0.8

97 1

.23

1.0

6

0.4

58 0

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0.5

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.600

0.6

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.742

0.8

36 0

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3 1

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1.2

1

0.67

70.

687

0.69

60.

703

0.71

00.

721

0.73

00.

737

0.74

30.

717

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3

0.4

97 0

.661

0.8

55 1

.08

1.3

4 1

.96

2.7

4 3

.69

4.8

3 6

.91

7.7

4

0.4

97 0

.588

0.6

84 0

.785

0.8

92 1

.12

1.3

7 1

.64

1.9

3 2

.76

2.5

8

0.75

30.

840

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011.

091.

251.

411.

571.

721.

702.

03

0.6

63 0

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0.9

31 1

.07

1.2

1 1

.50

1.8

0 2

.11

2.4

1 3

.33

3.0

4

January 2005 VI-37

RT

2 ×

3 ×

1/8

RT

2 ×

3 ×

1/4

RT

2 ×

4 ×

1/8

RT

2 ×

4 ×

3/1

6R

T 2

× 4

× 1

/4R

T 2

× 5

× 1

/8R

T 2

× 5

× 3

/16

RT

2 ×

5 ×

1/4

RT

2 ×

6 ×

1/8

RT

2 ×

6 ×

3/1

6R

T 2

× 6

× 1

/4R

T 2

× 8

× 1

/8

2.00

02.

000

2.00

02.

000

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000

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000

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000

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000

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000

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04.

000

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000

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05.

000

6.00

06.

000

6.00

08.

000

0.12

50.

250

0.12

50.

188

0.25

00.

125

0.18

80.

250

0.12

50.

188

0.25

00.

125

1.4

0 2

.65

1.6

9 2

.49

3.2

3 1

.98

2.9

3 3

.82

2.2

8 3

.37

4.4

1 2

.87

1.1

9 2

.25

1.4

4 2

.11

2.7

5 1

.69

2.4

9 3

.25

1.9

4 2

.87

3.7

5 2

.44

0.7

72 1

.30

0.9

92 1

.37

1.6

8 1

.21

1.6

8 2

.07

1.4

3 1

.99

2.4

5 1

.87

0.7

7 1

.30

0.9

92 1

.37

1.6

8 1

.21

1.6

8 2

.07

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3 1

.99

2.4

5 1

.87

0.80

60.

759

0.83

10.

806

0.78

20.

847

0.82

20.

798

0.86

00.

834

0.80

90.

876

1.4

7 2

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2.9

8 4

.23

5.3

1 5

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7.4

5 9

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8.2

811

.915

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0.9

78 1

.70

1.4

9 2

.11

2.6

5 2

.08

2.9

8 3

.78

2.7

6 3

.98

5.0

7 4

.36

1.11

1.06

1.44

1.41

1.39

1.76

1.73

1.70

2.07

2.04

2.01

2.68

1.5

3 2

.57

2.3

0 3

.19

3.9

2 3

.09

4.3

2 5

.32

3.9

1 5

.47

6.7

5 5

.59

RT

2 1

/2 ×

4 ×

1/8

RT

2 1

/2 ×

5 ×

1/8

2.50

02.

500

4.00

05.

000

0.12

50.

125

1.8

4 2

.13

1.5

6 1

.81

1.6

5 2

.00

1.3

2 1

.60

1.03

1.05

3.4

5 5

.95

1.7

2 2

.38

1.48

1.81

3.3

9 4

.62

RT

3 ×

4 ×

1/8

RT

3 ×

4 ×

3/1

6R

T 3

× 4

× 1

/4R

T 3

× 4

× 3

/8R

T 3

× 4

× 1

/2R

T 3

× 5

× 1

/8R

T 3

× 5

× 3

/16

RT

3 ×

5 ×

1/4

RT

3 ×

6 ×

1/8

RT

3 ×

6 ×

3/1

6R

T 3

× 8

× 1

/4

3.00

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000

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03.

000

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03.

000

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000

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03.

000

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0

4.00

04.

000

4.00

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000

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05.

000

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000

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06.

000

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0

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188

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125

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80.

250

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50.

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7 3

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7

1.6

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0 1

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9 3

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5

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4 5

.92

7.0

0 3

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9 5

.39

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3 5

.03

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3

1.6

7 2

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2.9

6 3

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4.6

7 2

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2.8

6 3

.59

2.3

6 3

.35

5.4

9

1.22

1.19

1.17

1.12

1.08

1.25

1.22

1.20

1.27

1.25

1.25

3.9

2 5

.59

7.0

7 9

.56

11.5

6.6

9 9

.63

12.3

10.4

15.1

40.1

1.9

6 2

.80

3.5

3 4

.78

5.7

5 2

.68

3.8

5 4

.91

3.4

8 5

.03

10.0

1.52

1.50

1.47

1.43

1.38

1.86

1.83

1.81

2.18

2.16

2.76

4.6

0 6

.52

8.1

810

.912

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.34

9.0

311

.4 8

.15

11.6

21.6

RT

4 ×

5 ×

1/4

RT

4 ×

6 ×

1/8

RT

4 ×

6 ×

3/1

6R

T 4

× 6

× 1

/4R

T 4

× 6

× 1

/2R

T 4

× 8

× 3

/16

RT

4 ×

8 ×

1/4

RT

4 ×

8 ×

3/8

RT

4 ×

8 ×

1/2

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

04.

000

4.00

0

5.00

06.

000

6.00

06.

000

6.00

08.

000

8.00

08.

000

8.00

0

0.25

00.

125

0.18

80.

250

0.50

00.

188

0.25

00.

375

0.50

0

5.0

0 2

.87

4.2

6 5

.59

10.6

5.1

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.76

9.9

212

.9

4.2

5 2

.44

3.6

2 4

.75

9.0

0 4

.37

5.7

5 8

.44

11.0

10.6

6.7

3 9

.69

12.3

20.8

12.4

15.9

21.9

26.9

5.2

9 3

.37

4.8

5 6

.17

10.4

6.2

1 7

.93

11.0

13.5

1.58

1.66

1.64

1.61

1.52

1.69

1.66

1.61

1.56

15.1

12.6

18.3

23.5

40.8

36.8

47.6

67.5

84.9

6.0

4 4

.20

6.0

9 7

.82

13.6

9.2

111

.916

.921

.2

1.88

2.27

2.25

2.22

2.13

2.90

2.88

2.83

2.78

18.7

13.3

19.2

24.5

41.2

28.7

36.7

50.9

62.6

RT

5 ×

8 ×

3/8

5.00

08.

000

0.37

510

.8 9

.19

37.0

14.8

2.01

78.4

19.6

2.92

76.1

1. U

sers

are

enc

oura

ged

to c

heck

ava

ilabi

lity

with

sup

plie

rs.

Add

ition

al s

izes

and

sha

pes

may

be

avai

labl

e fr

om s

uppl

iers

. 2.

Tol

eran

ces

for

extr

uded

sha

pes

are

give

n in

Alu

min

um S

tand

ard

s an

d D

ata .

VI-38 January 2005

TABLE 25 – ROOFING AND SIDING – DIMENSIONS AND WEIGHTS

January 2005 VI-39

TABLE 26 – ROOFING AND SIDING – SECTION PROPERTIES

VI-40 January 2005

TABLE 27 – DECIMAL EQUIVALENTS IN INCHES OF SHEET METAL AND WIRE GAUGES

January 2005 VI-41

TABLE 28 – GEOMETRIC SHAPES

VI-42 January 2005

TABLE 28 – GEOMETRIC SHAPES (Continued)

January 2005 VI-43


VI-44 January 2005


x = b2 + ct _______

2(b + c) y = d

2 + at _______ 2(b + c)

Ix = t(d – y)3 + by3 – a(y – t)3

___________________ 3 Iy =

t(b – x)3 + dx3 – c(x – t)3

___________________ 3

K = abcdt _______ 4(b + c)

α = (1/2)tan-1 ( 2K _____ Iy – Ix

)

Iz = Ix sin2 α + Iy cos2 α + K sin 2α

Ix + Iy = Iw + Iz

Iw = Ix cos2 α + Iy sin2 α – K sin 2α

xo = x – t/2 yo = y – t/2

wo = yo sin α + xo cos α zo = yo cos α – xo sin α

b' = d – t/2 d' = b – t/2

C1 = x 2 o __ 2 [ y 2 o – ( yo – b' ) 2 ] +

( y 4 o – ( yo – b' ) 4 ) _____________

4 +

yo __

3 [ x 3 o – ( xo – d' ) 3 ] + y 3 o d'

C2 = y 2 o __ 2 [ x 2 o – ( xo – d' ) 2 ] +

( x 4 o – ( xo – d' ) 4 ) _____________

4 +

xo __ 3 [ y 3 o – ( yo – b' ) 3 ] + x 3 o b'

βw = t(C1 cos α – C2 sin α)

__________________ Iw

– 2zo

YZ

X

WY

Z

X

W

x

y

t a

b

t

dc

ANGLE

z - z axis is axis of minimum I


PART VII

Design Aids



January 2005 VII-3

VIIDesign Aids

TABLE OF CONTENTS

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5

Compressive Strength Curves

Figure 1-1 Section 7 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1-2 Section 7 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1-3 Section 8 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 1-4 Section 8 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 1-5 Section 8.1 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1-6 Section 8.1 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1-7 Section 9 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 1-8 Section 9 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 1-9 Section 10 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1-10 Section 10 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1-11 Section 11 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 1-12 Section 11 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 1-13 Section 12 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1-14 Section 12 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1-15 Section 13 All Tempers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 1-16 Section 14 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1-17 Section 14 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1-18 Section 15 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 1-19 Section 15 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 1-20 Section 16 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1-21 Section 16 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1-22 Section 17 All Tempers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 1-23 Section 18 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1-24 Section 18 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1-25 Section 19 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1-26 Section 19 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1-27 Section 20 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1-28 Section 20 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 1-29 Section 21 Tempers O, H, T1, T2, T3, T4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1-30 Section 21 Tempers T5, T6, T7, T8, T9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

Allowable Stress Tables for Building and Similar Type Structures

Table 2-1 Buckling Constants for Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2-1W Buckling Constants for Welded Aluminum Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 2-2 1100-H14 Sheet, Plate, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 2-3 3003-H14 Sheet, Plate, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 2-4 3003-H16 Sheet, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 2-5 Alclad 3004-H34 Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 2-6 5005-H14 Sheet and Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 2-7 5005-H34 Sheet and Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 2-8 5050-H34 Sheet, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 2-9 5052-H32 Sheet, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 2-10 5052-H34 Sheet, Plate, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 2-11 5083-H111 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 2-12 5083-H116, -H32, -H321 Sheet and Plate (0.188 to 1.500 in. thick) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 2-13 5086-H34 Sheet and Plate, Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

VII-4 January 2005

2-14 5086-H111 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 2-15 5086-H116, -H32 Sheet and Plate, 5086-H32 Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 2-16 5454-H111 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 2-17 5454-H32 Sheet and Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58 2-18 5454-H34 Sheet and Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60 2-19 5456-H116, -H32, -H321 Sheet and Plate (0.188 to 1.250 in. thick) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62 2-20 6005-T5 Extrusions (up through 1.000 in. thick), 6105-T5 Extrusions (up through 0.500 in. thick) . . . . . . . . 64 2-21 6061-T6 Sheet, -T651 Plate (up through 4.000 in. thick), 6061-T6, -T651 Rolled or

Cold Finished Rod and Bar, 6061-T6 Drawn Tube . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 2-22 6061-T6, -T6510, -T6511 Extrusions, 6061-T6 Standard Structural Shapes, Pipe,

6351-T5 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68 2-23 6063-T5 Extrusions (up through 0.500 in. thick), 6063-T52 Extrusions (up through 1.000 in. thick) . . . . . . . 70 2-24 6063-T6 Extrusions and Pipe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72 2-25 6351-T6 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 2-26 7005-T53 Extrusions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

Bending

Table 3-1 Recommended Minimum Bend Radii for 90o Cold Bends of Sheet and Plate . . . . . . . . . . . . . . . . . . . . . . . . . . 78 3-2 Recommended Minimum Inside Radii for 180o Cold Bends, Wire and Rod . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 3-3 Sheet Thickness for 180o Cold Bending (Metal to Metal) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 3-4 Developed Length of Material for 90o Bends . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

Allowable Load Tables

Table 4-1 Allowable Uniform Beam Loads Aluminum Association Standard Channels, 6061-T6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 4-2 Allowable Uniform Beam Loads Aluminum Association Standard I-Beams, 6061-T6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84 4-3 Allowable Loads on Aluminum Tread Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85 4-4 Maximum Recommended Spans – Commercial Corrugated and V-Beam Roofing and Siding . . . . . . . . . . . . . 86 4-5 Maximum Recommended Spans – Commercial Ribbed Siding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88

Fasteners

Table 5-1 Load Required to Produce Failure of a Solid Rivet in Single Shear – lb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89 5-2 Reduction in Shear Strength of Rivets Resulting From Their Use in Thin Sheets and Shapes . . . . . . . . . . . . . 89 5-3 Tensile and Single-Shear Loads for 2024-T4 and 7075-T73 Machine Screws . . . . . . . . . . . . . . . . . . . . . . . . . 90 5-4 Single-Shear Loads for 2024-T4 and 7075-T73 Sheet Metal Screws . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91 5-5 Tensile and Single-Shear Strengths for 2024-T4 and 7075-T73 Bolts and Cap Screws . . . . . . . . . . . . . . . . . . 91 5-6 Rivet Head Styles and Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 5-7 Military Specifications for Aluminum Alloy Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92 5-8 Recommended Hole Sizes for Cold-Driven Solid Rivets with Corresponding Shear and Bearing Areas . . . . . 93 5-9 Recommended Hole Sizes for Hot-Driven Solid Rivets with Corresponding Shear and Bearing Areas . . . . . . 94 5-10 Approximate Driving Pressures with Squeeze Riveter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 5-11 Smallest Sizes of Pneumatic Hammers Considered Satisfactory for Driving Aluminum Alloy Rivets . . . . . . . 95 5-12 Length of Rivets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96 5-13 Flat Driven Heads - Maximum Rivet Grips . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97 5-14 Recommended Hole Sizes for 2024-T4 and 7075-T73 Sheet Metal Screws . . . . . . . . . . . . . . . . . . . . . . . . . . . 98 5-15 Dimensions for Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99 5-16 Bolt Nuts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 5-17 Machine Screw Nuts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101 5-18 Regular Spring Lock Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102 5-19 Plain Flat Washers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102 5-20 Internal Thread Stripping Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103

Beam Formulas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104

January 2005 VII-5

INTRODUCTION

This part includes information in the form of graphs and tables intended to aid the structural designer. Curves of ultimate strength in compression (Fc) divided by compressive yield strength (Fcy) for each of the Part I Sections 3.4.7 through 3.4.21 are given. They are independent of whether allowable stress design or load and resistance factor design is used. These are followed by allowable stresses determined in accordance with Part IA for Sections 3.4.1 through 3.4.21 for a number of common alloys for building type structures. Subsequently, allowable load tables for Aluminum Association standard channels and I beams, tread plate, and roofing and siding are given, also calculated by the allowable stress design Specification in Part IA.

For the fabrication of sheet and plate and wire and rod, minimum bend radii are furnished.The information given on the strength of some aluminum fasteners, including bolts, rivets, screws, nuts, and washers is based

both on specified shear strengths and test results. Dimensional information is also provided.Lastly, beam formulas for numerous cases are given.

January 2005 VII-7

Figures 1-1 and 1-2COMPRESSION IN COLUMNS

VII-8 January 2005

Figures 1-3 and 1-4COMPRESSION IN ELEMENTS OF COLUMNS: FLAT ELEMENTS SUPPORTED ON ONE EDGE

January 2005 VII-9

Figures 1-5 and 1-6COMPRESSION IN ELEMENTS OF COLUMNS: FLAT ELEMENTS SUPPORTED ON ONE EDGE

VII-10 January 2005

Figures 1-7 and 1-8COMPRESSION IN ELEMENTS OF COLUMNS:

FLAT ELEMENTS SUPPORTED ON BOTH EDGES

January 2005 VII-11

Figures 1-9 and 1-10COMPRESSION IN ELEMENTS OF COLUMNS:

CURVED ELEMENTS SUPPORTED ON BOTH EDGES

VII-12 January 2005

Figures 1-11 and 1-12COMPRESSION IN BEAMS:

SINGLE WEB SHAPES BENT ABOUT STRONG AXIS

January 2005 VII-13

Figures 1-13 and 1-14COMPRESSION IN BEAMS: ROUND OR OVAL TUBES

VII-14 January 2005

Figure 1-15COMPRESSION IN BEAMS:

SOLID RECTANGULAR SHAPES

January 2005 VII-15

Figures 1-16 and 1-17COMPRESSION IN BEAMS:

TUBULAR SHAPES

VII-16 January 2005

Figures 1-18 and 1-19COMPRESSION IN ELEMENTS OF BEAMS:

FLAT ELEMENTS SUPPORTED ON ONE EDGE

January 2005 VII-17



VII-18 January 2005

Figure 1-22COMPRESSION IN ELEMENTS OF BEAMS:

FLAT ELEMENTS WITH COMPRESSION EDGE FREE, TENSION EDGE SUPPORTED

January 2005 VII-19



VII-20 January 2005


FLAT ELEMENTS WITH HORIZONTAL STIFFENER, BOTH EDGES SUPPORTED

January 2005 VII-21

Figures 1-27 and 1-28SHEAR IN WEBS:

UNSTIFFENED FLAT WEBS

VII-22 January 2005

Figures 1-29 and 1-30SHEAR IN WEBS:

STIFFENED FLAT WEBS

January 2005 VII-23

Tab

le 2

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r

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r

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617

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311

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2014

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52 52 55 55

79.1

77.7

69.0

70.5

0.67

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656

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90.

567

48 49 52 51

74.3

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92.

699

94 95 105

103

119.

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278

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53 52 53

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98 94 98

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40 39 42

42.6

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H12

H14

H16

H18

H12

H14

H16

H18

She

et &

Pla

teS

heet

& P

late

She

etS

heet

Dra

wn

Tube

Dra

wn

Tube

Dra

wn

Tube

Dra

wn

Tube

11.0

15.7

20.4

22.8

12.2

18.0

21.6

24.0

0.04

40.

075

0.11

20.

133

0.05

20.

093

0.12

30.

144

165

138

121

114

157

129

118

112

12.8

18.4

24.2

27.1

14.2

21.3

25.7

28.6

0.05

60.

096

0.14

50.

172

0.06

50.

120

0.15

90.

187

153

127

111

105

145

119

108

102

12.7

18.1

23.5

26.3

14.1

20.8

24.9

27.7

0.37

20.

594

0.84

30.

977

0.42

40.

715

0.90

91.

046

573

416

327

295

523

366

310

282

17.0

24.5

32.2

36.1

18.8

28.3

34.1

38.1

0.08

50.

147

0.22

20.

264

0.10

00.

183

0.24

30.

286

133

111 96 91 126

103 94 89

19.1

27.1

35.3

39.4

21.1

31.2

37.4

41.5

0.87

51.

397

1.98

42.

298

0.99

91.

683

2.14

02.

461

160

127

106 99 150

115

102 96

9.1

13.2

16.6

19.2 9.1

13.2

16.6

19.2

0.03

30.

058

0.08

30.

103

0.03

30.

058

0.08

30.

103

182

151

134

125

182

151

134

125

Alc

lad

3003

Alc

lad

3003

Alc

lad

3003

Alc

lad

3003

Alc

lad

3003

Alc

lad

3003

H12

H14

H16

H18

H14

H18

She

et &

Pla

teS

heet

& P

late

She

etS

heet

Dra

wn

Tube

Dra

wn

Tube

9.9

14.5

19.2

21.6

16.8

22.8

0.03

80.

067

0.10

30.

123

0.08

40.

133

174

144

125

118

133

114

11.5

17.0

22.8

25.7

19.9

27.1

0.04

70.

086

0.13

20.

159

0.10

80.

172

162

133

115

108

123

105

11.4

16.7

22.2

24.9

19.4

26.3

0.32

10.

536

0.77

90.

909

0.65

40.

977

635

446

345

310

389

295

15.2

22.6

30.2

34.1

26.4

36.1

0.07

20.

131

0.20

20.

243

0.16

50.

264

140

115

100 94 107 91

17.1

25.1

33.2

37.4

29.2

39.4

0.75

61.

260

1.83

22.

140

1.53

82.

298

172

133

111

102

121 99

8.2

12.4

15.8

18.4

12.4

18.4

0.02

90.

053

0.07

60.

096

0.05

30.

096

190

156

138

128

156

128

3004

3004

3004

3004

3004

3004

H32

H34

H36

H38

H34

H36

She

et &

Pla

teS

heet

& P

late

She

et

She

et

Dra

wn

Tube

Dra

wn

Tube

20.4

25.3

29.0

33.9

27.7

31.4

0.11

20.

155

0.19

00.

241

0.17

80.

215

121

109

102 94 104 98

24.2

30.1

34.6

40.7

33.1

37.7

0.14

50.

201

0.24

80.

317

0.23

20.

282

111

100 93 86 95 89

23.5

29.0

33.2

38.8

31.8

36.0

0.84

31.

116

1.33

41.

643

1.26

01.

486

327

269

238

206

247

220

32.2

40.0

46.1

54.2

44.1

50.1

0.22

20.

309

0.38

10.

487

0.35

60.

433

96 86 81 74 82 77

35.3

43.6

49.8

58.2

47.7

54.0

1.98

42.

626

3.14

03.

865

2.96

63.

497

106 92 85 76 87 80

16.6

20.1

22.8

25.4

20.1

22.8

0.08

30.

110

0.13

20.

156

0.11

00.

132

134

122

115

108

122

115

Alc

lad

3004

Alc

lad

3004

Alc

lad

3004

Alc

lad

3004

Alc

lad

3004

Alc

lad

3004

H32

H34

H36

H38

H13

1,H

241,

H34

1H

151,

H26

1,H

361

She

etS

heet

She

etS

heet

She

etS

heet

19.2

24.0

27.7

32.7

25.3

32.7

0.10

30.

144

0.17

80.

228

0.15

50.

228

125

112

104 96 109 96

22.8

28.6

33.1

39.2

30.1

39.2

0.13

20.

187

0.23

20.

299

0.20

10.

299

115

102 95 87 100 87

22.2

27.7

31.8

37.4

29.0

37.4

0.77

91.

046

1.26

01.

564

1.11

61.

564

345

282

247

213

269

213

30.2

38.1

44.1

52.2

40.0

52.2

0.20

20.

286

0.35

60.

459

0.30

90.

459

100 89 82 76 86 76

33.2

41.5

47.7

56.1

43.6

56.1

1.83

22.

461

2.96

63.

680

2.62

63.

680

111 96 87 78 92 78

15.8

19.2

21.9

24.5

21.0

24.5

0.07

60.

103

0.12

50.

148

0.11

70.

148

138

125

117

110

119

110

3005

3005

H25

H28

She

etS

heet

22.8

29.0

0.13

30.

190

114

102

27.1

34.6

0.17

20.

248

105 93

26.3

33.2

0.97

71.

334

295

238

36.1

46.1

0.26

40.

381

91 8139

.449

.82.

298

3.14

099 85

17.5

21.9

0.08

90.

125

131

117

3105

H25

She

et19

.20.

103

125

22.8

0.13

211

522

.20.

779

345

30.2

0.20

210

033

.21.

832

111

14.9

0.07

014

2

VII-24 January 2005

Allo

yTe

mpe

rP

rodu

ct*

Bc

ksi

Dc

ksi

Cc

Bp

ksi

Dp

ksi

Cp

Bt

ksi

Dt

ksi

Ct

Bb

r

ksi

Db

r

ksi

Cb

rB

tb

ksi

Dtb

ksi

Ctb

Bs

ksi

Ds

ksi

Cs

5005

5005

5005

5005

5005

5005

H12

H14

H16

H32

H34

H36

She

et &

Pla

teS

heet

& P

late

She

et

She

et &

Pla

teS

heet

& P

late

She

et

14.5

16.8

20.4

12.2

15.7

18.0

0.06

70.

084

0.11

20.

052

0.07

50.

093

144

133

121

157

138

129

17.0

19.9

24.2

14.2

18.4

21.3

0.08

60.

108

0.14

50.

065

0.09

60.

120

133

123

111

145

127

119

16.7

19.4

23.5

14.1

18.1

20.8

0.53

60.

654

0.84

30.

424

0.59

40.

715

446

389

327

523

416

366

22.6

26.4

32.2

18.8

24.5

28.3

0.13

10.

165

0.22

20.

100

0.14

70.

183

115

107 96 126

111

103

25.1

29.2

35.3

21.1

27.1

31.2

1.26

01.

538

1.98

40.

999

1.39

71.

683

133

121

106

150

127

115

10.7

13.2

15.8 9.1

11.5

14.1

0.04

30.

058

0.07

60.

033

0.04

80.

064

167

151

138

182

161

146

5050

5050

5050

5050

H32

H34

H32

H34

She

etS

heet

Dra

wn

Tube

Dra

wn

Tube

15.7

20.4

16.8

21.6

0.07

50.

112

0.08

40.

123

138

121

133

118

18.4

24.2

19.9

25.7

0.09

60.

145

0.10

80.

159

127

111

123

108

18.1

23.5

19.4

24.9

0.59

40.

843

0.65

40.

909

416

327

389

310

24.5

32.2

26.4

34.1

0.14

70.

222

0.16

50.

243

111 96 107 94

27.1

35.3

29.2

37.4

1.39

71.

984

1.53

82.

140

127

106

121

102

12.4

15.8

12.4

15.8

0.05

30.

076

0.05

30.

076

156

138

156

138

5052

5052

5052

5052

O H32

H34

H36

She

et &

Pla

teS

heet

& P

late

Dra

wn

Tube

She

et

10.4

24.0

27.7

30.2

0.04

10.

143

0.17

70.

201

170

112

104

100

12.1

28.6

33.1

36.1

0.05

10.

186

0.23

10.

263

158

103 96 91

12.1

27.7

31.8

34.6

0.34

51.

042

1.25

61.

405

608

284

250

231

16.1

38.1

44.1

48.1

0.07

80.

285

0.35

50.

405

137 89 83 79

18.1

41.5

47.7

51.9

0.81

22.

453

2.95

63.

306

167 96 88 83

7.0

18.4

21.0

23.7

0.02

30.

095

0.11

70.

139

207

128

120

113

5083

5083

5083

5083

5083

O H11

1O H

116,

H32

1H

116,

H32

1

Ext

rusi

ons

Ext

rusi

ons

She

et &

Pla

teS

heet

& P

late

(1.

500)

Pla

te (

3.00

0)

18.0

24.0

20.4

30.2

27.7

0.09

20.

142

0.11

10.

199

0.17

5

131

113

123

101

105

21.3

28.6

24.2

36.1

33.1

0.11

80.

184

0.14

30.

261

0.22

9

120

104

113 92 96

20.8

27.7

23.5

34.6

31.8

0.70

81.

036

0.83

51.

396

1.24

8

376

289

336

235

254

28.3

38.1

32.2

48.1

44.1

0.18

10.

282

0.21

90.

401

0.35

1

104 90 98 80 84

31.2

41.5

35.3

51.9

47.7

1.66

72.

437

1.96

53.

285

2.93

7

118 97 108 84 89

12.4

19.2

14.1

25.4

23.7

0.05

20.

101

0.06

30.

154

0.13

8

158

127

148

110

114

5086

5086

5086

5086

5086

5086

5086

5086

O H11

1H

112

H11

2H

112

H11

6H

32

H34

Ext

rusi

ons,

She

et &

P

late

Ext

rusi

ons

Pla

te (

0.50

0)P

late

(1.

000)

Pla

te (

3.00

0)S

heet

& P

late

She

et &

Pla

te, D

raw

n Tu

beS

heet

& P

late

, Dra

wn

Tube

15.7

20.4

19.2

18.0

16.8

30.2

30.2

37.7

0.07

4

0.11

10.

101

0.09

20.

083

0.19

90.

199

0.27

8

140

123

127

131

135

101

101 90

18.4

24.2

22.8

21.3

19.9

36.1

36.1

45.4

0.09

5

0.14

30.

130

0.11

80.

106

0.26

10.

261

0.36

7

129

113

116

120

125 92 92 82

18.1

23.5

22.2

20.8

19.4

34.6

34.6

43.0

0.58

8

0.83

50.

771

0.70

80.

647

1.39

61.

396

1.86

7

427

336

355

376

400

235

235

192

24.5

32.2

30.2

28.3

26.4

48.1

48.1

60.5

0.14

5

0.21

90.

199

0.18

10.

163

0.40

10.

401

0.56

5

112 98 101

104

108 80 80 71

27.1

35.3

33.2

31.2

29.2

51.9

51.9

64.6

1.38

4

1.96

51.

814

1.66

71.

523

3.28

53.

285

4.39

4

129

108

113

118

123 84 84 73

10.7

16.6

14.1

12.4

10.7

22.8

22.8

28.2

0.04

2

0.08

10.

063

0.05

20.

042

0.13

00.

130

0.18

0

170

136

148

158

170

116

116

105

5154

H38

She

et39

.00.

294

8846

.90.

388

8144

.41.

956

184

62.6

0.59

770

66.7

4.60

271

29.1

0.18

910

2

Tab

le 2

-1B

UC

KL

ING

CO

NS

TAN

TS

FO

R A

LU

MIN

UM

AL

LOY

S (

Co

nti

nu

ed)

January 2005 VII-25

5454

5454

5454

5454

5454

O H11

1H

112

H32

H34

She

et &

Pla

te,

Ext

rusi

ons

Ext

rusi

ons

Ext

rusi

ons

She

et &

Pla

teS

heet

& P

late

13.3

18.0

14.5

27.7

31.4

0.05

8

0.09

20.

066

0.17

50.

212

152

131

146

105 99

15.6

21.3

17.0

33.1

37.7

0.07

4

0.11

80.

084

0.22

90.

278

140

120

135 96 90

15.4

20.8

16.7

31.8

36.0

0.47

4

0.70

80.

530

1.24

81.

472

495

376

458

254

227

20.7

28.3

22.6

44.1

50.1

0.11

3

0.18

10.

129

0.35

10.

426

122

104

117 84 78

23.1

31.2

25.1

47.7

54.0

1.11

6

1.66

71.

248

2.93

73.

463

144

118

136 89 82

9.1

14.9 9.1

21.0

23.7

0.03

3

0.06

90.

033

0.11

50.

138

184

144

184

121

114

5456

5456

5456

5456

O H11

6, H

321

H11

6, H

321

H11

6, H

321

She

et &

Pla

teS

heet

& P

late

(1.

250)

Pla

te (

1.50

0)P

late

(3.

000)

21.6

31.4

29.0

29.0

0.12

10.

212

0.18

70.

187

119 99 103

103

25.7

37.7

34.6

34.6

0.15

60.

278

0.24

50.

245

110 90 94 94

24.9

36.0

33.2

33.2

0.90

01.

472

1.32

11.

321

499

227

244

244

34.1

50.1

46.1

46.1

0.23

90.

426

0.37

60.

376

95 78 82 82

37.4

54.0

49.8

49.8

2.11

93.

463

3.11

03.

110

104 82 86 86

14.9

27.3

25.4

23.7

0.06

90.

171

0.15

40.

138

144

106

110

114

6005

6105

T5

T5

Ext

rusi

ons

Ext

rusi

ons

39.4

39.4

0.24

60.

246

66 6645

.045

.00.

301

0.30

161 61

43.2

43.2

1.55

81.

558

141

141

66.8

66.8

0.66

50.

665

67 6764

.864

.84.

458

4.45

855 55

26.1

26.1

0.13

30.

133

81 81

6061

6061

6061

6061

6061

T6,

T65

1T

6, T

6510

, T65

11T

6, T

651

T6

T6

She

et &

Pla

teE

xtru

sion

sC

old-

Fin

ishe

d R

od &

Bar

Dra

wn

Tube

Pip

e

39.4

39.4

39.4

39.4

39.4

0.24

60.

246

0.24

60.

246

0.24

6

66 66 66 66 66

45.0

45.0

45.0

45.0

45.0

0.30

10.

301

0.30

10.

301

0.30

1

61 61 61 61 61

43.2

43.2

43.2

43.2

43.2

1.55

81.

558

1.55

81.

558

1.55

8

141

141

141

141

141

66.8

66.8

66.8

66.8

66.8

0.66

50.

665

0.66

50.

665

0.66

5

67 67 67 67 67

64.8

64.8

64.8

64.8

64.8

4.45

84.

458

4.45

84.

458

4.45

8

55 55 55 55 55

26.1

26.1

26.1

26.1

26.1

0.13

30.

133

0.13

30.

133

0.13

3

81 81 81 81 81

6063

6063

6063

6063

T5

T5

T52

T6

Ext

rusi

ons

(0.5

00)

Ext

rusi

ons

(1.0

00)

Ext

rusi

ons

Ext

rusi

ons

& P

ipe

17.3

16.2

17.3

27.6

0.07

20.

065

0.07

20.

145

99 102 99 78

19.5

18.2

19.5

31.4

0.08

60.

078

0.08

60.

175

93 96 93 74

19.2

18.0

19.2

30.5

0.52

90.

484

0.52

90.

978

275

290

275

189

28.3

26.4

28.3

46.1

0.18

30.

165

0.18

30.

381

103

107

103 81

28.8

26.9

28.8

45.7

1.51

31.

384

1.51

32.

800

95 99 95 70

11.3

10.6

11.3

18.2

0.03

80.

034

0.03

80.

077

122

127

122 97

6066

T6,

T65

10, T

6511

Ext

rusi

ons

51.4

0.36

657

59.0

0.45

154

56.1

2.20

711

288

.21.

010

5884

.16.

315

4734

.30.

199

70

6070

T6,

T62

Ext

rusi

ons

51.4

0.36

657

59.0

0.45

154

56.1

2.20

711

288

.21.

010

5884

.16.

315

4734

.30.

199

70

6351

6351

T5

T6

Ext

rusi

ons

Ext

rusi

ons

39.4

41.7

0.24

60.

268

66 6445

.047

.80.

301

0.32

961 60

43.2

45.8

1.55

81.

682

141

134

66.8

71.0

0.66

50.

729

67 6564

.868

.64.

458

4.81

555 53

26.1

27.7

0.13

30.

145

81 78

6463

T6

Ext

rusi

ons

27.6

0.14

578

31.4

0.17

574

30.5

0.97

818

946

.10.

381

8145

.72.

800

7018

.20.

077

97

7005

T53

Ext

rusi

ons

48.9

0.33

460

56.2

0.41

156

53.5

2.04

512

183

.90.

918

6180

.25.

853

4933

.40.

189

73

* m

axim

um th

ickn

ess

(in.)

sho

wn

in p

aren

thes

es

VII-26 January 2005

Tab

le 2

-1W

BU

CK

LIN

G C

ON

STA

NT

S F

OR

WE

LD

ED

AL

UM

INU

M A

LLO

YS

Allo

yTe

mpe

rP

rodu

ct (

1)B

c

ksi

Dc

ksi

Cc

Bp

ksi

Dp

ksi

Cp

Bt

ksi

Dt

ksi

Ct

Bb

r

ksi

Db

r

ksi

Cb

rB

tb

ksi

Dtb

ksi

Ctb

Bs

ksi

Ds

ksi

Cs

1100

-H

12, H

14A

ll3.

70.

009

284

4.2

0.01

026

74.

30.

087

1375

5.5

0.01

623

26.

40.

204

332

2.4

0.00

535

1

3003

-A

lcla

d 30

03-

H12

, H14

, H16

, H18

H12

, H14

, H16

, H18

All

All

5.4

4.8

0.01

50.

013

236

250

6.1

5.5

0.01

80.

016

221

234

6.2

5.5

0.14

20.

123

1060

1145

8.1

7.2

0.02

80.

024

192

203

9.3

8.3

0.33

40.

289

259

279

3.5

3.2

0.00

80.

007

290

307

3004

-A

lcla

d 30

04-

H32

, H34

, H36

, H38

H32

, H34

, H36

, H38

All

All

9.3

8.7

0.03

40.

031

180

185

10.8

10.1

0.04

30.

039

167

172

10.7

10.1

0.29

70.

273

772

795

14.3

13.4

0.06

60.

060

145

150

16.1

15.1

0.69

80.

642

179

187

6.3

5.9

0.01

90.

017

219

226

3005

-H

25S

heet

7.0

0.02

320

68.

10.

028

192

8.1

0.20

487

510

.70.

043

167

12.2

0.48

121

64.

70.

012

253

5005

-H

12, H

14, H

32, H

34A

ll5.

40.

015

236

6.1

0.01

822

16.

20.

142

1065

8.1

0.02

819

29.

30.

334

259

3.5

0.00

829

0

5050

-H

32, H

34A

ll6.

50.

020

215

7.4

0.02

520

17.

50.

183

930

9.8

0.03

817

511

.20.

430

228

4.3

0.01

126

4

5052

-O

, H32

, H34

All

10.4

0.04

117

012

.10.

051

158

12.1

0.34

573

216

.10.

078

137

18.1

0.81

216

77.

00.

023

207

5083

-50

83-

5083

-

O, H

111

O, H

116,

H32

1

O, H

116,

H32

1

Ext

rusi

ons

She

et &

Pla

te

(1.5

00)

Pla

te (

3.00

0)

16.8

20.4

19.2

0.08

30.

111

0.10

1

135

123

127

19.9

24.2

22.8

0.10

60.

143

0.13

0

125

113

116

19.4

23.5

22.2

0.64

70.

835

0.77

1

573

515

532

26.4

32.2

30.2

0.16

30.

219

0.19

9

108 98 101

29.2

35.3

33.2

1.52

31.

965

1.81

4

123

108

113

12.4

14.1

13.2

0.05

20.

063

0.05

8

158

148

153

5086

-50

86-

5086

-

O, H

111

H11

2O

, H32

, H34

, H11

6

Ext

rusi

ons

Pla

te (

2.00

0)S

heet

& P

late

14.5

15.7

15.7

0.06

60.

074

0.07

4

146

140

140

17.0

18.4

18.4

0.08

40.

095

0.09

5

135

129

129

16.7

18.1

18.1

0.53

00.

588

0.58

8

622

596

596

22.6

24.5

24.5

0.12

90.

145

0.14

5

117

112

112

25.1

27.1

27.1

1.24

81.

384

1.38

4

136

129

129

10.7

10.7

10.7

0.04

20.

042

0.04

2

170

170

170

5154

-H

38S

heet

12.2

0.05

115

814

.20.

065

147

14.1

0.42

268

018

.80.

099

127

21.1

0.99

215

28.

20.

029

192

5454

-54

54-

5454

-

O, H

111

H11

2O

, H32

, H34

Ext

rusi

ons

Ext

rusi

ons

She

et &

Pla

te

12.2

13.3

13.3

0.05

10.

058

0.05

8

159

152

152

14.2

15.6

15.6

0.06

40.

074

0.07

4

147

140

140

14.1

15.4

15.4

0.42

00.

474

0.47

4

683

651

651

18.8

20.7

20.7

0.09

80.

113

0.11

3

128

122

122

21.1

23.1

23.1

0.98

91.

116

1.11

6

153

144

144

9.1

9.1

9.1

0.03

30.

033

0.03

3

184

184

184

5456

-

5456

-

O, H

116,

H32

1

O, H

116,

H32

1

She

et &

Pla

te

(1.5

00)

Pla

te (

3.00

0)

20.4

19.2

0.11

1

0.10

1

123

127

24.2

22.8

0.14

3

0.13

0

113

116

23.5

22.2

0.83

5

0.77

1

515

532

32.2

30.2

0.21

9

0.19

9

98 101

35.3

33.2

1.96

5

1.81

4

108

113

14.9

14.1

0.06

9

0.06

3

144

148

6005

-T

5E

xtru

sion

s14

.50.

067

144

17.0

0.08

613

316

.70.

536

446

22.6

0.13

111

525

.11.

260

133

9.9

0.03

817

4

6061

-60

61-

T6,

T65

1, T

6510

, T65

11

T6,

T65

1, T

6510

, T65

11

All

(2)

All

(3)

16.8

12.2

0.08

40.

052

133

157

19.9

14.2

0.10

80.

065

123

145

19.4

14.1

0.65

40.

424

389

523

26.4

18.8

0.16

50.

100

107

126

29.2

21.1

1.53

80.

999

121

150

11.5 8.2

0.04

80.

029

161

190

6063

-T

5, T

52, T

6A

ll8.

70.

031

185

10.1

0.03

917

210

.10.

273

795

13.4

0.06

015

015

.10.

642

187

5.9

0.01

722

6

6351

-63

51-

T5,

T6

T5,

T6

Ext

rusi

ons

(2)

Ext

rusi

ons

(3)

16.8

12.2

0.08

40.

052

133

157

19.9

14.2

0.10

80.

065

123

145

19.4

14.1

0.65

40.

424

389

523

26.4

18.8

0.16

50.

100

107

126

29.2

21.1

1.53

80.

999

121

150

11.5 8.2

0.04

80.

029

161

190

6463

-T

6E

xtru

sion

s8.

70.

031

185

10.1

0.03

917

210

.10.

273

795

13.4

0.06

015

015

.10.

642

187

5.9

0.01

722

6

7005

-T

53E

xtru

sion

s27

.70.

174

106

33.1

0.22

897

31.8

1.24

442

744

.10.

350

8447

.72.

928

8919

.20.

101

127

(1)

Max

imum

thic

knes

s (in

.) s

how

n in

par

enth

eses

.(2

) Val

ues

whe

n w

elde

d w

ith 5

183,

535

6, o

r 55

56 fi

ller,

rega

rdle

ss o

f thi

ckne

ss.

Val

ues

also

app

ly to

thic

knes

ses

< 0

.375

in. w

hen

wel

ded

with

404

3, 5

554,

or

5654

fille

r.(3

) Val

ues

appl

y to

thic

knes

ses

> 0

.375

in. w

hen

wel

ded

with

404

3, 5

554,

or

5654

fille

r.

January 2005 VII-27

Design Aid Tables 2-2 through 2-26

1. These tables provide allowable stresses for building type structures.2. Buckling constants used to calculate values in Tables 2-2 through 2-26 are calculated from minimum mechanical properties

given in Part I Tables 3.3-1 and 3.3-2 rather than the rounded buckling constants given in Part VII Tables 2-1 and 2-1W.3. Unshaded values apply to unwelded members.4. Shaded values apply to members with the full cross section weld affected and are calculated in accordance with Part IA

Section 7.1.2.5. For tubes with circumferential welds, equations of 3.4.10, 3.4.12, and 3.4.16.1 apply for Rb /t < 20.

VII-28 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

110

0-H

14 S

hee

t, P

late

, Dra

wn

Tu

be

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

8 8.5

5.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

28

2.1

Rou

nd o

r ov

al tu

bes

310

2.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

411

2.8

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

516

11.5

Sha

ded

bars

app

ly to

wel

d-af

fect

ed m

etal

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

611

7.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,

S1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

07.

4 –

0.03

4 kL

/r14

451

100

/(kL

/r)2

–0

1.9

– 0.

0045

kL/

r28

051

100

/(kL

/r)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

88

3.8

8.7

– 0.

224

b/t

1985

/(b

/t)

2.1

1.2

2.2

– 0.

027

b/t

3942

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

83.

88.

7 –

0.22

4 b

/t26

1970

/(b

/t)2

2.1

1.2

2.2

– 0

.027

b/t

5219

70 /(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

98

128.

7 –

0.07

0 b

/t62

271

/(b

/t)

2.1

3.7

2.2

– 0.

0086

b/t

125

135

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

86.

68.

6 –

0.27

5 √__

__

Rb/t

45

031

90 /

( Rb

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

2.1

2.6

2.2

– 0.

044

√____

Rb/t

13

8031

90 /

( Rb

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-29

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

118

268.

8 –

0.03

4 L b

/ry

172

8700

0 /(

L b/r

y)2

2.1

292.

2 –

0.00

44 L

b/r

y34

087

000

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

129

6215

.2 –

0.7

64 √

____

Rb/t

18

4S

ame

as

2.5

129

3.9

– 0.

124

√____

Rb/t

46

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1019

13.7

– 0

.182

d

__ t √__

_ L b

_

_

d

5011

400

/ ( d

__ t ) 2 L b

_

_

d

2.8

273.

4 –

0.02

2 d

__

t √___

L b

__

d

101

1140

0 / ( d

__

t ) 2 L b

__

d

Tubu

lar

shap

es

14

819

08.

8 –

0.06

5 √_

____

2L

bS

c _____

√___

I yJ

8070

2360

0 /

2LbS

c _____

√___

I yJ

2.1

221

2.2

– 0.

0084

√_____

2L

bS

c _____

√___

I yJ

3150

023

600

/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

158

9.2

10.3

– 0

.265

b/t

1910

1 /(

b/t)

2.1

132.

5 –

0.03

2 b

/t39

50 /(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

168

2910

.3 –

0.0

83 b

/t62

320

/(b

/t)

2.1

422.

5 –

0.01

0 b

/t12

515

9 /(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.19

8.2

10.1

– 0

.325

√__

__

Rb/t

45

037

80 /

( Rb

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

2.5

4.3

2.6

– 0.

0526

√__

__

Rb/t

13

8037

80 /

( Rb

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1012

13.7

– 0

.277

b/t

3349

30 /(

b/t)

2

2.8

183.

4 –

0.03

4 b

/t66

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1810

6513

.7 –

0.0

53 h

/t12

988

1 /(

h/t)

2.8

933.

4 –

0.00

64 h

/t26

043

6 /(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1910

150

13.7

– 0

.023

h/t

300

2040

/(h/

t)

2.8

214

3.4

– 0.

0028

h/t

600

1010

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

4.9

496.

5 –

0.03

2 h/

t13

438

700

/(h/

t)2

1.2

711.

5 –

0.00

35 h

/t28

038

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

214.

990

8.9

– 0.

044

a e/t

134

5320

0 /(

a e/t)

2

1.2

167

2.0

– 0.

0048

ae/

t28

053

200

/(a e

/t)2

VII-30 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-3

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

3003

-H14

Sh

eet,

Pla

te, D

raw

n T

ub

e

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

10.5

10.5

7

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

210

.53.

0

Rou

nd o

r ov

al tu

bes

312

3.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

413

.53.

9W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

521

14.5

Sha

ded

bars

app

ly to

wel

d-af

fect

ed m

etal

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

613

.59.

5F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

08.

0 –

0.03

9kL

/r13

851

100

/(kL

/r)2

–0

2.7

– 0.

0077

kL/r

236

5110

0 /(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

88.

53.

89.

5 –

0.25

2b

/t19

89

/(b

/t)

3.0

2.3

3.1

– 0.

048

b/t

3351

/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

8.5

3.8

9.5

– 0.

252

b/t

2519

70

/(b

/t)2

3.0

2.3

3.1

– 0.

048

b/t

4319

70

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

98.

512

9.5

– 0.

079

b/t

6028

2 /(

b/t)

3.0

7.3

3.1

– 0.

015

b/t

104

163

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

8.5

6.8

9.3

– 0.

305

√____

Rb/t

42

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.0

3.9

3.2

– 0.

073

√____

Rb/t

10

6031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-31

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

118.

526

9.5

– 0.

038

L b/r

y16

687

000

/(L b

/ry)

2

3.0

283.

2 –

0.00

76L b

/ry

280

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1210

5916

.4 –

0.8

47 √__

__

Rb/t

17

5S

ame

as

3.5

106

5.6

– 0.

203

√____

Rb/t

36

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1118

14.8

– 0

.206

d

__ t √__

_ L b

_

_

d

4811

400

/ ( d

__ t ) 2 L b

_

_

d

3.9

254.

9 –

0.03

9 d

__

t √___

L b

__

d

8411

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

8.5

188

9.5

– 0.

073

√_____

2L

bS

c _____

√___

I yJ

7470

2360

0/

2LbS

c _____

√___

I yJ

3.0

214

3.2

– 0.

015

√_____

2L

bS

c _____

√___

I yJ

2180

023

600

/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

158.

59.

011

.2 –

0.2

98b

/t19

105

/(b

/t)

3.0

123.

7 –

0.05

7 b

/t33

60/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

168.

529

11.2

– 0

.094

b

/t60

333

/(b

/t)

3.0

383.

7 –

0.01

8b

/t10

419

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.110

8.3

11.0

– 0

.360

√____

Rb/t

42

037

80 ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.5

5.7

3.8

– 0.

086

√____

Rb/t

10

6037

80 ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1112

14.8

– 0

.313

b

/t32

4930

/(b

/t)2

3.9

164.

9 –

0.05

9 b

/t55

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1811

6314

.8 –

0.0

60

h/t

124

917

/(h/

t)

3.9

854.

9 –

0.01

1 h/

t21

552

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1911

147

14.8

– 0

.026

h/

t29

021

20/(

h/t)

3.9

195

4.9

– 0.

0049

h/

t50

012

20/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

646

8.0

– 0.

044

h/t

120

3870

0/(

h/t)

2

1.7

652.

2 –

0.00

62h/

t23

238

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

216

8311

.0 –

0.0

61a e

/t12

053

200

/(a e

/t)2

1.7

142

3.0

– 0.

0085

a e/t

232

5320

0/(

a e/t)

2

VII-32 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-4

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

3003

-H16

Sh

eet,

Dra

wn

Tu

be

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

12.5

12.5

7

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

212

.53.

0

Rou

nd o

r ov

al tu

bes

315

3.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

417

3.9

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

525

14.5

Sha

ded

bars

app

ly to

wel

d-af

fect

ed m

etal

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

616

9.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

010

.5 –

0.0

58kL

/r12

151

100

/(kL

/r)2

–0

2.7

– 0.

0077

kL/r

236

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

811

4.0

12.4

– 0

.380

b/t

1610

1/(

b/t)

3.0

2.3

3.1

– 0.

048

b/t

3351

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

114.

012

.4 –

0.3

80b

/t22

1970

/(b

/t)2

3.0

2.3

3.1

– 0.

048

b/t

4319

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

911

1312

.4 –

0.1

19b

/t52

323

/(b

/t)

3.0

7.3

3.1

– 0.

015

b/t

104

163

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

117.

212

.1 –

0.4

32 √__

__

Rb/t

33

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.0

3.9

3.2

– 0.

073

√____

Rb/t

10

6031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-33

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1111

2612

.4 –

0.0

57L b

/ry

145

8700

0/(

L b/r

y)2

3.0

283.

2 –

0.00

76L b

/ry

280

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1213

5221

.4 –

1.2

0 √__

__

Rb/t

14

7S

ame

as

3.5

106

5.6

– 0.

203

√____

Rb/t

36

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1417

19.5

– 0

.310

d

__ t √__

_ L b

_

_

d

4211

400

/ ( d

__ t ) 2 L b

_

_

d

3.9

254.

9 –

0.03

9 d

__

t √___

L b

__

d

8411

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

1411

180

12.4

– 0

.109

√_____

2L

bS

c _____

√___

I yJ

5730

2360

0/

2LbS

c _____

√___

I yJ

3.0

214

3.2

– 0.

015

√_____

2L

bS

c _____

√___

I yJ

2180

023

600

/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1511

8.4

14.7

– 0

.449

b/t

1612

0/(

b/t)

3.0

123.

7 –

0.05

7b

/t33

60/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1611

2714

.7 –

0.1

41b

/t52

382

/(b

/t)

3.0

383.

7 –

0.01

8b

/t10

419

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.113

8.6

14.3

– 0

.511

√____

Rb/t

33

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.5

5.7

3.8

– 0.

086

√____

Rb/t

10

6037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1411

19.5

– 0

.471

b/t

2849

30/(

b/t)

2

3.9

164.

9 –

0.05

9b

/t55

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1814

5919

.5 –

0.0

90h/

t10

810

50/(

h/t)

3.9

854.

9 –

0.01

1h/

t21

552

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1914

136

19.5

– 0

.039

h/t

249

2430

/(h/

t)

3.9

195

4.9

– 0.

0049

h/t

500

1220

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

7.5

4410

.1 –

0.0

63h/

t10

738

700

/(h/

t)2

1.7

652.

2 –

0.00

62h/

t23

238

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

217.

576

13.8

– 0

.086

a e/t

107

5320

0/(

a e/t)

2

1.7

142

3.0

– 0.

0085

a e/t

232

5320

0/(

a e/t)

2

VII-34 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-5

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

Alc

lad

30

04-H

34 S

hee

t

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

16 14.5

11

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

214

.54.

8

Rou

nd o

r ov

al tu

bes

317

5.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

419

6.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

532

22S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

621

14.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

012

.3 –

0.0

74kL

/r11

251

100

/(kL

/r)2

–0

4.5

– 0.

016

kL/r

185

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

812

.54.

014

.7 –

0.4

88b

/t15

110

/(b

/t)

4.8

3.3

5.2

– 0.

102

b/t

2566

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

12.5

4.0

14.7

– 0

.488

b/t

2019

70/(

b/t)

2

4.8

3.3

5.2

– 0.

102

b/t

3419

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

12.5

1314

.7 –

0.1

53b

/t48

352

/(b

/t)

4.8

105.

2 –

0.03

2b

/t81

209

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

12.5

7.4

14.2

– 0

.536

√____

Rb/t

28

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

4.8

5.4

5.2

– 0.

140

√____

Rb/t

80

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-35

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1112

.525

14.6

– 0

.073

L b/r

y13

487

000

/(L b

/ry)

2

4.8

275.

3 –

0.01

6L b

/ry

222

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1215

4725

.1 –

1.4

9 √__

__

Rb/t

13

2S

ame

as

5.5

819.

2 –

0.38

9 √__

__

Rb/t

26

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1716

23.1

– 0

.399

d

__ t √__

_ L b

_

_

d

3911

400

/ ( d

__ t ) 2 L b

_

_

d

6.5

228.

1 –

0.08

3 d

__

t √___

L b

__

d

6511

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

12.5

175

14.6

– 0

.139

√_____

2L

bS

c _____

√___

I yJ

4860

2360

0/ 2L

bS

c _____

√___

I yJ

4.8

203

5.3

– 0.

030

√_____

2L

bS

c _____

√___

I yJ

1340

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1512

.58.

017

.3 –

0.5

77b

/t15

130

/(b

/t)

4.8

116.

1 –

0.12

1b

/t25

77/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1612

.526

17.3

– 0

.181

b/t

4841

5/(

b/t)

4.8

346.

1 –

0.03

8b

/t81

247

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.115

8.7

16.8

– 0

.634

√____

Rb/t

28

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

5.5

7.2

6.1

– 0.

165

√____

Rb/t

80

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1711

23.1

– 0

.607

b/t

2549

30/(

b/t)

2

6.5

148.

1 –

0.12

6b

/t43

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1817

5623

.1 –

0.1

16h/

t99

1140

/(h/

t)

6.5

748.

1 –

0.02

4h/

t16

767

8/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1917

130

23.1

– 0

.050

h/t

229

2640

/(h/

t)

6.5

172

8.1

– 0.

010

h/t

390

1570

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

8.5

4211

.7 –

0.0

78h/

t10

038

700

/(h/

t)2

2.8

573.

6 –

0.01

3h/

t18

138

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

218.

571

16.0

– 0

.107

a e/t

100

5320

0/(

a e/t)

2

2.8

116

4.9

– 0.

018

a e/t

181

5320

0/(

a e/t)

2

VII-36 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-6

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

5005

-H14

Sh

eet

and

Pla

te

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

11 10.5

7.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

210

.53.

0

Rou

nd o

r ov

al tu

bes

312

3.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

413

.53.

9W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

522

15S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

614

.510

.5F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

08.

6 –

0.04

3kL

/r13

351

100

/(kL

/r)2

–0

2.7

– 0.

077

kL/r

236

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

89

3.9

10.2

– 0

.282

b/t

1892

/(b

/t)

3.0

2.3

3.1

– 0.

048

b/t

3351

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

93.

910

.2 –

0.2

82b

/t24

1970

/(b

/t)2

3.0

2.3

3.1

– 0.

048

b/t

4319

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

912

10.2

– 0

.089

b/t

5829

3/(

b/t)

3.0

73.

1 –

0.01

5b

/t10

416

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

96.

910

.0 –

0.3

35 √__

__

Rb/t

39

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.0

3.9

3.2

– 0.

073

√____

Rb/t

10

7031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-37

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

119

2610

.2 –

0.0

43L b

/ry

160

8700

0/(

L b/r

y)2

3.0

283.

2 –

0.00

76L b

/ry

280

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1210

.557

17.7

– 0

.932

√____

Rb/t

16

7S

ame

as

3.5

106

5.6

– 0.

203

√____

Rb/t

36

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1218

16.0

– 0

.230

d

__ t √__

_ L b

_

_

d

4611

400

/ ( d

__ t ) 2 L b

_

_

d

3.9

254.

9 –

0.03

9 d

__

t √___

L b

__

d

8411

400

( d

__ t ) 2 L b

_

_

d /

Tubu

lar

shap

es

14

918

610

.2 –

0.0

82 √_

____

2L

bS

c _____

√___

I yJ

6940

2360

0/ 2L

bS

c _____

√___

I yJ

3.0

214

3.2

– 0.

015

√_____

2L

bS

c _____

√___

I yJ

2180

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

159

8.8

12.0

– 0

.334

b/t

1810

9/(

b/t)

3.0

123.

7 –

0.05

7b

/t33

60/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

169

2812

.0 –

0.1

05b

/t58

346

/(b

/t)

3.0

383.

7 –

0.01

8b

/t10

419

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.110

.58.

411

.8 –

0.3

96 √__

__

Rb/t

39

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.5

5.7

3.8

– 0.

086

√____

Rb/t

10

7037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1212

16.0

– 0

.350

b/t

3049

30/(

b/t)

2

3.9

164.

9 –

0.05

9b

/t55

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1812

6216

.0 –

0.0

67h/

t11

995

2/(

h/t)

3.9

854.

9 –

0.01

1h/

t21

552

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1912

144

16.0

– 0

.029

h/t

280

2200

/(h/

t)

3.9

195

4.9

– 0.

0049

h/t

500

1220

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

646

8.0

– 0.

044

h/t

120

3870

0/(

h/t)

2

1.7

652.

2 –

0.00

62h/

t23

238

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

216

8311

.0 –

0.0

61a e

/t12

053

200

/(a e

/t)2

1.7

142

3.0

– 0.

0085

a e/t

232

5320

0/(

a e/t)

2

VII-38 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-7

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

5005

-H34

Sh

eet

and

Pla

te

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

10.5 9

7.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

29

3.0

Rou

nd o

r ov

al tu

bes

310

.53.

5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

412

3.9

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

521

15S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

613

.510

.5F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

08.

0 –

0.03

9kL

/r13

851

100

/(kL

/r)2

–0

2.7

– 0.

077

kL/r

236

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

88.

53.

89.

5 –

0.25

2b

/t19

89/(

b/t)

3.0

2.3

3.1

– 0.

048

b/t

3351

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

8.5

3.8

9.5

– 0.

252

b/t

2519

70/(

b/t)

2

3.0

2.3

3.1

– 0.

048

b/t

4319

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

8.5

129.

5 –

0.07

9b

/t60

282

/(b

/t)

3.0

73.

1 –

0.01

5b

/t10

416

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

8.5

6.8

9.3

– 0.

305

√____

Rb/t

42

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.0

3.9

3.2

– 0.

073

√____

Rb/t

10

7031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-39

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

118.

526

9.5

– 0.

038

L b/r

y16

687

000

/(L b

/ry)

2

3.0

283.

2 –

0.00

76L b

/ry

280

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1210

5916

.4 –

0.8

47 √__

__

Rb/t

17

5S

ame

as

3.5

106

5.6

– 0.

203

√____

Rb/t

36

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1118

14.8

– 0

.206

d

__ t √__

_ L b

_

_

d

4811

400

/ ( d

__ t ) 2 L b

_

_

d

3.9

254.

9 –

0.03

9 d

__

t √___

L b

__

d

8411

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

8.5

188

9.5

– 0.

073

√_____

2L

bS

c _____

√___

I yJ

7470

2360

0/ 2L

bS

c _____

√___

I yJ

3.0

214

3.2

– 0.

015

√_____

2L

bS

c _____

√___

I yJ

2180

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

158.

59.

011

.2 –

0.2

98b

/t19

105

/(b

/t)

3.0

123.

7 –

0.05

7b

/t33

60/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

168.

529

11.2

– 0

.094

b/t

6033

3/(

b/t)

3.0

383.

7 –

0.01

8b

/t10

419

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.110

8.3

11.0

– 0

.360

√____

Rb/t

42

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.5

5.7

3.8

– 0.

086

√____

Rb/t

10

7037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1112

14.8

– 0

.313

b/t

3249

30/(

b/t)

2

3.9

164.

9 –

0.05

9b

/t55

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1811

6314

.8 –

0.0

60h/

t12

491

7/(

h/t)

3.9

854.

9 –

0.01

1h/

t21

552

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1911

147

14.8

– 0

.026

h/t

290

2120

/(h/

t)

3.9

195

4.9

– 0.

0049

h/t

500

1220

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

548

7.0

– 0.

036

h/t

129

3870

0/(

h/t)

2

1.7

652.

2 –

0.00

62h/

t23

238

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

215

889.

6 –

0.05

0a e

/t12

953

200

/(a e

/t)2

1.7

142

3.0

– 0.

0085

a e/t

232

5320

0/(

a e/t)

2

VII-40 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-8

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

5050

-H34

Sh

eet,

Dra

wn

Tu

be

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

13 129

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

212

3.6

Rou

nd o

r ov

al tu

bes

314

4.3

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

416

4.7

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

526

18S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

617

12.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

010

.5 –

0.0

58kL

/r12

151

100

/(kL

/r)2

–0

3.3

– 0.

010

kL/r

215

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

811

4.0

12.4

– 0

.380

b/t

1610

1/(

b/t)

3.6

2.7

3.8

– 0.

065

b/t

3056

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

114.

012

.4 –

0.3

80b

/t22

1970

/(b

/t)2

3.6

2.7

3.8

– 0.

065

b/t

3919

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1113

12.4

– 0

.119

b/t

5232

3/(

b/t)

3.6

8.7

3.8

– 0.

020

b/t

9417

9/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

117.

212

.1 –

0.4

32 √__

__

Rb/t

33

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

3.6

4.5

3.8

– 0.

094

√____

Rb/t

93

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-41

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1111

2612

.4 –

0.0

57L b

/ry

145

8700

0/(

L b/r

y)2

3.6

283.

9 –

0.01

0L b

/ry

260

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1213

5221

.4 –

1.2

0 √__

__

Rb/t

14

7S

ame

as

4.3

956.

8 –

0.26

1 √__

__

Rb/t

31

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1417

19.5

– 0

.310

d

__ t √__

_ L b

_

_

d

4211

400

/ ( d

__ t ) 2 L b

_

_

d

4.7

236.

0 –

0.05

2 d

__

t √___

L b

__

d

7611

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1118

012

.4 –

0.1

09 √_

____

2L

bS

c _____

√___

I yJ

5730

2360

0/ 2L

bS

c _____

√___

I yJ

3.6

210

3.9

– 0.

019

√_____

2L

bS

c _____

√___

I yJ

1810

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1511

8.4

14.7

– 0

.449

b/t

1612

0/(

b/t)

3.6

114.

5 –

0.07

6b

/t30

66/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1611

2714

.7 –

0.1

41b

/t52

382

/(b

/t)

3.6

364.

5 –

0.02

4b

/t94

212

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.113

8.6

14.3

– 0

.511

√____

Rb/t

33

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

4.3

6.3

4.5

– 0.

111

√____

Rb/t

93

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1411

19.5

– 0

.471

b/t

2849

30/(

b/t)

2

4.7

156.

0 –

0.08

0b

/t50

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1814

5919

.5 –

0.0

90h/

t10

810

50/(

h/t)

4.7

816.

0 –

0.01

5h/

t19

558

1/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1914

136

19.5

– 0

.039

h/t

249

2430

/(h/

t)

4.7

186

6.0

– 0.

0066

h/t

450

1340

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

744

9.5

– 0.

058

h/t

110

3870

0/(

h/t)

2

2.1

622.

6 –

0.00

83h/

t21

138

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

217

7713

.1 –

0.0

79a e

/t11

053

200

/(a e

/t)2

2.1

131

3.6

– 0.

011

a e/t

211

5320

0/(

a e/t)

2

VII-42 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-9

AL

LOW

AB

LE

ST

RE

SS

ES

FO

R

BU

ILD

ING

TY

PE

ST

RU

CT

UR

ES

5052

-H32

Sh

eet,

Dra

wn

Tu

be

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

16 1413

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

214

6

Rou

nd o

r ov

al tu

bes

316

6.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

418

7.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

532

26S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

621

17F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

012

.3 –

0.0

73kL

/r11

251

600

/(kL

/r)2

–0

5.3

– 0.

021

kL/r

170

5160

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

812

.54.

014

.7 –

0.4

86b

/t15

111

/(b

/t)

63.

56.

2 –

0.13

4b

/t23

72/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

12.5

4.0

14.7

– 0

.486

b/t

2019

80/(

b/t)

2

63.

56.

2 –

0.13

4b

/t31

1980

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

12.5

1314

.7 –

0.1

52b

/t48

353

/(b

/t)

611

6.2

– 0.

042

b/t

7423

0/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

12.5

7.4

14.2

– 0

.535

√____

Rb/t

28

032

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

66.

06.

2 –

0.17

7 √__

__

Rb/t

73

032

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-43

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1112

.526

14.6

– 0

.072

L b/r

y13

587

900

/(L b

/ry)

2

627

6.3

– 0.

021

L b/r

y20

487

900

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1215

4825

.1 –

1.4

9 √__

__

Rb/t

13

3S

ame

as

6.5

7411

.0 –

0.4

92 √__

__

Rb/t

23

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1716

23.1

– 0

.397

d

__ t √__

_ L b

_

_

d

3911

500

/ ( d

__ t ) 2 L b

_

_

d

7.5

219.

7 –

0.10

9 d

__

t √___

L b

__

d

6011

500

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

12.5

177

14.6

– 0

.139

√_____

2L

bS

c _____

√___

I yJ

4910

2380

0/ 2L

bS

c _____

√___

I yJ

620

16.

3 –

0.04

0 √_

____

2L

bS

c _____

√___

I yJ

1130

023

800

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1512

.58.

017

.3 –

0.5

74b

/t15

131

/(b

/t)

610

7.4

– 0.

159

b/t

2385

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1612

.526

17.3

– 0

.180

b/t

4841

8/(

b/t)

632

7.4

– 0.

050

b/t

7427

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.115

8.8

16.8

– 0

.632

√____

Rb/t

28

038

10/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

6.5

7.7

7.3

– 0.

209

√____

Rb/t

73

038

10/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1711

23.1

– 0

.604

b/t

2549

80/(

b/t)

2

7.5

149.

7 –

0.16

6b

/t39

4980

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1817

5623

.1 –

0.1

16h/

t10

011

50/(

h/t)

7.5

719.

7 –

0.03

2h/

t15

374

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1917

130

23.1

– 0

.050

h/t

230

2660

/(h/

t)

7.5

165

9.7

– 0.

014

h/t

350

1730

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

843

11.1

– 0

.072

h/t

103

3900

0/(

h/t)

2

3.3

554.

3 –

0.01

7h/

t16

639

000

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

218

7315

.3 –

0.0

99a e

/t10

353

700

/(a e

/t)2

3.3

108

5.9

– 0.

024

a e/t

166

5370

0/(

a e/t)

2

VII-44 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

0A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5052

-H34

Sh

eet,

Pla

te, D

raw

n T

ub

e

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

17 1613

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

216

6

Rou

nd o

r ov

al tu

bes

318

6.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

420

7.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

535

26S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

623

17F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

014

.2 –

0.0

91kL

/r10

451

600

/(kL

/r)2

–0

5.3

– 0.

021

kL/r

170

5160

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

814

.54.

017

.0 –

0.6

04b

/t14

119

/(b

/t)

63.

56.

2 –

0.13

4b

/t23

72/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

14.5

4.0

17.0

– 0

.604

b/t

1919

80/(

b/t)

2

63.

56.

2 –

0.13

4b

/t31

1980

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

14.5

1317

.0 –

0.1

90b

/t45

380

/(b

/t)

611

6.2

– 0.

042

b/t

7423

0/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

14.5

7.5

16.3

– 0

.644

√____

Rb/t

25

032

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

66.

06.

2 –

0.17

7 √__

__

Rb/t

73

032

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-45

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1114

.525

16.8

– 0

.089

L b/r

y12

587

900

/(L b

/ry)

2

627

6.3

– 0.

021

L b/r

y20

487

900

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1217

4428

.9 –

1.7

9 √__

__

Rb/t

12

1S

ame

as

6.5

7411

.0 –

0.4

92 √__

__

Rb/t

23

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1916

26.7

– 0

.494

d

__ t √__

_ L b

_

_

d

3611

500

/ ( d

__ t ) 2 L b

_

_

d

7.5

219.

7 –

0.10

9 d

__

t √___

L b

__

d

6011

500

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

14.5

172

16.8

– 0

.172

√_____

2L

bS

c _____

√___

I yJ

4260

2380

0/ 2L

bS

c _____

√___

I yJ

620

16.

3 –

0.04

0 √_

____

2L

bS

c _____

√___

I yJ

1130

023

800

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1514

.57.

720

.1 –

0.7

14b

/t14

141

/(b

/t)

610

7.4

– 0.

159

b/t

2385

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1614

.525

20.1

– 0

.224

b/t

4544

9/(

b/t)

632

7.4

– 0.

050

b/t

7427

2/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.117

8.8

19.3

– 0

.761

√____

Rb/t

25

038

10/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

6.5

7.7

7.3

– 0.

209

√____

Rb/t

73

038

10/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1910

26.7

– 0

.752

b/t

2449

80/(

b/t)

2

7.5

149.

7 –

0.16

6b

/t39

4980

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1819

5426

.7 –

0.1

44h/

t93

1240

/(h/

t)

7.5

719.

7 –

0.03

2h/

t15

374

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1919

125

26.7

– 0

.062

h/t

214

2860

/(h/

t)

7.5

165

9.7

– 0.

014

h/t

350

1730

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

941

12.7

– 0

.088

h/t

9639

000

/(h/

t)2

3.3

554.

3 –

0.01

7h/

t16

639

000

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

219

6917

.5 –

0.1

21a e

/t96

5370

0/(

a e/t)

2

3.3

108

5.9

– 0.

024

a e/t

166

5370

0/(

a e/t)

2

VII-46 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

1A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5083

-H11

1 E

xtru

sio

ns

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

21 14.5

20

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

214

.59.

5

Rou

nd o

r ov

al tu

bes

317

11.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

419

12.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

541

40S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

627

27F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

012

.3 –

0.0

73kL

/r11

352

600

/(kL

/r)2

–0

8.6

– 0.

043

kL/r

135

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

812

.54.

114

.7 –

0.4

81b

/t15

112

/(b

/t)

93.

910

.2 –

0.2

78b

/t18

93/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

12.5

4.1

14.7

– 0

.481

b/t

2020

20/(

b/t)

2

93.

910

.2 –

0.2

78b

/t24

2020

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

12.5

1314

.7 –

0.1

51b

/t49

357

/(b

/t)

913

10.2

– 0

.087

b/t

5829

7/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

12.5

7.5

14.2

– 0

.531

√____

Rb/t

29

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

97.

010

.0 –

0.3

32 √__

__

Rb/t

57

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-47

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1112

.526

14.6

– 0

.072

L b/r

y13

689

600

/(L b

/ry)

2

927

10.2

– 0

.042

L b/r

y16

289

600

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1215

4825

.1 –

1.4

8 √__

__

Rb/t

13

4S

ame

as

10.5

5817

.7 -

0.92

3 √__

__

Rb/t

17

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1717

23.1

– 0

.393

d

__ t √__

_ L b

_

_

d

3911

800

/ ( d

__ t ) 2 L b

_

_

d

1218

16.0

– 0

.227

d

__ t √__

_ L b

_

_

d

4711

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

12.5

180

14.6

– 0

.137

√_____

2L

bS

c _____

√___

I yJ

5010

2430

0/ 2L

bS

c _____

√___

I yJ

919

210

.2 –

0.0

80 √_

____

2L

bS

c _____

√___

I yJ

7150

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1512

.58.

117

.3 –

0.5

68b

/t15

132

/(b

/t)

99.

012

.0 –

0.3

29b

/t18

110

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1612

.526

17.3

– 0

.178

b/t

4942

2/(

b/t)

929

12.0

– 0

.103

b/t

5835

1/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.115

8.9

16.8

– 0

.628

√____

Rb/t

29

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

10.5

8.6

11.8

– 0

.392

√____

Rb/t

57

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1711

23.1

– 0

.598

b/t

2650

80/(

b/t)

2

1212

16.0

– 0

.345

b/t

3150

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1817

5723

.1 –

0.1

15h/

t10

111

60/(

h/t)

1263

16.0

– 0

.066

h/t

121

966

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1917

132

23.1

– 0

.050

h/t

233

2680

/(h/

t)

1214

616

.0 –

0.0

29h/

t28

022

30/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

8.5

4211

.7 –

0.0

77h/

t10

139

800

/(h/

t)2

5.5

487.

5 –

0.04

0h/

t12

639

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

218.

572

16.0

– 0

.105

a e/t

101

5470

0/(

a e/t)

2

5.5

8710

.3 –

0.0

54a e

/t12

654

700

/(a e

/t)2

VII-48 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

2A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5083

-H11

6, -

H32

, -H

321

Sh

eet

and

Pla

te(T

hic

knes

s 0.

188

to 1

.50

0 in

.)

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

23 1921

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

219

11

Rou

nd o

r ov

al tu

bes

322

13

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

424

14W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

545

41S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

630

27F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

015

.5 –

0.1

02kL

/r10

152

600

/(kL

/r)2

–0

10.5

– 0

.057

kL/r

123

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

816

4.1

18.5

– 0

.682

b/t

1412

6/(

b/t)

114.

012

.4 –

0.3

74b

/t17

103

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

164.

118

.5 –

0.6

82b

/t18

2020

/(b

/t)2

114.

012

.4 –

0.3

74b

/t22

2020

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1613

18.5

– 0

.214

b/t

4340

1/(

b/t)

1113

12.4

– 0

.117

b/t

5332

8/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

167.

717

.7 –

0.7

16 √__

__

Rb/t

23

532

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

117.

312

.1 –

0.4

28 √__

__

Rb/t

52

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-49

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1116

2518

.3 –

010

1L b

/ry

121

8960

0/(

L b/r

y)2

1126

12.4

– 0

.056

L b/r

y14

789

600

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1218

4331

.5 –

1.9

9 √__

__

Rb/t

11

6S

ame

as

1353

21.4

– 1

.19

√____

Rb/t

15

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2016

29.2

– 0

.559

d

__ t √__

_ L b

_

_

d

3511

800

/ ( d

__ t ) 2 L b

_

_

d

1417

19.5

– 0

.305

d

__ t √__

_ L b

_

_

d

4311

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1617

318

.3 –

0.1

93 √_

____

2L

bS

c _____

√___

I yJ

3990

2430

0/ 2L

bS

c _____

√___

I yJ

1118

612

.4 –

0.1

07 √_

____

2L

bS

c _____

√___

I yJ

5900

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1516

7.6

21.9

– 0

.806

b/t

1414

9/(

b/t)

118.

514

.7 –

0.4

42b

/t17

122

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1616

2421

.9 –

0.2

53b

/t43

474

/(b

/t)

1127

14.7

– 0

.139

b/t

5338

8/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.118

9.0

21.0

– 0

.846

√____

Rb/t

23

538

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

138.

814

.3 –

0.5

06 √__

__

Rb/t

52

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

2010

29.2

– 0

.850

b/t

2350

80/(

b/t)

2

1411

19.5

– 0

.465

b/t

2850

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1820

5329

.2 –

0.1

63h/

t90

1310

/(h/

t)

1460

19.5

– 0

.089

h/t

110

1070

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1920

123

29.2

– 0

.070

h/t

207

3020

/(h/

t)

1413

819

.5 –

0.0

38h/

t25

024

70/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1139

15.4

– 0

.117

h/t

8839

800

/(h/

t)2

6.5

468.

5 –

0.04

8h/

t11

839

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2111

6521

.2 –

0.1

61a e

/t88

5470

0/(

a e/t)

2

6.5

8211

.7 –

0.0

66a e

/t11

854

700

/(a e

/t)2

VII-50 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

3A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5086

-H34

Sh

eet

and

Pla

te, D

raw

n T

ub

e

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

23 2118

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

221

8.5

Rou

nd o

r ov

al tu

bes

324

10

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

427

11W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

545

36S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

630

24F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

019

.3 –

0.1

43kL

/r90

5260

0/(

kL/r

)2

–0

8.0

– 0.

038

kL/r

140

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

819

4.0

23.3

– 0

.960

b/t

1214

1/(

b/t)

8.5

3.9

9.5

– 0.

249

b/t

1990

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

194.

023

.3 –

0.9

60b

/t16

2020

/(b

/t)2

8.5

3.9

9.5

– 0.

249

b/t

2520

20/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1913

23.3

– 0

.301

b/t

3944

9/(

b/t)

8.5

129.

5 –

0.07

8b

/t61

286

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

197.

822

.1 –

0.9

58 √__

__

Rb/t

19

232

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

8.5

6.9

9.3

– 0.

302

√____

Rb/t

60

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-51

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1119

2522

.9 –

0.1

41L b

/ry

108

8960

0/(

L b/r

y)2

8.5

279.

5 –

0.03

8L b

/ry

168

8960

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1223

3839

.1 –

2.6

6 √__

__

Rb/t

10

0S

ame

as

1060

16.4

– 0

.839

√____

Rb/t

17

8S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

1325

1536

.6 –

0.7

87 d

__

t √___

L b

__

d

3111

800

/ ( d

__ t ) 2 L b

_

_

d

1119

14.8

– 0

.203

d

__ t √__

_ L b

_

_

d

4911

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1916

522

.9 –

0.2

70 √_

____

2L

bS

c _____

√___

I yJ

3190

2430

0/ 2L

bS

c _____

√___

I yJ

8.5

194

9.5

– 0.

072

√_____

2L

bS

c _____

√___

I yJ

7690

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1519

7.1

27.5

– 1

.134

b/t

1216

7/(

b/t)

8.5

9.2

11.2

– 0

.294

b/t

1910

6/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1619

2327

.5 –

0.3

56b

/t39

531

/(b

/t)

8.5

2911

.2 –

0.0

92b

/t61

338

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.123

9.0

26.1

– 1

.132

√____

Rb/t

19

238

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

108.

511

.0 –

0.3

56 √__

__

Rb/t

60

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

259.

536

.6 –

1.2

0b

/t20

5080

/(b

/t)2

1112

14.8

– 0

.308

b/t

3250

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1825

5036

.6 –

0.2

29h/

t80

1460

/(h/

t)

1164

14.8

– 0

.059

h/t

126

931

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1925

115

36.6

– 0

.099

h/t

185

3380

/(h/

t)

1114

914

.8 –

0.0

26h/

t29

021

50/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1238

17.1

– 0

.136

h/t

8439

800

/(h/

t)2

4.9

506.

5 –

0.03

2h/

t13

639

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2112

6223

.5 –

0.1

87a e

/t84

5470

0/(

a e/t)

2

4.9

928.

9 –

0.04

4a e

/t13

654

700

/(a e

/t)2

VII-52 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

4A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5086

-H11

1 E

xtru

sio

ns

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

18 12.5

18

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

212

.58.

5

Rou

nd o

r ov

al tu

bes

315

10

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

417

11W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

537

36S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

625

24F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

010

.5 –

0.0

57kL

/r12

352

600

/(kL

/r)2

–0

7.4

– 0.

034

kL/r

146

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

811

4.0

12.4

– 0

.374

b/t

1710

3/(

b/t)

83.

98.

7 –

0.22

1b

/t20

86/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

114.

012

.4 –

0.3

74b

/t22

2020

/(b

/t)2

83.

98.

7 –

0.22

1b

/t26

2020

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1113

12.4

– 0

.117

b/t

5332

8/(

b/t)

812

8.7

– 0.

069

b/t

6327

5/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

117.

312

.1 –

0.4

28 √__

__

Rb/t

34

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

86.

88.

6 –

0.27

2 √__

__

Rb/t

62

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-53

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1111

2612

.4 –

0.0

56L b

/ry

147

8960

0/(

L b/r

y)2

827

8.8

– 0.

033

L b/r

y17

589

600

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1213

5321

.4 –

1.1

9 √__

__

Rb/t

15

0S

ame

as

963

15.2

– 0

.756

√____

Rb/t

18

8S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

1314

1719

.5 –

0.3

05 d

__

t √___

L b

__

d

4311

800

/ ( d

__ t ) 2 L b

_

_

d

1019

13.7

– 0

.180

d

__ t √__

_ L b

_

_

d

5111

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1118

612

.4 –

0.1

07 √_

____

2L

bS

c _____

√___

I yJ

5900

2430

0/ 2L

bS

c _____

√___

I yJ

819

68.

8 –

0.06

4 √_

____

2L

bS

c _____

√___

I yJ

8310

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1511

8.5

14.7

– 0

.442

b/t

1712

2/(

b/t)

89

10.3

– 0

.261

b/t

2010

2/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1611

2714

.7 –

0.1

39b

/t53

388

/(b

/t)

830

10.3

– 0

.082

b/t

6332

5/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.113

8.8

14.3

– 0

.506

√____

Rb/t

34

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

98.

410

.1 –

0.3

21 √__

__

Rb/t

62

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1411

19.5

– 0

.465

b/t

2850

80/(

b/t)

2

1013

13.7

– 0

.273

b/t

3350

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1814

6019

.5 –

0.0

89h/

t11

010

70/(

h/t)

1066

13.7

– 0

.052

h/t

131

894

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1914

138

19.5

– 0

.038

h/t

250

2470

/(h/

t)

1015

213

.7 –

0.0

23h/

t30

020

70/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

7.5

4410

.1 –

0.0

62h/

t10

939

800

/(h/

t)2

4.9

506.

5 –

0.03

2h/

t13

639

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

217.

577

13.8

– 0

.085

a e/t

109

5470

0/(

a e/t)

2

4.9

928.

9 –

0.04

4a e

/t13

654

700

/(a e

/t)2

VII-54 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

5A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5086

-H11

6, -

H32

Sh

eet

and

Pla

te50

86-H

32 D

raw

n T

ub

e

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

21 1718

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

217

8.5

Rou

nd o

r ov

al tu

bes

320

10

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

422

11W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

541

36S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

627

24F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

015

.5 –

0.1

02kL

/r10

152

600

/(kL

/r)2

–0

8.0

– 0.

038

kL/r

140

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

816

4.1

18.5

– 0

.682

b/t

1412

6/(

b/t)

8.5

3.9

9.5

– 0.

249

b/t

1990

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

164.

118

.5 –

0.6

82b

/t18

2020

/(b

/t)2

8.5

3.9

9.5

– 0.

249

b/t

2520

20/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1613

18.5

– 0

.214

b/t

4340

1/(

b/t)

8.5

129.

5 –

0.07

8b

/t61

286

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

167.

717

.7 –

0.7

16 √__

__

Rb/t

23

532

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

8.5

6.9

9.3

– 0.

302

√____

Rb/t

60

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-55

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1116

2518

.3 –

0.1

01L b

/ry

121

8960

0/(

L b/r

y)2

8.5

279.

5 –

0.03

8L b

/ry

168

8960

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1218

4331

.5 –

1.9

9 √__

__

Rb/t

11

6S

ame

as

1060

16.4

– 0

.839

√____

Rb/t

17

8S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

1320

1629

.2 –

0.5

59 d

__

t √___

L b

__

d

3511

800

/ ( d

__ t ) 2 L b

_

_

d

1119

14.8

– 0

.203

d

__ t √__

_ L b

_

_

d

4911

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1617

318

.3 –

0.1

93 √_

____

2L

bS

c _____

√___

I yJ

3990

2430

0/ 2L

bS

c _____

√___

I yJ

8.5

194

9.5

– 0.

072

√_____

2L

bS

c _____

√___

I yJ

7690

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1516

7.6

21.9

– 0

.806

b/t

1414

9/(

b/t)

8.5

9.2

11.2

– 0

.294

b/t

1910

6/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1616

2421

.9 –

0.2

53b

/t43

474

/(b

/t)

8.5

2911

.2 –

0.0

92b

/t61

338

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.118

9.0

21.0

– 0

.846

√____

Rb/t

23

538

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

108.

511

.0 –

0.3

56 √__

__

Rb/t

60

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

2010

29.2

– 0

.850

b/t

2350

80/(

b/t)

2

1112

14.8

– 0

.308

b/t

3250

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1820

5329

.2 –

0.1

63h/

t90

1310

/(h/

t)

1164

14.8

– 0

.059

h/t

126

931

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1920

123

29.2

– 0

.070

h/t

207

3020

/(h/

t)

1114

914

.8 –

0.0

26h/

t29

021

50/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1040

13.8

– 0

.099

h/t

9339

800

/(h/

t)2

4.9

506.

5 –

0.03

2h/

t13

639

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2110

6719

.0 –

0.1

36a e

/t93

5470

0/(

a e/t)

2

4.9

928.

9 –

0.04

4a e

/t13

654

700

/(a e

/t)2

VII-56 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

6A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5454

-H11

1 E

xtru

sio

ns

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

17 11.5

16

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

211

.57.

5

Rou

nd o

r ov

al tu

bes

313

.58.

5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

415

9.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

534

32S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

623

21F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

09.

2 –

0.04

7kL

/r13

152

600

/(kL

/r)2

–0

6.2

– 0.

026

kL/r

159

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

89.

54.

010

.9 –

0.3

09b

/t18

97/(

b/t)

6.5

3.7

7.3

– 0.

168

b/t

2279

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

9.5

4.0

10.9

– 0

.309

b/t

2420

20/(

b/t)

2

6.5

3.7

7.3

– 0.

168

b/t

2920

20/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

9.5

1310

.9 –

0.0

97b

/t56

308

/(b

/t)

6.5

127.

3 –

0.05

3b

/t69

251

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

9.5

7.1

10.7

– 0

.363

√____

Rb/t

38

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

6.5

6.4

7.2

– 0.

216

√____

Rb/t

68

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-57

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

119.

526

10.9

– 0

.046

L b/r

y15

789

600

/(L b

/ry)

2

6.5

277.

4 –

0.02

6L b

/ry

191

8960

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1211

.556

18.9

– 1

.01

√____

Rb/t

16

2S

ame

as

869

12.8

– 0

.599

√____

Rb/t

21

1S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

12.5

1817

.1 –

0.2

52 d

__

t √___

L b

__

d

4511

800

/ ( d

__ t ) 2 L b

_

_

d

8.5

2011

.4 –

0.1

37 d

__

t √___

L b

__

d

5611

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

9.5

189

10.9

– 0

.089

√_____

2L

bS

c _____

√___

I yJ

6680

2430

0/ 2L

bS

c _____

√___

I yJ

6.5

201

7.4

– 0.

049

√_____

2L

bS

c _____

√___

I yJ

9900

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

159.

58.

812

.9 –

0.3

65b

/t18

114

/(b

/t)

6.5

108.

6 –

0.19

9b

/t22

93/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

169.

528

12.9

– 0

.115

b/t

5636

4/(

b/t)

6.5

318.

6 –

0.06

2b

/t69

297

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.111

.58.

612

.6 –

0.4

29 √__

__

Rb/t

38

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

88.

18.

5 –

0.25

5 √__

__

Rb/t

68

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

12.5

1217

.1 –

0.3

83b

/t30

5080

/(b

/t)2

8.5

1311

.4 –

0.2

08b

/t37

5080

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1812

.562

17.1

– 0

.073

h/t

117

1000

/(h/

t)

8.5

6911

.4 –

0.0

40h/

t14

381

7/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1912

.514

317

.1 –

0.0

32h/

t27

023

10/(

h/t)

8.5

159

11.4

– 0

.017

h/t

330

1890

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

6.5

469.

0 –

0.05

2h/

t11

539

800

/(h/

t)2

4.2

525.

5 –

0.02

5h/

t14

839

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

216.

580

12.4

– 0

.072

a e/t

115

5470

0/(

a e/t)

2

4.2

987.

5 –

0.03

4a e

/t14

854

700

/(a e

/t)2

VII-58 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

7A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5454

-H32

Sh

eet

and

Pla

te

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

18 1616

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

216

7.5

Rou

nd o

r ov

al tu

bes

318

8.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

420

9.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

537

32S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

625

21F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

014

.2 –

0.0

90kL

/r10

552

600

/(kL

/r)2

–0

6.8

– 0.

030

kL/r

152

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

814

.54.

117

.0 –

0.5

98b

/t14

120

/(b

/t)

7.5

3.8

8.0

– 0.

194

b/t

2183

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

14.5

4.1

17.0

– 0

.598

b/t

1920

20/(

b/t)

2

7.5

3.8

8.0

– 0.

194

b/t

2820

20/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

14.5

1317

.0 –

0.1

88b

/t45

384

/(b

/t)

7.5

128.

0 –

0.06

1b

/t66

263

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

14.5

7.6

16.3

– 0

.640

√____

Rb/t

25

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

7.5

6.6

7.9

– 0.

243

√____

Rb/t

65

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-59

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1114

.525

16.8

– 0

.089

L b/r

y12

789

600

/(L b

/ry)

2

7.5

278.

1 –

0.02

9L b

/ry

183

8960

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1217

4528

.9 –

1.7

8 √__

__

Rb/t

12

2S

ame

as

8.5

6614

.0 –

0.6

77 √__

__

Rb/t

19

8S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

1916

26.7

– 0

.490

d

__ t √__

_ L b

_

_

d

3611

800

/ ( d

__ t ) 2 L b

_

_

d

9.5

2012

.5 –

0.1

58 d

__

t √___

L b

__

d

5311

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

14.5

176

16.8

– 0

.170

√_____

2L

bS

c _____

√___

I yJ

4340

2430

0/ 2L

bS

c _____

√___

I yJ

7.5

198

8.1

– 0.

057

√_____

2L

bS

c _____

√___

I yJ

9040

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1514

.57.

820

.1 –

0.7

07b

/t14

142

/(b

/t)

7.5

109.

5 –

0.22

9b

/t21

98/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1614

.525

20.1

– 0

.222

b/t

4545

3/(

b/t)

7.5

309.

5 –

0.07

2b

/t66

311

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.117

8.9

19.3

– 0

.756

√____

Rb/t

25

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

8.5

8.2

9.3

– 0.

286

√____

Rb/t

65

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

1910

26.7

– 0

.745

b/t

2450

80/(

b/t)

2

9.5

1312

.5 –

0.2

40b

/t35

5080

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1819

5526

.7 –

0.1

43h/

t94

1250

/(h/

t)

9.5

6712

.5 –

0.0

46h/

t13

785

6/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1919

126

26.7

– 0

.062

h/t

216

2890

/(h/

t)

9.5

156

12.5

– 0

.020

h/t

320

1980

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

941

12.7

– 0

.087

h/t

9739

800

/(h/

t)2

4.2

525.

5 –

0.02

5h/

t14

839

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

219

7017

.5 –

0.1

20a e

/t97

5470

0/(

a e/t)

2

4.2

987.

5 –

0.03

4a e

/t14

854

700

/(a e

/t)2

VII-60 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

8A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5454

-H34

Sh

eet

and

Pla

te

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

20 1816

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

218

7.5

Rou

nd o

r ov

al tu

bes

321

8.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

423

9.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

540

32S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

627

21F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

016

.1 –

0.1

09kL

/r99

5260

0/(

kL/r

)2

–0

6.8

– 0.

030

kL/r

152

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

816

4.1

19.3

– 0

.726

b/t

1312

8/(

b/t)

7.5

3.8

8.0

– 0.

194

b/t

2183

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

164.

119

.3 –

0.7

26b

/t18

2020

/(b

/t)2

7.5

3.8

8.0

– 0.

194

b/t

2820

20/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1613

19.3

– 0

.228

b/t

4240

9/(

b/t)

7.5

128.

0 –

0.06

1b

/t66

263

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

167.

718

.5 –

0.7

55 √__

__

Rb/t

22

732

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

7.5

6.6

7.9

– 0.

243

√____

Rb/t

65

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-61

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1116

2519

.1 –

0.1

07L b

/ry

119

8960

0/(

L b/r

y)2

7.5

278.

1 –

0.02

9L b

/ry

183

8960

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1219

4232

.7 –

2.1

0 √__

__

Rb/t

11

3S

ame

as

8.5

6614

.0 –

0.6

77 √__

__

Rb/t

19

8S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2115

30.4

– 0

.594

d

__ t √__

_ L b

_

_

d

3411

800

/ ( d

__ t ) 2 L b

_

_

d

9.5

2012

.5 –

0.1

58 d

__

t √___

L b

__

d

5311

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1617

219

.1 –

0.2

05 √_

____

2L

bS

c _____

√___

I yJ

3830

2430

0/ 2L

bS

c _____

√___

I yJ

7.5

198

8.1

– 0.

057

√_____

2L

bS

c _____

√___

I yJ

9040

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1516

7.5

22.8

– 0

.858

b/t

1315

2/(

b/t)

7.5

109.

5 –

0.22

9b

/t21

98/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1616

2422

.8 –

0.2

69b

/t42

484

/(b

/t)

7.5

309.

5 –

0.07

2b

/t66

311

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.119

9.0

21.8

– 0

.892

√____

Rb/t

22

738

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

8.5

8.2

9.3

– 0.

286

√____

Rb/t

65

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

2110

30.4

– 0

.905

b/t

2250

80/(

b/t)

2

9.5

1312

.5 –

0.2

40b

/t35

5080

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1821

5330

.4 –

0.1

73h/

t88

1330

/(h/

t)

9.5

6712

.5 –

0.0

46h/

t13

785

6/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1921

122

30.4

– 0

.075

h/t

203

3080

/(h/

t)

9.5

156

12.5

– 0

.020

h/t

320

1980

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1040

14.3

– 0

.105

h/t

9139

800

/(h/

t)2

4.2

525.

5 –

0.02

5h/

t14

839

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2110

6619

.7 –

0.1

44a e

/t91

5470

0/(

a e/t)

2

4.2

987.

5 –

0.03

4a e

/t14

854

700

/(a e

/t)2

VII-62 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-1

9A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

5456

-H11

6, -

H32

, -H

321

Sh

eet

and

Pla

te(T

hic

knes

s 0.

188

to 1

.250

in.)

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

24 2022

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

220

11.5

Rou

nd o

r ov

al tu

bes

323

13.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

426

15W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

547

43S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

631

29F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

016

.1 –

0.1

09kL

/r99

5260

0/(

kL/r

)2

–0

10.5

– 0

.057

kL/r

123

5260

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

816

4.1

19.3

– 0

.726

b/t

1312

8/(

b/t)

114.

012

.4 –

0.3

74b

/t17

103

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

164.

119

.3 –

0.7

26b

/t18

2020

/(b

/t)2

114.

012

.4 –

0.3

74b

/t22

2020

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

1613

19.3

– 0

.228

b/t

4240

9/(

b/t)

1113

12.4

– 0

.117

b/t

5332

8/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

167.

718

.5 –

0.7

55 √__

__

Rb/t

22

732

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

117.

312

.1 –

0.4

28 √__

__

Rb/t

52

032

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-63

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1116

2519

.1 –

0.1

07L b

/ry

119

8960

0/(

L b/r

y)2

1126

12.4

– 0

.056

L b/r

y14

789

600

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1219

4232

.7 –

2.1

0 √__

__

Rb/t

11

3S

ame

as

1353

21.4

– 1

.19

√____

Rb/t

15

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2115

30.4

– 0

.594

d

__ t √__

_ L b

_

_

d

3411

800

/ ( d

__ t ) 2 L b

_

_

d

1417

19.5

– 0

.305

d

__ t √__

_ L b

_

_

d

4311

800

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1617

219

.1 –

0.2

05 √_

____

2L

bS

c _____

√___

I yJ

3830

2430

0/ 2L

bS

c _____

√___

I yJ

1118

612

.4 –

0.1

07 √_

____

2L

bS

c _____

√___

I yJ

5900

2430

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1516

7.5

22.8

– 0

.858

b/t

1315

2/(

b/t)

119

14.7

– 0

.442

b/t

1712

2/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1616

2422

.8 –

0.2

69b

/t42

484

/(b

/t)

1127

14.7

– 0

.139

b/t

5338

8/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.119

9.0

21.8

– 0

.892

√____

Rb/t

22

738

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

138.

814

.3 –

0.5

06 √__

__

Rb/t

52

038

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

2110

30.4

– 0

.905

b/t

2250

80/(

b/t)

2

1411

19.5

– 0

.465

b/t

2850

80/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1821

5330

.4 –

0.1

73h/

t88

1330

/(h/

t)

1460

19.5

– 0

.089

h/t

110

1070

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1921

122

30.4

– 0

.075

h/t

203

3080

/(h/

t)

1413

819

.5 –

0.0

38h/

t25

024

70/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

11.5

3816

.5 –

0.1

29h/

t85

3980

0/(

h/t)

2

6.5

469.

0 –

0.05

2h/

t11

539

800

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2111

.563

22.7

– 0

.178

a e/t

8554

700

/(a e

/t)2

6.5

8012

.4 –

0.0

72a e

/t11

554

700

/(a e

/t)2

VII-64 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

0A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6005

-T5

Ext

rusi

on

s u

p t

hro

ug

h 1

.00

0 in

. th

ick

6105

-T5

Ext

rusi

on

s u

p t

hro

ug

h 0

.50

0 in

. th

ick

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

19 2112

.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

219

8

Rou

nd o

r ov

al tu

bes

324

9

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

428

10W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

539

25S

hade

d ba

rs a

pply

to w

eld-

affe

cted

met

al

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

626

16F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

020

.2 –

0.1

26kL

/r66

5110

0/(

kL/r

)2

–0

7.4

– 0.

034

kL/r

144

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

821

2.4

23.1

– 0

.787

b/t

1015

4/(

b/t)

83.

88.

7 –

0.22

4b

/t19

85/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

212.

423

.1 –

0.7

87b

/t12

1970

/(b

/t)2

83.

88.

7 –

0.22

4b

/t26

1970

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

217.

623

.1 –

0.2

47b

/t33

491

/(b

/t)

812

8.7

– 0.

070

b/t

6227

1/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

211.

422

.1 –

0.7

99 √__

__

Rb/t

14

131

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

86.

68.

6 –

0.27

5 √__

__

Rb/t

45

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-65

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1121

2123

.9 –

0.1

24L b

/ry

7987

000

/(L b

/ry)

2

826

8.8

– 0.

034

L b/r

y17

287

000

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1225

2939

.3 –

2.7

0 √__

__

Rb/t

81

Sam

e as

962

15.2

– 0

.764

√____

Rb/t

18

4S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2814

40.5

– 0

.927

d

__ t √__

_ L b

_

_

d

2911

400

/ ( d

__ t ) 2 L b

_

_

d

1019

13.7

– 0

.182

d

__ t √__

_ L b

_

_

d

5011

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

2112

323

.9 –

0.2

38 √_

____

2L

bS

c _____

√___

I yJ

1680

2360

0/ 2L

bS

c _____

√___

I yJ

819

08.

8 –

0.06

5 √_

____

2L

bS

c _____

√___

I yJ

8070

2360

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1521

6.5

27.3

– 0

.930

b/t

1018

2/(

b/t)

89

10.3

– 0

.265

b/t

1410

1/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1621

2127

.3 –

0.2

92b

/t33

580

/(b

/t)

829

10.3

– 0

.083

b/t

6232

0/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.125

2.1

26.2

– 0

.944

√____

Rb/t

14

137

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

98.

210

.1 –

0.3

25 √__

__

Rb/t

45

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

289.

140

.5 –

1.4

1b

/t19

4930

/(b

/t)2

1012

13.7

– 0

.277

b/t

3349

30/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1828

4840

.5 –

0.2

70h/

t75

1520

/(h/

t)

1065

13.7

– 0

.053

h/t

129

881

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1928

110

40.5

– 0

.117

h/t

173

3500

/(h/

t)

1015

013

.7 –

0.0

23h/

t30

020

40/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1236

15.8

– 0

.101

h/t

6438

700

/(h/

t)2

4.5

506.

0 –

0.02

9h/

t13

938

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2112

–12

6653

200

/(a e

/t)2

4.5

938.

2 –

0.03

9a e

/t13

953

200

/(a e

/t)2

VII-66 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

1A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6061

-T6

Sh

eet,

-T65

1 P

late

up

th

rou

gh

4.0

00

in. t

hic

k60

61-T

6, -

T65

1 R

olle

d o

r C

old

Fin

ish

ed R

od

an

d B

ar60

61-T

6 D

raw

n T

ub

e

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

22 2112

.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

221

9

Rou

nd o

r ov

al tu

bes

325

10.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

428

12W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

543

25S

hade

d ba

rs a

pply

to a

ll th

ickn

esse

s w

ith fi

llers

518

3, 5

356,

or

5556

and

thic

knes

ses

< 0

.375

in. w

ith fi

llers

404

3, 5

554,

or

5654

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

629

16F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

020

.2 –

0.1

26kL

/r66

5110

0/(

kL/r

)2

–0

8.6

– 0.

043

kL/r

133

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

821

2.4

23.1

– 0

.787

b/t

1015

4/(

b/t)

93.

910

.2 –

0.2

82b

/t18

92/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

212.

423

.1 –

0.7

87b

/t12

1970

/(b

/t)2

93.

910

.2 –

0.2

82b

/t24

1970

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

217.

623

.1 –

0.2

47b

/t33

491

/(b

/t)

912

10.2

– 0

.089

b/t

5829

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

211.

422

.1 –

0.7

99 √__

__

Rb/t

14

131

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

96.

910

.0 –

0.3

35 √__

__

Rb/t

39

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-67

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1121

2123

.9 –

0.1

24L b

/ry

7987

000

/(L b

/ry)

2

926

10.2

– 0

.043

L b/r

y16

087

000

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1225

2939

.3 –

2.7

0 √__

__

Rb/t

81

Sam

e as

10.5

5717

.7 –

0.9

32 √__

__

Rb/t

16

7S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2814

40.5

– 0

.927

d

__ t √__

_ L b

_

_

d

2911

400

/ ( d

__ t ) 2 L b

_

_

d

1218

16.0

– 0

.230

d

__ t √__

_ L b

_

_

d

4611

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

2112

323

.9 –

0.2

38 √_

____

2L

bS

c _____

√___

I yJ

1680

2360

0/ 2L

bS

c _____

√___

I yJ

918

610

.2 –

0.0

82 √_

____

2L

bS

c _____

√___

I yJ

6940

2360

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1521

6.5

27.3

– 0

.930

b/t

1018

2/(

b/t)

99

12.0

– 0

.334

b/t

1810

9/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1621

2127

.3 –

0.2

92b

/t33

580

/(b

/t)

928

12.0

– 0

.105

b/t

5834

6/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.125

2.1

26.2

– 0

.944

√____

Rb/t

14

137

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

10.5

8.4

11.8

– 0

.396

√____

Rb/t

39

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

289.

140

.5 –

1.4

1b

/t19

4930

/(b

/t)2

1212

16.0

– 0

.350

b/t

3049

30/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1828

4840

.5 –

0.2

70h/

t75

1520

/(h/

t)

1262

16.0

– 0

.067

h/t

119

952

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1928

110

40.5

– 0

.117

h/t

173

3500

/(h/

t)

1214

416

.0 –

0.0

29h/

t28

022

00/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1236

15.8

– 0

.101

h/t

6438

700

/(h/

t)2

548

7.0

– 0.

036

h/t

129

3870

0/(

h/t)

2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2112

–12

6653

200

/(a e

/t)2

588

9.6

– 0.

050

a e/t

129

5320

0/(

a e/t)

2

VII-68 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

2A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6061

-T6

, -T

6510

, -T

6511

Ext

rusi

on

s60

61-T

6 S

tan

dar

d S

tru

ctu

ral S

hap

es, P

ipe

6351

-T5

Ext

rusi

on

s

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

19 2112

.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

219

9

Rou

nd o

r ov

al tu

bes

324

10.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

428

12W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

539

25S

hade

d ba

rs a

pply

to a

ll th

ickn

esse

s w

ith fi

llers

518

3, 5

356,

or

5556

and

thic

knes

ses

< 0

.375

in. w

ith fi

llers

404

3, 5

554,

or

5654

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

626

16F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

020

.2 –

0.1

26kL

/r66

5110

0/(

kL/r

)2

–0

8.6

– 0.

043

kL/r

133

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

821

2.4

23.1

– 0

.787

b/t

1015

4/(

b/t)

93.

910

.2 –

0.2

82b

/t18

92/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

212.

423

.1 –

0.7

87b

/t12

1970

/(b

/t)2

93.

910

.2 –

0.2

82b

/t24

1970

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

217.

623

.1 –

0.2

47b

/t33

491

/(b

/t)

912

10.2

– 0

.089

b/t

5829

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

211.

422

.1 –

0.7

99 √__

__

Rb/t

14

131

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

96.

910

.0 –

0.3

35 √__

__

Rb/t

39

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-69

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1121

2123

.9 –

0.1

24L b

/ry

7987

000

/(L b

/ry)

2

926

10.2

– 0

.043

L b/r

y16

087

000

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1225

2939

.3 –

2.7

0 √__

__

Rb/t

81

Sam

e as

10.5

5717

.7 –

0.9

32 √__

__

Rb/t

16

7S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2814

40.5

– 0

.927

d

__ t √__

_ L b

_

_

d

2911

400

/ ( d

__ t ) 2 L b

_

_

d

1218

16.0

– 0

.230

d

__ t √__

_ L b

_

_

d

4611

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

2112

323

.9 –

0.2

38 √_

____

2L

bS

c _____

√___

I yJ

1680

2360

0/ 2L

bS

c _____

√___

I yJ

918

610

.2 –

0.0

82 √_

____

2L

bS

c _____

√___

I yJ

6940

2360

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1521

6.5

27.3

– 0

.930

b/t

1018

2/(

b/t)

99

12.0

– 0

.334

b/t

1810

9/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1621

2127

.3 –

0.2

92b

/t33

580

/(b

/t)

928

12.0

– 0

.105

b/t

5834

6/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.125

2.1

26.2

– 0

.944

√____

Rb/t

14

137

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

10.5

8.4

11.8

– 0

.396

√____

Rb/t

39

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

289.

140

.5 –

1.4

1b

/t19

4930

/(b

/t)2

1212

16.0

– 0

.350

b/t

3049

30/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1828

4840

.5 –

0.2

70h/

t75

1520

/(h/

t)

1262

16.0

– 0

.067

h/t

119

952

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1928

110

40.5

– 0

.117

h/t

173

3500

/(h/

t)

1214

416

.0 –

0.0

29h/

t28

022

00/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1236

15.8

– 0

.101

h/t

6438

700

/(h/

t)2

548

7.0

– 0.

036

h/t

129

3870

0/(

h/t)

2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2112

–12

6653

200

/(a e

/t)2

588

9.6

– 0.

050

a e/t

129

5320

0/(

a e/t)

2

VII-70 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

3A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6063

-T5

Ext

rusi

on

s u

p t

hro

ug

h 0

.50

0 in

. th

ick

6063

-T52

Ext

rusi

on

s u

p t

hro

ug

h 1

.00

0 in

. th

ick

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

11.5

9.5

8.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

29.

54.

8

Rou

nd o

r ov

al tu

bes

311

.55.

5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

412

.56.

5W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

523

17S

hade

d ba

rs a

pply

to w

eld-

affe

cted

mat

eria

l

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

615

11.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

08.

9 –

0.03

7kL

/r99

5110

0/(

kL/r

)2

–0

4.5

– 0.

016

kL/r

185

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

89.

51.

410

.0 –

0.2

25b

/t16

101

/(b

/t)

4.8

3.3

5.2

– 0.

102

b/t

2566

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

9.5

1.4

10.0

– 0

.225

b/t

1819

70/(

b/t)

2

4.8

3.3

5.2

– 0.

102

b/t

3419

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

9.5

4.6

10.0

– 0

.071

b/t

5032

3/(

b/t)

4.8

105.

2 –

0.03

2b

/t81

209

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

9.5

0.3

9.8

– 0.

271

√____

Rb/t

28

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

4.8

5.4

5.2

– 0.

140

√____

Rb/t

80

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-71

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

119.

523

10.5

– 0

.036

L b/r

y11

987

000

/(L b

/ry)

2

4.8

275.

3 –

0.01

6L b

/ry

222

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1211

.544

17.5

– 0

.917

√____

Rb/t

13

9S

ame

as

5.5

819.

2 –

0.38

9 √__

__

Rb/t

26

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

12.5

1817

.1 –

0.2

56 d

__

t √___

L b

__

d

4511

400

/ ( d

__ t ) 2 L b

_

_

d

6.5

228.

1 –

0.08

3 d

__

t √___

L b

__

d

6511

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

9.5

138

10.5

– 0

.070

√_____

2L

bS

c _____

√___

I yJ

3820

2360

0/ 2L

bS

c _____

√___

I yJ

4.8

203

5.3

– 0.

030

√_____

2L

bS

c _____

√___

I yJ

1340

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

159.

58.

111

.8 –

0.2

66b

/t16

120

/(b

/t)

4.8

116.

1 –

0.12

1b

/t25

77/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

169.

526

11.8

– 0

.083

b/t

5038

2/(

b/t)

4.8

346.

1 –

0.03

8b

/t81

247

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.111

.50.

811

.6 –

0.3

20 √__

__

Rb/t

28

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

5.5

7.2

6.1

– 0.

165

√____

Rb/t

80

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

12.5

1217

.1 –

0.3

89b

/t29

4930

/(b

/t)2

6.5

148.

1 –

0.12

6b

/t43

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1812

.561

17.1

– 0

.074

h/t

115

986

/(h/

t)

6.5

748.

1 –

0.02

4h/

t16

767

8/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1912

.514

117

.1 –

0.0

32h/

t27

022

80/(

h/t)

6.5

172

8.1

– 0.

010

h/t

390

1570

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

5.5

446.

9 –

0.02

9h/

t98

3870

0/(

h/t)

2

2.8

573.

6 –

0.01

3h/

t18

138

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

215.

597

9.4

– 0.

039

a e/t

9853

200

/(a e

/t)2

2.8

116

4.9

– 0.

018

a e/t

181

5320

0/(

a e/t)

2

VII-72 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

4A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6063

-T6

Ext

rusi

on

s an

d P

ipe

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

15 158.

5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

215

4.8

Rou

nd o

r ov

al tu

bes

318

5.5

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

420

6.5

Whi

te b

ars

appl

y to

unw

elde

d m

etal

BE

AR

ING

On

rivet

s an

d bo

lts

531

17S

hade

d ba

rs a

pply

to w

eld-

affe

cted

mat

eria

l

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

621

11.5

For

tube

s w

ith c

ircum

fere

ntia

l wel

ds, S

ectio

ns 3

.4.1

0, 3

.4.1

2, a

nd

3.4.

16.1

app

ly fo

r R

b /

t < 2

0

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

014

.2 –

0.0

74kL

/r78

5110

0/(

kL/r

)2

–0

4.5

– 0.

016

kL/r

185

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

815

2.1

16.1

– 0

.458

b/t

1212

9/(

b/t)

4.8

3.3

5.2

– 0.

102

b/t

2566

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

152.

116

.1 –

0.4

58b

/t14

1970

/(b

/t)2

4.8

3.3

5.2

– 0.

102

b/t

3419

70/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

156.

716

.1 –

0.1

44b

/t39

410

/(b

/t)

4.8

105.

2 –

0.03

2b

/t81

209

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

150.

915

.6 –

0.5

02 √__

__

Rb/t

18

931

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

4.8

5.4

5.2

– 0.

140

√____

Rb/t

80

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-73

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1115

2216

.7 –

0.0

73L b

/ry

9487

000

/(L b

/ry)

2

4.8

275.

3 –

0.01

6L b

/ry

222

8700

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1218

3527

.7 –

1.7

0 √__

__

Rb/t

10

2S

ame

as

5.5

819.

2 –

0.38

9 √__

__

Rb/t

26

0S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2015

27.9

– 0

.531

d

__ t √__

_ L b

_

_

d

3511

400

/ ( d

__ t ) 2 L b

_

_

d

6.5

228.

1 –

0.08

3 d

__

t √___

L b

__

d

6511

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

1513

016

.7 –

0.1

40 √_

____

2L

bS

c _____

√___

I yJ

2400

2360

0/ 2L

bS

c _____

√___

I yJ

4.8

203

5.3

– 0.

030

√_____

2L

bS

c _____

√___

I yJ

1340

023

600

/ 2LbS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1515

7.2

19.0

– 0

.541

b/t

1215

2/(

b/t)

4.8

116.

1 –

0.12

1b

/t25

77/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1615

2319

.0 –

0.1

70b

/t39

484

/(b

/t)

4.8

346.

1 –

0.03

8b

/t81

247

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.118

1.6

18.5

– 0

.593

√____

Rb/t

18

937

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

5.5

7.2

6.1

– 0.

165

√____

Rb/t

80

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

2010

27.9

– 0

.808

b/t

2349

30/(

b/t)

2

6.5

148.

1 –

0.12

6b

/t43

4930

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1820

5327

.9 –

0.1

55h/

t90

1260

/(h/

t)

6.5

748.

1 –

0.02

4h/

t16

767

8/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1920

123

27.9

– 0

.067

h/t

208

2910

/(h/

t)

6.5

172

8.1

– 0.

010

h/t

390

1570

/(h/

t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

8.5

3911

.0 –

0.0

59h/

t77

3870

0/(

h/t)

2

2.8

573.

6 –

0.01

3h/

t18

138

700

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

218.

5–

8.5

7853

200

/(a e

/t)2

2.8

116

4.9

– 0.

018

a e/t

181

5320

0/(

a e/t)

2

VII-74 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

5A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

6351

-T6

Ext

rusi

on

s

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

22 2212

.5

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

222

9

Rou

nd o

r ov

al tu

bes

326

11

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

429

12W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

543

25S

hade

d ba

rs a

pply

to w

eld-

affe

cted

mat

eria

l

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

629

16F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

021

.4 –

0.1

38kL

/r64

5110

0/(

kL/r

)2

–0

8.6

– 0.

043

kL/r

133

5110

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

822

2.4

24.5

– 0

.860

b/t

1015

9/(

b/t)

93.

910

.2 –

0.2

82b

/t18

92/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

222.

424

.5 –

0.8

60b

/t12

1970

/(b

/t)2

93.

910

.2 –

0.2

82b

/t24

1970

/(b

/t)2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

227.

824

.5 –

0.2

70b

/t32

506

/(b

/t)

912

10.2

– 0

.089

b/t

5829

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

221.

523

.5 –

0.8

63 √__

__

Rb/t

13

431

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

96.

910

.0 –

0.3

35 √__

__

Rb/t

39

031

90/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-75

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1122

2125

.3 –

0.1

36L b

/ry

7787

000

/(L b

/ry)

2

926

10.2

– 0

.043

L b/r

y16

087

000

/(L b

/ry)

2

Rou

nd o

r ov

al tu

bes

1226

2841

.6 –

2.9

2 √__

__

Rb/t

78

Sam

e as

1157

17.7

– 0

.932

√____

Rb/t

16

7S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

2914

43.0

– 1

.02

d

__ t √__

_ L b

_

_

d

2811

400

/ ( d

__ t ) 2 L b

_

_

d

1218

16.0

– 0

.230

d

__ t √__

_ L b

_

_

d

4611

400

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

2212

225

.3 –

0.2

60 √_

____

2L

bS

c _____

√___

I yJ

1590

2360

0/ 2L

bS

c _____

√___

I yJ

918

610

.2 –

0.0

82 √_

____

2L

bS

c _____

√___

I yJ

6940

2360

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1522

6.4

29.0

– 1

.02

b/t

1018

7/(

b/t)

98.

812

.0 –

0.3

34b

/t18

109

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1622

2129

.0 –

0.3

19b

/t32

598

/(b

/t)

928

12.0

– 0

.105

b/t

5834

6/(

b/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.126

2.1

27.7

– 1

.02

√____

Rb/t

13

437

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

118.

411

.8 –

0.3

96 √__

__

Rb/t

39

037

80/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

299.

043

.0 –

1.5

5b

/t19

4930

/(b

/t)2

1212

16.0

– 0

.350

b/t

3049

30/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1829

4743

.0 –

0.2

96h/

t73

1560

/(h/

t)

1262

16.0

– 0

.067

h/t

119

950

/(h/

t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1929

108

43.0

– 0

.128

h/t

168

3610

/(h/

t)

1214

416

.0 –

0.0

29h/

t28

022

00/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1335

16.8

– 0

.110

h/t

6338

700

/(h/

t)2

548

7.0

– 0.

036

h/t

129

3870

0/(

h/t)

2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2113

–13

6453

200

/(a e

/t)2

588

9.6

– 0.

050

a e/t

129

5320

0/(

a e/t)

2

VII-76 January 2005

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le S

tres

sTa

ble

2-2

6A

LLO

WA

BL

E S

TR

ES

SE

S F

OR

B

UIL

DIN

G T

YP

E S

TR

UC

TU

RE

S

7005

-T53

Ext

rusi

on

s

TE

NS

ION

, axi

alA

ny te

nsio

n m

embe

rgr

oss

sect

ion

net s

ectio

n1

26 2721

TE

NS

ION

IN

BE

AM

S,

extr

eme

fiber

, ne

t sec

tion

Fla

t ele

men

ts in

uni

form

tens

ion

226

14.5

Rou

nd o

r ov

al tu

bes

331

17

Fla

t ele

men

ts in

ben

ding

in th

eir

own

plan

e,

sym

met

ric s

hape

s

435

19W

hite

bar

s ap

ply

to u

nwel

ded

met

al

BE

AR

ING

On

rivet

s an

d bo

lts

551

41S

hade

d ba

rs a

pply

to w

eld-

affe

cted

mat

eria

l

On

flat s

urfa

ces

and

pins

and

on

bolts

in s

lotte

d ho

les

634

27F

or tu

bes

with

circ

umfe

rent

ial w

elds

, Sec

tions

3.4

.10,

3.4

.12,

and

3.

4.16

.1 a

pply

for

Rb

/ t <

20

Typ

e o

f S

tres

sTy

pe

of

Mem

ber

or

Ele

men

tS

ec.

3.4.

Allo

wab

le

Str

ess,

S <

S1

S1

Allo

wab

le S

tres

s,S

1 <

S <

S2

S2

Allo

wab

le S

tres

s,

S >

S2

CO

MP

RE

SS

ION

IN

CO

LUM

NS

, ax

ial

All

colu

mns

7–

025

.1 –

0.1

71kL

/r60

5310

0/(

kL/r

)2

–0

14.2

– 0

.089

kL/r

106

5310

0/(

kL/r

)2

CO

MP

RE

SS

ION

IN

CO

LUM

N

ELE

ME

NT

S,

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

buc

klin

g ab

out a

sym

met

ry a

xis

826

2.6

28.8

– 1

.08

b/t

9.4

175

/(b

/t)

14.5

4.1

17.0

– 0

.596

b/t

1412

1/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edge

–

colu

mns

not

buc

klin

g ab

out a

sym

met

ry a

xis

8.1

262.

628

.8 –

1.0

8b

/t11

2040

/(b

/t)2

14.5

4.1

17.0

– 0

.596

b/t

1920

40/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

9

268.

228

.8 –

0.3

37b

/t30

559

/(b

/t)

14.5

1317

.0 –

0.1

87b

/t45

386

/(b

/t)

Fla

t ele

men

ts s

uppo

rted

on

one

edg

e an

d w

ith

stiff

ener

on

othe

r ed

ge

9.1

see

Par

t IA

Sec

tion

3.4.

9.1

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

an

inte

rmed

iate

stif

fene

r

9.2

see

Par

t IA

Sec

tion

3.4.

9.2

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

10

261.

727

.4 –

1.0

5 √__

__

Rb/t

12

133

20/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

14.5

7.7

16.3

– 0

.638

√____

Rb/t

43

033

20/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

January 2005 VII-77

CO

MP

RE

SS

ION

IN

BE

AM

S,

extr

eme

fiber

, gr

oss

sect

ion

Sin

gle

web

sha

pes

1126

2129

.7 –

0.1

69L b

/ry

7290

400

/(L b

/ry)

2

14.5

2616

.8 –

0.0

88L b

/ry

127

9040

0/(

L b/r

y)2

Rou

nd o

r ov

al tu

bes

1230

2648

.6 –

3.5

5 √__

__

Rb/t

72

Sam

e as

1745

28.9

– 1

.77

√____

Rb/t

12

3S

ectio

n 3.

4.10

Sol

id r

ecta

ngul

ar a

nd r

ound

sec

tions

13

3413

50.8

– 1

.28

d

__ t √__

_ L b

_

_

d

2611

900

/ ( d

__ t ) 2 L b

_

_

d

1916

26.7

– 0

.487

d

__ t √__

_ L b

_

_

d

3711

900

/ ( d

__ t ) 2 L b

_

_

d

Tubu

lar

shap

es

14

2612

429

.7 –

0.3

24 √_

____

2L

bS

c _____

√___

I yJ

1410

2450

0/ 2L

bS

c _____

√___

I yJ

14.5

178

16.8

– 0

.169

√_____

2L

bS

c _____

√___

I yJ

4380

2450

0/ 2L

bS

c _____

√___

I yJ

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n

unifo

rm

com

pres

sion

),

gros

s se

ctio

n

Fla

t ele

men

ts s

uppo

rted

on

one

edge

1526

6.3

34.1

– 1

.27

b/t

9.4

207

/(b

/t)

14.5

7.8

20.1

– 0

.704

b/t

1014

3/(

b/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1626

2034

.1 –

0.3

99b

/t30

661

/(b

/t)

14.5

2520

.1 –

0.2

21b

/t45

456

/(b

/t)

Cur

ved

elem

ents

sup

port

ed o

n bo

th e

dges

16

.130

2.4

32.4

– 1

.24

√____

Rb/t

12

139

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

179.

019

.3 –

0.7

54 √__

__

Rb/t

43

039

30/ ( R

b

___ t

) ( 1 +

√__

__

Rb/t

_____

35

) 2

Fla

t ele

men

ts s

uppo

rted

on

on

e ed

ge a

nd w

ith s

tiffe

ner

on

oth

er e

dge

16.2

see

Par

t IA

Sec

tion

3.4.

16.2

Fla

t ele

men

ts s

uppo

rted

on

both

ed

ges

and

with

an

in

term

edia

te s

tiffe

ner

16.3

see

Par

t IA

Sec

tion

3.4.

16.3

CO

MP

RE

SS

ION

IN

BE

AM

E

LEM

EN

TS

, (e

lem

ent i

n be

ndin

g in

ow

n pl

ane)

, gro

ss

sect

ion

Fla

t ele

men

ts s

uppo

rted

on

tens

ion

edge

, co

mpr

essi

on e

dge

free

17

348.

750

.8 –

1.9

5b

/t17

5130

/(b

/t)2

1911

26.7

– 0

.741

b/t

2451

30/(

b/t)

2

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

1834

4550

.8 –

0.3

73h/

t68

1730

/(h/

t)

1955

26.7

– 0

.142

h/t

9412

60/(

h/t)

Fla

t ele

men

ts s

uppo

rted

on

both

edg

es

and

with

a lo

ngitu

dina

l stif

fene

r

1934

105

50.8

– 0

.161

h/t

158

4000

/(h/

t)

1912

726

.7 –

0.0

61h/

t21

729

00/(

h/t)

SH

EA

R IN

E

LEM

EN

TS

, gr

oss

sect

ion

Uns

tiffe

ned

flat e

lem

ents

sup

port

ed

on b

oth

edge

s 20

1534

20.3

– 0

.143

h/t

5840

200

/(h/

t)2

8.5

4311

.7 –

0.0

76h/

t10

240

200

/(h/

t)2

Stif

fene

d fla

t ele

men

ts s

uppo

rted

on

bot

h ed

ges

2115

–15

6055

300

/(a e

/t)2

8.5

7316

.0 –

0.1

05a e

/t10

255

300

/(a e

/t)2

VII-78 January 2005

Table 3-1RECOMMENDED MINIMUM BEND RADII FOR 90º COLD BENDS

OF SHEET AND PLATE ① ② ③ ④ ⑤

Alloy TemperRADII FOR VARIOUS THICKNESSES EXPRESSED IN TERMS OF THICKNESS “t”

1/64 in. 1/32 in. 1/16 in. 1/8 in. 3/16 in. ¼ in. 3/8 in. ½ in.

1100

OH12H14H16H18

00001t

000½t1t

0001t1½t

0½t1t1½t2½t

½t1t1t1½t3t

1t1t1½t2½t3½t

1t1½t2t3t4t

1½t2t2½t4t4½t

2014

OT3T4T6

01½t1½t3t

02½t2½t4t

03t3t4t

½t4t4t5t

1t5t5t6t

1t5t5t8t

2½t6t6t8½t

4t7t7t9½t

2024

OT3T361⑥ T4T81T861⑥

02½t3t2½t4½t5t

03t4t3t5½t6t

04t5t4t6t7t

½t5t6t5t7½t8½t

1t5t6t5t8t9½t

1t6t8t6t9t10t

2½t7t8½t7t10t11½t

4t7½t9½t7½t10½t11½t

2036 T4 . . 1t 1t . . . . . . . . . .

3003

OH12H14H16H18

000½t1t

0001t1½t

0001t2t

0½t1t1½t2½t

½t1t1t2½t3½t

1t1t1½t3t4½t

1t1½t2t3½t5½t

1½t2t2½t4t6½t

3004

OH32H34H36H38

0001t1t

001t1t1½t

0½t1t1½t2½t

½t1t1½t2½t3t

1t1t1½t3t4t

1t1½t2½t3½t5t

1t1½t2½t4t5½t

1½t2t3t4½t6½t

3105 H25 ½t ½t ½t . . . . . . . . . .

5005

OH12H14H16H18H32H34H36H38

000½t1t00½t1t

0001t1½t001t1½t

0001t2t001t2t

0½t1t1½t2½t½t1t1½t2½t

½t1t1½t2½t3½t1t1½t2½t3½t

1t1t1½t3t4½t1t1½t3t4½t

1t1½t2t3½t5½t1½t2t3½t5½t

1½t2t2½t4t6½t2t2½t4t6½t

5050

OH32H34H36H38

0001t1t

0001t1½t

001t1½t2½t

½t1t1½t2t3t

1t1t1½t2½t4t

1t1½t2t3t5t

1½t. .. .. .. .

1½t. .. .. .. .

5052

OH32H34H36H38

0001t1t

001t1t1½t

01t1½t1½t2½t

½t1½t2t2½t3t

1t1½t2t3t4t

1t1½t2½t3½t5t

1½t1½t2½t4t5½t

1½t2t3t4½t6½t

5083OH321

. .

. .. .. .

½t1t

1t1½t

1t1½t

1t1½t

1½t2t

1½t2½t

5086

OH32H34H36

00½t1½t

0½t1t2t

½t1t1½t2½t

1t1½t2t3t

1t1½t2½t3½t

1t2t3t4t

1½t2½t3½t4½t

1½t3t4t5t

5154

OH32H34H36H38

00½t1t1½t

0½t1t1½t2½t

½t1t1½t2t3t

1t1½t2t3t4t

1t1½t2½t3½t5t

1t2t3t4t5t

1½t2½t3½t4½t6½t

1½t3½t4t5t6½t

January 2005 VII-79

Table 3-1RECOMMENDED MINIMUM BEND RADII FOR 90º COLD BENDS

OF SHEET AND PLATE ① ② ③ ④ ⑤ (Continued)

Alloy TemperRADII FOR VARIOUS THICKNESSES EXPRESSED IN TERMS OF THICKNESS “t”

1/64 in. 1/32 in. 1/16 in. 1/8 in. 3/16 in. ¼ in. 3/8 in. ½ in.

5252H25H28

01t

01½t

1t2½t

2t3t

. .

. .. .. .

. .

. .. .. .

5254

OH32H34H36H38

00½t1t1½t

0½t1t1½t2½t

½t1t1½t2t3t

1t1½t2t3t4t

1t1½t2½t3½t5t

1t2t3t4t5t

1½t2½t3½t4½t6½t

1½t3½t4t5t6½t

5454OH32H34

0½t½t

½t½t1t

1t1t1½t

1t2t2t

1t2t2½t

1½t2½t3t

1½t3t3½t

2t4t4t

5456OH321

. .

. .. .. .

1t. .

1t2t

1½t2t

1½t2½t

2t3t

2t3½t

5457 O 0 0 0 . . . . . . . . . .

5652

OH32H34H36H38

0001t1t

001t1t1½t

01t1½t1½t2½t

½t1½t2t2½t3t

1t1½t2t3t4t

1t1½t2½t3½t5t

1½t1½t2½t4t52t

1½t2t3t4½t62t

5657H25H28

01t

01½t

02½t

1t3t

. .

. .. .. .

. .

. .. .. .

6061OT4T6

001t

001t

01t1½t

1t1½t2½t

1t2½t3t

1t3t3½t

1½t3½t4½t

2t4t5t

7050 T7 . . . . . . . . . . 8t 9t 9½t

7072OH14H18

001t

001t

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

. .

7075OT6

03t

04t

1t5t

1t6t

1½t6t

2½t8t

3½t9t

4t9½t

7178OT6

03t

04t

1t5t

1½t6t

1½t6t

2½t8t

3½t9t

4t9½t

① The radii listed are the minimum recommended for bending sheets and plates without fracturing in a standard press brake with air bend dies. Other types of bending operations may require larger radii or permit smaller radii. The minimum permissible radii will also vary with the design and condition of the tooling.

② Alclad sheet in the heat-treatable alloys can be bent over slightly smaller radii than the corresponding tempers of the bare alloy.

③ Heat-treatable alloys can be formed over appreciably smaller radii immediately after solution heat treatment.

④ The H112 temper (applicable to non-heat treatable alloys) is supplied in the as-fabricated condition without special property control but usually can be formed over radii applicable to the H14 (or H34) temper or smaller.

⑤ The reference test method is ASTM E290.

⑥ Tempers T361 and T861 formerly designated T36 and T86, respectively.

VII-80 January 2005

Table 3-2RECOMMENDED MINIMUM INSIDE RADII FOR 180º COLD BENDS, WIRE AND ROD*

Table 3-3SHEET THICKNESS FOR 180º COLD BENDING (METAL TO METAL)*

January 2005 VII-81

Tab

le 3

-4D

EV

ELO

PE

D L

EN

GT

H O

F M

AT

ER

IAL

FO

R 9

0º B

EN

DS

VII-82 January 2005

Tab

le 3

-4D

EV

ELO

PE

D L

EN

GT

H O

F M

AT

ER

IAL

FO

R 9

0º B

EN

DS

(C

on

tin

ued

)

January 2005 VII-83

Table 4-1ALLOWABLE UNIFORM BEAM LOADS*

Aluminum Association Standard Channels, 6061-T6

*Total uniformly distributed load (W) on a simply supported single span braced against twisting, calculated using the section properties listed in Part VI, Table 4, the allowable stresses for Building and Similar Type Structures (Table 2-22) and effective ry (Section 4.9.1) of the Aluminum Association’s Specification For Aluminum Structures. Since the actual conditions of use can affect allowable loads, the information in Table 4-1 is intended for use by engineers and architects qualified to assess these effects.

VII-84 January 2005

Table 4-2ALLOWABLE UNIFORM BEAM LOADS*

Aluminum Association Standard I-Beams, 6061-T6

Total uniformly distributed load (W) on a simply supported single span, cal-culated using the section properties listed in Part VI, Table 8, the allowable stresses for Building and Similar Type Structures (Table 2-22) and effective ry (Section 4.9.1) of the Aluminum Association’s Specification for Aluminum Structures. Since the actual conditions of use can effect allowable loads, the information in Table 4-2 is intended for use by engineers and architects quali-fied to assess these effects.

January 2005 VII-85

Table 4-3ALLOWABLE LOADS ON ALUMINUM TREAD PLATE

Tread Plate is sheet or plate having a raised figure pattern on one surface to provide improved traction

VII-86 January 2005

Table 4-4MAXIMUM RECOMMENDED SPANS (IN.) –

COMMERCIAL CORRUGATED AND V-BEAM ROOFING AND SIDING

Design Load (psf)

Number of Equal Spans

One Two Three

Strength Deflection Strength Deflection Strength Deflection

Corrugated Roofing and Siding – 0.024”

20 79 61 79 – 88 76

25 70 57 70 – 79 70

30 64 54 64 – 72 66

35 60 51 60 – 67 63

40 56 49 56 – 63 60

45 53 47 53 – 59 58

50 50 45 50 – 56 56

Corrugated Roofing and Siding – 0.032”

20 92 67 92 90 102 83

25 82 63 82 – 92 77

30 75 59 75 – 84 73

35 70 56 70 – 78 69

40 65 54 65 – 73 66

45 62 52 62 – 69 64

50 58 50 58 – 65 62

V-Beam Roofing and Siding – 0.032”, 4 7/8” Pitch

20 128 110 128 – 144 136

25 115 102 115 – 129 127

30 105 97 105 – 118 –

35 98 92 98 – 109 –

40 92 88 92 – 102 –

45 86 85 86 – 97 –

50 82 82 82 – 92 –

55 78 – 78 – 87 –

60 75 – 75 – 84 –


20 150 118 150 – 167 146

25 134 110 134 – 150 136

30 123 104 123 – 137 128

35 114 99 114 – 127 122

40 107 94 107 – 119 117

45 101 91 101 – 113 112

50 96 88 96 – 107 –

55 91 85 91 – 102 –

60 87 83 87 – 98 –

See last page of table for footnotes.

January 2005 VII-87

Table 4-4MAXIMUM RECOMMENDED SPANS (IN.) –

COMMERCIAL CORRUGATED AND V-BEAM ROOFING AND SIDING (Continued)

Design Load (psf)

Number of Equal SpansOne Two Three

Strength Deflection Strength Deflection Strength DeflectionV-Beam Roofing and Siding – 0.050”, 4 7/8” Pitch

20 171 127 171 170 191 157

25 154 118 154 – 172 146

30 141 111 141 – 158 138

35 131 106 131 – 146 131

40 122 102 122 – 137 125

45 116 98 116 – 129 121

50 110 94 110 – 123 117

55 105 92 105 – 117 113

60 100 89 100 – 112 110


20 128 114 128 – 143 141

25 115 106 115 – 129 –

30 105 100 105 – 118 –

35 98 95 98 – 109 –

40 91 91 91 – 102 –

45 86 – 86 – 96 –

50 82 – 82 – 91 –

55 78 – 78 – 87 –

60 75 – 75 – 84 –


20 153 123 153 – 171 151

25 137 114 137 – 154 141

30 126 108 126 – 141 133

35 117 102 117 – 130 126

40 109 98 109 – 122 121

45 103 94 103 – 115 –

50 98 91 98 – 110 –

55 93 88 93 – 104 –

60 90 86 90 – 100 –


20 176 132 176 176 197 163

25 158 123 158 – 177 151

30 145 116 145 – 162 143

35 134 110 134 – 150 136

40 126 105 126 – 141 130

45 119 101 119 – 133 125

50 113 98 113 – 126 121

55 108 95 108 – 120 117

60 103 92 103 – 115 114

1. Maximum recommended spans are calculated in accordance with the Specification for Aluminum Structures, Allowable Stress Design, for building type structures.

2. Material is Alclad 3004-H151, -H261, or –H361 (which are stucco embossed tempers) or Alclad 3004-H16. Dimensions are given in Part VI Table 25 and section properties are given in Part VI Table 26.

3. The deflection limit is 1/60 of the span.

VII-88 January 2005

Table 4-5MAXIMUM RECOMMENDED SPANS (IN.) – COMMERCIAL RIBBED SIDING

Design Load (psf)

Number of Equal SpansOne Two Three

Strength1 Strength2 Defl1 Defl2 Strength1 Strength2 Defl1 Defl2 Strength1 Strength2 Defl1 Defl2

Ribbed Siding – 0.032”, 4” Pitch

20 98 101 85 101 98 – 113 110 106

25 88 91 79 91 88 – 101 98 98

30 80 83 75 83 80 – 93 90 93

35 75 77 71 77 75 – 86 83 –

40 70 72 68 72 70 – 80 78 –

45 66 68 66 68 66 – 76 74 –

50 63 64 63 64 63 – 72 70 –


20 118 120 92 120 118 – 134 132 113

25 106 107 85 107 106 – 120 118 105

30 97 98 80 98 97 – 110 108 99

35 90 91 76 91 90 – 102 100 94

40 84 85 73 85 84 – 95 94 90

45 79 80 70 80 79 – 90 89 87

50 75 76 68 76 75 – 85 84 84


20 62 77 74 – 77 62 – – 78 69 – –

25 56 69 – – 69 56 – – 70 62 – –

30 51 63 – – 63 51 – – 64 57 – –

35 47 59 – – 59 47 – – 59 53 – –

40 44 55 – – 55 44 – – 55 49 – –

45 42 52 – – 52 42 – – 52 47 – –

50 40 49 – – 49 40 – – 49 44 – –


20 75 91 80 84 91 75 – – 94 84 – –

25 67 82 74 79 82 67 – – 84 75 – –

30 62 75 70 74 75 62 – – 77 69 – –

35 57 69 67 – 69 57 – – 71 64 – –

40 54 65 64 – 65 54 – – 67 60 – –

45 51 61 – – 61 51 – – 63 56 – –

50 48 58 – – 58 48 – – 60 54 – –

1. Wide flat is on loaded side; load is toward neutral axis.2. Narrow flat is on loaded side; load is toward neutral axis.3. Maximum recommended spans are calculated in accordance with the Specification for Aluminum Structures, Allowable Stress Design, for

building type structures.4. Material is Alclad 3004-H151, -H261, or –H361 (which are stucco embossed tempers) or Alclad 3004-H16. Dimensions are given in Part VI

Table 25 and section properties are given in Part VI Table 26.5. The deflection limit is 1/60 of the span.

January 2005 VII-89

Table 5-1LOAD REQUIRED TO PRODUCE FAILURE OF A SOLID RIVET IN SINGLE SHEAR-LB

Calculated on Basis of Expected Shear Strengths Given Below and SingleShear Areas Given in Tables 5-8 and 5-9

Table 5-2REDUCTION IN SHEAR STRENGTH OF RIVETS

RESULTING FROM THEIR USE IN THIN SHEETS AND SHAPES

VII-90 January 2005

Table 5-3TENSILE AND SINGLE-SHEAR LOADS FOR 2024-T4 AND 7075-T73 MACHINE SCREWS

All values calculated using the tensile and shear strengths given in Part V, Table 5

NominalSize

BasicMajor

DiameterThreadsper in.*

NominalMinor

Diameterin.

Tensile Strength†lb

Single-Shear Strength†lb

2024-T4 7075-T73 2024-T4 7075-T73

4

5

6

8

10

12

¼

5/16

3/8

0.112

0.125

0.138

0.164

0.190

0.216

0.250

0.3125

0.375

40 UNC48 UNF40 UNC44 UNF




16 UNC24 UNF

0.08050.08570.09350.0964

0.09890.10650.12480.1291

0.13790.15080.16390.1712

0.18760.20520.24310.2603

0.29700.3228

316357425453

476552759812

9261,1001,3101,430

1,7102,0502,8803,300

4,3005,070

346392466496

522606832890

1,0201,2101,4401,570

1,8802,2503,1603,620

4,7105,570

188213254270

284330453484

553661781852

1,0201,2201,7201,970

2,5603,030

209237282299

315365502537

612732865944

1,1301,3601,9002,180

2,8403,350

* UNC = Unified National Coarse Thread Series; UNF = Unifed National Fine Thread Series. All are Class 2A, External Threads.

† Area at root of screw threads used. This area computed for each fastener size using the Nominal Minor Diameter for External Threads (Class 2A) given in ANSI Standard B1.1.Allowable loads are obtained by dividing values in this table by safety factors of 2.34 for building and 2.64 for bridges.

January 2005 VII-91

Table 5-4SINGLE-SHEAR LOADS FOR

2024-T4 AND 7075-T73 SHEET METAL SCREWS


NominalSize

Single Shear Strengths in lb *

Type A screws Type AB and B screws

2024-T4 7075-T73 2024-T4 7075-T73

45

67

810

1214

177235

268339

391461

698925

196260

297376

433511

7731,025

195235

285345

391529

716995

216260

316382

433586

7931,100

Allowable loads are obtained by dividing values in this table by safety factors of 2.34 for building and 2.64 for bridges.

Table 5-5TENSILE AND SINGLE-SHEAR STRENGTHS FOR 2024-T4 AND 7075-T73 BOLT AND CAP SCREWS


NominalSize

BasicMajorDiam.

in.

Threadsperin.*

Tensile Strength, lb†

Single-Shear Strength, lb

Threads in Shear Plane † Shank in Shear Plane ‡

2024-T4 7075-T73 2024-T4 7075-T73 2024-T4 7075-T73

10¼

5/16

3/8

½5/8

¾7/8

1

0.1900.2500.3125

0.3750.5000.625

0.7500.8751.000

242018

161311

1098

9261,7102,880

4,3007,95012,800

19,10026,40034,700

1,0201,8803,160

4,7108,72014,000

20,90029,00038,100

5531,0201,720

2,5604,7507,620

11,40015,80020,700

6121,1301,900

2,8405,2608,440

12,60017,50022,900

9781,7202,710

3,9307,06011,060

16,00021,80028,500

1,0801,9103,000

4,3507,82012,300

17,70024,20031,600

* Class 2A external threads, Unified National Coarse Thread Series.† Area at root of threads used, computed using the nominal minor diameter for external threads, Class 2A, ANSI Standard B1.1.‡ Based on area computed for minimum body diameter.Allowable loads are obtained by dividing values in this table by safety factors of 2.34 for building and 2.64 for bridges.

VII-92 January 2005

Table 5-6RIVET HEAD STYLES AND SPECIFICATIONS

Table 5-7MILITARY SPECIFICATIONS FOR ALUMINUM ALLOY RIVETS

January 2005 VII-93

Table 5-8RECOMMENDED HOLE SIZES FOR COLD-DRIVEN SOLID RIVETS

WITH CORRESPONDING SHEAR AND BEARING AREAS

VII-94 January 2005

Table 5-9RECOMMENDED HOLE SIZES FOR HOT-DRIVEN SOLID RIVETS

WITH CORRESPONDING SHEAR AND BEARING AREAS

January 2005 VII-95

Table 5-10APPROXIMATE DRIVING PRESSURE WITH SQUEEZING RIVETER

Table 5-11SMALLEST SIZES OF PNEUMATIC HAMMERS CONSIDERED SATISFACTORY

FOR DRIVING ALUMINUM ALLOY RIVETS BASED ON ACTUAL DRIVING TESTS WITH 90-PSI AIR PRESSURE

VII-96 January 2005

Table 5-12LENGTH OF RIVETS

(Driven heads are dimensioned in Table 5-10) Lengths are based on hole sizes shown in Tables 5-8 and 5-9)

January 2005 VII-97

Table 5-12 (Continued)LENGTH OF RIVETS

Table 5-13FLAT DRIVEN HEADS—MAXIMUM* RIVET GRIPS FOR GIVEN LENGTHS, IN.

VII-98 January 2005

Table 5-14RECOMMENDED HOLE SIZES FOR

2024-T4 AND 7075-T73 SHEET METAL SCREWS

In Alloys 1100, 3003, 5052 (All Tempers), 6061-T4 and 6063-T5

January 2005 VII-99

Table 5-15DIIMENSIONS FOR BOLTS

VII-100 January 2005

Table 5-15 (Continued)DIIMENSIONS FOR BOLTS

Table 5-16BOLT NUTS

January 2005 VII-101

Table 5-16 (Continued)BOLT NUTS

Table 5-17MACHINE SCREW NUTS


Table 5-18REGULAR SPRING LOCK WASHERS

Table 5-19PLAIN FLAT WASHERS


Table 5-20INTERNAL THREAD STRIPPING AREA

FOR CLASS 2B UNC THREADS

Nominal Size-Threads per in.

Internal Thread Stripping Area (in2) per in.

of Engagement

8-32 0.334

10-24 0.401

12-24 0.458

1/4 - 20 0.539

5/16 - 18 0.682

3/8 - 16 0.828


BEAM FORMULAS






CASE 12A. Trapezoidally distributed load:

Total Load: W = w(L – a)Max. Load: w lb/inReactions: R1 = W/2, R2 = W/2Shear Forces: V1 = R1; V2 = -R2

Maximum bending moment =

w ___ 24

( 3L2 – 4a2 ) , x = L __ 2

Maximum deflection =

wL4 _______

1920EI [ 25 – 40 ( a __

L ) 2 + 16 ( a __

L ) 4 ] , x = L __

2














PART VIII

Illustrative Examples of Design



January 2005 VIII-3

VIIIIllustrative Examples of Design

FOREWORD

This part of the Design Manual is written as a companion to the Specification for Aluminum Structures, Allowable Stress Design, Part IA. It is intended to illustrate the application of various provisions of the Specification.

Terms and symbols used in this document are consistent with those used in the Specification for Aluminum Structures, which should be consulted for their definitions.

The examples and data presented here and publications incorporated by reference have been prepared in accordance with recognized engineering principles and are for general information only. These examples and data should not be used without first securing competent advice with respect to their suitability for any given application.

VIII-4 January 2005

Table of Contents

Example Type of Member Type of Load Page VIII-

1 Rod, round Tension, axial 9

2 Strap, rectangular Tension, axial 10

3 I beam Bending 11

4 Tube, square Bending 13

5 Tube, round Bending 15

6 Plate Bending 16

7 Rivets Bearing 18

8 Pin Bearing 19

9 I beam Compression, axial 21

10 Box section, latticed Compression, corner 23

11 Wide flange section Compression, axial 25

12 Tube, square Compression, axial 26

13 Tube, square with stiffeners Compression, axial 28

14 Tube, round Compression, axial 29

15 I beam Bending 30

16 Girder, welded Bending 32

17 Welded girder, transverse stiffeners Bending 36

18 Tube, round Bending 37

19 Bar, rectangular Bending 38

20 Tube, rectangular Bending 39


22 Unsymmetric shape Bending 43

23 Channel Bending 45

24 Welded beam Bending 48

25 Welded beam, stiffened web Bending 49

26 I beam Shear 50

27 Girder, riveted, stiffened web Shear 52

28 Curtainwall beam Bending 56

29 Formed sheet Bending, shear 62

30 Tapping screw connection Shear, tension 66


January 2005 VIII-5

CORRELATION OF SPECIFICATION SECTIONS AND ILLUSTRATIVE EXAMPLES

Type of Stress Type of Member and Element Section No.* Main Examples Other Examples

TENSION, axial Any tension member 1 1 2

TENSION IN BEAMS, extreme fiber, net section

Flat elements in uniform tension 2 3,4 15, 16, 20, 21, 22, 26, 27, 28, 29

Round or oval tubes 3 5 18

Flat elements in bending in their own plane, symmetric shapes

4 6 19, 23

BEARING On rivets and bolts 5 7 27

On flat surfaces and pins 6 8

COMPRESSION IN COLUMNS, axial, gross section

All columns 7 9 10. 11, 12, 14

COMPRESSION IN COLUMN ELEMENTS, gross section

Flat elements supported on one edge – columns buck-ling about a symmetry axis

8 10, 11 9, 13

Flat elements supported on both edges 9 12 9, 11

Curved elements supported on both edges 10 14 12

COMPRESSION IN BEAMS, extreme fiber, gross section

Single web shapes 11 15, 16, 17 3, 21, 22, 23, 26, 27, 28

Round or oval tubes 12 18 5

Solid rectangular and round sections 13 19 6

Tubular shapes 14 20 4

COMPRESSION IN BEAM ELEMENTS, (element in uniform compression), gross section

Flat elements supported on one edge 15 21 3, 16, 22, 23, 26, 27

Flat elements supported on both edges 16 22 4, 20, 24, 29

COMPRESSION IN BEAM ELEMENTS, (element in bending in own plane), gross section

Flat elements supported on tension edge, compression edge free

17 23

Flat elements supported on both edges 18 24 3, 16, 20, 21, 22, 23, 27

Flat elements supported on both edges and with a longi-tudinal stiffener

19 25

SHEAR IN ELEMENTS, gross section

Unstiffened flat elements supported on both edges 20 26 3, 4, 15, 20, 21, 22, 23

Stiffened flat elements supported on both edges 21 27

*The section number refers to the type of stress and member used and corresponds to the number in Table 3.4-3 of the Specification for Aluminum Structures.

VIII-6 January 2005

CORRELATION OF TABLES IN SPECIFICATION FOR ALUMINUM STRUCTURES AND OTHER PARTS OF THE DESIGN MANUAL

Table No. in Specification Examples

3.3-1 2, 6, 7, 16, 21, 23, 27

3.3-2 16

3.3-3 16, 29

3.4-1 2, 7, 16, 27

3.4-2 2, 16

3.4-3 2, 7, 16, 29

4.8-1 16, 17

5.3.4-1 7, 27

Part VII, Table 2-1 16, 29

Part No. & Table No. in Design Manual Examples

VI-3 2

VI-4 8

VI-8 3, 9, 15, 21, 26

VI-10 11

VI-14 10, 27

VI-16 27

VI-21 14

VI-22 5, 18

VI-23 4

VI-26 29

VI-28 6, 8, 12, 16, 20

VII-4-2 15, 21, 26

VII-4-3 6

VII Beam Formulas 3, 4, 5, 6, 8, 15, 19, 20, 21, 26, 27, 28

VII-5-2 27

VII-5-8 7, 27

January 2005 VIII-7

CORRELATION OF SECTION NUMBERS OF SPECIFICATION AND ILLUSTRATIVE EXAMPLES

Section of Specification Examples

Allowable Stress3.4.1 thru 3.4.21 See correlation on page VIII-5

Special Design Rules

4.1 9

4.2 26

4.3 9

4.4 22

4.5 25

4.6 27

4.7.2 12

4.7.4 9, 12

4.7.5 16, 21

4.7.6 29

4.7.7 4, 29

4.7.8 29

4.8.1 16, 17

4.9 15, 16, 21, 28

4.10 23

Mechanical Connections

5.3.6 7, 27

5.4 30

Welded Construction

7.2 16, 24

VIII-8 January 2005

PREFACE

In the following illustrative examples, widths of elements are conservatively calculated ignoring the effect of corner fillets. For example, in example 3 the flange element width b, used to calculate the allowable stress in the flange of I 5 × 3.70, is calculated from the face of the web as shown in Figure i

Figure i

January 2005 VIII-9

Example 1DESIGN OF A ROUND ROD TO RESIST AXIAL TENSION

Illustrating Section 3.4.1

From Part VI, Table 28,Required diameter for A = 0.237 in2:

πD2 ____

4 = 0.237

D = √________

4×0.237 _______ π = 0.549 in.

use D = 9/16 in.

NOTES:1. The example assumes that the rod area is not reduced

at the connections. If the area is reduced in any way, such as by threading, a larger rod may be required so that the net tensile area at the smallest section is at least 0.237 in.2.

2. Long slender members have little resistance to lat-eral loads. Therefore, tension members with values of slenderness ratio L/r greater than 200 should not be used unless special care is taken to insure that such members are designed to resist vibration or any lateral loads such as wind, dead load, or the weight of work-men and equipment.

3. Combined tension and bending is treated in Section 4.1.2.

GIVEN:

1. Tensile load: 4.50 kips (4,500 lb).2. Alloy: 6061-T6.3. Structure type: building truss.

REQUIRED:

Diameter of smallest standard round rod that will safely resist the load.

SOLUTION:

From Part VII, Design Aids, Table 2-22,Section 3.4.1: Allowable tensile stress

F = 19 ksi (on gross section)

Given load

P = 4.50 kips

Required area

A = P __ F

= 4.50 ____ 19.0

= 0.237 in.2

Figure 1

VIII-10 January 2005

Example 2DESIGN OF A RECTANGULAR STRAP TO RESIST AXIAL TENSION


Use F = 17.6 ksi

Given load

P = 1.20 kips

Required area

A = P __ F

= 1.20 ____ 17.6

= 0.0682 in2

Required thickness for 1.00-in. width

t = 0.0682 ______ 1.00

= 0.0682 in.

From Part VI, Table 3Minimum standard thickness ≥ 0.0682 in.t = 0.071 in.

NOTES: The example assumes that the strap area is not reduced at connections. In the case of a bolted or riveted connection this reduction in area can be taken into account by subtracting the hole diameter from the overall width and recalculating the required thickness using 0.0682 in2 as the required net area. In addition, for a bolted or riveted con-nection shear and bearing stresses must be considered as in example 7.

See also second and third notes under example 1.

GIVEN:

1. Tensile load: 1.20 kips (1,200 lb).2. Alloy: 5052-H36.3. Structure type: Building.

REQUIRED:

Thickness of 1 in. strap which will safely resist the load.

SOLUTION:

From Specification, Table 3.4-3Section 3.4.1: Allowable tensile stress

F = Fty ___ ny

(gross section) or Ftu ____ kt nu

(net section)

Reading Fty and Ftu from Table 3.3-1, ny and nu from Table 3.4-1 and kt from Table 3.4-2

F = Fty ___ ny

= 29 ____ 1.65

= 17.6 ksi, or

F = Ftu ____ ktnu

= 37 __________ 1.00 × 1.95

= 19.0 ksi

Figure 2

January 2005 VIII-11

Example 3DESIGN OF AN I-BEAM WITH MULTIPLE SUPPORTS

Illustrating Sections 3.4.2, 11, 15, 18 and 20

From Part VII, Design Aids, Table 2-22.Conservatively using the lesser of 3.4.2 (for the flanges)

and 3.4.4 (for the web), Section 3.4.2: Allowable tensile stress

F = 19 ksi

Section 3.4.11: Allowable compressive stress

Fb = 21 ksi for laterally supported beam.

Section 3.4.2 controls. Required section modulus

S = M __ F

= 92.6 ____ 19

= 4.87 in3

From Part VI, Table 8Select trial I-beam I 5 × 3.70Sx = 5.58 in3

From Part VII, Table 2-22Section 3.4.15: Allowable stress in flange.

b __ t = 3.50 – 0.19 __________ 2 × 0.32

= 5.2

Slenderness is less than S1 = 6.5

F = 21 ksi, allowable flange stress.

GIVEN:

1. Uniform load of 4.50 kips/ft (4,500 lb/ft) including dead load.

2. Beam length 16 ft with continuous lateral support.3. Vertical support spacing 4 ft o.c. (first support at end

of beam).4. Alloy: 6061-T6.5. Structure type: Industrial (Building).

REQUIRED:

Size of lightest Aluminum Association standard I-beam that will safely support the load.

SOLUTION:

From Part VII Beam Formula Case 43 continuous beam of four equal spans-uniformly distributed load.

Load, w = 4.50 ____ 12

= 0.375 kips per in.

Maximum bending moment

M = – 168wL2 _______

1568 = – 168 × 0.375 × 482

_______________ 1568

= –92.6 in.-kips

The negative sign for the bending moment M indicates that the top flange of the beam is in tension. The critical point of maximum stress is at the first interior support.

Figure 3


Section 3.4.20: Web shear

h __ t = 5.00 – 2 × 0.32 _____________ 0.19

= 22.9

Slenderness is less than S1 = 36

Fs = 12 ksi, allowable shear stress

From Part VII Beam Formula Case 43, Continuous beam of four equal spans.

V = 17wL _____ 28

= 17 × 0.375 × 48 _____________ 28

= 10.9 kips, maximum web shear

A = V __ Fs

= 10.9 ____ 12

= 0.908 in.2 required web area

The above is an approximate method. See example 26 and note thereto.

For I 5 × 3.70

A1 = 0.19 × (5.00 – 2 × 0.32)

= 0.828 in2 < 0.908 in2

For I 6 × 4.03

A2 = 0.19 × (6.00 – 2 × 0.29)

= 1.03 in2 > 0.908 in2

The I 6 × 4.03 is therefore the smallest satisfactory beam.

NOTES: For alloys other than 6061-T6 and for sections other than those in Tables 4 and 8 of Part VI, the local buck-ling stress of Section 3.4.18 of the Specification should be checked to see if the allowable stress is less than those computed above.

The local building code should be checked to see if anal-ysis under other loading conditions, such as alternate span loading is required in addition to the one studied above. Generally, the use of the formula

M = ± wL2 ____

8

will satisfy all building code requirements for uniformly loaded beams without excessive overhang beyond the end supports.

If holes are to be drilled in the flange at or near points of high tensile stress, it may be necessary to use a larger beam. This may be determined by multiplying the com-puted flange stress at the section under consideration by the ratio of the gross area of the flange to the net area of the flange and comparing the result with the allowable stress.

Web crippling at the support should be checked; see Example 4.


Example 4DESIGN OF A SQUARE TUBULAR BEAM TO RESIST A BENDING LOAD

Illustrating Sections 3.4.2, 14, 16 and 20

Section modulus required

S = M __ F

= 15.0 ____ 15

= 1.00 in3

From Part VI, Table 23, trial section is 3 in. × 0.095 in.

f = M __ S = 15.0 ____

1.04 = 14.4 ksi

From Part VII, Table 2-24Section 3.4.16: Allowable compressive stress

b __ t = 3.00 – 2 × 0.095 ______________ 0.095

= 29.6

Slenderness lies between S1 = 23 and S2 = 39

Fb = 19.0 – 0.170 × 29.6

= 14.0 ksi; 14.0 < 14.4

Since this is less than f, a thicker section must be used; try 3 in. × 0.120 in.

b __ t = 3.00 – 2 × 0.120 ______________ 0.120

= 23.0

Slenderness is ≤ S1 = 23

Fb = 15 ksi; 15 > 14.5; bending stress is satisfactory and need not be rechecked.

Shear in WebsFrom Part VII, Beam Formula Case 1

V = P __ 2 = 1.50 ____

2 = 0.750 kips

GIVEN:

1. Concentrated load of 1.50 kips (1,500 lb) including dead load, applied at mid span.

2. Span 40 in., simply supported3. Alloy: 6063-T64. Structure type: Theatre (Building)

REQUIRED:

Thickness of standard 3 in. square tube that will safely sup-port the load.

SOLUTION:

From Part VII, Beam Formula Case 1, simply supported beams, concentrated load at P at center.

Load P = 1.50 kips, given

Maximum bending moment,

M = PL ___ 4 = 1.50 × 40 ________

4 = 15.0 in.-kips

From Part VII, Design Aids, Table 2-24,Using the lesser of 3.4.2 (for the flanges) and 3.4.4 (for

the webs), Section 3.4.2: Allowable tensile stress

F = 15 ksi


For a square tube, use 3.4.16 to determine allowable compressive stress.


Fb = 15 ksi, to be confirmed when the wall thickness is known.

Figure 4


From Part VII, Table 2-24,Section 3.4.20: Allowable shear stress

h __ t = 3.00 – 2 × 0.120 ______________ 0.120

= 23.0


Fs = 8.5 ksi

Area of webs, A = 2 × 0.120 × (3.00 – 2 × 0.120) = 0.662 in2

Approximate web shear stress

fs = V __ A

= 0.750 _____ 0.662

= 1.13 ksi, shear stress

See example 26 for accuracy of this method. Com-paring with the allowable, 1.13 < 8.5, section is sat-isfactory. It is not necessary to check lateral torsional buckling of a box beam unless it is relatively deep and narrow.

Use 3 in. × 0.120 in. hollow square tubing.

NOTES: A lighter tube in 6061-T6 alloy would be sat-isfactory structurally; however, for architectural uses, alloy 6063-T6 is usually preferred because of its superior finish-ing characteristics.

The supports and load point of Figure 4 are shown as sharp, a condition seldom used in actual practice, but used here to define the span length more clearly. In an actual installation, the forces on the beam will be distributed over a distance N, which should be large enough to prevent local crippling of the webs.

Section 4.7.7, Web Crippling, governs this situation.

From Table 3.3-1

Fcy = 25 ksi, E = 10,100 ksi

Ri = 0 for fillets and other situations where the juncture of the web to the flange is not in the form of a bent radius.

t = 0.120 in.

θ = 90°

From practical considerations try

N = 0.10 in.

Allowable reaction is

Pc = 1.2 Cwa (N + Cw2) ______________

ny Cwb

where

Cwa = t2 sin (0.46 Fcy + 0.02 √____

EFcy )

= (0.12)2 sin 90° (0.46 × 25 + .02 √__________

10,100 × 25 )

= 0.310 kips

Cwb = Cw3 + Ri (1 – cos θ)

Cw3 = 0.4 in. so

Cwb = 0.4 + 0(1 – cos 90) = 0.4 in.

Cw2 = 1.3 in.

So

Pc = 1.2 × 0.310 (0.10 + 1.3)

____________________ 1.65 × 0.4

Pc = 0.789 kips allowable, per web.

For two webs the end reaction per web is

V __ 2 = 0.75 ____

2 =0.375 kips

0.375 < 0.789 therefore a bearing length of 0.10 in. is satisfactory.


Example 5DESIGN OF A STANDARD PIPE SUBJECTED TO BENDING

Illustrating Sections 3.4.3 and 3.4.12

Load = 25 lb/ft2 or 0.025 k/ft2

P = 0.025 × 3.00 × 4.00 = 0.30 k L = (15 + 0.5 × 3) × 12 = 198 in. M1 = PL = 0.30 × 198 = 59.4 in.-k

This is the portion of the total load moment due to wind load on the sign and must be corrected later when the pipe size is known for the additional moment caused by wind load on the pipe.

Trial section modulus

S = M1 ___ F

= 59.4 ____ 10.6

= 5.60 in3

From Part VI, Table 22, a trial pipe size is obtained.

6 in. Schedule 40, S = 8.50 in3, OD = 6.63 in., t = 0.280 in.

Adding the moment due to wind load on the pipe, from Case 16, cantilever beams, uniformly distributed load of w k/in.

w = (0.0201)(6.63)/(144) = 0.000925 k/in.

M2 = wL2/2 = (0.000925)[(15)(12)]2/2 = 15.0 in-k

Total moment M = M1 + M2 = 59.4 + 15.0 = 74.4 in-k

f = M __ S = 74.4 ____

8.50 = 8.8 ksi < 10.6 ksi

Size selected is satisfactory for tension.

Section 3.4.12 addresses compression in round tubes.

Rb /t = (6.63 – 0.280)/2

_____________ 0.280

= 11.3

Taking buckling constants from Part VII, Table 2-1W

S1 = ( Btb – 1.17 Fcy ___________ Dtb

) 2 = ( 29.2 – (1.17)(15) ______________

1.538 ) 2

= 57 > 11.3,

so Fb = 1.17Fcy /ny = (1.17)(15 ksi)/1.65 = 10.6 ksi > 8.8 ksi; so the size is satisfactory. Use 6 in. Schedule 40 pipe.

NOTES: 1. The wind pressure on the supports is given as a smaller

pressure than that on the sign in accordance with the reduced height and shape factors.

2. The axial stress in the supports due to dead load is assumed to be negligible in comparison to the reserve strength available; however, if the sign is very heavy, the effect should be considered.

GIVEN:

1. Wind load 25 lb/ft2 on 3 ft high signboard, the bot-tom of which is 15 ft above the base of the supporting pipes, and 20.1 lb/ft2 on the supports, see Figure 5.

2. Support: Schedule 40 standard pipes spaced as shown in Figure 5.

3. Alloy: 6061-T64. Base: Welded.5. Structure type: Sign (building type structure)

REQUIRED:

Size of standard pipe to safely resist the load

SOLUTION:

The properties for welded 6061-T6 are given in Table 3.3-2 as:

Ftu = 24 ksi, Fty = 15 ksi, Fcy = 15 ksi

The allowable bending stress in the pipe at the welded base from Part IA, Section 3.4.3, is the lesser of

1.17Fty /ny = (1.17)(15 k/in2)/1.65 = 10.6 k/in2 and

1.24Ftu /nu = (1.24)(24 k/in2)/1.95 = 15.3 k/in2; 10.6 k/in2 controls.

From Part VII, Beam Formula Case 14, concentrated load, P, at free end of cantilever beam:

The load from the sign is not actually a concentrated load as in the beam diagram, however, the moment at the base is correctly determined using the resultant of the sign force acting at the center of the sign.

Figure 5


Example 6DESIGN OF A PLATE SUBJECTED TO BENDING LOAD

Illustrating Sections 3.4.4 and 13


S = M __ F

= 3.60 ____ 28

= 0.129 in3

From Part VI, Table 28, fourth case, section modulus of rectangle

S = bd2 ___

6 , in this case b = 24 in. and d = t1

Solving for t1

t1 = √___

6S ___ b = √

_________

6 × 0.129 ________ 24

= 0.179 in.

DeflectionFrom Part VII, Case 1

Deflection = PL3 _____

48EI

A correction is required for plates because individual fibers are restricted in the way they can change shape in the direction perpendicular to the stress. They can change in vertical dimension but not in horizontal dimension. The correction is as follows:*

Deflection = PL3(1 – v2)

_________ 48EI

where v = Poisson’s ratio = 0.33 for aluminum.

GIVEN:

1. Load 0.400 kips (400 lb), concentrated along a line at a center of plate.

2. Plate: 24 in. wide, spanning 36 in.3. Alloy: 6061-T64. Type of structure: Building

REQUIRED:

Minimum standard thickness to support the load safely without deflecting more than 3/8 in.

SOLUTION:

From Part VII, Design Aids, Table 2-21Section 3.4.4: Allowable tensile stress

F = 28 ksi

Section 3.4.13. Allowable compressive stress

Fb = 28 ksi for rectangular sections bent about the weak axis.

From Part VII, Beam Formula Case 1, simply supported beam, concentrated load P at center

M = PL ___ 4 = 0.400 × 36 _________

4 = 3.60 in.-kips

Figure 6


From Part VI, Table 28, fourth case, moment of inertia for a rectangle

I = bt 3 2 ___ 12

From Specification Table 3.3-1, and footnote thereto,

E = 10,000

Combining,

t2 = 3 √_________________

12PL3 × (1 – v2)

_________________ b × deflection × 48E

t2 = 3 √_________________________

12 × 0.400 × 363 × (1 – 0.332)

_________________________ 24 × 0.375 × 48 × 10,000

= 0.359 in., from deflection.

Since t2 > t1 deflection controls.Use 3/8 in. thick plate.

* See: Timoshenko and Gere, “Theory of Elastic Stability,” second edition, 1961, McGraw-Hill, Eq. 8 p. 320

NOTES: The rails supporting the plate are assumed to have been checked structurally to see that they will safely support the load. They should be fastened to the plate at intervals to prevent spreading.

This problem differs from that shown in Table 4-3 of Part VII in that the loading arrangement and deflection are based on other criteria.

The 24 in. width was chosen as the minimum, there-fore the job specifications should prohibit narrower pieces unless the applied loads are reduced proportionately.


Example 7BEARING ON RIVETS


From Table 3.3-1, Ftu = 37 ksiFrom Table 3.4-1, nu = 1.95

F = 2 × 37 ______ 1.95

= 37.9 ksi

Load, P = 0.090 × 3 = 0.270 kips, each rivetActual bearing stress

f = P ___ Ab

= 0.270 _______ 0.01203

= 22.4 ksi

From Section 5.1.1, allowable edge distance

Ratio of edge distance to diameter = 0.375 ______ 0.1875

= 2.00

Full stress may be used, F = 37.9 ksi 37.9 > 22.4, therefore the bearing stress is satisfactory.

From Table 5.3.4-1

Fs = 11 ksi

fs = P/As = 0.270/0.02865 = 9.42 ksi,

9.42 < 11, satisfactory

Since both bearing and shear are satisfactory, the con-nection will adequately resist the shear load.

NOTES: The rivet spacing in this example is quite large in comparison with the diameter ; however, in the case of close spacing see Specification Section 5.3.6 which sets the minimum rivet spacing at three times the diameter.

The effective diameter of rivets of non-standard diam-eter and/or hole size can be computed using Section 5.3.5.

For bolted connections the effective diameter is the nominal bolt diameter, see Sections 5.2.4 and 5.2.5

GIVEN:

1. Rivets: 3/16 in. diameter, cold-driven 2117-T3 alloy, (2117-T4 before driving) 3 in. o.c., edge distance 0.375 in.

2. Sheet: 0.063 in., 5052-H36 alloy.3. Corner post extrusion considerably thicker than the

sheet and having equivalent unit bearing strength.4. Load: 0.090 kips/in. shear (90 lb/in.).5. Structure type: Building.

REQUIRED:

Check the strength of the connection to see that it is ade-quate for the load.

SOLUTION:

From Part VII, Design Aids, Table 5-8 for a 3/16 in. rivet (0.191 in. hole)

Single shear area As = 0.02865 in2

Bearing area Ab = 0.01203 in2 for 0.063 in. sheet

From Specification Table 3.4-3Section 3.4.5: Bearing on 5052-H36 sheet

F = 2Ftu ____ nu

Figure 7


Example 8BEARING ON A PIN


From Part VII, Beam Formula Case 6Simply supported beam, uniformly distributed load,

R = W __ 2 = 1.20 ____

2

= 0.600 kips, connection load

A = R __ F

= 0.600 _____ 15

= 0.04 in2, required bearing area

The bearing area on the pin is taken as the diameter of the pin times the length in bearing.

D1 = A ___ 2T

= 0.04 ________ 2 × 0.080

= 0.25 in., diameter required, based on wall bear-ing stress in the beam wall.

Determine the pin diameter based on bending of the pin.

GIVEN:

1. Beam: Hollow rectangular tube 4 in. × 6 in. with wall thickness 0.080 in.

2. Use: Dunnage control beam for a truck.3. End supports: Aluminum Association standard 5-in. ×

2.25 in. channel. (CS5 × 2.21).4. Beam load: 1.20 kips (1,200 lb) including impact, uni-

formly distributed.5. Pin: Allowable bending stress 25 ksi.6. Beam and end support alloy: 6063-T5.7. Structure type: Truck (Building).

REQUIRED:

The minimum pin size for the end connection.

SOLUTION:

From Part VII, Design Aids, Table 2-23Section 3.4.6: bearing on pins

F = 15 ksi

Figure 8


From Part VI, Table 4,The clearance between flanges of the 5 in. channel is:

C = 5.00 – 2 × 0.26 = 4.48 in.

Assuming the beam is at the bottom of the supporting channel, the lever arm for bending is the net clearance plus half the wall thicknesses of the adjacent bearing surfaces.

L = (C – 4.00) + T1 __ 2 +

T2 __ 2

= (4.48 – 4.00) + 0.080 _____

2 + 0.26 ____

2 = 0.65 in.

A reasonable assumption for figuring pin bending is that half of the connection load is transferred at the top of the beam.

M = L × P = 0.065 × 0.600 ____________ 2 = 0.195 in.-kips


S = M __ F

= 0.195 _____ 25

= 0.00780 in3,

From Part VI, Table 28, circle

S = πD3 ____

32 , which can be solved for D

D2 = 3 √____

32S ____ π = 3 √____________

32 × 0.00780 ___________ π = 0.430 in.

Comparing this diameter with that based on bearing,

D2 > D1 therefore the required diameter is 7/16 in.

Use a 7/16 in. diameter pin.

NOTES: For other loading arrangements in which the bearing load on a pin is toward the edge of the member, the edge distance should be checked as required in Section 3.4.5 of the Specification.

The beam should be checked for bending and shear stresses as in example 4 in order to determine the maxi-mum allowable length.


Example 9ALLOWABLE AXIAL LOAD ON AN I-SHAPED COLUMN

Illustrating Sections 3.4.7, 8, and 9

SOLUTION:

From Part VI, Table 8Section properties of 8 in. × 6.18-lb/ft I-beam

(I 8 × 6.18)

A = 5.26 in2, rx = 3.37 in., ry = 1.18 in.

From Part VII, Design Aids, Table 2-22Section 3.4.7: Compression in columns

kL ___ r = 8 × 12 ______ 3.37

= 28.5


F = 20.2 – 0.126 × kL ___ r

= 20.2 – 0.126 × 28.5 =16.6 ksi

Section 3.4.8: Compression on flat element with one edge supported (flange)

b __ t = 5.00 – 0.23 __________ 2 × 0.35

= 6.8

Slenderness lies between S1 = 2.4 and S2 = 10

F = 23.1 – 0.787 × 6.8 = 17.7 ksi

Section 3.4.9: Compression in flat elements with both edges supported.

b __ t = 8.00 – 2 × 0.35 _____________ 0.23

= 31.7


F = 23.1– 0.247 × 31.7 = 15.2 ksi

15.2 < 16.6 and 17.7. Therfore the allowable load is

P = FA = 15.2 × 5.26 = 79.9 kips.

NOTES: The above solution is based on buckling about the X-X axis pursuant to item 4 of the GIVEN. However, if the lateral support to prevent buckling about the Y-Y axis is removed the allowable load is reduced as follows:

L __ r = 8 × 12 ______ 1.18

= 81.4,

Slenderness is greater than S2 = 66

F = 51,100

______ (L/r)2 =

51,100 ______

81.42 = 7.70 ksi

P = FA = 7.70 × 5.26 = 40.5 kips

GIVEN:1. Standard Aluminum Association 8 in. I-beam weigh-

ing 6.18 lb/ft (I 8 × 6.18) used as a column.2. Length: 8 ft.3. End conditions: Assume pinned.4. Laterally supported to resist buckling about the Y-Y

(weak) axis.5. Alloy: 6061-T6.6. Structure type: Building.

REQUIRED:The value of the maximum allowable axial load.

Figure 9


The allowable axial load without lateral support about the Y-Y axis is 40.5 kips.

End conditions other than pinned are treated in Part III, Design Guide, Section 3.4.*

Eccentric loading is treated in Part VII, Beam Formulas. Combined compression and bending resulting from lat-eral or eccentric loading is treated in Specification Section 4.1.1. If the shear stress is high also, Section 4.4 should be checked.

Columns such as this with one or more stiffened ele-ments require a study of the combination of local and overall buckling if the b/t ratio of the stiffened element is greater than S2 of the Section 3.4.9 of Table 3.4-3 and also greater than 0.6 (L/r). A formula for the allowable stress under these conditions is given in Specification Section 4.7.4. Standard sections listed in Part VI, Tables 4 and 8 in alloy 6061-T6, have webs of sufficient thickness that this type of buckling need not be checked. For a sample calcula-tion, see Example 12.

If, in place of this symmetrical I-beam, an unsymmetri-cal open shape such as a channel, lipped angle, or hat shape is to be substituted a special analysis should be made of the resistance to buckling by combined torsion and flexure.**

* See also: Galambos, Theodore V. (editor). “Guide to Stability Design Criteria for Metal Structures, Fourth edition,” Structural Stability Research Council, 1988.**See: “Structural Use of Aluminum Part I. Code of Practice for Design, British Standard BS8118, 1991,” The Council for Codes of Practice, Brit-ish Standards Institiute, 1991.


Example 10ALLOWABLE AXIAL LOAD ON THE CORNER ANGLE OF A LATTICED BOX COLUMN


SOLUTION:

From Part VI, Table 14Section properties of 4 in. × 4 in. × 3/8 in. angle

A = 2.86 in.2

rx = ry = 1.22 in.

rz = 0.766 in.

From Part VII, Design Aids, Table 2-22, Section 3.4.8.1: Compression in flat element with one edge supported (outstanding leg)

b __ t = 4.00 – 0.375 ___________ 0.375

= 9.67


F1 = 23.1 – 0.787 × 9.67 = 15.5 ksi, from local buckling.

Section 3.4.7: Compression in column

Although the end of each 27 in. segment of the column is restrained by the adjoining segment, the adjoining segments may buckle in opposite direc-tions; therefore, the ends are assumed pinned.

L = 27 in.

The section tends to buckle about the axis having the smallest radius of gyration.

r = rz = 0.766 in.

L __ r = 27 _____ 0.766

= 35.2


F2 = 20.2 – 0.126 × 35.2 = 15.8 ksi, from buckling between lattice points.

F1 < F2, therefore Fc = F1 = 15.5 ksi

P = FA = 15.5 × 2.86 = 44.3 kips, the allowable load in each corner angle.

NOTES: The allowable load in the latticed column must also be checked for full length buckling resistance in accor-dance with Section 3.4.7. The load capacity is the answer thus obtained or four times the capacity of the corner angle computed above, whichever is smaller.

GIVEN:

1. Latticed box section column.2. Corner components: 4 in. × 4 in. × 3/8 in. angle.3. Alloy: 6061-T6.4. Spacing of lattice points: 27 in. o.c.5. Connection of lattice: Riveted.6. Structure: Sign (Building)

REQUIRED:

Allowable axial load in one corner angle between lattice points.

Figure 10


Had the lattice diagonals been welded, the value of Fc for the corner angle would have dropped to 9 ksi in accor-dance with Section 3.4.8. In this case, the welding would have been at a lattice point, which is a point of lateral sup-port for the corner angle; therefore, Section 3.4.7 would be checked as “farther than 1.0 in. from a weld.”

The load on the lattice diagonals appears to be zero for a concentrically loaded column; however, they must be rigid enough to keep the corner angles straight.*

Sections that are not hollow are termed “open sections” and are subject to failure by combined twisting and lateral buckling. Roll formed sections that have a lock seam may be classified as either “closed” or “open” sections depend-ing on how tight the seam is. If the seam is tight enough to prevent longitudinal slippage, the section may be con-sidered “closed.” Open sections that have as their main ele-ments radiating unstiffened fins are covered for this com-bined buckling by Section 3.4.8. Examples are angles, tees,

and crosses. If the flanges are stiffened at the tip by a lip, the designer may wish to take advantage of the additional column strength; however, the special analysis for these sections and for other open sections unsymmetrical about one or both principal axes such as channels, zees, hats, and loosely locked tubes are not covered by the Specification. The computations are quite complex.**

*See: “Task Committee on Lightweight Alloys, Suggested Specifications for Structures of Aluminum Alloys 6061-T6 and 6062-T6,” Paper 3341, pages 62, 81 and 85, Journal of the Structural Division, Proceedings ASCE, Vol. 88, No. ST6, December, 1962, and: Galambos, Theodore V., Guide to Stability Design Criteria for Metal Structures, Fourth edition, page 390, Structural Stability Research Council, 1988.** “Structural Use of Aluminum Part I”. Code of Practice for Design, British Standard BS 8118, 1991. The Council for Codes of Practice, Brit-ish Standards Institute, 1991.


Example 11ALLOWABLE LOAD ON A WIDE FLANGE COLUMN


t = 0.250 in.

rx = 1.64 in.

ry = 0.793 in.

From Part VII, Design Aids, Table 2-22Section 3.4.7: Compression in column

Use minimum radius of gyration.

r = ry = 0.793 in.,

L __ r = 42 _____ 0.793

= 53.0


F1 = 20.2 – 0.126 × 53.0 = 13.5 ksi

Section 3.4.8: Compression in column flanges

b __ t = 3.50 – 0.250 ___________ 2 × 0.250

= 6.5

Slenderness is between S1 = 2.4 and S2 = 10

F2 = 23.1 – 0.787 (6.5) = 18.0 ksi

Section 3.4.9: Compression in column web

b __ t = 4.00 – 2 × 0.250 ______________ 0.250

= 14


F3 = 23.1 – 0.247 × 14 = 19.6 ksi

Selecting the controlling (lowest allowable) stress,

F1 < F2 < F3, therefore

Fc = F1 = 13.5 ksi

P = FA = 13.5 × 2.60

= 35.1 kips, the allowable load.

NOTE: The formulas under Section 3.4.8 do not apply to sections that are unsymmetrical about the buckling axis; see section 3.4.8.1.

GIVEN:

1. Column section: 4 in. × 3.50 in. × 3.06 lb/ft Army-Navy wide flange section. (WF (A-N) 4 × 3.06)

2. Length: 42 in.3. End conditions: Pinned.4. Alloy: 6061-T6.5. Structure: Building.

REQUIRED:

Maximum concentric load that may safely be applied.

SOLUTION:

From Part VI, Table 10Section properties of WF (A-N) 4 × 3.06

A = 2.60 in2

Flange width = 3.50 in.

Figure 11


Example 12ALLOWABLE LOAD ON A SQUARE TUBE COLUMN

Illustrating Sections 3.4.7, 9 and 10

NOTE: This method assumes sharp corners, whereas the actual corners of roll formed sections are rounded. Where the corner radius is small in comparison with the width of the section, the method is sufficiently accurate for practical purposes.

From Part VII, Design Aids, Table 2-3Section 3.4.7: Compression in columns

L __ r = 48 ____ 1.61

= 29.8


F1 = 8.0 – 0.039 × 29.8 = 6.84 ksi

Section 3.4.9: Compression in flat elements, both edges supported

b __ t = (4.00 – 0.063 × 2)

_______________ 0.063

= 61.5

Slenderness > S2 = 60

F2 = 282 ____ 61.5

= 4.59 ksi

For this case, it is necessary to calculate the effect of combined local and overall buckling as required by Sec-tion 4.7.4. This will govern if

Fcr ___ nu

< Fc

where Fcr is the local buckling of an element (in this case, the wall of the tube per Section 3.4.9) as given in Section 4.7.1:

Fcr = π2E ________ (1.6 b/t)2 =

π2(10,000) ___________

(1.6 × 61.5)2 = 10.2 ksi

Fcr ___ nu

= 10.2 ____ 1.95

= 5.23 ksi > 4.59 ksi = Fc

So combined local and overall buckling does not govern.

Fc = F2 = 4.59 ksi; the buckling stress in this case is controlled by local buckling.

P = FA = 4.59 × 0.992 = 4.55 kips, allowable load

NOTES: The area of the lockseam is generally small and can be neglected. However, the seam must resist longitudinal slippage, otherwise the shape would be classed as an “open section” and would be subject to combined torsional and

GIVEN:

1. 4 in. square tube column formed with lock-seam from 0.063 in. sheet.

2. Length: 48 in.3. End conditions: Unrestrained.4. Alloy: 3003-H14.5. Type of structure: Building.

REQUIRED:

Allowable concentric load.

SOLUTION:

From Part VI, Table 28Hollow square section properties.

A = d 2 1 – d 2 2

= 42 – (4.00 – 0.063 × 2)2

= 0.992 in2

r = √_______

d 2 1 + d 2 2 _______

12

= √____________________

42 + (4.00 – 0.063 × 2)2

___________________ 12

= 1.61 in.

Figure 12


lateral buckling; see notes for Example 10. From Part VII, Design Aids, Table 3-1, 0.063 in. thick 3003-H14 is satisfac-tory for a zero bend radius; therefore the 0.063 in. material will make a good lockseam with proper equipment.

If the corner radii are large, they should be checked using Section 3.4.10. When the corners are calculated separately, the weighted average method of Section 4.7.2 may be used to obtain an increased allowable compressive stress.


Example 13DESIGN OF A COLUMN WITH INTERMEDIATE STIFFENERS

Illustrating Section 3.4.9.2

The element width b = 3.85 in.

The element thickness t = 0.1 in.

Stiffener properties As and Io are calculated from Part VI, Table 28:

In = bnd 3 n _____

12 , where bn is the width and dn is the height

An = Area of an element

Yn = Vertical distance from bottom fiber to the centroid of the element

n bn dn An Yn AYn AY 2 n In

1 3.95 0.1 0.395 1.05 0.4147 0.4355 0.0003

2 0.1 1.0 0.1 0.5 0.05 0.025 0.0083

Totals 0.495 0.4647 0.4605 0.0086

c = AnYn ____ ∑An

= 0.4647 ______ 0.495

= 0.9389 in.

Io = ∑(AnY2n) – c2∑An + ∑In

Io = 0.4605 – (0.9389)2 (0.495) + (0.0086) = 0.03275

λs = 4.62 (3.85)

______ (0.1)

√_____________________

1 +

(1.0)(0.1) _________

(3.85)(0.1) _____________________

1 + √_________________

1 + 10.67 (0.03275)

______________ (3.85)(0.1)3

λs = 61.4 < 66 = S2

F1 = 20.2 – 0.126 (61.4) = 12.5 ksi

Check flat elements on either side of the stiffener:

b/t = 3.85 ____ 0.10

= 38.5 > 33 = S2

from Section 3.4.9 then

F2 = 491 ____ (b/t)

= 491 ____ 38.5

= 12.7 ksi > 12.5 ksi = F1

So FC = F1 = 12.5 ksi

GIVEN:

1. An 8 in. square tube column, 0.10 in. thick walls, with 0.10 in. thick by 1 in. long stiffeners at the middle of each side.

2. Alloy: 6061-T6 extrusion.3. Type of structure: Building.

REQUIRED:

Allowable compressive stress assuming the column height is short enough that its slenderness ratio is less than S1.

SOLUTION:

Section 3.4.9.2: Uniform Compression in Elements of Columns-Flat Elements supported on both edges and with an intermediate stiffener:

For purposes of calculating the moment of inertia (Io) of the stiffener, the stiffener is defined in the Specification to include the area shown in the detail of Figure 13.

The stiffener width is 3.85 + 0.1 = 3.95 in.

Figure 13


Example 14DESIGN OF A ROUND TUBULAR COLUMN

TO SUPPORT AN AXIAL COMPRESSION LOADIllustrating Sections 3.4.7 and 10

SOLUTION:

From Part VI, Table 21, Round tubes The radius of gyration, r, of 6 in. OD tubing ranges from 1.80 in. to 2.08 in. Use a trial value of 2 in.

From Part VII, Design Aids, Table 2-22,Section 3.4.7: Compression in columns

Trial value: L __ r = 18 ___ 2 = 9, slenderness

The slenderness limit S1 is 0. The allowable stress is

F = 20.2 – 0.126(9) = 19.1 ksi.

A ≥ P __ F

= 40 ____ 19.1

= 2.09 in2, trial value.

From Part VI, Table 21Select from the table the wall thickness

t = 0.188 in.,

A = 3.43 in2

r = 2.06 in.

Since 2.06 > 2, the trial value of L/r is conservative and the trial area is sufficient.

From Part VII, Table 2-22,Section 3.4.10: Compression in curved plates and tubes

Rb = 6.00 – 0.188 ___________ 2

= 2.91 in., to midthickness of wall

Rb ___ t = 2.91 _____

0.188 = 15.5

Since this is greater than S1 (15.5 > 1.4), use

F = 22.1 – 0.799 ( √____

15.5 ) = 19.0 ksi

This is the same as was used to obtain the trial section; therefore, the 6 O.D. × 0.188 wall tube is satisfactory.

GIVEN:

1. Shape: Round tube, 6 in. OD (outside diameter).2. Load: 40 kips (40,000 lb), concentric.3. Length: 18 in.4. Alloy: 6061-T6.5. End Conditions: Assume pinned.6. Structure type: Building.

REQUIRED:

The wall thickness of a standard tube that will safely sup-port the load.

Figure 14


Example 15ALLOWABLE BENDING LOAD ON AN I-BEAM



Fc = 23.9 – 0.124 × Lb __ ry

Fc = 23.9 – 0.124 × 56.3 = 16.9

The allowable stress from Section 3.4.11 is less than that from Section 3.4.2; therefore,

F = Fc = 16.9 ksi

M = FS = 16.9 × 5.58 = 94.3 in.-kips, allowable moment

From Part VII, Beam Formula Case 43. Continuous beam of four equal spans, uniformly distributed load,

M = –168wL2 ________

1568 , maximum bending moment

Rewriting to solve for w,

w = 1568M ______ 168L2 =

1568(94.3) __________

168(48)2 = 0.382 kips/in.

The section is symmetrical about its X axis; therefore, the allowable positive moment is equal to the allowable negative moment. Thus, the minus sign for w may be removed. Converting to the more usual units kips/ft:

w1 = 0.382(12) = 4.58 kips/ft, allowable from consideration of bending stresses.

From Part VII, Design Aids, Table 2-22Section 3.4.20: Web shear

h __ t = 5.00 – 2(0.32)

____________ 0.19

= 22.9

GIVEN:

1. Section: Standard Aluminum Association 5 in. × 3.5 in. I-beam weighing 3.70 lb/ft (I5 × 3.70)

2. Beam length: 16 ft. with lateral supports at reaction points only.

3. Vertical support spacing 4 ft. o.c. (first support at end of beam).

4. Alloy: 6061-T6.5. Structure type: Building.

REQUIRED:

Allowable uniform load that can be applied to the bottom flange.

SOLUTION:

From Part VI, Table 8Section properties

Sx = 5.58 in3, web thickness = 0.19 in.

ry = 0.853 in., flange thickness = 0.32 in.

From Part VII, Design Aids, Table 2-22Using the lesser of Sections 3.4.2 (for the flanges) and

3.4.4 (for the web), allowable tensile stress

F = 19 ksi

Section 3.4.11: Allowable compressive stress: to deter-

mine the slenderness ratio Lb _____

ry √___

Cb , the bending coefficient

Cb may conservatively be taken as 1:

Lb __ ry

= 48 _____ 0.853

= 56.3

Figure 15



Fs = 12 ksi

A = 0.19(5.00 – 2(0.32)) =0.828 in2 = area of web

V = FA = 12(0.828) = 9.94 k, allowable shear

From Part VII, Beam Formula Case 43. Continuous beam of four spans,

V = 17wL _____ 28

, maximum value

which can be written

w = 28V ____ 17L

, when w is unknown

w2 = 28 ( 9.94 ) ________ 17 ( 4 )

= 4.09 kips/ft,

allowable from consideration of web shear

Using the smaller load, w2 < w1, the allowable uniform load is 4.09 kips/ft.

The resulting allowable load is identical with the value 16.37-kip total load shown in Table 4-2 of Part VII, but this is merely a coincidence because actually the loading arrangements differ.

NOTES: The notes under example 3 also apply to this example.

The controlling factor is web shear; therefore, no advan-tage is gained by using the formulas of Section 4.9 to com-pute rye. The following is presented as an example of the use of Section 4.9.1:

Iy = 2.29 in4, from Part VI, Table 8

Sc = 5.58 in3, from Part VI, Table 8

For sections symmetrical about the X axis

Sc = Sx

J = ∑ bt3 ___

3 = 3.50 ( 0.32 ) 3 __________

3 ( 2 )

+ ( 5.00 – 2 ( 0.32 ) ) ( 0.19 ) 3 ___________________

3 = 0.0864 in4

J is also given in Part VI Table 8 as 0.0984 in4, which includes fillets. Conservatively use J without fillets here.

Lb = 48 in., given.

ry = 1 ___ 1.7

[ √_______________________________________

2.29 ( 5.00 ) _________ 5.58

√_____________________________

0.5 + √_______________________

1.25 + 0.152 0.0864 ______ 2.29

( 48 ____ 5.00

) 2 ] = 0.981 in.

The result can be used in place of ry = 0.853 in. in computing the allowable bending stress Fc from Section 3.4.11.


Example 16ALLOWABLE BENDING MOMENT IN A WELDED GIRDER

Illustrating Sections 3.4.2, 11, 15 and 18, and 4.8

n bn dn An Yn AYn AY 2 n In

1 16.0 1.00 16.0 49.5 792 39204 1

2 0.375 48.0 18.0 25.0 450 11250 3456

3 12.0 1.00 12.0 0.5 6 3 1

Totals ∑ 46.0 1248 50457 3458

The height of the centroid of the section

Ct = AnYn ____ ƩAn

= 1248 _____ 46.0

= 27.1 in., height of neutral axis

Ix = Ʃ ( AnY 2 n ) – c 2 t ƩAn + ƩIn

= 20,132 in4

For the compression flange,

cc = 50.0 – 27.1

= 22.9 in., extreme fiber distance.

Section modulus for compression

Sc = Ix __ Cc

= 20,132

______ 22.9

= 879 in3

Section modulus for tension

St = Ix __ Ct

= 20,132

______ 27.1

= 743 in3

From Specification Section 3.4.11The definition of ry requires computation of the area

and the moment of inertia about the Y axis of a section with both tension and compression flanges identical to the compression flange of the actual section.

n bn dn An In

1 1.0 16.0 16.0 341

2 48.0 0.375 18.0 0

3 1.0 16.0 16.0 341

Totals 50.0 682

Iy = ƩIn = 682 in4

Ay = 50.0 in2

ry = √___

Iy __ Ay

= √____

682 ____ 50.0

= 3.69 in.

GIVEN:

1. Welded girder, see Figure 16.2. Lateral support spacing, compression flange, 10 ft o.c.3. Alloy: 5456-H321.4. Type of structure: Bridge.5. Number of cycles of load: 500,000.

REQUIRED:

Allowable bending moment.

SOLUTION:

Computation of section properties

From Part VI, Table 28,

Moment of inertia of a rectangle about its centroid

In = bnd 3 n ____ 12

, where bn is the width, and dn, is the height.

An = Area of an element

Yn = Vertical distance from bottom fiber to centroid of element

Figure 16


Mechanical Properties and ConstantsFrom Table 3.3-1, mechanical properties,

E = 10,400 ksi

Ft u = 46 ksi

Ft y = 33 ksi

Fc y = 27 ksi

From Part VII, Design Aids, Table 2-1, buckling constants,

Bc = 31.4 Bp = 37.7 Bbr = 50.1

Dc = 0.212 Dp = 0.278 Dbr = 0.426

Cc = 99 Cp = 90 Cbr = 78

From Table 3.4-1, factors of safety

nu = 2.20

ny = 1.85

From Table 3.4-2, value of kt,

kt = 1.0

From Table 3.3-3, values of k1 and k2

k1 = 0.50, k2 = 2.04

Allowable moment based on tension

From Table 3.4-3, general formulas,Section 3.4.2

Fty ___ ny

= 33 ____ 1.85

= 17.8 ksi

Ftu ____ kt nu

= 46 __________ 1.0 × 2.20

= 20.9 ksi, 17.8 < 20.9

Fn = 17.8 ksi allowable tensile stress one inch or more from a weld.

Effect of welding. From Section 7.2.2, the effect of the heat of welding involves a computation of the area of the ten-sion flange, which includes the area in the outer 1/3 of the distance ct .

A = 12 × 1 + 0.375 × ( 27.1 ____ 3 – 1 )

= 15.0 in2

The area in the heat-affected zone is (see Figure 16):

Aw = 2.375 × 1 + 0.375 × 1 = 2.75 in2

The percentage is:

100 × Aw ________

A = 100 × 2.75 __________

15.0 = 18.3%

Since this is more than 15%, Section 7.2.2 requires reduction in allowable stress because of the welding.

From Table 3.3-2 and Section 3.4.2

Ftyw ____ ny

= 19 ____ 1.85

= 10.3 ksi.

From Table 3.4-2, value of kt within 1.0 in. of weld,

kt = 1.0

Ftuw ____ kt nu

= 42 _________ 1.0 × 2.20

= 19.1 ksi, 10.3 < 19.1

Fw = 10.3 ksi allowable tensile stress within one inch of a weld.

From Section 7.2.2

Fpw = Fn – Aw ___ A

( Fn – Fw )

= 17.8 – 2.75 ____ 15.0

( 17.8 – 10.3 )

= 16.4 ksi allowable tensile stress.

Allowable moment from tension in bottom fiber.

Mt = FSt = 16.4 × 743 = 12,200 in.-kips

Allowable moment based on compression

From Part VII, Design Aids, Table 2-19, building struc-tures, Section 3.4.11, the slenderness limits for alloy 5456-H321 are:

S1 = 25, and S2 = 119

NOTE: The slenderness limits listed may differ slightly between Building and Bridge type structures due to rounding of the coefficients in the allowable stress for-mulas; however, this produces only a negligible effect on allowable stress. If desired, S1 and S2 may be calcu-lated from the general formulas of Table 3.4-3.


From Table 3.4-3, Section 3.4.11, lateral buckling,

Lb __ ry

= 10 × 12 _______ 3.69

= 32.5

The slenderness lies between S1 = 25 and S2 = 119; therefore

F1 = 1 __ ny ( Bc –

DcLb ____ 1.2ry

)

= 1 ____ 1.85

( 31.4 – 0.212 × 10 × 12 ______________ 1.2 × 3.69

)

F1 = 13.9 ksi

NOTE: Under certain conditions a larger value of stress may be allowable, see Section 4.9; however, in this case F3 controls as is shown below and there is no need to investigate further. See example 15, notes.

Section 3.4.15, compression in outstanding flange,

b __ t = 16.0 – 0.375 ___________ 2 × 1

= 7.8, slenderness

From Part VII, Design Aids, Table 2-19, S1 = 7.5The slenderness is greater than S1

F2 = 1 __ ny ( Bp – 5.1Dp

b __ t ) = 1 ____

1.85 ( 37.7 – 5.1 ( 0.278 ) 7.8 ) = 14.4 ksi

Section 3.4.18: compression in web,

h __ t = 48 _____ 0.375

= 128, slenderness

From Part VII, Table 2-19, S1 = 53, S2 = 88Therefore the slenderness is greater than S2

F3 = k2 √

____ BbrE _________

ny ( 0.67h/t )

= 2.04 √

____________ 50.1 × 10,400 _________________

1.85 × 0.67 × 128 = 9.28 ksi

This stress is at the extreme fiber of the web and can be extrapolated to the extreme fiber of the beam.

F4 = 9.28 × 22.9 __________ 22.9 – 1.0

= 9.70 ksi

Comparing the allowable compressive stresses,

F4 < F1 < F2, use Fb = F4 = 9.70 ksi, web compres-sion controls

Effect of welding. From Section 7.2.2: the effect of the heat of welding involves a computation of the area of the compression flange. The compression flange is con-sidered to include only those parts in the outer 1/3 of the distance cc.

A = 16 × 1 + 0.375 × ( 22.9 ____ 3 – 1 ) = 18.5 in2

The area in the heat-affected zone is (see Figure 16):

A = 2.375 × 1 + 0.375 × 1 = 2.75 in2

The percentage is:

100 × Aw ___ A

= 100 × 2.75 __________ 18.5

= 14.9%

Since this is less than 15%, Section 7.2.2 requires no reduction in allowable stress because of the welding.

Allowable moment from consideration of compression in top fiber.

Mc = FbSc = 9.70 × 879 = 8530 in.-kips

Allowable moment based on fatigue

From Specification Figure 4.8-1, Example 4 is a girder with continuous welds attaching web and flange, simi-lar to that shown in Figure 16. The stress category is selected from Table 4.8-1. The category for a built-up member (see general condition in left column) with continuous weld parallel to the direction of stress for example numbers 3, 4, and 5 (right column) is B.

For constant amplitude loading, the applied stress range Sra shall not exceed the allowable stress range Srd (see Section 4.8.1)

Srd = Cf × N–1/m

Where, for Stress Category B,

Cf = 130 ksi and m = 4.84

for the number of cycles, N = 500,000,

Srd = (130) × (500,000)–1/4.84 = 8.6 ksi

The value 8.6 ksi is the stress range allowed in each cycle. The dead load stress should be added to this value to obtain the maximum stress. It is assumed here that the dead load stresses are negligible. The section modu-


lus, Sw corresponding to the weld location on the tension flange is:

Sw = 20,132

_________ 27.1 – 1.0

= 771 in3

The allowable moment for fatigue Mf, is calculated for tensile stress range at the web.

Mf = Ff Sw = 8.6 × 771 = 6630 in.-kips

If variable amplitude loading occurred, an equivalent stress range would be calculated and compared to the allowable stress range. For example, if the loading were

100,000 cycles 9.5 ksi stress range 50,000 cycles 10.0 ksi stress range350,000 cycles 7.1 ksi stress range500,000 cycles at various stress ranges

In accordance with Section 4.8.2, the equivalent stress range Sre which may not exceed the allowable stress range Srd is

Sre = [ 100 ____ 500

×9.54.84 + 50 ____ 500

×10.04.84 + 350 ____ 500

×7.14.84 ] -1/4.84

Sre = 8.2 ksi < 8.6 ksi = Srd

So this variable amplitude loading does not exceed the allowable stress range.

Selection of allowable moment

Comparing the allowable tensile, compressive, and fatigue moments,

Mf < Mc < Mt, M = Mf = 6630 in.-kips.

The allowable moment is 6630 in.-kips.

NOTES: In this case the value of b/t was less than slen-derness S2; however, for very thin flanges the local buckling of the top flange may influence the lateral buckling of the compressive flange. This effect is covered in Specification Section 4.7.5.

In the example, lateral buckling in Section 3.4.11 was not the controlling factor. If lateral buckling had been criti-cal, the designer may have wanted to use the larger, more accurate value of ry, computed according to Specification Section 4.9.

The lateral buckling formulas used in Section 3.4.11 were derived on the assumption that in the distance Lb between lateral restraints of the compression flange, there are no restraints of any type at either the tension or com-pression flange. Often, there are some restraints, such as the case of roof beams subjected to uplift wind load. In the lat-ter case the bottom flange becomes a laterally unsupported compression member except for the staying action that is obtained through the web from what may be laterally and torsionally restrained tension flange at the top. A solution of this type of problem utilizing Engesser’s formula for a column with an elastic lateral support is available.*

Filler metal for welds should be selected from Table 7.1-1 of the Specification.

*Haussler, Robert W. “Some Aspects of the Stability of Cold Formed Shapes,” Meeting Preprint MTL-21, ASCE/EIC/RTAC Joint Transpor-tation Engineering Meeting, July 1974, p 4.

Haussler, Robert W. “Strength of Elastically Stabilized Beams,” ASCE, Transactions, Vol. 130, 1965, p 637.


Example 17ALLOWABLE BENDING MOMENT IN A WELDED GIRDER

WITH TRANSVERSE STIFFENERSIllustrating Section 4.8

The value 7.6 ksi is the stress range that occurs each cycle. Neglecting dead load effects, the section modulus at the bottom end of the stiffener is:

Sw = 20,132

_________ 27.1 – 4.0

= 872 in3

The allowable moment for fatigue, Mf , is calculated for a tensile stress range at the end of the stiffener.

Mf = 7.6 (872) = 6630 in.-kips

Selection of allowable moment.

Comparing the allowable tensile, compressive and fatigue moments,

Mf < Mc < Mt, Mf = 6630 in.-kips

The allowable moment with the transverse stiffeners is the same as the allowable moment without the stiffeners.

GIVEN:

Same as Example 16 except that brackets are welded to girder web and top flange.

REQUIRED:


SOLUTION:

Allowable moment based on fatigue.

From Specification Figure 4.8-1, Example 6 is a girder with a similar detail at the bottom of the stiffener to that shown in Figure 17. The category corresponding to Exam-ple 6 is C.

For constant amplitude loading, the applied stress range Sra shall not exceed the allowable stress range Srd (see Section 4.8.1)

Srd = Cf × N–1/m

Where, for stress category C,

Cf = 278 ksi and m = 3.64

for the number of cycles, N = 500,000,

Srd = (278) × (500,000)–1/3.64 = 7.6 ksi

Figure 17


Example 18DESIGN OF A PIPE BEAM


From Part VII, Beam Formula Case 1, Simply supported beam, concentrated load P at center.

M = PL ___ 4 = 5.50 × 10 × 12 _____________

4 = 165 in. –kips.

S = M __ F

= 165 ____ 24

= 6.88 in3, trial section modulus

From Part VI, Table 22, 6.625 in. OD Schedule 40 pipe with a wall thickness of 0.280 in. has a section modulus of 8.50 in3 and is the thinnest 6 in. pipe with a sufficiently large section modulus.

From Specification Section 3.2: NomenclatureDefinition of Rb is “midthickness radius.”Section 3.4.12. Compression in round tube beam,

Rb __ t = 6.625 – 0.280 ____________

2×0.280 = 11.3


The trial beam is therefore satisfactory; use Schedule 40 pipe.

GIVEN:

1. Concentrated load of 5.50 kips (5,500 lb) including impact and dead loads at mid-span.

2. Span: 10 ft, simply supported.3. Alloy: 6061-T6.4. Type of structure: Tip bar of A-frame crane. Use build-

ing structure allowable stresses.

REQUIRED:

Wall thickness of thinnest 6 in. pipe that will safely support the load.

SOLUTION:

From Part VII, Design Aids, 2-22,Section 3.4.3:

F = 24 ksi,

Section 3.4.12:

F = 25 ksi, assuming slenderness < S1

Use lower value of stress, 24 ksi, for trial beam.

Figure 18


Example 19DESIGN OF A SOLID RECTANGULAR BAR BEAM


From Part VII, Design Aids, Table 2-10 Sections 3.4.4 and 13 both indicate lower allowable stress even where the slenderness is less than S1

F = 20 < 24.1 ksi, F = 19 < 24.1 ksi

Try a 3/8 in. thick bar.

A = 0.563 in2

Ix = 0.106 in4

f = Mc ___ I = 2.25×0.75 _________

0.106

= 15.9 ksi, bending stress

From Part VII, Table 2-10, Section 3.4.13,

d __ t √___

Lb __ d = 1.50 _____

0.375 √

____

36 ____ 1.50

= 19.6


F = 26.7 – 0.494 d __ t √___

Lb __ d

= 26.7 – 0.494 × 19.6 = 17.0 ksi

The section modulus of a 5/16 in. wide bar would be 5/6 of the section modulus of a 3/8 in. wide bar. Since the stress f = 15.9 ksi is more than 5/6 of the allowable F = 17.0 ksi, a 5/16 in. bar will not be usable even at the highest stress permitted for a 3/8 in. bar.

Use a 3/8 in. thick bar.

GIVEN:

1. Beam section: 1.50 in. deep solid rectangular bar.2. Load 0.500 kips (500 lb) at mid-span.3. Span: 36 in.4. Ends of beam restrained, lateral support at ends only.5. Alloy: 5052-H34.6. Type of structure: Building.

REQUIRED:

The thinnest standard bar that will safely support the load.

SOLUTION:

From Part VI, Table 28 rectangleTry a 1/4 in. thick bar

A = 0.25 × 1.50 = 0.375 in2

Ix = 0.25×1.503 __________

12 = 0.070 in4

Since this section is symmetric about the x-axis,

c = d __ 2 = 1.50 ____

2 = 0.75 in.

From Part VII, Beam Formula Case 26, concentrated load P at center,

M = PL ___ 8 = 0.50×36 ________

8 = 2.25 in. –kips

flexural stress at extreme fiber

f = Mc ___ I = 2.25×0.75 _________

0.070 = 24.1 ksi

Figure 19


Example 20ALLOWABLE SPACING OF RECTANGULAR TUBULAR BEAMS

Illustrating Sections 3.4.2, 14, 16, 18 and 20

From VII, Design Aids, Table 2-23 Conservatively using the lesser of the allowable stresses for the flanges (3.4.2) and the webs (3.4.4), Section 3.4.2: Tension in rectangular tube beams

F1 = 9.5 ksi

Section 3.4.14: Compression in rectangular tube beam

LbSc ______

0.5 √___

IyJ = 12×12×2.11 _____________

0.5 √_________

1.37×3.19 = 291


F2 = 10.5 – 0.070× √______

LbSc _____

0.5 √___

IyJ

= 10.5 – 0.070× √____

291 = 9.31 ksi

Section 3.4.16: Compression in component

b __ t = 1.624 _____ 0.188

= 8.6


F3 = 9.5 ksi

Section 3.4.18: Compression in web

h __ t = 3.624 _____ 0.188

= 19.3


F4 = 12.5 ksi

The lowest stress F = F2 = 9.31 ksi

M = FSc = 9.31 × 2.11 = 19.6 in.-kips

GIVEN:

1. 4 in. × 2 in rectangular tube with 0.188 in. wall (RT 2 × 4 × 0.188)

2. Load: 20 lb/ft2 total live and dead loads.3. 12 ft simple span, laterally unsupported.4. Alloy: 6063-T5.5. Type of structure: Building.

REQUIRED:

The maximum allowable spacing of the beams.

SOLUTION:

From Part VI, Table 28, properties of rectangle. The properties of the tube are obtained by subtracting the inside rectangle from the outside rectangle. This will produce correct results for evaluating A and I.

Ix = b1d 3

1 ____

12 –

b2d 3 2 ____

12

= 2×43 _____

12 – 1.624×3.6243

____________ 12

= 4.23 in4

Sc = Ix __ c = 4.23 ____

2 = 2.11 in3

Iy = 4×23 _____

12 – 3.624×1.6243

____________ 12

= 1.37 in4

From the Commentary for Section 3.4.14

J = ( 2 ) ( .188 ) 2 ( 4 – .188 ) 2 ( 2 – .188 ) 2 ___________________________ 4 ( .188 ) + 2 ( .188 ) – .1882 – .1882 = 3.19 in4

Figure 20


From Part VII, Beam Formula Case 6Simply supported beam, uniform load

M = WL ____ 8 , which can be written

W = 8M ____ L

, when W is unknown

W1 = 8M ____ L

= 8×19.6 _______ 12×12

= 1.09 kips

From Part VII, Table 2-23,Section 3.4.20: Web shear

h __ t = 3.624 _____ 0.188

= 19.3


Fs = 5.5 ksi

Web area

A = 2 × 0.188 × 3.624 = 1.36 in2

Average vertical shear stress

V = Fs A = 5.5 × 1.36 = 7.48 kips

W2 = 2V = 2 × 7.48 = 15.0 kips,

allowable load from shear stress consideration; see notes of Example 26 for accuracy of this method. Since W1 is less than W2, the lateral buckling stress in flexure controlsW = W1 = 1.09 kips, total allowable load per beam.

The allowable spacing can now be determined from the given unit load of 20 lb/ft2 or 0.020 kips/ft2

Spacing = W _______ 0.20×L

= 1.09 ________ 0.20×12

= 4.54 ft o.c.

The center to center spacing of the beams should therefore not exceed 54 in.



Fb = 21 ksi

From Part VI Table 8Select trial beam I 10 × 8.65S = 26.4 in3, tw = 0.25 in. tf = 0.41 in.

f = M/S = 486 ____ 26.4

= 18.4 ksi < 19

Check allowable stress based on local buckling of com-pression flange

From Part VII, Table 2-22Section 3.4.15.

b = 1 __ 2 ( 6.00 – 0.25 ) = 2.875

b __ t = 2.875 _____ 0.41

= 7.0

Slenderness limits S1 = 6.5, S2 = 10.Since 6.5 < 7.0 < 10.0,

Fb = 27.3 – 0.93 b __ t

= 27.3 – 0.93 × 7.0 = 20.8 ksi

Since the calculated stress, 18.4 ksi, is less than the allowable tensile stress, 19 ksi, and the allowable compressive stress, 20.8 ksi, the trial beam is satis-factory.

GIVEN:

1. Uniform load: 1.00 kips/ft (1,000 lb/ft) including dead load.

2. Span: 18 ft, simply supported.3. Compression flange is adequately supported laterally.4. Alloy: 6061-T6.5. Structure type: Building.

REQUIRED:

Size of lightest Aluminum Association standard I-beam that will safely support the load.

SOLUTION:

From Part VII, Beam Formula Case 6Load, W = wL = 1.00 × 18.0 = 18.0 kips

Part VII, Table 4-2 indicates that an I 10 × 8.65 will support 19.69 kips at a 17 ft span; therefore, it may be the desired beam. However, the allowable load for 18 ft span is not tabulated, but it can be determined by com-putations as follows:

Maximum bending moment,

M = WL ____ 8 = 18.0×18×12 ___________

8 = 486 in. –kips

From Part VII, Design Aids, Table 2-22Section 3.4.2: Allowable tensile stress

F = 19 ksi

Figure 21

Example 21DESIGN OF A SIMPLY SUPPORTED I-BEAMIllustrating Sections 3.4.2, 11, 15, 18 and 20


NOTES: the use of an Aluminum Association standard I-beam usually makes it unnecessary to reduce the stress for local buckling. Where Table 4 or 8 of Part VI is used and the alloy is 6061-T6, it is not necessary to check for local buckling under Section 3.4.18.

On the other hand, extruded I-shapes that are specially designed should always be checked to see that Section 3.4.18 does not restrict the allowable bending stress more than Sections 3.4.2, 11, and 15.

If slenderness S2 is exceeded in Section 3.4.15, there is a possibility of combined overall and local buckling. In this case the special design rule in Section 4.7.5 should be checked. For increased economy in this case of combined buckling the use of Section 4.9 will often be of consider-able assistance.

For short, heavily loaded beams, Section 3.4.20 should be checked.

Where deflection must be limited, it may be calculated from Part VII Beam Formula Case 6

Deflection = 5WL3 ______

384EI

= 5×18.0× ( 18×12 ) 3 ________________ 384×10,000×132

= 1.79 in.

in which E is obtained from Table 3.3-1 of the Specification and footnote thereto and I is obtained from Table 8 of Part VI.


Example 22ALLOWABLE BENDING MOMENT OF AN UNSYMMETRIC BEAM

Illustrating Sections 3.4.2, 11, 15, 16, 18 and 20

Section 3.4.11: Compression in extreme fiber

F = 21 ksi. (Beam is laterally supported)

M2 = 21×5.15 ________ 6 – 3.70

= 47.0 in. –kips,

allowable moment from Section 3.4.11.

Section 3.4.15: Compression in outstanding flanges (see note to Part I of Example 23).

b __ t = 0.70 – 0.072 ___________ 0.072

= 8.7,


F = 27.3 – 0.93 × 8.7 = 19.2 ksi

c = 6 – 3.70 – 0.072 – 0.5 × (0.7 – 0.072)

= 1.91 in., distance from neutral axis to centroid of flange lip.

M3 = 19.2×5.15 _________ 1.91

= 51.8 in. –kips,


Section 3.4.16.2: Compression in elements of beams-flat ele-ments with one edge supported and other edge with stiffener.

b = 4 – 0.72×3 __________ 2 = 1.89 in. –kips,

Ds = 0.70 – 0.072 = 0.628

Ds ___ b = 0.628 _____

1.89 = 0.33 < 0.8, So 3.4.16.2 applies

S = 1.28 √___

E ___ Fcy

= 1.28 √______

10,100

______ 35

= 21.7

b __ t = 1.89 _____ 0.072

= 26.25; rs = dssinθ _____

√__

3 = 0.7 – 0.072 __________

√__

3 = 0.363

2S = 43.5 > 26.25 = b/t > 21.7 = S, so

ρst = rs __________

1.5t ( b/t ___ S + 3 )

= 0.363 _________________ 1.5 ( .072 ) ( 26.26 _____

21.7 + 3 )

ρst = 0.797 < 1.0

GIVEN:

1. Beam of cross section shown in Figure 22.2. Continuous lateral support of compression flange.3. Alloy: 6061-T6.4. Type of structure: Building.

REQUIRED:


SOLUTION:

The section properties are computed as shown in exam-ple 16 with the following results:

ct = 3.70 in.

Ix = 5.15 in4

From Part VII, Design Aids, Table 2-22,Section 3.4.2: Tension in beams

F = 19 ksi

M1 = F×I ____ ct = 19×5.15 ________

3.70

= 26.4 in.-kips

allowable moment from Section 3.4.2

Figure 22


FUT = allowable stress for flange as if supported per 3.4.15

b __ t = 26.25 > 10 = S2, so

FUT = 182 ____ ( b/t )

= 182 _____ 26.25

= 6.93 ksi

FST = allowable stress for flange as if fully stiffened per 3.4.16

21 < b/t = 26.25 < 33

FST = 27.3 – 0.292 (b/t) = 27.3 – 0.292 (26.25)

FST = 19.7 ksi

Fc = FUT + (FST – FUT)ρST ≤ FST

Fc = 6.93 + (19.7 – 6.93) (0.797) = 17.1 ksi

(Note this is less than Fcy ___ ny

= 35 ____ 1.65

= 21.2 ksi)

M4 = 17.1×5.15 ___________________ 6 – 3.70 – ( 0.072×0.5 )

= 38.9 in. –kips

allowable moment from Section 3.4.16.2.


h __ t = 6 – 0.072×2 ___________ 0.072

= 81.3

Slenderness is greater than S2 = 75

F = 1520 _____ 81.3

= 18.7

M5 = 18.7×5.15 ______________ 6 – 3.70 – 0.072

= 43.2 in. –kips


Comparing the allowable moments M1 thru M5, it is clear that M1 is the smallest,

M = 26.4 in.-kips, allowable moment in beam.

NOTE: When the actual loading is known the shear stress should be checked under Section 3.4.20.


Example 23ALLOWABLE STRESS FOR A CHANNEL BEAMIllustrating Sections 3.4.4, 11, 15, 17, 18, and 20

sive stress is the smaller stress means that compression controls.

The allowable stress is 15.8 ksi.

Allowable bending moment: The section properties are computed as in example 16 with the following results:

c = 1.34 in.

I = 0.325 in4

Computing the allowable bending moment,

M = FI ___ c = 15.8×0.325 __________ 1.34

= 3.83 in. –kips

NOTES, Part I:For sections having an element similar to those covered

by Section 3.4.15, but not parallel to the neutral axis, the question arises as to which Section to use, 3.4.15 or 3.4.17. A case of this type was studied under example 22 where the lip on the top flange was checked under Section 3.4.15, even though it was not under uniform compression. The general rule is as follows: First determine the distance from the neutral axis to the centroid of the element, then multi-ply that distance by 1.3. If the result equals or exceeds the distance from the neutral axis to the free end of the ele-ment, use Section 3.4.15; otherwise, use Section 3.4.17.

The stress limit of Section 3.4.17 applies only to the free end of the element. When the free end of such an element is in tension use Section 3.4.18 to determine the allowable compressive stress at the attached end of the element.

GIVEN:

1. 2.5 in. × 2 in. × 0.125 in. channels as shown in Figure 23.

2. Alloy: 6063-T6.3. Type of structure: Building.

REQUIRED:

The allowable positive bending moment about the X-X axis for each type of channel shown in Figure 23

SOLUTION:

Part I, channel without stiffener lips:

From Part VII, Design Aids, Table 2-24, Section 3.4.17: Compression in element under bending in own plane,

b __ t = 2 – 0.125 ________ 0.125

= 15.0


Fc = 27.9 – 0.808× b __ t

= 27.9 – 0.808 × 15.0 = 15.8 ksi

Section 3.4.4: Tensile stress in flat elements bent in their own plane,

Ft = 20 ksi, 20 > 15.8

The distance from the neutral axis to the extreme tensile fiber is less than that to the extreme compressive fiber. This combined with the fact that the allowable compres-

Figure 23


Part II, channel with stiffener lips:

From Part VII, Design Aids, Table 2-24,Section 3.4.4: Tension in flat elements bent in their own

plane,

Ft = 20 ksi

Section 3.4.18: Compression in webs,

h __ t = 2 – 2×0.125 ___________ 0.125

= 14


Fc = 20 ksi

The use of Section 3.4.18 assumes that the lip provides lateral support at the top of the web. For single web beams this is checked by Section 3.4.11. For multiple web beams, such as the case at hand Section 4.10 is used in conjunction with Section 3.4.11.

Section 4.10: Compression in elastically supported flanges.

E = 10,000 ksi, from Specification Table 3.3-1 and footnote thereto related to deflection. The section properties are computed as in example 16 with the following results:

c = 1.20 in. to top fiber.

Ix = 0.461 in4

The area of the compression flange includes the web area that lies in the top third of the compression area:

Ac = ( 0.5 – 0.125 + 1.20 ____ 3 ) × 0.125

= 0.0969 in2 for each flange

In order to compute Iyc the horizontal distance from the center of one web to the centroid of the compres-sion flange, cx is needed.

cx = ∑Ax ____ Ac

where x is horizontal distance from the

center of the web to the centroid of the area A

cx = 0.5×0.125 _________ 0.0969

× ( 0.5 ___ 2 – 0.125 _____

2 ) = 0.121 in.

Dividing the compression flange into two rectangles, the horizontal rectangle is 0.5 by 0.125 while the vertical rectangle is

1.20 ____ 3 – 0.125 = 0.275 by 0.125 inches.

Iyc = 0.125 0.53 _________

12 + 0.275 × 0.1253

____________ 12

+ 0.125×0.5× ( 0.5 ___ 2 – 0.125 _____

2 )

2

– 0.0969×0.12122 = 0.00213 in4

The spring constant, βs, is defined in Section 3.2. It is obtained from the elastic properties of the section as developed in the reference*:

βs = 6EI ________________ ( 3l1 + 2a1 ) a 2

1 ( 1–v2 )

I = t3 ___

12 = 0.1253

______ 12

= 0.000163 in4, moment of inertia of a unit length of the web about a longitudinal axis.

I1 = 2.50 – 0.125

= 2.38 in., length of bottom flange.

a1 = 2.00 – 0.125

= 1.88 in., height to compression flange.

v = 0.33, Poisson’s ratio for aluminum.

βs = 6×10,000×0.000163

____________________________ 3×2.38 + 2×1.88×1.882 ( 1– 0.332 )

= 0.285 kips/in.

Effective Lb /ry = 2.7 4 √______________

10,000×0.09692

______________ 0.285×0.00213

= 53.5

Slenderness lies between S1 = 22 and S2 = 94 of Section 3.4.11.

F = 16.7 – 0.073 × 53.5 = 12.8 ksi at centroid.

The allowable stress thus obtained is at the centroid of the compression flange which is a distance cy above the neutral axis.

cy = 0.125 ______ 0.0969

× [ 0.5 ( 1.20 – 0.125 × 0.5 )

+ 0.275 ( 1.20 – 0.125 –0.275×0.5 ) ]

= 1.07 in.


Proportioning the stress to the extreme fiber,

F = 12.8× 1.20 ____ 1.07

= 14.4 ksi

Comparing this with the allowable stress for slenderness less than S1,

14.4 < 15, use F = 14.4 ksi

Allowable bending moment: Comparing the allowable stress from Section 3.4.11 with those obtained from Sections 3.4.4 and 3.4.18, the controlling stress is from Section 3.4.11.

M = FIx ___ c = 14.4×0.461 __________

120

= 5.53 in. –kips

NOTES, Part II:If the shape of the stiffener is more complex than a

simple flange, and has considerable torsional stiffness the designer may include this effect in the computations. How-ever, if the torsional stiffness of the compression flange is included as in the reference* the value of a1 must be the height to the shear center of the compression flange.

When the actual loading is known, the shear stress should be checked according to Section 3.4.20.

*See: Haussler, Robert W. “Strength of Elastically Stabilized Beams,” Paper 3951, Journal of the Structural Division, Proceedings ASCE, ST3, June, 1964, Eq. 27 page 227.


Example 24ALLOWABLE WEB STRESS IN A WELDED BEAM


Figure 24

GIVEN:

1. Beam cross section as shown in Figure 24.2. Alloy of web: 6061-T6.3. Type of structure: Building.

REQUIRED:

Allowable stress at the extreme fiber of web.

SOLUTION:

From Part VII, Design Aids, Table 2-22,Section 3.4.18: Compression in web

h __ t = 72 _____ 0.190

= 379

The slenderness is greater than S2 = 119 for both welded and nonwelded members.

Fc = 1,520

_____ h/t

= 1,520

_____ 379

= 4.01 ksi

The allowable compressive web stress is 4.01 ksi.

NOTES:In sections which are not symmetrical about the neutral

axis the value of h may be taken as twice the height of the compression portion of the web. For a sloping web the measurement is taken along the web rather than vertically.

Had the slenderness been such that the formulas for welded and nonwelded beams were different, it would have been necessary to check Section 7.2 to see which formula should be used. If more than 15% of the area of the com-pression flange were within 1 in. of the weld, both formulas would have been needed plus the formula of Section 7.2. See Figure 16 for application of the 1 in. rule.

For sections having an element similar to those covered by Section 3.4.16, but not parallel to the neutral axis, the question arises as to which Section to use, 3.4.16 or 3.4.18. The general rule is that where both ends of the element are in the compression zone (above the neutral axis) Sec-tion 3.4.16 should be used. When using Section 3.4.16 the critical fiber is at the centroid of the element. However the extreme fiber of the element should also be checked using Section 3.4.16 with slenderness less than S1.

Filler metal for welds should be selected from Specifica-tion Table 7.1-1.


Example 25ALLOWABLE WEB STRESS IN A WELDED BEAM WITH STIFFENED WEB


GIVEN:

1. Beam cross section as shown in Figure 25.2. Neutral axis of beam is at mid-height of web.3. Vertical stiffener spacing 10 ft o.c.4. Alloy of web: 6061-T6.5. Type of structure: Building.

REQUIRED:

1. Allowable web stress at the toe of the compression flange.

2. Confirm adequacy of horizontal stiffener.

SOLUTION:

From Part VII, Design Aids, Table 2-22,Section 3.4.19: Compression in stiffened web

h __ t = 72 _____ 0.190

= 379

The slenderness is greater than S2 = 280 for both welded and nonwelded members.

Fc = 3,500

_____ h/t

= 3,500

_____ 379

= 9.23 ksi

Check adequacy of horizontal stiffener, Section 4.5Longitudinal Stiffeners for Webs.

αs = 3.5

h = 72 in.

t = 0.190 in.

f = 9.23 ksi

s = 120 in.

Ah = 5.25 × 2.50 – 5.06 × 2.12

+ 0.19 × 1.00 = 2.59 in2

Ih = 0.02×3.5×9.23×0.190×723

× [ ( 1 + 6×2.59 _________ 72×0.190

) ( 120 ____ 72

) 2

+ 0.4 ] ÷10,100

Ih = 28.7 in4, required moment of inertia stiffener.

Actual moment of inertia = ¹/3 (5.253 × 2.50 –5.063 × 2.12 + 0.193 × 1.00) = 29.0 in4

Figure 25

The stiffener is therefore satisfactory.

The required distance from the toe of the compres-sion flange to the centroid of the stiffener

0.4× 72 ___ 2 = 14.4 in.

The allowable web stress is 9.23 ksi.

NOTES: The notes of example 24 also apply to this example.


Example 26ALLOWABLE LOAD ON AN I-BEAM WITH WEB SHEAR CONTROLLING

Illustrating Sections 3.4.2, 11, 15, and 20

F1 = 19 ksi

Section 3.4.11: Allowable compression. Use slender-ness less than S1 for continuous lateral supports.

F2 = 21 ksi

Section 3.4.15: Allowable compression in unstiffened flanges

b __ t = 5.00 – 0.23 __________ 2×0.35

= 6.8

6.8 > 6.5 = S1, so

F3 = 27.3 – 0.93(6.8)

F3 = 21 ksi

Section 3.4.18 need not be checked for Aluminum Asso-ciation standard beams in alloy 6061-T6.

From Part VII, Beam Formula Case 6, Simply supported beam, uniform load,

M = wL2 ____

8 , which can be written

w1 = 8M ____ L2 , when W is unknown

V = wL ___ 2 , shear at end of beam. Rearranging

w2 = 2V ___ L

GIVEN:

1. 8 in. × 5 in. Aluminum Association standard I-beam weighing 6.18 lb/ft (I 8 × 6.18)

2. Span: 4 ft, simply supported at ends.3. Compression flange continuously laterally supported.4. Alloy: 6061-T6.5. Type of structure: Building.

REQUIRED:

Allowable uniform load.

SOLUTION:

From Part VI, Table 8, Aluminum Association standard I-beams.

d = 8.00 in.

b = 5.00 in.

A = 5.26 in2

tf = 0.35 in.

tw = 0.23 in.

Ix = 59.7 in4

Sx = 14.9 in3

From Part VII, Design Aids, Table 2-22 Conservatively using the lesser of allowable stresses for the flanges (3.4.2) and the web (3.4.4), allowable ten-sion in bottom fiber

Figure 26


F1 < F2 or F3; therefore tension controls the design in bending.

F = F1 = 19 ksi

M = FS = 19 × 14.9 = 283 in.-kips

w1 = 8M ____ L2 = 8×283 ______

482

= 0.983 kips/in. or 11.8 kips/ft,

allowable load based on bending.

From Part VII, Design Aids, Beam Formula

V = Fs Ix b1 _____

Q , horizontal shear.

See notes for approximate method.

b1 = tw = 0.23 in.

The maximum shear is at the neutral axis. Horizontal shear equals vertical shear.

The fillets may be neglected when figuring Q.

Q1 = ( 5.00×0.35 ) × ( 8.00 ____ 2 – 0.35 ____

2 )

= 6.69 in3, top flange

h = 8.00 – 2 × 0.35

= 7.30 in., web height

Q2 = ( 7.30 ____ 2 ×0.23 ) × ( 7.30 ____

4 )

= 1.53 in3, top half of web.

Q = Q1 + Q2 = 6.69 + 1.53 = 8.22 in3

From Part VII, Table 2-22Section 3.4.20: Shear in web

h __ t = 7.30 ____ 0.23

= 31.7

Slenderness is less than S1 = 36.

Fs = 12 ksi, allowable web shear stress.

V = Fs Ix b1 _____

Q = 12×59.7×0.23 _____________

8.22

= 20.0 kips, allowable shear.

w2 = 2V ___ L

= 2×20.00 ________ 4 = 10.0 kips/ft

Comparing w1, the allowable load based on bending, to w2, the allowable load from shear,

w2 < w1

w = w2 = 10.0 kips/ft.

The allowable load is 10.0 kips/ft

NOTES: An acceptable simplified method of approxi-mating the shear stress in the web of I-beams and other beams in which the web area is smaller than the area of both the top flange and the bottom flange is to divide the total shear V by the area of the web between flanges. In the above example, this would result in a shear stress as follows:

fs = V ___ Aw

= 20.0 _________ 7.30×0.23

= 11.9 ksi

The accuracy of this simplification is demonstrated by the fact the stress thus obtained is very close to the 12.0 ksi used in the example. In Part VII, Table 4-2, the allowable load is shown as 44.16 kips or 11.04 kips/ft based on a web area equal to the web thickness times the overall depth of the beam, an assumption that is frequently used in engineering practice.

For other beams, the shear stress generally lies between that obtained by the simplified method and 1.5 times that value.

For the shear stress in round or oval tubes, see Specifica-tion Section 4.2.


Example 27DESIGN OF A RIVETED GIRDER WITH WEB STIFFENERS

Illustrating Sections 3.4.2, 5, 11, 15, 18, and 21

4. Size of end stiffeners.5. Size and spacing of required rivets connecting top and

bottom flanges to web.

SOLUTION:

1. Verify beam capacity in bending.Section 3.4.2: Tension in beam

F1 = 25 ksi = lesser of ( 60 _________ 1.25(1.95)

and 53 ____ 1.65

)

Section 3.4.11: Compression in beam, laterally supported.

F2 = 32 ksi = 53 ____ 1.65

Section 3.4.15: Compression in outstanding flange

b __ t = ( 5.00 – 0.50 ) ___________

0.50 = 9.0

Slenderness is greater than S2 = 8.5 = 0.35(69.0)

_________ 5.1(0.549)

F3 = 2.27 (69(10,900))½

________________ 1.65(5.1)(b/t)

= 230 ____ b/t

= 230 ____ 9.0

= 25.6 ksi

GIVEN:

1. Riveted girder as shown in Figure 27 and section prop-erties.

Ix = 1414 in4

Sx = 141 in3

A = 18.8 in2

Wt/ft = 22.8 lb/ft

2. Total uniform load: 84.4 kips (84,400 lb) including dead load.

3. Span: 15 ft, simple.4. Compression flange lateral supports: Continuous.5. Alloy: 2014-T6.6. Type of structure: Building.

REQUIRED:

1. Verify beam capacity in bending.2. Spacing and size of vertical stiffeners for web.3. Size and spacing of stiffener rivets.

Figure 27



h __ t = 14 _____ 0.190

= 73.7

Slenderness is greater than S2 = 0.5(103.6)

__________ 0.67(1.238)

= 62

F4 = 2.04 √

____________ 103.6(10,900) _________________

1.65(0.67)(h/t) = 1940 _____

h/t = 1940 _____

73.7 = 26.3 ksi

The smallest value of F is F1; therefore, tension in the flange controls the design for bending.

F = F1 = 25 ksi.

From Part VII, Beam Formula Case 6, simply supported beam, uniformly distributed load,

M = WL ___ 8 = 84.4× ( 15×12 ) _____________

8

= 1899 in.-kips, bending moment

f = M __ S = 1899 _____

141

= 13.5 ksi, actual bending stress

f < F, the actual bending stress is less than the allowable

The design is therefore satisfactory for bending stress.

2. Compute spacing and size of vertical stiffeners for web.

V = W __ 2 = 84.4 ____

2 = 42.2 kips, shear.

Approximate shearing stress in web between top and bottom rivet centers,

fs = 42.2 ________ 0.19×17

= 13.1 ksi, shear stress in web.

Section 3.4.21: Shear in stiffened web

Using the formula for slenderness greater than S2.

Fs = π2(10,900)

_____________ 1.2(1.25)2(ae/t)2 =

56,000 ______

( ae /t ) 2 ,

which can be written with ae unknown,

ae = t × √_________

56,000/Fs

= 0.19 × √__________

56,000/13.1 = 12.4 in.

ae is defined in the diagram for Section 3.4.21.

ae = a1 ______________

√____________

1+0.7× ( a1/a2 ) 2 , in which a1 = 14 in.

Note that by definition a1< a2. It is assumed that a2 will be greater than 14 in.

Solving for a2

a2 = a1 _____________

√____________

1 ___ 0.7

× ( a 2 1 ___

a 2 e – 1 )

= 14 _______________ √

_____________

1 ___ 0.7

× ( 142 _____

12.42 – 1 ) = 22.3 in.

The spacing of vertical stiffeners shall not exceed 22.3 in. Use 9 stiffeners spaced 22.3 in. o.c. (8 spaces). Size of vertical stiffeners from Section 4.6.

V = 42.2 kips, maximum at end stiffener

s __ h

= 22.3 ____ 14

= 1.59

1.59 > 0.4 therefore, use second formula.

Is = 0.073naVh2

__________ E

( h __ s ) =

( 0.073 ) ( 1.2 ) ( 42.2 ) 143 __________________

( 10,900 ) ( 22.3 ) = 0.042 in4

Bearing stiffener requirement from third formula using E from Table 3.3-1 and nu from Table 3.4-1,

Ib = Is + Pbsh2nu ______ π2E

= 0.042 + 42.2×142×1.95 _____________ π2×10,900

= 0.192 in4

From Part VI, Table 14The moment of inertia of a shape about its centroidal axis is always less than that about another parallel axis; therefore, the 1 1/2 × 1 1/2 × 1/8 angle with Ix of 0.074 in4 will be satisfactory for the intermediate stiff-eners for which the required Is is 0.042 in4.


Check the ratio of leg thickness to leg clear width,

t/b = 0.125/(1.5 – 0.125) = 1/11

The angle selected is satisfactory since 1/11 > 1/12 as required in Section 4.6 of the Specification.

For the vertical stiffener at the bearing, try two 1 1/2 × 1 1/2 × 1/8 angles, one on each side of the web.Distance from centroid to center of web is

x + t/2 = 0.41 + 0.19/2 = 0.505 in.

I = 2Ix + 2A × 0.5052

= 2 × 0.074 + 2 × 0.36 × 0.5052

= 0.332 in4

The pair of angles is satisfactory for the end stiffeners since I > Ib.

3. Compute the size and spacing of stiffener rivets. The 42.2 kip reaction must be transferred to the web. Try 1/2-in. rivets; from Part VII, Design Aids, Table 5-8, rivet areas,

A1 = 0.2091 × 2 = 0.418 in2 double shear.

A2 = 0.098 in2 bearing.

Reduction in shear strength from Part VII Table 5-2,

D/t = 0.5/0.19 = 2.63

Use 14.7% reduction.

Bearing on web,

F = 2(66)

_____ 1.95

= 68 ksi

Note: Since the web is fabricated from sheet, Ftu = 66 ksi.

Allowable bearing per rivet,

Pb = F × A2 = 68 × 0.098 = 6.66 kips

From Table 5.3.4-1, try alloy 2017-T4 rivets.Allowable shear per rivet

Ps = F × A1 × (1 – 0.147)

= 14 × 0.418 × 0.853 = 4.99 kips

Ps < Pb; therefore, the allowable load per rivet,

P = 4.99 kips

Number of rivets required,

V/P = 42.2/4.99 = 8.46 use 9 rivets

From Section 5.1.1, minimum edge distance is 1.5 times the diameter, which is 0.75 in. for a 1/2 in. rivet; therefore, a 1 1/2 in. angle is satisfactory.

From Section 5.3.6, the minimum spacing of rivets is 3 times the diameter or 1.50 in. in this example. Plac-ing one rivet in each flange, the spacing of the seven remaining required rivets is

S = 14/7 = 2 in. o.c., rivet spacing in end stiffeners.

Intermediate stiffener rivets can have a larger spac-ing, say 4 in. o.c.; however, if a concentrated load has been present at a stiffener, the rivets would be spaced to transfer the load to the web.

Filler plates 1/2 in. thick are required in Section 4.6 to eliminate the gaps between the stiffeners and the web. Grip of rivet is 1.44 in. and is therefore less than the four and one-half diameters above, which Section 5.1.6 requires in capacity.

4. Compute the size of end stiffeners.From Part VII, Design Aids, Table 5-8, bearing stress in end stiffeners,

f = 42.2/(2 × 0.0645 × 9) = 36.3 ksi

From Specification Section 3.4.5Allowable bearing stress for alloy 2014-T6 extrusions

= 2(60)

_____ 1.95

= 62 ksi, which is satisfactory.

Figure 27 shows the end reaction at the bottom flange for simplicity. Actually, the end of the beam is usually riveted to the support at the outstanding flange of the vertical stiffeners and the end stiffeners are satisfac-tory as calculated above. If the structure is supported as shown in the figure, the bearing on that portion of the stiffener beyond the fillet of the bottom flange can be used to transfer the reaction by substituting consider-ably larger angles for the end stiffeners. In this case, the required bearing area is

Ab = V/F = 42.2/62 = 0.681 in2

From Part VI, Table 16Radius of fillet of 5 × 3 × 1/2 angle is 3/8 in. Try 1/4 in. thick stiffener; required flange length.

d = 0.681/(2 × 0.25) + 0.375 = 1.74 in.


Use pair of 2 1/2 × 2 × 1/4 angles for vertical stiffeners at ends. Cope 2 in. flange and heel of 2 1/2 in. flange to clear fillet of bottom angle and fit remaining portion to form a tight and uniform bearing.

5. Compute size and spacing of required rivets connecting top and bottom flanges to web.

Shearing stress at flange angles,

fs = VQ

___ Ix b

, where Q is the static moment of the

flange angles about the neutral axis.

From Part VI, Table 14. Angles with equal legs,

A = 3.74 in2

x = 0.74 in.

Q = (2 × 3.74) × (10 – 0.74) = 69.3 in3

fs = VQ

___ Ixb

= 42.2×69.3 __________ 1414×0.19

= 10.9 ksi, shear in web at rivet line.

The rivet spacing s is determined by setting the allow-able rivet load as calculated above equal to the total shear stress in the web of the beam between rivets.

P = fs × b × s or, rearranging

s = P ___ fsb

= 4.99 _________ 10.9×0.19

= 2.41 in.

The maximum allowable spacing of 1/2-in. 2017-T4 rivets is therefore 2.375 in. o.c.

NOTES: The rivet spacing of 2.375 in. o.c. applies to the region of maximum shear, which is confined to the part near the supports of a simple span with a uniform load. The maximum shear in the middle half of the beam (starting at L/4 and ending at 3L/4) does not exceed 50% of the maxi-mum shear; therefore, in this region the rivet spacing can be twice as great, or 4 3/4 in. o.c.


Example 28ANALYSIS OF AN ALUMINUM CURTAINWALL I-BEAM

Illustrating Sections 3.4.11, 4.9.1, and 4.9.3

At any point x between supports 1 and 2,

M ( x ) = R1x – wx2 ___

2

= ( 3 __ 8 ) wLx – wx2

___ 2

Mmax = wL2 ____

8

M1 = 9 ____ 128

wL2

Since the loadings and support conditions are identical in spans 1 and 2, only span 1 will be reviewed.

Since the load acts both inward and outward, four possible failure modes exist. These include failure due to:

For the interior flange:1. extreme fiber tensile stress 2. extreme fiber compressive stress

For the exterior flange: 3. extreme fiber tensile stress 4. extreme fiber compressive stress

1. First consider pressure (inward) loadings:

GIVEN:

1. Twin span curtainwall I-beam as shown in Figure 28d.2. Beam cross section and properties as given in Figure 28e.3. Uniform wind load of 26.3 lb/ft2. Load must be applied

as both a pressure (positive inward) and suction (nega-tive) loading. Beams are spaced 5 ft o.c.

4. Lateral bracing provided at anchors and at horizon-tals.

5. Alloy: 6063-T5.6. Structure type: Building.

REQUIRED:

Check the given I-beam’s ability to carry the wind load safely.

SOLUTION:

From Part VII, Beam Formula Case 36, continuous beam of two equal spans-uniformly distributed load:

Load, w = (26.3 lb/ft2) (5 ft) (1 ft/12 in.) = 11.0 lb/in. (positive and negative)

Figure 28a

Figure 28b

(A) Consider extreme fiber tensile stresses:From Part VII, Design Aids, Table 2-23, Section 3.4.2

Fb = 9.5 ksi

For the beam, the maximum moment occurs at support 2:

Mmax = wL2 ____

8 =

( 11.0 ) ( 150 ) 2 ___________ 8 = 30,940 in.-lb

This results in the maximum extreme fiber tensile stress, which occurs in the exterior flange:

fb = Mc

___ I =

( 30.94 ) ( 6.00 – 3.05 ) _________________ 11.28

= 8.1 ksi < Fb; there-

fore, it is satisfactory


B) Consider extreme fiber compressive stresses: Allowable compressive stresses are a function of the unbraced length (Lb) and the compression flange geometry. Compressive stresses must therefore be reviewed at the var-ious combinations of moment and unbraced length.

SpanLb

(in.)Mmax

(in.-lb)Compression

flange0’ to 2’ 24 11,680 Exterior2’ to 10’-6” 102 17,400 Exterior10’-6” to 12’-6” 24 30,940 Interior

(1) From 0’ to 2’: To determine the slenderness ratio

Lb _____

ry √___

Cb , the bending coefficient Cb may be conservatively

taken as 1:

Lb __ ry

= 24 ____ 0.84

= 28.6

From Section 3.4.11,

Fb = 10.5 – 0.036(28.6) = 9.5 ksi

fb = Mc ___ I =

( 11.68 ) ( 6.00 – 3.05 ) _________________ 11.28

= 3.05 ksi < Fb ; there-

fore, it is satisfactory.

(2) From 2’ to 10’-6”: To determine the slenderness

ratio Lb _____

ry √___

Cb , the bending coefficient Cb may be conserva-

tively taken as 1:

Lb __ ry

= 102 ____ 0.84

= 121.4


Fb = 87,000

_______ ( 121.4 ) 2

= 5.9 ksi

fb = Mc

___ I =

( 17.4 ) ( 6.00 – 3.05 ) ________________ 11.28

= 4.6 ksi < Fb ; therefore,

it is satisfactory.

(3) From 10’-6” to 12’-6”: To determine the slenderness

ratio Lb _____

ry √___


taken as 1:

Lb __ ry

= 24 ____ 0.50

= 48


Fb = 10.5 – 0.036(48) = 8.8 ksi

fb = Mc

___ I =

( 30.94 ) ( 6.00 – 3.05 ) _________________ 11.28

= 8.4 ksi < Fb ; there-

fore, it is satisfactory

Figure 28c

2. Next, consider suction (outward) loadings:(A) Extreme fiber tensile stresses are similar to those under

pressure loading, therefore, it is satisfactory by inspection(B) Consider extreme fiber compressive stresses:

SpanLb

(in.)Mmax

(in.-lb)Compression

flange0’ to 2’ 24 11,680 Interior2’ to 10’-6” 102 17,400 Interior10’-6” to 12’-6” 24 30,940 Exterior

(1) From 0’ to 2’: To determine the slenderness ratio

Lb _____

ry √___


taken as 1:

Lb __ ry

= 24 ____ 0.50

= 48

From Section 3.4.11, Fb = 8.8 ksi

fb = Mc

___ I =

( 11.68 ) ( 3.05 ) ___________ 11.28

= 3.2 ksi < Fb ; therefore, it is

satisfactory.

(2) From 2’ to 10’-6”:To calculate the slenderness ratio

Lb _____ ry √

___ Cb , the bending

coefficient Cb must be calculated. To calculate Cb, deter-mine the moments at the quarter-point, midpoint, and three-quarter point of the span from 2’ to 10’-6”, in accordance with Section 4.9.4:

location xmoment(in.-lb)

3wLx _____ 8 –

wx2

___ 2

quarter-point 49.5 17,100 = MA

midpoint 75 15,400 = MB

three-quarter point 100.5 6,600 = MC

Mmax = 9wL2 _____

128 = 17,400 in-lb

Cb = 12.5Mmax ________________________ 2.5Mmax + 3MA + 4MB + 3MC

= 12.5 ( 17400 ) _____________________________________ 2.5 ( 17400 ) + 3 ( 17100 ) + 4 ( 15400 ) + 3 ( 6600 )

Cb = 1.23


Lb _____

ry √___

Cb = 102 ________

0.50 √____

1.23 = 183.9


Fb = 87,000

_______ ( 183.9 ) 2

= 2.6 ksi

fb = Mc

___ I =

( 17.4 ) ( 3.05 ) __________ 11.28

= 4.7 ksi < Fb ; therefore, it is

satisfactory.

Redetermine the allowable stress using the effective ry from Section 4.9.1. This allows use of equation 4.9.1-2:

rye = 1 ___ 1.7

√________________________________

Iy d ___ Sc

[ ± 0.5 + √____________________

1.25 + 0.152 ( J __ Iy

) ( kyLb ____ d ) 2 ]

calculated by taking Iy , Sc, and J as though both flanges were the same as the compression flange with the overall depth remaining the same. Because the load is on a flange and acts in a direction away from the shear center, the plus sign in front of “0.5” is to be used (see note 2 below also).

rye =

1 ___ 1.7

√_______________________________________

( 0.48 ) 6 ______ 3.65

[ + 0.5 + √_________________________

1.25 + 0.152 ( 0.033 _____ 0.48

) ( ( 1.0 ) ( 102 ) ________ 6 ) 2 ]

rye = 0.837 in.

Alternately, use the provisions of Section 4.9.3 to deter-mine rye:

rye = Lb ____

1.2π √____

Me ___ ESc

(Eq. 4.9.3-1)

Lb = 102”, E = 10,100 k/in2

Sc = Ix __ cx

= 11.28 _____ 3.05

= 3.70 in3

Me = AFey [ U + √___________

U2 + r 2 o ( Fet ___ Fey

) ] A = 1.92 in2 (area of full section)

This section is singly symmetric, so Section 4.9.4.2 may be applied to determine Cb. The moment of inertia of the compression flange about the y-axis is Icy:

Icy = 1 ___ 12

( 0.125 ) ( 1 ) 3 + 2 ___ 12

( 0.625 ) ( 0.375 ) 3

+ 2 ( 0.375 ) ( 0.625 ) ( 1.75 ____ 2 – 0.375 _____

2 )

2

Icy = 0.237 in4

Icy __ Iy

= 0.237 _____ 0.92

= 0.26 < 0.9, and 0.26 > 0.1, so

Fey = π2E ______ ( kyLb ____ ry

) 2 =

π2 ( 10,100 ) ___________

( ( 1.0 ) ( 102 ) _________ 0.69

) 2 = 4.56 k/in2

U = C1 go + C2 j

From the commentary for Section 4.9.3, for continuous beams loaded as shown in the top two cases of Figure C4.9-2, C1 = 0.41Cb and C2 = 0.47Cb.

So C1 = 0.41 (1.23) = 0.50 and C2 = 0.47(1.23) = 0.58

go = distance from the shear center to the point of application of load

go = 6 – c = 6 – 4.31 = 1.69 in. (+ since load acts away from the shear center)

j = 0.45df ( 2Icy ___ I – 1 ) [ 1 – ( Iy __

Ix ) 2 ] (Eq. 4.9.3-6)

for singly symmetric sections. smaller flange area = Afi = (1) (0.125) + 2(0.625)(0.375) = 0.594 in2

larger flange area = Afe = (2)(0.125) + 2(0.375)(0.50) = 0.625 in2

Afi /Afe = 0.594/0.625 = 0.95 > 0.8, so j may be taken as – yo = – (y coordinate of the shear center)

yo = – (4.31 – 3.05) = – 1.26 in.

Compare this with the more accurately calculated j:

df = distance between flange centroids

df = 6 – 0.260 – 0.375/2 = 5.55 in.

Note: 0.260 is the calculated distance from the extreme fiber of the interior flange to the centroid of the interior flange.

j = ( 0.45 ) ( 5.55 ) [ 2 ( 0.26 ) – 1 ] ( 1– ( 0.92 _____ 11.28

) 2 ) = –1.20 in

Note the two values for j are approximately equal.

U = C1go + C2 j = (0.50)(1.69) + (0.58)( –1.20)

U = 0.149 in.

ro = (r 2 x + r 2 y + x 2 o + y 2 o )1/2 (Eq. 4.9.3-7)

rx = 2.42, ry = 0.69, xo = 0, yo = 4.31 – 3.05 = 1.26

ro = (2.422 + 0.692 + 02 + 1.262)1/2 = 2.81 in.

Fet = 1 ____ Ar 2 o

( GJ + π2ECw ______

L 2 t )

Lt = 102 in., G = 3800 k/in2


Fet = 1 ___________ ( 1.92 ) ( 2.81 ) 2

( ( 3800 ) ( 0.0293 )

+ π2 ( 10,100 ) ( 6.11 )

______________ ( 102 ) 2

) Fet = 11.2 k/in2

Now evaluating the equation for Me:

Me = AFey [ U + √___________

U2 + r 2 o ( Fet ___ Fey

) ] Me = ( 1.92 ) ( 4.56 ) [ 0.149 √

__________________

0.1492 + 2.812 ( 11.2 ____ 4.56

) ] Me = 39.9 k-in.

rye = Lb ____

1.2π √____

Me ___ ESc

= 102 ____ 1.2π √

_____________

39.9 ____________ ( 10,100 ) ( 3.70 )

rye = 0.884 in.

Lb ______

rye √___

Cb = 102 __________

0.884 √____

1.23 = 104


Fb = [10.5 – 0.036(104)] = 6.8 ksi > fb; therefore it is satisfactory.

(3) From 10’-6” to 12’-6”: conservatively take Cb =1

Lb /ry = 24/0.84 = 28.6

From Section 3.4.11, Fb = 9.5 ksi

fb = Mc

___ I = 30.94 ( 2.95 ) __________

11.28 = 8.1 ksi < Fb; therefore it is

satisfactory.

The given I-beam is therefore satisfactory to carry the required wind load.

NOTES:1. The equation used for rye was chosen because the load is

applied at the exterior flange. In cases where the load is applied at one of the flanges, the following table can be used to determine the correct sign:

Beam/load combination Sign

If the load is applied to the web (i.e., near the neutral axis), use the first equation given in Section 4.9.1.

2. Since the moment is greater between supports than at the ends, Cb can be taken conservatively as 1.0.

3. The beam must also be checked for local buckling.

For the flange, Section 3.4.16.2, flat elements with one edge supported and one edge with stiffener, applies if Ds /b < 0.8; however,

Ds /b = (0.625 – 0.125)/[(1.75 – 2(0.375) – 0.125)/2] = 0.5/0.4375 = 1.14 > 0.8,

so 3.4.16.2 cannot be applied. Using instead Section 3.4.15, flat elements supported on one edge,

b/t = (1.75 – 0.125)/2/0.125 = 6.5 < 8.1 = S1, so Fb = 9.5 ksi

Checking the web (Section 3.4.18, flat element with both edges supported):

h/t = (6 – 0.125 – 0.125 – 0.125)/0.125 = 45 < 61 = S1

So Fb = 12.5 ksi

So local buckling does not govern any of the above checks.

4. In order to minimize the calculations shown, some cases not governing were noted to be satisfactory by inspec-tion or were not done. In general, both flanges need to be checked at all critical moment locations (particularly for unsymmetrical sections).


Figure 28d


Figure 28e


Example 29FORMED SHEET CALCULATIONS

Illustrating Sections 3.4.16, 4.7.6, 4.7.7, and 9.4

Calculations of Section PropertiesThe small radii are ignored. Nodal geometry is based on points of intersection of centerlines of elements.

Nodal geometry

Node x y

1 0.000 0.016

2 1.375 0.016

3 1.875 0.984

4 7.500 0.984

5 8.000 0.016

Element Properties

Element y L yL y2L I

1 0.016 1.375 0.022 0.000 0.000

2 0.500 1.090 0.545 0.272 0.085

3 0.984 5.625 5.535 5.446 0.000

4 0.500 1.090 0.545 0.272 0.085

Totals 9.179 6.647 5.992 0.170

GIVEN:

1. 8 in. rib panel, repeating pattern.2. Thickness = 0.032 in.3. Alclad 3004-H151 (Fcy = 28 ksi, Ftu = 34 ksi,

Fty = 30 ksi) (Table 3.3-1).4. Bend radii are 0.0625 in. at inner surface of each bend.

REQUIRED:

1. Allowable bending moments for: a. top in compression b. bottom in compression2. Moment of inertia for deflection calculations.3. Allowable reactions: a. interior b. exterior4. Check the applicability of calculations for the above

against the criteria of Section 9.4.

SOLUTION:

1. Allowable bending moments for: a. top in compression b. bottom in compression

Figure 29


ct = Ʃ ( yL )

_____ ƩL


I ’ x = Ʃ ( y2L ) – c 2 t ƩL + ƩI

= 1.349 in3

Ix = I ’ x × t

= 0.0432 in4

Sbot = Ix __ ct

= 0.0596 in3

Stop = Ix __________

( height – ct )

= 0.1565 in3

Also see Table 26 of Part VI for properties

Allowable compressive stressese.g. Element 3. Section 3.4.16 of applies.

No Design Aid table applies, so allowable stresses are determined by hand:

b/t = 5.625/0.032

= 175.8

Since b/t > S2 = 41,

F = 490/(b/t)

= 2.79 ksi

The table below summarizes results for all elements.

Element Length Spec.Slend. Ratio

Comp. Stress(ksi)

1 1.375 16 43.0 11.402 1.090 18 34.0 22.003 5.625 16 175.8 2.794 1.090 18 34.0 22.00

The weighted average allowable compressive stress, Fba, for trapezoidal formed sheet beams is:

e.g. node 3:

Fbf = 2.79 ksi, allowable compressive stress, element 3Fbh = 22.00 ksi, allowable compressive stress, element 2h = 1.090 in.b = 5.625 in.

Fba = Fbf + Fbh h/3b

___________ 1 + h /3b

= 3.95 ksi

The results for all nodes are summarized in the table below.

Node Fba (ksi) S (in3)Mom. Allow.

comp.(in.-kips) tensile*

1 -see node 5-2 13.62 0.0596 0.811 1.0133 3.95 0.1565 0.618 2.6604 3.95 0.1565 0.618 2.6605 13.62 0.0596 0.811 1.013

* Note: Allow. tensile stress = min (Fty /1.65, Ftu /1.95) = min(30/1.65, 34/1.95) = min(18.2, 17.4) = 17 ksi

Allowable MomentsTop in compression: nodes 3,4 in compression; 2,5 in tension:

Since the allowable moment based on nodes 3 and 4 in compression is smaller than the allowable moment for nodes 2 and 5 in tension, the former governs.

Mtc = 3.95 × 0.1565 = 0.618 in.-kips per cycle, allowable moment, top in compression.

Bottom in compression: nodes 2.5 in compression; nodes 3,4 in tension:

Since the allowable moment based on nodes 2 and 5 is smaller than the allowable moment for nodes 3 and 4 in tension, the compressive side again governs.

Mbc = 13.61 × 0.0596 = 0.811 in.-kips per cycle, allowable moment, bottom in compression.

The above two results can be converted to allowable moments per foot of width as follows:

Mtcf = Mtc (12 in./ft.)/(8 in./cycle)

= (0.618) (12)/(8)

= 0.927 kip-in./ft-width (top in compression)


Mtbf = Mbc (12in./ft)/(8 in./cycle)

= (0.811) (12)/(8)

= 1.217 kip-in./ft-width (bottom in compression)

2. Moment of inertia for deflection calculations

Refer to Section 4.7.6 Effective Width for Calculation of Bending Deflection

e.g., element 1:

Section 3.4.16, S2 = 41. From above, b/t = 43 for this element. Obviously, b/t < 1.65 × S2 and thus the full width of the element may be used.

e.g., element 3:

As with element 1, S2 = 41. Since b/t = 175.8, b/t > 1.65 × S2 and thus element 3 must be reduced in length to account for buckling.

From Section 4.7.1,

Fcr = π2E _______ ( 1.6b/t ) 2

E is modulus of elasticity10,100 ksi

Compare the allowable stress for element 3 with Fcr:

fa = 3.95 ksi for element 3

thus, fa > Fcr. The effective width of element 3 must be reduced

be = b (Fcr /fa)½

= 5.625 (1.26/3.95)½

= 3.176 in.

Similarly, it can be seen that elements 2 and 4 are not reduced. A recalculation of the moment of inertia follows:

Element Properties

Element y L Leff yLeff y2Leff Ieff

1 0.016 1.375 1.375 0.022 0.000 0.0002 0.500 1.090 1.090 0.545 0.272 0.0853 0.984 5.625 3.176 3.125 3.075 0.0004 0.500 1.090 1.090 0.545 0.272 0.085

Totals 6.730 4.237 3.620 0.170

ct = ∑ (yLeff)/∑L


I ’ x = ∑(y2Leff) – c 2 t ∑Leff + ∑Ieff

= 1.123 in3

Ix = I ’ x × t

= 0.0359 in4, for deflection calculations when ele-ment 3 is at its allowable compressive stress.

3. Allowable reactions:a. interiorb. exterior

a. allowable interior reaction

Reference: Section 4.7.7

Let the bearing length, N, be 2.0 in. Consider element 2 (a web).

Pc = Cwa (N + Cw1) ___________

nyCwb

where Cwa = t2 sin θ ( 0.46Fcy + 0.02 √____

EFcy )

where t = 0.032 in.

θ = 63.4°

Fcy = 28 ksi

E = 10,100 ksi

so Cwa = (0.032)2 sin63.4°

( 0.46(28) + 0.02 √___________

(10,100)(28) )

Cwa = 0.0215 kips

Cw1 = 5.4 in.

Cwb = C3 + Ri (1 – cos θ)

where Cw3 = 0.4 in.

Ri = 0.0625 in.

so Cwb = 0.4 + 0.0625 (1 – cos 63.4°)

Cwb = 0.435 in.

so Pc = (0.0215)(2.0 + 5.4)

________________ (1.65)(0.435)

= 0.222 kips per web

The allowable interior reaction, Fint is


Fint = Pc (2 webs/cycle)(12 in./ft.)(1 cycle/8 in.)(1000lb/kip)

= 666 lb/ft-width.

Section 4.7.8, combined web crippling end bending, should also be considered.

b. Allowable end reaction

Let the bearing length, N, be 2.0 in.

Again, consider element 2.

Pc = (1.2)Cwa(N + Cw2) _______________

nyCwb

where Cwa = 0.0215 kips [see (a) above]

Cw2 = 1.3 in.

Cwa = 0.435 in. [see (a) above]

Pc = (1.2)(0.0215)(2.0 + 1.3)

____________________ (1.65)(0.435)

= 0.119 kips per web.

The allowable end reaction, Fend, is:

Fend = Pc(2 webs/cycle)(12 in./ft)(1 cycle/8 in.)(1000 lb/kips)

= 357 lb/ft-width

4. Check the applicability of calculations for the above against the criteria of Section 9.4.

Cases (a), (b), and (e) do not apply. Cases (c), (f), and (g) vary with each installation.

Case (d) is checked as follows:

maximum l = 5.625 + 2(0.25)

= 6.125 in.

lt = 6.125/0.032

= 191

Condition (1) is stated then algebraically rearranged.

(1) l/t < 1230/ 3 √__

q , otherwise tests are required.

q < (1230/(l/t))3

q < 265 psf

Condition (2) is treated likewise

(2) l/t < 435 √______

(Fty /q) , otherwise tests are required.

q <[435/(l/t)]2Fty

q < [435/191]2(30)

qw < 155 psf

Subcase (2) governs. Tests must be run to establish the load carrying capacity of the panel when:

a. q > 155 psf

b. Cases (c), (f), or (g) are not satisfied.


Example 30DESIGN OF A SCREW CONNECTION

Illustrating Section 5.4

The ultimate shear capacity of the screw: Since threads are in the shear plane, the effective shear area is calculated from the root diameter. The root diameter is given in Part VII, Table 5-3 as 0.1876 in.

effective shear area = (π/4)(0.1876 in.)2 = 0.0276 in2

From Specification Table 5.2.3-1, the ultimate shear strength of 7075-T73 is 41 ksi, so

ultimate shear capacity = Pss =

(41 ksi) (0.0276 in2) = 1.1 kips = 1100 lb

Pss /(1.25 ns) = (1100 lb)/(1.25(3)) = 290 lb

so use 170 lb as the allowable shear.

2. Allowable tensile force Specification Section 5.4.2 requires that the washer out-side diameter Dw equal or exceed 5/16 in.:

Dw = 5/8 > 5/16

The allowable pull-out force, Pnot, per Section 5.4.2.1 is:

Pnot = KsDtcFty2 /3

= (1.01)(0.25)(0.04)(23)/3 = 0.077 kips = 77 lb

The allowable pull-over force, Pnov, per Section 5.4.2.2 is:

Pnov = Ct1Ftu1(Dws – Dh)/3

= (1.0)(0.05)(24)(0.625 – 0.25)/3

= 0.15 kips = 150 lb

The ultimate tensile capacity of the screw is:

From Table 5.2.3-1 the minimum tensile strength is 68 ksi, so the ultimate tensile capacity of the screw is

1900 ________ (1.25)(3)

= 510 lb

The allowable tension is, then, the least of 77, 150, and 510 1b, or 77 1b.

GIVEN:

1. Tapping screw of 7075-T73 aluminum, 1/4” diameter, UNC thread joining 0.05 in. thick 3003-H16 sheet to 0.04 in. thick 5052-H32 sheet.

2. 5/8” outside diameter flatwasher under the screw head.

REQUIRED:

The allowable shear and tension forces for the connection.

SOLUTION:

1. Allowable shear force

The allowable connection shear is determined according to Specification Section 5.4.3. Ftu is from Table 3.3-1.

Sheet Alloy Thickness Ftu 2FtuDt/nu

1 3003-H16 0.05 24 310 lb

2 5052-H32 0.04 31 320 lb

Since t2 = 0.04 < 0.05 = t1,

4.2 (t 3 2 D)1/2Ftu2 /ns

4.2 (0.043 × 0.25)1/2(31)/3 = 0.17 kips = 170 lb

The smallest of (310, 320, and 170) is

170 lb = allowable shear

Also per Section 5.4.3, shear in screws:

Figure 30


Example 31WEIGHTED AVERAGE BENDING STRENGTH


3.4.18: Web: h/t = (10.76”)/(0.31”) = 34.7 < 48 = S1, so Fcw = 28 ksi

Tension3.4.2: Flange: Ftf = 19 ksi3.4.4: Web: Ftw = 28 ksi

If =2[(7”)(0.62”)3/12 + (7”)(0.62”)(6” – 0.62”/2)2] = 281.3 in4

ccf = 12”/2 – (0.62”/2) = 5.69”

ctf = 12”/2 = 6”

Iw = (0.31”)(10.76”)3/12 = 32.2 in4

ccw = ctw = 10.76”/2 = 5.38”

GIVEN:

1. Symmetric Shape: Aluminum Association standard I 12 × 14.3

d = 12 in.

bf = 7 in.

tf = 0.62 in.

tw = 0.31 in.

Sx = 52.9 in3

web height h = 10.76 in. = 12 – 2(0.62)

flange area = 7(0.62) = 4.34 in2

web area = 10.76(0.31) = 3.34 in2

Unsymmetric Shape: Modified I 12 × 14.3 (top flange 1 in. wide instead of 7 in. wide)

d = 12 in.

bf (bottom) = 7 in.

bf (top) = 1 in.

tf = 0.62 in.

tw = 0.31 in.

web height h = 10.76 in. = 12 – 2(0.62)

bottom flange area = 7(0.62) = 4.34 in2

top flange area = 1(0.62) = 0.62 in2

web area = 10.76(0.31) = 3.34 in2

2. Alloy: 6061-T63. Type of Structure: Building 4. Continuous minor axis lateral bracing

REQUIRED:

The allowable bending moment about the major axis for each shape for loading causing compression in the top flange

SOLUTION:

Part I, Symmetric Shape: Aluminum Association standard I 12 × 14.3:

From Part VII, Table 2-22:

Compression3.4.15: Flange: b/t = (7” – 0.31”)/2/(0.62”) =

5.4 < 6.5 = S1, so Fcf = 21 ksi

FIGURE 31


From 4.7.3:

Mac = Fcf If ____ ccf

+ FcwIw _____ ccw

= ( 21 ) ( 281.3 ) __________

5.69 +

( 28 ) ( 32.2 ) _________ 5.38

= 1206 in-k

Mat = Ftf If ____ ctf

+ FtwIw ____ ctw

= ( 19 ) ( 281.3 ) __________

6 +

( 28 ) ( 32.2 ) _________ 5.38

= 1058 in-k

The allowable bending moment is the lesser of Mac and Mat, which is Mat = 1058 in-k.

Part II, Unsymmetric Shape: Modified I 12 × 14.3 (top flange 1” wide):

Determine moment of inertia:A y Ay d Ad2 I Ad2 + I

bottom flange

4.34 11.69 50.73 3.14 42.79 0.14 42.93

web 3.34 6 20.04 2.55 21.72 32.18 53.9

top flange 0.62 0.31 0.19 8.24 42.10 0.02 42.12

total 8.3 70.96 106.61 32.34 139

The neutral axis is located (70.96 in3)/(8.3 in2) = 8.55” below the top of the section.

From Part VII, Table 2-22:

Compression

Flange: 3.4.15: b/t = (1” – 0.31”)/2/(0.62”) = 0.6 < 6.5 = S1,

so Fcf = 21 ksi

Web: 3.4.18: h/t = (10.76”)/(0.31”) = 34.7

The neutral axis is located 8.55” – 0.62” = 7.93” below top end of web and 10.76” – 7.93” = 2.83” above bottom of web.

co /cc = 2.83/(–7.93) = –0.36, so m = 1.15 + (–0.36)/2 = 0.97.

S1 = (Bbr – 1.3Fcy)/(mDbr) = (66.8 – 1.3(35))/ [(0.97)(0.665)] = 33 < 34.7 = h/t, so Fcw = Bbr/ny – mDbr(h/t)/ny = 66.8/1.65 – 0.97(0.665)(34.7)/1.65 = 26.9 ksi

Tension

Flange: 3.4.2: Ftf = 19 ksi

Web: 3.4.4: Ftw = 28 ksi

If = 42.93 + 42.12 = 85.05 in4

ccf = 8.55” – 0.62”/2 = 8.24”ctf = 12” – 8.55” = 3.45”Iw = 53.9 in4

ccw = 7.93” ctw = 2.83”

From 4.7.3:

Mac = Fcf If ____ ccf

+ FcwIw _____ ccw

= ( 21 ) ( 85.05 ) __________

8.24 +

( 26.9 ) ( 53.9 ) __________ 7.93

= 400 in-k

Mat = Ftf If ____ ctf

+ FtwIw ____ ctw

= ( 19 ) ( 85.05 ) __________

3.45 +

( 28 ) ( 53.9 ) _________ 2.83

= 1002 in-k

The allowable bending moment is the lesser of Mac and Mat, which is Mac = 400 in-k.


PART IX

Guidelines for Aluminum Sheet Metal Work

in Building Construction


Second Edition, January 2005

January 2005 IX-3

IXGuidelines For Aluminum Sheet Metal Work In Building Construction

TABLE OF CONTENTS

1. Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52. Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53. Surface Preparation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84. Joining . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85. Standing Seam Roofing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106. Batten Seam Roofing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127. Aluminum Roof Shingles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 148. Flashing For Non-Metallic Shingle Roofs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 149. Valleys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1610. Gravel Stops . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1611. Base Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1812. Cap Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1813. Chimney Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2014. Through-Wall Flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2015. Standing Seam Siding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2216. Coping Covers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2417. Miscellaneous . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2618. Rainwater Goods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 Commentary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

January 2005 IX-5

1. SCOPE

These guidelines apply to the use of aluminum in roof-ing, flashing and other sheet metal work in building con-struction. They do not apply to proprietary or pre-formed

sheet metal systems or products such as horizontal siding, fascia and soffit systems, curtain wall systems, or corru-gated or ribbed roofing and siding.

2. MATERIALS

2.1 Aluminum Sheet

2.1.1 Alloy and Temper

Sheet shall be 1100, 3003, Alclad 3003, 3004, Alclad 3004, 3105, 5005, 5050, or 5052 alloy and H14 or H34 temper. Properties shall conform to Aluminum Standards and Data published by the Aluminum Association.

2.1.2 Thickness

Sheet thickness shall be sufficient for the intended use, but not less than the minimum nominal thickness listed in Table 1. The thickness of shingles and proprietary roofing systems shall be determined for specific applications on the basis of load tests.

2.1.3 Dimensional Tolerances

Tolerances on sheet dimensions shall conform to Alu-minum Standards and Data published by the Aluminum Association.

2.1.4 Finish

Sheet shall be mill finish unless otherwise specified. Embossed, anodized, or painted sheet shall be acceptable provided it has the necessary strength and formability for the intended purpose.

2.2 Building Paper and Roofing Felt

Building paper or roofing felt used where condensation occurs such as over poorly vented spaces shall be vapor barriers conforming to Federal Specifications UU-B-790A, Type I, Grade A; HH-R-590A, Type II, Class C; or poly-ethylene not less than 4 mils (0.1 mm) thick conforming to Federal Specifications L-P-378B or L-P-512A.

Building paper or roofing felt over well ventilated spaces need not be water proof but shall be water repellant and con-form to Federal Specifications UU-B-790A, Type I, Grade C or D; HH-R-590A, Type II; or HH-R-595B, Type I or II.

Building paper and roofing felt that contains additives of heavy metals or chemicals corrosive to aluminum shall not be used.

Building paper or roofing felt shall have a minimum weight of 15 lb (6.8 kg) and shall be overlapped at least 2 in. (50 mm) so as to shed water and shall be secured along the laps with large flat headed aluminum nails spaced no farther than 6 in. (150 mm) on centers.

2.3 Sealants

2.3.1 One part

One part synthetic or rubber base sealants shall conform to Federal Specification TT-S-230A(1). Use shall conform to manufacturers’ specifications.

2.3.2 Two part

Two part synthetic or rubber base sealants shall conform to Federal Specification TT-S-00227E(1) or ANSI A116.1. Use shall conform to manufacturers’ specifications.

2.4 Elastic Cement

Elastic cement shall conform to Federal Specification SS-C-153.

2.5 Fasteners

2.5.1 Cleats

Cleats shall be aluminum of the same alloy, temper, and nominal thickness as the sheet unless otherwise specified. Cleats shall be at least 2 in. (50 mm) wide and long enough to be fully incorporated into the seam with the other end folded back over the nail heads. They shall be fastened securely with two aluminum nails placed parallel to the seam.

2.5.2 Nails

Nails shall be 5056 or 6061 aluminum and conform to Federal Specification FF-N-105B, Type II, Style 20.

2.5.3 Screws, bolts, and nuts

Screws and bolts shall be 6061-T6 or 2024-T4 alumi-num except that 2024-T4 fasteners shall not be used in marine or corrosive industrial environments. Nuts shall be 6061-T6 or 6262-T9 aluminum. Alternately, screws, bolts and nuts shall be 300 series stainless steel. Washers shall be used under bolt and screw heads.

2.5.4 Washers

Washers shall be 1100-H18 aluminum or of the same material as the sheet or fasteners used. The minimum nom-inal thickness of washers shall be 0.040 in.(1 mm). Where watertightness is required an elastomeric washer shall be used with the metal washer.

IX-6 January 2005

2.5.5 Miscellaneous hardware

Expansion inserts, plugs, anchors, and shields shall be wood, fiber, plastic, lead, or aluminum and shall be chosen to suit the environment of each application.

2.5.6 Rivets

Rivets shall be 1100-H14 aluminum unless otherwise specified. Rivets shall have a shank diameter of at least 0.187 in. (4.75 mm) and sufficiently long to form a proper head. Blind rivets shall be used only where maximum

watertightness, strength, or corrosion resistance is not required. Blind rivets shall be 1100 sleeve, 5056 mandrel; 5050 sleeve, 5056 mandrel; 5052 sleeve, 5056 mandrel; 5052 sleeve, 7178 mandrel; 5056 sleeve, 1020 steel man-drel; stainless steel; or monel.

2.6 Paint

Paint for back painting aluminum shall be bituminous paint of the cut-back type conforming to specification MIL-C-450 B (1) or TT-C-494 or methacrylate type lac-quers conforming to MIL-L-19537C (2).

Table 1MINIMUM NOMINAL SHEET THICKNESS

Residential Non-Residential

(in.) (mm) (in.) (mm)

RoofingStanding SeamBatten SeamShinglesProprietary Systems

FlashingsBaseCapRidge, HipCoping CoversScuppersSplash PansChimneyApronHeadSillCurbsThrough-Wall Lintel Spandrel Sill ParapetsGravel Stops and FasciaEdge StripsGuttersGuttersContinuous CleatsHangersRainwater GoodsDownspouts (Leaders)ElbowsLeader HeadsClipsStrapsValleySnow, EaveExpansion Joint, Building

0.0240.0240.0190.019

0.0190.0190.0240.0240.0240.0320.0190.0240.0190.0190.024

0.0240.0240.0240.0240.0240.024

0.0270.0240.064

0.0190.0190.0240.0400.0400.0190.024

0.600.600.500.50

0.500.500.600.600.600.800.500.600.500.500.60

0.600.600.600.600.600.60

0.700.601.6

0.500.500.601.01.00.500.60

0.0320.0320.0190.024

0.0320.0320.0320.0320.0320.0400.0320.0320.0320.0320.032

0.0320.0320.0320.0320.0320.032

0.0320.0320.080

0.0240.0240.0320.0640.0640.0320.0320.032

0.800.800.500.60

0.800.800.800.800.801.00.800.800.800.800.80

0.800.800.800.800.800.80

0.800.802.0

0.600.600.801.61.60.800.800.80

January 2005 IX-7

Figure 9-1

IX-8 January 2005

3. SURFACE PREPARATION

3.1 General

All surfaces upon which aluminum sheet is to be placed shall be smooth, even and free of projections and hollows. The surface shall be dry before and during the placing of the aluminum. For wood surfaces the lumber shall be of good quality, well seasoned, straight, and free of knotholes and splits. It shall be laid with joints true, even, and firmly attached with all fastener heads flush with the top surface. On masonry surfaces adequate provision shall be made for receiving fasteners in accordance with the plans for sheet metal work.

3.2 Dissimilar Metals

Galvanic corrosion of aluminum caused by contact with dissimilar metals shall be prevented by proper design considerations and installation procedures. Water that has come in contact with copper, brass, or bronze shall be directed away from aluminum.

3.3 Wood

Wood sheathing or wood surfaces to be covered with aluminum shall be covered with building paper or roofing felt (Section 2.2) or the wood shall be painted with two coats of good quality exterior type paint or the aluminum shall be back painted (Section 2.6).

3.4 Concrete and Masonry

Concrete and masonry surfaces to be covered with alu-minum shall be covered with building paper or roofing felt (Section 2.2) or the aluminum shall be back painted (Section 2.6). Where aluminum is to be caulked into slots or reglets in masonry, brickwork, or concrete, the slot or reglet shall be filled with sealant (Section 2.3) so that the sealant covers both surfaces of that part of the aluminum in the slot or reglet.

4. JOINING

4.1 Mechanical Joints

Mechanical seams and joints for aluminum shall be the same as those used for other sheet metals. Lap and lock seams shall not be riveted or otherwise fastened together to restrict relative movement unless such seams are designed to transfer movement to a different location.

End joints of formed sheet members such as ridge, hip, valley, gable or rake strips, battens, aprons, gravel stops, coping and cap flashing shall not be riveted or fastened together to restrict movement. Simple laps shall not be used unless the slope is sufficient to provide drainage and flat widths are less than 8 in. (200 mm). For flashing with flat widths over 8 in. (200 mm) or surfaces with slopes less than 3 in 12 (1:4), sealant filled controlled slip joints shall be used. Joints shall allow for thermal movement of 0.125 in. (3 mm) or that determined for the application allowing for the temperature of the metal at the time of installation, whichever is greater.

The installer shall account for the metal temperature at the time of installation and leave adequate allowance for expansion and contraction.

4.2 Soldering

Aluminum shall not be soldered.

4.3 Brazing

Brazing shall be done in the shop and flux residue shall be completely removed.

4.4 Welding

Welding aluminum sheet metal in the field shall be done with the gas tungsten arc (TIG) and gas metal arc (MIG) welding processes only. Where sheet has been anodized, the anodic coating shall be removed in the weld area prior to welding.

Oxyfuel-gas welding shall be done under shop condi-tions and flux residue shall be completely removed.

January 2005 IX-9

Figure 9-2

IX-10 January 2005

5. STANDING SEAM ROOFING

5.1 Roof Slopes

These specifications do not apply to roofs with slopes less than 3 in 12 (1:4).

5.2 Dimensions

Roof sheets shall not exceed 10 ft (3 m) and no straight run of roofing shall exceed 30 ft (10 m). Nominal sheet thickness shall be 0.024 in. (0.6 mm) where the distance between standing seams does not exceed 20 in. (500 mm) and 0.032 in. (0.8 mm) where the distance between standing seams is from 20 in. (500 mm) to 27 in. (700 mm). To allow for expansion, sheet width shall be 0.125 in. (3 mm) less than the center to center spacing of the standing seams.

5.3 Transverse Seams

5.3.1

(See figures on pages 9 and 13). For roofs with slopes 6 in 12 (1:2) or greater, the lower end of each sheet shall be folded under 0.75 in. (20 mm). The fold shall be slit 1 in. (25 mm) away from the corner to form a tab where the sheet turns up to make a standing seam. The upper end of each sheet shall be folded over 2 in. (50 mm). The 0.75 in. (20 mm) fold on the lower end of the upper sheet shall be hooked into the 2 in. (50 mm) fold on the upper end of the underlying sheet. Transverse seams shall be staggered a distance of one half the sheet length in adjacent roof sheets.

5.3.2

(See figures on pages 9 and 13). For roofs with slopes at least 3 in 12 (1:4) but less than 6 in 12 (1:2), the lower end of each sheet shall be folded under 0.75 in. (20 mm). The fold shall be slit 1 in. (25 mm) away from the corner to form a tab where the sheet turns up to make a standing seam. The upper end of each sheet shall be folded over 0.5 in. (12 mm). A 1.5 in. (38 mm) wide locking strip the full width of the sheet shall be secured at least 4 in. (100 mm) below the top folded edge by rivets spaced no more than 6 in. (150 mm) apart. The 0.75 in. (20 mm) fold on the lower end of the upper sheet shall hook into the locking strip on the upper end of the underlying sheet. Alternately, transverse seams shall be made as specified in Section 5.3.1 and filling the seams with sealant. Transverse seams shall be staggered a distance of one half the sheet length in adjacent roof sheets.

5.4 Dimensions

(See figure on page 9). Standing seams shall finish 1 in. (25 mm) high except on curved surfaces where they shall finish a minimum of 0.75 in. (20 mm) high. One side edge of roof sheets shall be 1.5 in. (38 mm) high and the other

1.75 in. (44 mm) high. The first fold shall be a single fold 0.25 in. (6 mm) wide and the second fold shall be 0.5 in. (12 mm) wide. The lock portion of the standing seam shall be 5 plies thick. A space at least 0.125 in. (3 mm) wide shall be provided between adjacent sheets at the bottom of each standing seam. At eaves, ends of standing seams shall be closed by folding over a tab provided at one side of each roof sheet.

5.5 Cleats

Cleats shall be at least 2 in. (50 mm) wide and shall be spaced not more than 12 in. (300 mm) apart between cen-ters. If the roof deck is a material other than wood, nailers shall be provided for the securement of cleats.

5.6 Ridges and Hips

(See figures on page 11). Ridges and hips shall be pro-vided with standing seams constructed as for the main roof. Where standing seams of the main roof terminate at ridges or hips they shall be laid flat and folded into ridge or hip standing seams. Standing seams on opposite sides of ridges or hips shall be staggered to avoid excessive thicknesses of metal in the ridge or hip standing seam.

5.7 Valleys

Valleys shall be formed from aluminum sheets not exceed-ing 10 ft (3 m) in length of the same nominal thickness and alloy as used for the roof sheets. Each sheet shall lap the lower one at least 6 in. (150 mm) in the direction of drainage. The valley sheet shall extend at least 6 in. (150 mm) under the roof sheets on both sides. At the valley line adjacent to the lower edge of the roof sheets, a 0.75 in. (20 mm) double fold shall be made to engage a 0.75 in. (20 mm) single fold at the lower ends of the roof sheets. The outer edge of the valley sheets shall be folded 0.5 in. (12 mm) for cleating and in these folds cleats shall be spaced not more than 24 in. (600 mm) apart between centers. Valley sheets shall be nailed along their top edge only.

5.8 Eaves

(See figure on page 11). At eaves without gutters, each sheet shall be hooked 0.75 in. (20 mm) over a previously placed aluminum edge strip. Edge strips shall be continu-ous and shall be formed from sheets not longer than 10 ft (3 m); ends of adjacent lengths shall lap at least 1 in. (25 mm). The edge strip shall extend up the roof deck at least 4 in. (100 mm) and be secured with nails spaced not more than 4 in. (100 mm) apart along the upper edge. The lower edge shall be turned out 0.75 in. (20 mm) to form a drip edge. The edge strip shall not be face nailed.

January 2005 IX-11

Figure 9-3

IX-12 January 2005

(See figure on page 11). Where seams finish back from eave edges, the lower edge of the roofing shall engage a previously placed apron strip. The connection between the roof sheets and the upper edge of the apron strip shall be as described in 5.3. The lower edge of the apron strip shall be hooked over a previously placed edge strip as previously described.

5.9 Gable Rakes

(See figure on page 11). Side edges of roof sheets at gable rakes shall finish over an edge strip as described in Section 5.8 or shall turn up 1.5 in. (38 mm) and be locked into an aluminum fascia strip forming a standing seam 1 in. (25 mm) high. Where the standing seam finishes at the roof edge, the lower edge of the fascia strip shall be hooked 0.75 in. (20 mm) over a previously placed continuous edge strip that is secured to the deck with aluminum nails spaced no more than 4 in. (100 mm) apart.

6. BATTEN SEAM ROOFING

6.1 Roof Slopes

These specifications do not apply to roofs with slopes less than 3 in 12 (1:4).

6.2 Battens

(See figure on page 9). Battens shall be aluminum or wood unless otherwise specified and at least 1.5 in. (38 mm) high. Battens shall be attached to concrete roof decks by through bolts or cinch bolts and to gypsum or steel decks by through bolts, none spaced more than 3.5 ft (1 m) between centers. Bolt heads shall be countersunk.

6.3 Dimensions

Roof sheets shall be no longer than 10 ft (3 m) and be installed between battens. Nominal sheet thickness shall be 0.024 in. (0.6 mm) when the distance between battens does not exceed 20 in. (500 mm) and 0.032 in. (0.8 mm) when the distance between battens is from 20 in. (500 mm) to 27 in. (700 mm). To allow for expansion, sheet width shall be 0.125 in. (3 mm) less than the clear distance between the battens. Sides of sheets shall be turned up the height of the batten and terminate in a 0.5 in. (12 mm) horizontal flange.

6.4 Transverse Seams

6.4.1

(See figures on pages 9 and 13). For roofs with slopes 6 in 12 (1:2) or greater, the lower end of each sheet shall be folded under 0.75 in. (20 mm). The fold shall be slit 1 in. (25 mm) away from the corner to form a tab where the sheet turns up against the batten. The upper end of each sheet shall be folded over 2 in. (50 mm). The 0.75 in. (20 mm) fold on the lower end of the upper sheet shall be hooked into the 2 in. (50 mm) fold on the upper end of the underly-ing sheet. Transverse seams shall be staggered a distance of one half the sheet length in adjacent roof sheets.

6.4.2

(See figures on pages 9 and 13). For roofs with slopes at least 3 in 12 (1:4) but less than 6 in 12 (1:2), the lower end of each sheet shall be folded under 0.75 in. (20 mm). The fold shall be slit 1 in. (25 mm) away from the corner to form a tab where the sheet turns up against the batten. The upper end of each sheet shall be folded over 0.5 in. (12 mm). A 1.5 in. (38 mm) wide locking strip the full width of the sheet shall be secured at least 4 in. (100 mm) below the top folded edge by rivets spaced not more than 6 in. (150 mm) apart. The 0.75 in. (20 mm) fold on the lower end of the upper sheet shall hook into the locking strip on the upper end of the underlying sheet. Alternately, transverse seams shall be made as specified in Section 6.4.1 and filling the seams with sealant. Transverse seams shall be staggered a distance of one half the sheet length in adjacent roof sheets.

6.5 Cleats

Cleats shall not be less than 2 in. (50 mm) wide and spaced not more than 12 in. (300 mm) apart on centers. Cleats shall be secured to the sides of the battens or a U-shaped cleat passing under the batten shall be used.

6.6 Cover Strips

Cover strips formed of the same alloy and nominal thickness of aluminum sheets as used for the roof sheets shall be applied over the battens. Edges of cover strips shall lock into the 0.5 in. (12 mm) horizontal flanges of the roof sheets and shall be turned down against the vertical sides of the battens. Lengths of cover strips shall be joined by a 0.5 in. (12 mm) lock or shall be lapped at least 3 in. (75 mm) with the uphill strip on top of the downhill strip. Batten ends shall be covered with an end cap folded and locked into tabs 0.5 in. (12 mm) long on the top and two vertical sides of the cap. The tabs shall be 0.5 in. (12 mm) extensions of the cover strip and vertical legs of the roof sheets.

January 2005 IX-13

Figure 9-4

IX-14 January 2005

6.7 Hips and Ridges

(See figure on page 13). Hips and ridges shall be alu-minum covered battens similar to the roof battens. At their intersection with ridge or hip battens, the edges of roof sheets shall be turned up the height of the ridge or hip batten and terminate in a 0.5 in. (12 mm) horizontal flange. Cover strips, as specified for the roof battens, shall be installed over hip and ridge battens. Alternate methods of finishing hips and ridges shall be as shown in the detail drawings.

6.8 Valleys

(See figure on page 13). Valleys shall be formed from aluminum sheets no longer than 10 ft (3 m) of the same gauge and alloy as used for the roof sheets. At laps, the uphill valley sheet shall overlap the downhill valley sheet at least 6 in. (150 mm). Each valley sheet shall extend under the roof sheets at least 6 in. (150 mm). At the valley adja-cent to the lower edge of the roof sheets, a 0.75 in. (20 mm) double fold shall be made to engage a 0.75 in. (20 mm) single fold at the lower ends of the roof sheets. The outer edge of the valley sheets shall be folded 0.5 in. (12 mm) for cleating and in these folds cleats shall be spaced no more than 24 in. (600 mm) on centers. The under edge of wood battens shall be notched to permit the folded edge of val-ley sheets to pass under the battens. Valley sheets shall be nailed along the top edge only.

6.9 Eaves

(See figure on page 11). At eaves without gutters, each sheet shall be hooked 0.75 in. (20 mm) over a previously placed aluminum edge strip. Edge strips shall be continu-ous and shall be formed from sheets no longer than 10 ft (3 m); ends of adjacent lengths shall lap at least 1 in. (25 mm). The edge strip shall extend up the roof deck at least 4 in. (100 mm) and be secured with aluminum nails spaced no more than 4 in. (100 mm) apart along the upper edge. The lower edge shall be turned out 0.75 in. (20 mm) to form a drip edge. The edge strip shall not be face nailed.

(See figure on page 11). Where seams finish back from eave edges, the lower edge of the roofing shall engage a previously placed apron strip. The connection between the roof sheets and the upper edge of the apron strip shall be as described in 5.3. The lower edge of the apron strip shall be hooked over a previously placed edge strip as previously described.

6.10 Gable Rakes

Side edges of roof sheets at gable rakes shall finish over an edge strip as described in Section 6.9 or a batten shall be set flush with the gable end. Where battens occur at gable ends, a cover strip shall lock into the roof sheets and extend over the batten and down the face of the gable end to hook 0.75 in. (20 mm) over a previously placed continuous edge strip that is secured to the deck with aluminum nails spaced no more than 4 in. (100 mm) apart.

7. ALUMINUM ROOF SHINGLES

Aluminum roof shingles shall be of the size and shape shown on the drawings. Installation shall be in accordance with manufacturer’s specifications.

8. FLASHING FOR NON-METALLIC SHINGLE ROOFS

8.1 Apron Flashing

8.1.1 General

Apron flashing shall be formed of sheets not longer than 10 ft (3 m). The ends of each length of flashing shall be lapped at least 4 in. (100 mm) or a 2 in. (50 mm) sealant filled “S” lock shall be formed at one end of the flashing sheet to receive the end of the adjacent flashing sheet.

8.1.2 Change of Roof Slope Flashing

(See figure on page 15). At changes of roof slope the flashing on the uphill side shall extend at least 6 in. (150 mm) under the shingles and be secured by alumi-num nails along the uphill side spaced no further than 6 in. (150 mm) apart. An inverted V cant shall be formed

in the flashing near the butt edge of the first shingle course or a wood cant strip shall be placed under the butts of the first shingle course and be secured with narrow strips of aluminum attached to the roof deck above the flashing. The flashing on the downhill side shall extend at least 5 in. (125 mm). The downhill edge shall be hemmed 0.5 in. (12 mm) for stiffness and be secured by blind cleats spaced no further apart than 24 in. (600 mm). Where the flash-ing is to be concealed on the downhill side it shall extend between the shingles of the top double course of shingles to within 0.5 in. (12 mm) of the butts of the top shingles. With slate roofing, sealant shall be applied to the underside of the pre-drilled holes in the slates before the slates are applied.

January 2005 IX-15

Figure 9-5

IX-16 January 2005

8.1.3 Flashing Where Sloping Roof Meets Vertical Wall

(See figure on page 15). Where sloping roofs meet verti-cal walls the flashing shall extend up the wall at least 4 in. (100 mm) under the siding and be secured to the sheathing along its upper edge with aluminum nails spaced no further apart than 24 in. (600 mm). At masonry walls, the flashing shall extend up the wall face at least 4 in. (100 mm) and be counter flashed as described in Section 12. The flashing shall extend under the roofing at least 5 in. (125 mm). The lower edge shall be hemmed for stiffness and be secured by blind cleats spaced no further than 24 in. (600 mm) on centers.

8.2 Eave Snow Flashing

(See figure on page 15). Eave snow flashing shall be formed and secured as for standing seam roofing. Where the flashing extends more than 4 ft (1.2 m), center to center spacing of standing seams shall not exceed 26 in. (660 mm). The flashing shall extend up the roof at least 18 in. (460 mm) beyond the exterior wall face. Along the upper edge, stand-ing seams shall be laid flat for approximately 6 in. (150 mm), and the top edge shall be folded over 0.5 in. (12 mm) to form

a hook dam. The starter course of shingles shall be lapped over the top flat surface at least 6 in. (150 mm).

At eaves, the flashing shall be hooked 0.75 in. (20 mm) over a previously placed aluminum edge strip as described in Section 5.9.

At valleys a 1.5 in. (38 mm) wide locking strip the full length of the snow flashing shall be secured to the valley sheet 6 in. (150 mm) from its outer edge by rivets spaced not more than 6 in. (150 mm) apart. The edge of the snow flashing at the valley shall be folded under 0.75 in. (20 mm) and engage the locking strip that is filled with sealant or the outer edge of the valley shall be folded over 0.75 in. (20 mm), filled with sealant, and the edge of the snow flashing inserted in the fold.

8.3 Hip and Ridge Flashing

(See figure on page 17). Hip and ridge flashings shall be formed from sheets not longer than 10 ft (3 m) and ends of adjacent lengths shall lap at least 4 in. (100 mm). The flashing shall be fastened on both side flanges by alumi-num screws spaced no farther apart than 24 in. (600 mm). Screws shall be provided with washers having neoprene gaskets under the heads.

9. VALLEYS

9.1 Open Valleys

(See figure on page 17). Valley flashing shall be formed of aluminum sheets not longer than 10 ft (3 m). The sheets shall extend at least 6 in. (150 mm) under the roof covering on each side of the valley and the side edges shall be folded 0.5 in. (12 mm) for cleating. Uphill sheets shall overlap downhill sheets by at least 6 in. (150 mm). The upper end of each sheet shall be fastened to the roof deck. Side edges shall be secured with aluminum cleats spaced no farther apart than 24 in. (600 mm) on centers. The open portion of the valley shall not be less than 5 in. (125 mm) wide at the top and shall increase in width 0.125 in. (3 mm) per foot (300 mm) towards the eaves. Where intersecting roofs are on different slopes, an inverted V 1.5 in. (38 mm) high shall be formed along the centerline of the valley flashing

and the lap of the valley sheets shall be increased to 8 in. (200 mm) unless otherwise shown on the drawings.

9.2 Closed Valleys

(See figure on page 17). Separate pieces of aluminum sheet shall be built in with each course of roofing material. The flashing shall be as long as the diagonal of the shingle at the center of the valley, and at least 18 in. (460 mm) wide where the roof slope is more than 6 in 12 (1:2) and 24 in. (600 mm) wide where the roof slope is less than or equal to 6 in 12 (1:2). The bottom edge of each piece of flashing shall be 0.5 in. (12 mm) short of the butt line of the shingle in the succeeding course. Each piece of flashing shall be fastened to the roof deck along the upper edge with alumi-num nails.

10. GRAVEL STOPS

10.1 Sheet Gravel Stops

(See figures on page 19). Sheet gravel stops shall be formed from sheets not longer than 10 ft (3 m). The hori-zontal flange shall extend at least 4 in. (100 mm) onto the previously built-up roofing and be secured through the roof-ing and into the deck with aluminum nails not more than 3 in. (75 mm) apart. Wood nailing strips shall be provided on decks that are not wood. Over the horizontal flange a

layer of elastic cement shall be applied; a strip of fabric shall be embedded into this elastic cement. A second strip of fabric shall be similarly applied or, alternately, the first strip of fabric shall be covered with hot pitch into which the top strip of felt shall be embedded. The top strip shall be surfaced the same as the adjacent built-up roofing.

The aluminum shall be bent to form a gravel stop at least 1 in. (25 mm) high and the outer edge shall extend

January 2005 IX-17

Figure 9-6

IX-18 January 2005

down as a fascia. For facias 4 in. (100 mm) or less in depth the lower edge shall be hemmed at least 0.5 in. (12 mm) and turned out 0.75 in. (20 mm) at an angle of 45° to form a drip. For fascias more than 4 in. (100 mm) in depth the lower edge shall hook 0.75 in. (20 mm) over a previously placed continuous aluminum edge strip.

End joints shall be made using a back-up plate and top cover plate. The 12 in. (300 mm) long back-up plate shall be nailed in place before the gravel stop is installed. A 0.25 in. (6 mm) opening shall be left between the ends of the gravel stop sections. This opening shall be covered by a 6 in. (150 mm) top cover plate. The cover plate shall be embedded in mastic and fastened through the opening between the sections.

Where depths of fascias vary from 8 to 16 in. (200 to 400 mm), longitudinal steps or ridges shall be formed in

the fascia to minimize waviness. Steps or ridges shall be at least 0.5 in. (12 mm) high and proportionally spaced not more than 6 in. (150 mm) apart.

Edge strips shall be continuous and shall be formed of sheets no longer than 10 ft (3 m); ends of adjacent lengths shall lap at least 1 in. (25 mm). The lower edge shall be turned out 45° to form a drip. Edge strips shall be fastened to wood with nails spaced no more than 4 in. (100 mm) apart, or to masonry with screws in expansion sleeves spaced no more than 10 in. (250 mm) apart.

10.2 Extruded Gravel Stops

Extruded gravel stops shall be installed in accordance with manufacturers’ specifications.

11. BASE FLASHING

11.1 Straight Base Flashing

(See figure on page 21). Straight base flashing for built-up roofing shall extend up on vertical surfaces at least 8 in. (200 mm) and to a height of at least 3 in. (75 mm) above the bottom of the cap flashing. Base flashing shall extend onto the previously placed built-up roofing at least 4 in. (100 mm).

The base flashing shall be made of aluminum sheets not longer than 10 ft (3 m). Ends of sheets shall be joined by 1 in. (25 mm) wide loose lock seams filled with sealant. The horizontal leg of the base flashing shall be nailed along its outer edge with aluminum nails spaced no more than 3 in. (75 mm) apart. On decks not made of wood, wood nailers shall be provided. Over the horizontal flange a layer of elastic cement shall be troweled; a strip of fabric shall be embedded into this elastic cement. A second strip of fabric shall be similarly applied or, alternately, the first strip of fabric shall be covered with hot pitch into which the top strip of felt shall be embedded. The top strip shall be sur-faced in the same manner as the adjacent built-up roofing.

11.2 Stepped Base Flashing

(See figure on page 21). Where slate, flat tile or shingle roofs abut vertical brick or other masonry surfaces, sepa-rate pieces of aluminum flashing shall be woven in with each course. Each piece of flashing shall extend out onto the roof at least 4 in. (100 mm) and up on the vertical wall at least 4 in. (100 mm) and under the cap flashing or fin-ish siding at least 3 in. (75 mm). The flashing pieces shall extend from the top edge of the shingle on which it rests to within 0.5 in. (12 mm) of the butt of the course placed over the flashing. For slate or tile, the flashing piece shall extend at least 2 in. (50 mm) above the top edge of slate for nail-ing, or two lugs approximately 1 in. (25 mm) wide shall be made at the top of each flashing piece bent to hook over the top edge of the slate or tile. Flashing used with slate or tile roofing shall be at least 0.032 in. (0.8 mm) thick.

12. CAP FLASHING

12.1 Straight Cap Flashing

(See figure on page 21). Straight cap flashing shall be pro-vided with all base flashings. The flashing shall be formed of sheets not longer than 10 ft (3 m) and shall be built into the masonry approximately 4 in. (100 mm) with the inner edge terminating in a 0.25 in. (6 mm) hook dam or, alternately, turning up 1 in. (25 mm) behind the first brick course. The built-in portion of the flashing shall be painted (Section 2.6) before installation. The apron shall be of sufficient width to overlap the base flashing at least 3 in. (75 mm). Ends of adja-cent lengths of flashing shall overlap at least 3 in. (75 mm)

and the built-in horizontal portion of the joint shall be set in elastic cement. The flashing shall have a layer of mortar above and below the horizontal flange in the wall.

12.2 Stepped Cap Flashing

(See figure on page 21). Stepped cap flashing shall be provided at the intersection of pitched roofs with vertical surfaces. The flashing pieces shall extend into the wall at least 4 in. (100 mm) and terminate in a 0.25 in. (6 mm) hook dam. The steps shall lap at least 3 in. (75 mm) over each other and at least 3 in. (75 mm) over the base flashing.

January 2005 IX-19

Figure 9-7

IX-20 January 2005

12.3 Attaching Cap Flashing to Existing Masonry Walls

(See figure on page 21). On existing masonry walls the mortar joint to receive the flashing shall be raked out to

a depth of 1 in. (25 mm). The flashing shall extend into the raked-out joint with the inner edge bent back to form a hook dam. It shall be secured by aluminum wedges or plugs spaced not more than 8 in. (200 mm) apart and the raked-out joint shall be filled with sealant.

13. CHIMNEY FLASHING

13.1 Chimneys on Sloped Roofs

(See figure on page 21). At the front of the chimney, an apron flashing of aluminum shall extend over the roof-ing material at least 5 in. (125 mm) and up the chimney face at least 4 in. (100 mm). The lower edge of the apron flashing shall be hemmed 0.5 in. (12 mm) for stiffness and be secured in place with blind cleats or screws with neo-prene gaskets not more than 18 in. (460 mm) apart. Along the chimney sides, separate pieces of flashing at least 8 in. (200 mm) long bent to extend at least 4 in. (100 mm) onto the roof and at least 4 in. (100 mm) onto the chimney wall shall be woven in with each course of roofing material. At the chimney corners, the base flashing shall be connected

to the apron flashing by a lapped or locked seam filled with sealant. Crickets above chimneys shall be flashed and the flashing shall extend under the roofing material at least 6 in. (150 mm) and terminate in a 0.5 in. (12 mm) fold. All joints shall be lapped or locked and filled with sealant.

Cap flashing shall extend through the chimney wall and the back edge shall turn up 1 in. (25 mm) against the flue lin-ing. Pieces of stepped cap flashing shall lap the base flashing at least 3 in. (75 mm) and each other at least 3 in. (75 mm).

13.2 Chimneys on Flat Roofs

Chimneys on flat roofs shall be flashed as straight base and cap flashing (Sections 11 and 12).

14. THROUGH-WALL FLASHING

14.1 General

Through-wall flashing shall be installed under para-pet copings, for counter flashing in parapets and in rising masonry walls where roofs abut, over lintels of exterior openings, under window sills and stone band courses, and continuously over spandrel beams. All flashing in exterior walls shall extend through the wall to within 0.5 in. (12 mm) of the exterior face and turn up 2 in. (50 mm) on the inte-rior wall face unless otherwise shown on the drawings. Cap flashing shall turn extend at least 4 in. (100 mm) down the face of the wall and shall overlap the base flashing at least 3 in. (75 mm). Flashing over spandrel beams and lintels and under band courses and sills shall be installed as indi-cated on the drawings and specified elsewhere.

All through-wall flashing shall be set with a bed of mortar above and below the flashing. The flashing shall be factory formed to provide a mechanical bond in the mor-tar bed in all directions. Where aluminum flashing is to be embedded in masonry walls, it shall first be coated with bituminous paint or methacrylate lacquer (Section 2.6). Alternately, painted sheet shall be used.

14.2 Spandrel Flashings

(See figure on page 23). A continuous through-wall flashing shall be installed on top of all spandrel beams. The flashing shall extend through the masonry to within 0.5 in. (12 mm) of the exterior wall face. The rear edge of the flashing shall be turned up at least 2 in. (50 mm) against the interior face of the wall. Where the flashing intersects

columns, it shall turn up at least 2 in. (50 mm) against the sides and face of columns. At the bottom of concrete span-drel beams the flashing shall be set into a continuous reglet, placed so that the bottom edge of the receiving slot is 2.5 in. (63 mm) above the top edge of the lintel or carrier angles or as detailed on the drawings. It shall extend down to the second brick joint or first stone joint above the horizontal leg of the carrier or lintel angle, and out within 0.5 in. (12 mm) of the exterior wall face. The ends of each length of flashing shall lap at least 3 in. (75 mm) and be sealed with elastic cement.

Where the front face of the steel spandrel beams are fireproofed with brick masonry, the through-wall flashing on top of the beam shall be installed as heretofore speci-fied. At the bottom of the spandrel, the lintels or carrier angles shall be flashed with a separate strip of flashing. The flashing shall extend through the masonry to within 0.5 in. (12 mm) of the exterior wall face in the second brick joint, or first stone joint above the horizontal leg of the angle. The flashing shall turn up at least 2 in. (50 mm) against the web of the steel beam and the joint between the flashing and steel shall be sealed with elastic cement.

14.3 Sill Flashing

(See figure on page 23). The flashing under masonry sills shall extend the full depth of the sill or as detailed and at least 4 in. (100 mm) beyond the ends of the sill. The front edge of the flashing shall be 0.5 in. (12 mm) back of the exterior wall face and the back edge shall turn up at least 2 in. (50 mm) unless shown otherwise on the drawings.

January 2005 IX-21

Figure 9-8

IX-22 January 2005

14.4 Lintel Flashing

(See figure on page 23). Where openings occur in solid brick or tile walls, the flashing shall extend the full length of the lintel. It shall extend through the wall one brick course above the outer lintel to within 0.5 in. (12 mm) of the exterior face of the masonry wall, or alternately, shall be bent down to lap over the vertical leg of the outer lintel angle at least 2 in. (50 mm). The back edge of the flashing shall be bent up at least 2 in. (50 mm) against the interior wall face.

Where the bottom of concrete spandrels form the head of openings a reglet shall be installed in the face of the spandrel the full length of the lintel. The reglet shall be so placed that the bottom edge of the receiving slot is 2.5 in. (63 mm) above the top edge of the lintel, or as detailed on the drawings. the flashing shall be inserted the full depth of the reglet and shall extend horizontally through the mortar joint to within 0.5 in. (12 mm) of the exterior face of the masonry wall, or alternately, shall lap over the vertical leg of the lintel by at least 2 in. (50 mm).

Where the front face of the steel spandrel beams are fireproofed with brick masonry, the flashing shall extend the full length of the lintel. The flashing strip shall lap over the vertical leg of the lintel at least 2 in. (50 mm) and shall be bent to extend up onto the web of the steel spandrel at least 2 in. (50 mm). The joint between the flashing and steel shall be sealed with elastic cement.

14.5 Brick Parapet Walls

(See figure on page 25). Where the height of the parapet is 6 in. (150 mm) to 15 in. (380 mm) from the roof line to the underside of the coping, the through-wall flashing shall be placed directly under the coping stone. Where the height to the underside of the coping is less than 6 in. (150 mm), a one piece combination coping and base flashing shall be installed. The outer edge of the combination flashing shall extend over the coping and be secured as specified under coping covers (Section 16). The inner edge of flashing shall extend 4 in. (100 mm) onto the roof deck and be installed as specified in Section 11, Base Flashing.

(See figure on page 25). Where the height of the para-pet is more than 15 in. (380 mm) from the roof line to the underside of the coping, a through-wall flashing shall be installed directly under the coping stone. The flashing shall extend to within 0.5 in. (12 mm) of the exterior wall face and the edge shall be folded over 0.25 in. (6 mm) to form a hook dam. At the inside face of the wall, the flashing shall project 0.5 in. (12 mm) and be bent down at an angle of 45° to form a drip. Directly above the base flashing a cap flashing that extends 4 in. (100 mm) into the wall shall be installed.

14.6 Concrete Parapets and Walls

(See figure on page 25). For counter flashing and other flashing which connect with concrete walls, furnish and install a reglet in the concrete to receive metal flashing where indicated on the drawings.

The flashing shall be inserted into the reglet and secured with aluminum wedges no farther apart than 16 in. (400 mm). The reglet shall then be filled with sealant. The ends of each piece of counter flashing shall lap at least 3 in. (75 mm). A slight bend shall be made in the counter flashing to provide spring action of the lower edge against the base flashing.

15. STANDING SEAM SIDING

Where drawings call for metal covering minor vertical surfaces (walls of penthouses, monitors, skylights, fascias, the inside face of parapet walls, etc.), covering shall be Standing Seam Siding constructed according to the Sec-tion 5, standing seam roofing.

The upper edge of the siding shall be counterflashed and the lower edge shall lap over the base flashing a minimum of 3 in. (75 mm).

January 2005 IX-23

Figure 9-9

IX-24 January 2005

16. COPING COVERS

16.1 Flat Seam Coping Covers

Flat seam coping covers shall be formed of sheets not longer than 10 ft (3 m), joined by 1 in. (25 mm) loose lock seams that are filled with sealant.

(See figure on page 27). On stone copings where the covering extends down over the front face of the stone, the aluminum sheet shall hook 0.75 in. (20 mm) over a con-tinuous edge strip made of 8 or 10 ft (2.5 or 3 m) lengths of aluminum. Edge strips shall be secured with aluminum screws in expansion sleeves spaced no farther than 10 in. (250 mm) apart. Ends of adjacent lengths shall lap at least 1 in. (25 mm).

(See figure on page 27). Where the covering does not extend over the front face a separate continuous locking strip of aluminum shall be secured into a reglet in the stone with aluminum wedges, or aluminum screws in expansion sleeves, and the reglet filled with sealant. Ends of adjacent lengths of locking strip shall lap at least 2 in. (50 mm). The aluminum covering shall engage the locking strip with a 0.75 in. (20 mm) loose lock seam. The inner edge of the coping shall lock into the aluminum base flashing or be secured by cleats spaced not more than 2 ft (0.6 m) apart. Cleats shall be secured to the stone coping with two alumi-num screws in expansion sleeves.

(See figure on page 27). Walls topped with wood plate shall have a continuous edge strip, made of 8 or 10 ft (2.5 or 3 m) long lengths of aluminum , secured along the front edge with aluminum nails spaced no farther than 4 in. (100 mm) apart. The coping cover shall be hooked over the edge strip with a 0.75 in. (20 mm) loose lock seam. The inner edge of the aluminum coping shall lock into the top of the aluminum base flashing with a 0.75 in. (20 mm) loose lock seam. Where aluminum base flashing is not provided, the coping shall hook over an edge strip as specified for the front edge, or, alter-nately, it shall be secured by aluminum cleats spaced no more

than 2 ft (0.6 m) apart. Cleats shall be secured to the wood plate with two aluminum nails.

(See figure on page 27). Where the height of the coping above the roof deck is less than 6 in. (150 mm), a one-piece combination coping cover and base flashing shall be installed. The inner edge of the flashing shall extend onto the previously placed built-up roofing 4 in. (100 mm) and shall be nailed along its outer edge with aluminum nails spaced no more than 3 in. (75 mm) apart. The horizon-tal flange shall then be stripped into the built-up roofing. Where the height of the coping above the roof deck is more than 6 in. (150 mm), the inner edge of the coping cover shall lock into the aluminum base flashing or be secured by cleats not more than 2 ft (0.6 m) apart.

16.2 Standing Seam Coping Covers

(See figure on page 27). Standing seam coping covers shall be formed from sheets not longer than 10 ft (3 m). Ends of sheets shall be connected by a single fold stand-ing seam finishing at least 1.25 in. (32 mm) high. The tab at the ends of standing seams shall be folded over to close the ends of seams. Front and rear sides of the aluminum coping shall extend down over the edge of the masonry at least 2 in. (50 mm). The lower edges shall be bent out to form a drip and hook over continuous edge strips. Edge strips, in 8 or 10 ft (2.5 or 3 m) lengths, shall be attached to the inner and outer faces of the wood plate with alumi-num nails spaced no more than 4 in. (100 mm) apart. Edge strips shall extend over the top of the wood plate at least 2 in. (50 mm).

16.3 Extruded Coping Covers

Extruded coping covers shall be of the size and shape shown on the drawings. Installation shall be in accordance with manufacturer’s specifications.

January 2005 IX-25

Figure 9-10

IX-26 January 2005

17. MISCELLANEOUS

17.1 Scupper Flashing

(See figure on page 29). Scupper flashing shall cover the interior of the opening in the wall and shall extend through and project outside the wall as shown on the drawings. The dimensions of the flashing shall be 0.5 in. (12 mm) less than the masonry opening. On the roof side, the scupper lining shall be of sufficient length to be built into a membrane base flashing at least 4 in. (100 mm) or locked to the aluminum base flashing with a 0.75 in. (20 mm) sealant filled seam. The bottom edge shall extend at least 4 in. (100 mm) into the built-up roofing and where required a 0.75 in. (20 mm) high gravel stop ridge shall be formed around the scupper inlet.

17.2 Splash Pans

(See figure on page 29). Splash pans shall be installed under all downspouts discharging onto composition roofs. Pans shall be made of sheets 24 in. (600 mm) long by 18 in. (460 mm) wide unless otherwise indicated on the drawings. 1 in. (25 mm) inverted V members placed 4 in. (100 mm) from the outside edges shall be formed on two sides and one end of the sheet. Filler pieces shall be provided at the corners so that they lap over the flanges on the sides at least 3 in. (75 mm) with the lapped joints being set in elastic cement. The rear side of the pan shall be at least 8 in. (200 mm) high

and shall extend under the side wall covering or be cap flashed on masonry walls. Pans shall be bedded in elas-tic cement and the 4 in. (100 mm) side flanges shall be stripped and mopped into the built-up roofing as specified in Section 11.1.

17.3 Curb Flashing

Curb flashing shall be provided on all curbs, roof scut-tles, etc. The flashing shall extend up the full height and over the top of the curbs. The lower edge shall extend 4 in. (100 mm) onto the roof deck and with built-up roofing be installed as specified in Section 11.1 or with slate, tile or shingle roofing be installed as specified in Section 10.2.

17.4 Door Sills

(See figure on page 29). The sills of doors leading onto flat roofs (except where the bottom of the sill is at or above the level of cap flashing) shall be provided with aluminum flashing. The flashing shall extend under the sill and be turned up behind and at the two ends of the sill at least 2 in. (50 mm). The sill flashing shall be joined to the base flashing by a 0.75 in. (20 mm) lock seam filled with seal-ant. All lock seams and joints shall be made watertight with sealant.

January 2005 IX-27

Figure 9-11

IX-28 January 2005

18. RAINWATER GOODS

18.1 Hung Gutters

(See figure on page 29). Hung gutters shall be of the size and shape shown on the drawings. Outer edges shall be rolled or beaded to provide stiffness. Inner edges shall finish at least 1 in. (25 mm) above outer edges. Gutters shall be secured by cleats engaged along the inner edge and by hang-ers or straps spaced not more than 32 in. (800 mm) apart. Ends of gutter sections shall be joined in a separate S lock or, alternately, the ends shall lap at least 3 in. (75 mm) in the direction of flow, be riveted and the joint covered with seal-ant. Gutters shall slope at least 1/16 in. per ft (1:192) toward leaders. Expansion joints shall be provided on long straight runs at spacings not greater than 50 ft (15 m) and at inside and outside corners at spacings not greater than 20 ft (6 m).

18.2 Outlet Tubes

(See figure on page 29). Outlet tubes shall be of the size and shape required to fit the gutter. They shall be located as shown on the drawings, but at spacings not more than 50 ft (15 m). Holes shall be provided in the gutter bottom through which the outlet shall extend. The flanges formed at the top of the outlet tube shall be riveted to the gutter

and the connection sealed with sealant. Outlet tubes shall extend at least 3 in. (75 mm) into leaders.

18.3 Leader Heads

Leader heads shall be of the size and shape shown on the drawings.

18.4 Leaders

Leaders or downspouts shall be of the size and shape shown on the drawings. End joints shall telescope at least 1.5 in. (38 mm) and longitudinal joints shall be locked. All necessary elbows, offsets, and other fittings shall be provided.

18.5 Leader Straps

Leader straps shall hold leaders clear of the wall. Leader straps shall be spaced as shown on the drawings, but not more than 10 ft (3 m) apart. They shall be securely attached to the wall with aluminum fasteners and shall grip the leader securely by means of punched prongs, screws, riv-ets, or other mechanical fasteners.

January 2005 IX-29

COMMENTARY

2.1.1 Where severe forming is involved a softer temper may

be employed and where little forming is required a harder temper may be used. Minimum bend radii for common alloy/tempers and thicknesses can be found in Aluminum Standards and Data. Alclad sheet provides extra protection against pitting in corrosive environments.

2.1.2The smallest nominal thickness preferred is 0.024 in.

(0.60 mm).

2.5.3The use of washers increases the fastener’s resistance to

the sheet pulling over the head of the fastener. The strength of self tapping screw connections is addressed in the Aluminum Design Manual, Specifications for Aluminum Structures, Section 5.3.

3.2Indoors under dry conditions, galvanic corrosion of alu-

minum will not occur and therefore aluminum may be used in contact with any metal commonly used in buildings.

Outdoors and indoors where moisture is present galvanic corrosion may occur. Galvanic corrosion between alumi-num and zinc, stainless steel, monel, or lead is insignifi-cant. Between aluminum and iron or steel, such corrosion is very slow and can be prevented readily by painting the iron or steel with a good quality exterior grade primer and top coat or bituminous paint. Galvanic corrosion between aluminum and galvanized steel is insignificant, but once the zinc is consumed, steel will rust which may cause stain-ing. In severe industrial environments this can happen in a short time and painting may be required.

Highly corrosive environments such as those on the sea-coast and around industrial plants may promote galvanic corrosion even though aluminum by itself has good corro-sion resistance. Consult specialists in such cases.

3.3Kiln dried lumber, impregnated against decay, is recom-

mended for sheathing, cant strips, coping blocks, and fascia boards. Preservatives that are compatible with aluminum are coal tar creosote, coal tar oil, chlorinated naphthalenes, zinc naphthenate, pentachloroxide, and orthophenylphenol. Other preservatives may be used but assurance should be obtained from the manufacturer that they are not harmful to aluminum.

Aluminum paint, consisting of 2 pounds of aluminum paste pigment (ASTM D962, Type 2, Class B) per gallon of varnish meeting Federal Specification TT-V-81F, Type II or equivalent, is an excellent primer and paint for wood. However, any good quality exterior paint may be used.

4.1Solar radiation can develop material temperatures of

140oF (60oC) on bare aluminum and up to 180oF (80oC) on dark painted metal. Radiation to the night sky can produce surface temperatures 10oF to 15oF (5oC to 7oC) below ambi-ent air (more in arid regions and at higher altitudes), so joints should be designed for temperature variations of 100oF (50oC) minimum or more depending on the application.

4.4Filler alloy selection is a function of the alloys of the

metals to be welded and may be made using the Aluminum Design Manual, Specifications for Aluminum Structures, Table 7.2-1 for MIG and TIG welds. Filler alloy 4043 can be used for oxyfuel-gas welding all sheet alloys; however, 1100 filler alloy can be used for welding 1100 and 3003 base alloys for improved weld ductility and color match with parts to be anodized after welding. Filler alloy 5356 is not suitable for oxyfuel-gas welding.

5.1Standing seam roofs with slopes less than 3 in 12 (1:4)

require special precautions in design and installation to ensure leaktightness.

5.3Standing seam roofing is best installed over wood decks

since the cleats used to secure the aluminum roofing are nailed directly to the deck. If decks other than wood are used, properly located nailers should be incorporated in the deck.

When standing seams are formed or finished in the field the cleats become rigidly locked into the multiple folds of the seam; slippage does not occur between standing seam roof sheets and the cleats that are secured to the deck. Long runs of roofing may eventually loosen the nails in the deck. Where runs of standing seam roofing over 30 ft (9 m) are unavoidable, expansion or sliding cleats should be used.

6.1Batten seam roofs with slopes less than 3 in 12 (1:4)

require special precautions in design and installation to ensure leaktightness.

6.3The size and spacing of battens may vary within reason-

able limits to suit architectural style, scale of buildings, and width of sheets.

18.1Alclad sheet is recommended for gutters, especially in

corrosive environments.

18.4Leaders should be formed in lengths at least 10 ft (3 m)

long where possible.

IX-30 January 2005

REFERENCES

1. Metal Construction Association, Guide Specification for Residential Metal Roofing, Chicago, IL, 1995.

2. Aluminum Association, Aluminum Standards and Data, Washington, DC, 2003.

3. National Roofing Contractors Association, The Metal Roofing Manual, Rosemont, IL, 1996.

4. American Architectural Manufacturer’s Association (AAMA) Standard Specifications for Aluminum Siding,

Soffit & Fascia (ANSI/AAMA 1402-86), Schaumburg, IL, 1986.

5. American Architectural Manufacturer’s Association (AAMA) Voluntary Specifications for Aluminum Gutter and Downspout Systems (AAMA 1405.1-1976) Schaum-burg, IL, 1976.


Appendix 1

Metric Guide for Aluminum Structural Design



January 2005 Appendix-I-3

Guidelines are included here for metric conversion from English to SI units.

For a more thorough treatise on all types of SI or metric units, reference is provided to two sources:

• “Metric Guide for Federal Construction,” published by the National Institute of Building Sciences, Wash-ington, D.C., 1993.

• “Conversion Tables of Units for Science and Engi-neering,” by Ari L. Horvath, published by Elsevier, New York, 1986.

SI Units for Structures

The SI or metric units used in civil and structural engi-neering are:

Length—meter, abbreviated “m”; small sizes are expressed in millimeters, “mm” and very long lengths in kilometers, “km”. Area is expressed in square meters, square millimeters or square kilometers; very large areas are expressed in hectares, “ha”, which are 10,000 square meters.

Mass—kilogram, “kg”; note that there are separate units for mass and force, kilogram is the unit quantity independ-ent of gravity.

Force—Newton, “N”; this is a derived unit (mass times acceleration, kg • m/s2). It replaces the unit kilogram-force (kgf), which should not be used. A Newton is very small, and so is usually used as kiloNewtons, “kN”.

Stress, strength and pressure—pascal, “Pa”; a derived unit, for divided by area, A/m2”. It is a very small unit and is customarily used as megapascals, “MPa”.

Tables A1-1 and A1-2 list the SI units most commonly used in the design and construction industries, together with the recommended conversion factors, for getting SI values from English units.

These conversion factors are especially useful for “soft” unit conversion, that is, conversion of English units to SI units maintaining the same basic sizes implied by the Eng-lish units. Such conversions have the advantage of rather accurately reflecting the dimension and capabilities of structures as they were originally established in English units. However, they have the disadvantage of typically resulting in “odd” numbers, not comfortably rounded num-bers typical of a structure that was designed in SI units in the first place. The latter is known as “hard” conversion.

Table A1-1AREA, LENGTH AND VOLUME CONVERSION FACTORS

QuantityFrom

Inch-PoundUnits

ToMetricUnits

Multiplyby

Length mileyardfoot

inch

kmmmmmmm

1.609 344 0.914 4 0.304 8 304.8 25.4

Area square mileacre

square yardsquare footsquare inch

km2

m2

ha (10 000 m2)m2

m2

mm2

2.590 00 4 046.856 0.404 685 6 0.836 127 36 0.092 903 04 645.16

Volume acre footcubic yardcubic footcubic footcubic foot100 board feetgalloncubic inchcubic inch

m3

m3

m3

cm3

L (1000 cm3)m3

L (1000 cm3)cm3

mm3

1 233.49 0.764 555 0.028 316 8 28 316.85 28.316 85 0.235 974 3.785 41 16.387 064 16 387.064

Note: Underline denotes exact number

Appendix-1-4 January 2005

Table A1-2CIVIL AND STRUCTURAL ENGINEERING

CONVERSION FACTORS

QuantityFrom

Inch-PoundUnits

ToMetricUnits

Multiplyby

Mass lbkip (1000 lb)

kgmetric ton (1000 kg)

0.453 5920.453 592

Mass/unit length plf kg/m 1.488 16

Mass/unit area psf kg/m2 4.882 43

Mass density pcf kg/m3 16.018 5

Force lbkip

NkN

4.448 224.448 22

Force/unit length plfklf

N/mkN/m

14.593 914.593 9

Pressure, stress, modulus of elasticity

psfksfpsiksi

PakPakPaMPa

47.880 347.880 36.894 766.894 76

Bending moment, torque,moment of force

ft-lbft-kip

N • mkN • m

1.355 821.355 82

Moment of Mass lb • ft kg • m 0.138 255

Moment of inertia in4 mm4 416 231

Section modulus in3 mm3 16 387.064

Note: Underline denotes exact number


Index



For references to Parts IA and IB, see also the corresponding section in Parts IIA and IIB.

adhesive joints, III-26adhesives, III-28 ASTM tests, III-29 design, III-28 surface pretreatment, III-28aerospace, III-7allowable stresses: formulas, IA-24, 25 general, IA-23 tables by alloy-temper, VII-28-77 welded members, IA-62alloys: commonly used examples, III-6 comparative characteristics and applications, IV-13 designation system, cast alloys, IV-7 designation system, wrought alloys, IV-6 foreign designation systems, IV-17 metallurgy, IV-8 tempers, IV-8angles: equal leg, VI-18 in flexure, IA-49, IB-54 in tension, III-10 section property formulae, VI-44 square end, VI-20, 24 unequal leg, VI-21anodizing, III-43ASTM, IA-9, IB-9automotive, III-7batten seam roofing, IX-12beams: angles, IA-49, IB-54 bars, IA-32, IB-36, III-13, VIII-38 examples, VIII-30-61 formulas, VII-104-121 round or oval tubes, IA-32, IB-35, III-16, VIII-37 single web, IA-32, IB-35, III-13 tubular shapes, IA-33, IB-36, III-13, VIII-39 welded, III-14, VIII-32-36bearing: examples, VIII-18-20 on holes, IA-26, IB-26, IIA-8, III-11, VIII-18 on flat surfaces, IA-26, IB-26, IIA-8, III-11 on slots, IA-26, IB-26, IIA-8, III-11 pins, IA-26, IB-26, IIA-8, III-11, VIII-19bending, IA-61, IB-67 developed lengths, VII-81 maximum thickness for 180 degree bends, VII-80 minimum radii for sheet and plate, VII-78 minimum radii for wire and rod, VII-80biaxial stresses, III-19block shear rupture, IA-52, IB-58, IIA-22, III-23bolts:

design stresses, IA-53, IB-59 dimensions, VII-99 material, IA-53, IB-59 shear, IB-59 slip critical connections, IA-54, IB-59, III-23 spacing, IA-54, IB-59 tension, IA-53, IB-59 installation, IA-61, IB-67, III-23bridges, III-7buckling: constants, IA-21-22, IB-21-22, VII-23-26 local buckling effect on beam strength, IA-40, IB-45, III-18 local buckling effect on column strength, IA-40, IB-45, III-18 local buckling stresses, IA-39, IB-43 strength graphed, VII-7-22 torsional, IA-26-27, IB-27, III-12 torsional-flexural, IA-26-27, IB-27, III-12building codes, IA-10, IB-10building sheathing: allowable deflection, IA-71, IB-77 connections, IA-58, IB-62 dimensions, VI-38 example, VIII-62 maximum recommended spans, VII-86-88 section properties, VI-39 testing, IA-71, IB-77 weights, VI-38Canadian beams, VI-16, 17cantilevers, IA-49, 62, IB-54, 68castings: design stresses, IA-67, IB-73 mechanical property limits for permanent mold casting alloys, V-14 mechanical property limits for sand casting alloys, V-12 weld fillers for, IA-69, IB-75 channels, VI-7-11 Aluminum Association Standard Channels, VI-7, VII-83 American Standard Channels, VI-8 Canadian Channels, VI-11 Car and Ship Building Channels, VI-10cladding, IV-6cleaning, IA-60, IB-66coefficient: moment gradient, IA-48, IB-53 tension, IA- 23, 26, IB- 23, 26, IIA-7 thermal expansion, IA-11, 59, IB-11, 65columns: examples, VIII-21-29 member buckling, IA-26, IB-26, III-12 welded, IA-62, IB-68, III-12combined stresses: compression and bending, IA-37, IB-41, III-18 shear, compression, and bending, IA-37, IB-42, III-18

January 2005 Index-3

tension and bending, IA-37, IB-41, III-18 web crippling and bending, IA-41, IB-46, III-18compression: axial, IA-26, IB-26concrete in contact with aluminum, IA-60, IB-66conductivity electrical, IV-5, V-25-28 thermal, IV-5, V-25-28connections: mechanical, IA-52, IB-58, III-23 welded, IA-62, IB-68, III-24contact with other materials, IA-60, IB-66corrosion, IA-60, IB-66, III-42-43 cathodic protection, III-43 crevice, III-43 galvanic, III-42 stress corrosion cracking, III-43corrugations, see building sheathingcutting, IA-59, IB-65damping, III-21dead load, IB-3deflection, IA-16, 40, 71, IB-16, 45, 77, III-15density, IA-11, IB-11, V-29design stresses (LRFD): formulas, IB-24-25 weighted average axial compressive strength, IB-43 weighted average bending strength, IB-43 welded members, IB-68designation system for sections, VI-5diaphragms, III-17doubly symmetric sections, IA-27, 47, IB-27, 52drilling, see holesductility, III-10earthquake load, see seismic loadedge distance, see fastenerseffective length factor, IA-12, 26, IB-12, 27, IIA-9, III-12effective radius of gyration, IA-32, 47, IB-35, 52effective width, IA-40, IB-45, III-15elements: III-14-16 bending, IA-33-35, IB-37-40 compression, IA-27-32, IB-27-35 edge stiffeners, IA-28, 34, IB-31, 38 intermediate stiffeners, IA-30, 34, IB-33, 38 curved, IA-32, 34, IB-35, 37 post-buckling strength, III-15 welded, III-15 width defined, IA-27, 28, 29, 33, 34, IB-28, 30, 31, 37, 38elevated temperatures, see heatingerection, IA-61, IB-67examples, VIII-1-68extrusions, III-6, III-31-41 alloy selection, III-35-36 circle size, III-37 design, III-38-39 finish, III-35 joining, III-40

screw slots, III-41 shapes, III-33-35fabrication, IA-59, IB-66 layout, IA-59, IB-66 tolerances, IA-61, IB-67factor of safety, see safety factorsfasteners: III-23 edge distance, IA-52, IB-58, III-11, 23 gage, IA-52, IB-58 grip, IA-52, IB-59 pitch, IA-52, IB-58fatigue: IA-41, IB-46, IIA-15, III-21 allowable stress range, IA-41, IB-46 constant amplitude loading, IA-46, IB-46 design details, IA-44-45, IB-49-50 examples, VIII-32-36 fatigue limit, IA-46, IB-51 stiffeners, III-26 stress category, IA-42-43, IB-47-48 variable amplitude loading, IA-41, IB-46finishes, IA-60, IB-66, IV-5fire protection, III-44flange: elastically supported, IA-49, IB-54, III-19, VIII-45flashing, IA-58, IB-62, IX-14, 18, 20formulas for geometric shapes, VI-41gages, sheet metal and wire, VI-40grip, see fastenersheating, IA-59, IB-65, IV-6, V-30-39holes: drilling, IA-60, IB-65 punching, IA-60, IB-65 reaming, IA-60, IB-65 rivets, IA-55, IB-60I-beams: Aluminum Association Standard I-beams, VI-12, VII-84 American Standard I-beams, VI-15inquiries, IA-4, IB-4interpretations, IA-4, IB-4joining, see connectionslaps, see building sheathing connectionslighting poles, IA-66, IB-72, III-7live load, IIB-3load and resistance factor design, IB-1-77, IIB-1-13load factors, IIB-3lockbolts, IA-54, IB-59magnesium content in aluminum alloys, III-42, IV-8material specifications, IA-9, IB-9mechanical properties: fastener alloys, V-16 minimum properties for aluminum alloys, IA-15-18, IB-15-18, V-5-9 minimum properties for welded aluminum alloys, IA-19-20, IB-19-20, V-10-11 permanent mold alloys, V-14 sand casting alloys, V-12

Index-4 January 2005

testing to determine, IA-70, IB-76 typical, V-17-24metric conversions, Appendix Imodulus of elasticity, IA-15-18, IB-15-18, V-6-9, 17-24net area, IA-52, IB-58, IIA-22nomenclature, IA-11-13, IB-11-14nonsymmetric sections, IA-27, IB-27nuts, IA-53, IB-59, VII-100-101painting, IA-60, IB-66, IX-6physical properties, typical, V-25-29pipe, III-7, VI-32pipe bursting pressure, III-19Poisson’s ratio, IA-11, IB-11polar radius of gyration, IA-48, IB-53punching, see holesradius of gyration, IA-32, 47, IB-35, 52, VIII-57-61railroad cars, III-7rainwater goods, IX-28reaming, see holesreferences, IIA-32, IIB-13, III-7, 45, V-5, IX-30resistance factors, IB-23rivets: bearing areas, VII-93-94 blind, IA-56, IB-61 design loads, IA-55-56, IB-60-61 driving pressures, VII-95 grips, maximum VII-97 head styles and specifications, VII-92 heads, IA-, IB-66 hole, IA-55, 60, IB-60, 66 hole sizes, VII-93-94 hollow-end, IA-56, IB-61 lengths, VII-96-97 material, IA-55, IB-60 military specifications, VII-92 pneumatic hammer sizes for, VII-95 reduction in strength for use in thin sheets, VII-89 removal, IA-60, IB-66 shear areas, VII-93-94 spacing, IA-56, IB-61 steel, IA-55, IB-60 strengths, VII-89roofing, see building sheathingsafety factors: bridge structures, IA-9, 23 building structures, IA-9, 23sandwich panels, III-30section properties, IA-10, IB-10, VI-1-44screws, tapping: example, VIII-66 internal thread stripping area, VII-103 material, IA-57, IB-61 pull-out, IA-57, IB-61 pull-over, IA-57, IB-62 shear and bearing, IA-57, IB-62 tension, IA-57, IB-61

screws: hole sizes recommended, VII-98 machine screws tensile and shear strengths, VII-90 sheet metal screws shear strengths, VII-91 slot dimensions, III-41sections, nomenclature, VI-5seismic load, IIA-7, IIB-3shape factors, III-11shear, see webs in tubes, IA-37, IB-41shear center, IA-27, 47, 48, IB-27, 52, 53, III-14sheet gages, VI-40siding, see building sheathingsingly symmetric sections, IA-26, 47, IB-27, 52slenderness ratio, , IA-26 IB-27specific gravity, IV-5, V-29stainless steel, IA-53, 55, 57, IB-59, 60, 61standing seam roof, IA-49, IB-54, IX-10standing seam siding, IX-22steel, III-9 bolts, see bolts, steel fatigue performance, III-21 rivets, see rivets, steelstiffeners: III-18 circumferential stiffeners on tubes, IA-37, IB-41 edge, IA-28, 34, IB-31, 38 example, VIII-43 intermediate stiffeners, IA-30, 34, IB-33, 38, III-19 lip, IA-28, 34, IB-31, 38 longitudinal, IA-35, 38, IB-40, 42, III-19 transverse stiffener in web, IA-38, IB-42, III-19strengths, see mechanical propertiessymbols, see nomenclaturetanks, III-7tapered thickness elements, IA-51, IB-56, III-15tees, VI-25-26 Army-Navy, VI-26 Special, VI-26temperature, effect on tensile strength, IA-59, IB-65, V-30tension, axial: allowable stress, IA-26, IB-26 example, VIII-9-10tension, beams: allowable stress, IA-26, IB-26tension field action, III-17testing, IA-70, IB-76 mechanical properties, IA-70, IB-76 structural performance, IA-70, IB-76torsion: and bending, IA-37, IB-41 in tubes, IA-37, IB-41torsional flexural buckling equivalent slenderness ratio, IA-26, IB-27torsion constant, IA-47, IB-52, IIA-11tread plate, allowable load tables, VII-85triaxial stresses, III-19

January 2005 Index-5

tubes: circumferentially welded, III-17 column examples, VIII-29 in bending, IA-32, IB-35, III-16 in compression, III-16 rectangular, VI-36 round, VI-28 round or oval, IA-26, 32, IB-26, 35 shear stress, IA-37, IB-41, III-18 square, VI-34unbraced length, IA-32, 33, 47, IB-35, 36, 52V-beam, see building sheathingvon Mises stresses, III-19warping constant, IA-27, 47, IB-27, 52, VI-41washers, IA-53, 54, IB-59, 60, VII-102, IX-5webs: corrugated, III-17 crippling, IA-41, IB-45 crippling example, VIII-14, 64 examples of shear checks, VIII-50, 53 longitudinal stiffeners for, IA-38, IB-42, VIII-49 shear in stiffened webs, IA-36, IB-40, III-17 shear in unstiffened webs, IA-36, IB-40, III-17 tension field action, III-17 transverse stiffeners for, IA-38, IB-42, VIII-52weighted average strengths axial compression, IA-39, IB-43 bending, IA-39, IB-43, VIII-67weights, VI-6welding: allowable stresses in welded members, IA-62 beams, see beams, welded circumferential on tubes, III-17 columns, see columns, welded corners, III-26 fabrication, IA-62, IB-68, III-24 filler wire, IA-63, IB-69 fillet welds, IA-64, IB-70, III-24 groove welds, IA-62, IB-68, III-24 inspection, III-24 lap joints, III-26 longitudinal welds, IA-62, IB-68 plug and slot welds, IA-65, IB-71 post-weld heat treating, IA-66, IB-72, III-10 stud welding, IA-65, IB-71 transverse welds, IA-66, IB-68wide flange sections, VI-13, 14, 17wind load, IIA-7, IIB-3, III-21zees, VI-27

Index-6 January 2005

Documents

Aluminum Design Manual