Mantra: 365-08-00-99626-GBA1, Rev: A, RELEASED, 16-NOV-10 ... · 365-08-00-99626-gba1, for special freighter. all other chapters do not apply to the sf rb configurations. chapters

This supplement (IAI 365-08-00-99626-GBA1) must be attached to the Boeing 737-300 Airplane Weight and Balance Manual, Boeing Document No. D043A530-GBA1, Highlights Revision No. 2, when the provisions of STC No. SA-136, which converts the Boeing 737-300 passenger airplane to special freighter are incorporated according to IAI Report No. TR-365-00-00-92100 Issue AL.

The information contained herein supplements or supersedes the basic manual and any applicable appendices and supplements thereto only in those area listed herein. Weight and Balance information not contained in this supplement, consult the basic Weight and Balance Manual, Operation Manual and applicable appendices and supplements thereto.

REVISION 8: Jul 03/2007

ORIGINALLY ISSUED: JUL 19/2010IAI 365-08-00-99626-GBA1

REVISION 2: OCT 25/2010

Mantra: 365-08-00-99626-GBA1, Rev: A, RELEASED, 16-NOV-10, EO: 00012561

PAGE 1 OF 1IAI 365-08-00-99626-GBA1

APPLICABLE CONFIGURATIONS

OCT 25/2010SF RB

REVISIONS

REVISION RECORD1. General

A. Enter the revision number in numerical order, together with the date filed and the initials of the person filling in the form below.

REVISION No.

DATE FILED

BYREVISION

No.DATE FILED

BY

Original(Revision 1)

Jul 19/2010 IAI - MHT

Revision 2 Oct 25/2010 IAI - MHT

REVISION RECORD


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


JUL 19/2010SF RB (ALL)

FOREWORD

A. This supplement Report No. IAI 365-08-00-99626-GBA1 updates the relevant subject sections of the Boeing 737-300 Weight and Balance Control and Loading Manual, D043A530-GBA1, Highlights Revision No. 2, when a passenger 737-34S is converted into a 737-34S SF/RB, Special Freighter, using CAAI STC SA-136.

B. This Supplement report is organized with full compliance to Boeing Weight and Balance Control and Loading Manual, Report No. D043A530-GBA1, Highlights Revision No. 2, as presented in Chapter 1 - Control.

C. ALL CHAPTERS IN THE TABLE OF CONTENTS WHICH ARE MARKED ALL OR SF RB-A, SF RB-B OR SF RB (ALL) APPLY TO THIS SUPPLEMENT REPORT NO. IAI 365-08-00-99626-GBA1, FOR SPECIAL FREIGHTER. ALL OTHER CHAPTERS DO NOT APPLY TO THE SF RB CONFIGURATIONS.

CHAPTERS MARKED "ALL" ARE NOT COPIED INTO THIS SUPPLEMENT. REFER TO BOEING DOCUMENT D043A530-GBA1 HIGHLIGHT REVISION NO. 2.

FOREWORD


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


HIGHLIGHTS REVISION NO. 2 SF RB (ALL) Oct 25/2010

This revision updates this manual to include the applicable chapters when a passenger configuration 737-34S is converted into 737-34S SF/RB, Special Freighter.

The following chapters were changed:

• TITLE

- Date revised

• TABLE OF CONTENTS

- Updated for this revision

• AIRPLANE CONFIGURATION

- Registry numbers were corrected

• INTERIOR EFFECTIVITY

- Drawing numbers were corrected

OCT 25/2010SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


HIGHLIGHTS REVISION NO. 1 SF RB (ALL) Jul 19/2010

This revision updates this manual to include the applicable chapters when a passenger configuration 737-34S is converted into 737-34S SF/RB, Special Freighter.

The following chapters were changed:

• TABLE OF CONTENTS

- The following chapters were defined for "All except SF RB". These sections are not effective after conversion to Special Freighter: 1-02-040, 1-32-001, 1-34-001, 1-44-035, 1-62-001, 1-62-401, 1-090-001

• AIRPLANE CONFIGURATION

- Assign configuration for Serial No. 29108, 28109

• INTERIOR EFFECTIVITY

- Assign configuration for Serial No. 29108, 28109

• 1-00-001

- Terms for cargo added.

The following chapters were added:

• TITLE

• FOREWORD

• 1-02-041

• 1-32-002

• 1-34-002

• 1-45-001

• 1-60-002

• 1-61-001

• 1-62-002

• 1-62-042

• 1-62-101

• 1-63-001

• 1-64-001

• 1-65-001

• 1-84-002

JUL 19/2010SF RB (ALL)


PAGE 1 OF 5IAI 365-08-00-99626-GBA1


TABLE OF CONTENTS

TITLE CHP-SEC-SUB DATE/PAGE CONFIGURATION

PREFACEINTRODUCTION 12/18/2009 All

Chapter 1 - Control 1Managing Aircraft Configurations 2Document Numbering 2Chapter 2 - Aircraft Reports 2

FOREWORD 07/19/2010 SF RB (All)HIGHLIGHTS REVISION NO: 2 SF RB 10/25/2010 SF RB (All)HIGHLIGHTS REVISION NO: 1 SF RB 07/19/2010 SF RB (All)HIGHLIGHTS REVISION NO: 2 05/26/2010 AllHIGHLIGHTS REVISION NO: 1 04/06/2010 AllHIGHLIGHTS REVISION NO: ORIGINAL RELEASE 08/27/2010 All

AIRPLANE CONFIGURATION 10/25/2010 SF RB (All)Configuration Assignment 1

INTERIOR EFFECTIVITY 10/25/2010 SF RB (All)Main Deck 1

GENERALGENERAL INFORMATION 1-00-001 07/19/2010 SF RB (All)

Weight and Balance Definitions 1Abbreviations 4Conversion Factors 4Cargo Terms and Definitions 5

AIRPLANE DIMENSIONS 1-00-021 12/14/1999 AllGeneral Arrangement and Primary Dimensions 1

BALANCE REFERENCE SYSTEM 1-00-041 12/14/1999 AllBalance Arms / Body Stations 1Mean Aerodynamic Chord 2Body Buttock Line 2Water Line 2

FACTORS AFFECTING PERFORMANCE AND OPERATIONAL LIMITATIONS 1-02-001 06/29/2005 AllOperational Weight and Center of Gravity Requirements 1Commonwealth of Independent States (CIS) Requirements 1

CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS 1-02-040 06/06/2005 All Except SF RBCertified Weight Limits - MTW 140000 LB (63502 KG) 1Limitations 1C.G. Limits - MTW 140000 LB, MLW 116600 LB, MZFW 109600 LB 2C.G. Limtis - MTW 63502 KG, MLW 52888 KG, MZFW 49713 KG 3

CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS 1-02-041 07/19/2010 SF RB (All)Certified Weight Limits - MTW 140000 LB (63502 KG) 1Limitations 1C.G. Limits - MTW 140000 LB, MLW 116600 LB, MZFW 109600 LB 2C.G. Limtis - MTW 63502 KG, MLW 52888 KG, MZFW 49713 KG 3

OCT 25/2010

TABLE OF CONTENTSALL


PAGE 2 OF 5IAI 365-08-00-99626-GBA1


TAKEOFF HORIZONTAL STABILIZER TRIM SETTING 1-06-001 11/07/2005 AllEnglish Units Flaps 1 & 5 1Metric Units Flaps 1 & 5 2English Units Flaps 15 3Metric Units Flaps 15 4

LANDING GEAR AND FLAP MOVEMENT BALANCE EFFECT 1-08-001 12/14/1999 AllLanding Gear Retraction Movement 1Flaps Retraction Moment 1

FUELFUEL TANK ARRANGEMENT AND CAPACITIES 1-20-001 02/01/2001 ALL

Fuel Tank Locations 1Maximum Allowable Fuel Weight 2Usable Fuel Quantities and Locations 2Unusable Fuel Quantities and Locations 3

FUEL MANAGEMENT 1-22-001 03/19/2002 ALLFuel Loading Procedures 1Lateral Fuel Imbalance 1Fuel Usage Procedures 2

FUEL TANK QUANTITIES AND BALANCE ARMS 1-24-001 12/14/1999 AllCombined Main Tanks 1 and 2 U.S. Gallons 1Combined Main Tanks 1 and 2 in Liters 2

FUEL TANK QUANTITIES AND BALANCE ARMS 1-24-021 02/01/2001 AllCenter Tank in U.S. Gallons 1Center Tank in Liters 2

FLUIDSSYSTEM FLUIDS 1-30-001 12/14/1999 All

Engine System Oil 1Constant Speed Drive Oil 1Hydraulic System Fluid 1Landing Gear System Fluid 2Operating System Fluid 2

POTABLE WATER SYSTEM 1-32-001 07/19/2010 All Except SF RBTank Quantities and Locations 1

POTABLE WATER SYSTEM 1-32-002 07/19/2010 SF RB (All)Tank Quantities and Locations 1

WASTE DISPOSAL SYSTEM 1-34-001 12/14/1999 All Except SF RBLavatory Quantities and Location - 3 Gallon Precharge 1

WASTE DISPOSAL SYSTEM 1-34-002 07/19/2010 SF RB (All)Lavatory Quantities and Location - 3 Gallon Precharge 1

TABLE OF CONTENTS (CONT)


OCT 25/2010



PAGE 3 OF 5IAI 365-08-00-99626-GBA1


PERSONNELPASSENGER AND PERSONNEL WEIGHT ALLOWANCES 1-40-001 09/26/2007 All

FAA Advisory Circular 120-27E Allowances 1

INTERIOR ARRANGEMENT - MAIN DECK 1-44-035 08/27/2007 All Except SF RBFlight Deck 1Main Cabin - 32C/82Y and OC/130Y Arangement 2

INTERIOR ARRANGEMENT - MAIN DECK 1-45-001 07/19/2010 SF RB (All)Flight Deck 1Supernumeraries Area 2

CARGOCARGO COMPARTMENTS - LOAD LIMITS 1-60-001 07/13/2005 All

Maximum Allowable Weights 1

CARGO COMPARTMENTS - LINEAR AND LOAD LIMITS 1-60-002 07/19/2010 SF RB (All)Compartment and Floor Limits 1Maximum Combined (Monocoque) Linear Load Limits 2

FORWARD AND AFT BODY CUMULATIVE LOAD LIMITS 1-61-001 07/19/2010 SF RB (All)Forebody Cumulative Load Limits 1Aftbody Cumulative Load Limits 2

CARGO COMPARTMENTS 1-62-001 04/12/2000 All Except SF RBGeneral Location and Arrangement 1

CARGO COMPARTMENTS 1-62-002 07/19/2010 SF RB (All)General Location and Arrangement 1

FORWARD CARGO COMPARTMENTS 1-62-401 08/17/2007 All Except SF RBForward Cargo Compartment Volumes 1Forward Cargo Compartment Cross Sections 2Cargo Door Dimensions and Allowable Package Sizes 4

FORWARD CARGO COMPARTMENTS 1-62-042 07/19/2010 SF RB (All)Forward Cargo Compartment Volumes 1Forward Cargo Compartment Cross Sections 2Cargo Door Dimensions and Allowable Package Sizes 4

AFT CARGO COMPARTMENTS 1-62-601 08/17/2007 AllAft Cargo Compartment Volumes 1Aft Cargo Compartment Cross Sections 2Cargo Door Dimensions and Allowable Package Sizes 4

MAIN DECK CARGO COMPARTMENT 1-62-101 07/19/2010 SF RB (All)Main Deck Cargo Compartment Cross Section 1

UNIT LOAD DEVICE - MAIN DECK 1-63-001 07/19/2010 SF RB (All)Allowable Center of Gravity Range 1Maximum Allowable ULD Contour 2



OCT 25/2010



PAGE 4 OF 5IAI 365-08-00-99626-GBA1


MAIN DECK UNIT LOAD DEVICE LOCATIONS 1-64-001 07/19/2010 SF RB (All)Size Code A (88 X 125) and Position 10 1Size Code B (88 X 109) and Position 10 2Size Code M (96 X 125) and Position 10 3

MAIN DECK UNIT LOAD DEVICES LOAD LIMITS 1-65-001 07/19/2010 SF RB (All)Size Codes A, B, M, K and LD-4 Load Limits 1Size Codes A, B, M, K and LD-4 Load Limits with Missing/ Inoperative Restraints

2

Size Codes A, B, M, K and LD-4 Load Limits 3Size Codes A Load Limits with Missing/Inoperative Restraints 4Size Codes B Load Limits with Missing/Inoperative Restraints 5Size Codes M Load Limits with Missing/Inoperative Restraints 6Size Codes K and LD-4 Load Limits with Missing/Inoperative Restraints 7

CARGO TIE-DOWNS 1-68-001 12/17/1999 AllTie-down Limitations 1

GROUND OPERATIONS

AIRPLANE JACKING 1-80-001 12/14/1999 AllJack Point Locations 1Maximum Allowable Jacking Loads 2Limitations Envelopes 3

NOSE GEAR JACK POINTS FOR VARIOUS OLEO EXTENSIONS 1-80-051 02/17/2006 AllJack Point Balance Arms Versus Oleo Extension 1

MAIN LANDING GEAR JACK POINTS FOR VARIOUS OLEO EXTENSIONS 1-80-081 02/17/2006 AllJack Point Balance Arms Versus Oleo Extension 1

AIRPLANE WEIGHING PROCEDURE 1-82-001 12/05/2005 AllGeneral Information 1Weighing Facilities and Equipment 1Preparation for Airplane Weighing 1Weighing Operation 2Weighing Procedure Using Platform Scales 3Weighing Procedure Using Electronic Load Cells 3Non-level Weighing 5

TOWING AND TIPPING LIMITATIONS 1-84-001 09/26/2007 AllTowing and Tipping Considerations 1Towing and Tipping Limits (English) 2Towing and Tipping Limits (Metric) 3

TIPPING LIMITATIONS (TAIL JACK) 1-84-002 07/19/2010 SF RB (All)1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-001 12/14/1999 AllWing Components 1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-011 12/14/1999 AllHorizontal Stabilizer Components 1



OCT 25/2010



PAGE 5 OF 5IAI 365-08-00-99626-GBA1


COMPONENT WEIGHTS AND BALANCE ARMS 1-86-021 12/14/1999 AllVertical Fin Components 1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-031 12/14/1999 AllBody Components 1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-041 12/14/1999 AllMain Gear Components 1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-051 12/14/1999 AllNose Gear Components 1

COMPONENT WEIGHTS AND BALANCE ARMS 1-86-061 12/17/1999 AllNacelle and Power Plant Components 1

EXAMPLESLOADING SCHEDULE DEVELOPMENT 1-90-001 04/05/2007 All Except SF RB

Introduction 1Ordering Instructions 2



OCT 25/2010



PAGE 1 OF 1IAI 365-08-00-99626-GBA1


AIRPLANE CONFIGURATION

The engineering data and CAAI certification provided by this document is applicable and valid only forthe airplane in list bellow. With respect to any other modifications, it shall be the responsibility of thebuyer to obtain the data and appropriate regulatory agency approval.

CONFIGURATION ASSIGNMENT

The table shown below correlates each airplane serial number to the currently allowed configuration(s) for thatairplane. Each configuration is designated by a different letter. Configuration qualifications are listed following thetable and indicate the change authorization involved for airplanes with multiple allowable configurations. Becausethere may be multiple configuration letters applicable to any serial number, and also multiple configuration qualifi-cations listed for any configuration letter, care should be exercised when determining the configuration letterwhich correctly reflects the applicable configuration of the airplane.

Line number and variable number per Boeing document D043A530-GBA1, Highlight Revision No. 2.

LIST OF APPLICABLE CHAPTERS

All chapters which are marked ALL or SF RB (ALL) in the table of contents are applicable for all the aircraft in theconfiguration assignment.

CONFIGURATION QUALIFICATIONS

Not applicable for this airplane.

LINENUMBER

SERIALNUMBER

VARIABLENUMBER

REGISTRYNUMBER CONFIGURATION AIRCRAFT REPORT

2983 29108 PR091 N491MS B IAI 365-08-00-B5457

3001 29109 PR092 N132MN B IAI 365-08-00-B5458

OCT 25/2010

AIRPLANE CONFIGURATION

SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


INTERIOR EFFECTIVITY

The tabular data shown below correlates each airplane serial number to the cargo arrangement(s) certified forthat airplane. Each cargo arrangement is designated by drawing number and revision letter. To locate a particular cargo arrangement(s), refer to the interior section listed below. Drawing numbers are listed beside eachinterior drawing in the interior section..

SERIAL NUMBER

PASSENGER OR CARGO ARRANGEMENT EFFECTIVITY - MAIN DECK

DRAWING #

RE

V DRAWING #

RE

V DRAWING #

RE

V

29108 LD 365-25-00-92900-126 -

29109 LD 365-25-00-92900-127 -

OCT 25/2010

INTERIOR EFFECTIVITY

SF RB (ALL)


PAGE 1 OF 5IAI 365-08-00-99626-GBA1


GENERAL INFORMATION

WEIGHT AND BALANCE DEFINITIONS

The following definitions are provided to assist operators in having a better understanding of the terms usedthroughout the Weight and Balance Manual.

General Terms or Acronyms

Balance Arm (B.A.) A true measure of distance from forward to aft, in inches, from a fixed datum. The fixed datum is selected by the airplane manufacturer. Balance Arms are used in weight and balance calculations. To see the relationship between B.A. and B.S., refer to CHP-SEC-SUB 1-00-04X of the Boeing manual.

Body Station (B.S.) A manufacturing location on the airplane. For first of an airplane model, B.S. are continuous from the front to the aft of the airplane. For later versions that are either stretched (i.e. fuselage inserts added) or shrunk (i.e. fuselage sections removed), B.S. becomes discontinuous, for manufacturing reasons. To see the relationship between B.A. and B.S., refer to CHP-SEC-SUB 1-00-04x of the Boeing manual.

Layout of Passenger Arrangement(LOPA)

Not applicable for special freighter

Layout of Passenger Systems(LOPS)

A Boeing internal drawing that depicts the interior layout.

Dimensional Drawing(DD)

An IAI internal drawing that depicts the Special Freighter Configuration top drawing.

WEIGHT TERMS

Basic Empty Weight(BEW)

Standard Basic Empty Weight plus or minus weight of standard item variations.

Delivery Empty Weight(DEW)

Manufacturer's Empty Weight, less any shortages, plus those standard items and operational items in aircraft at time of delivery.

Fleet Empty Weight(FEW)

Average Basic Empty Weight used for a fleet or group of aircraft of the same model and configuration. (The weight of any fleet member shall not vary more than the tolerance established by government regulations.)

Guaranteed Weight Weight the manufacturer clearly defines and guarantees, subject to contractual tolerances and adjustments.

Manufacturer's Empty Weight(MEW)

Weight of structure, powerplant, furnishings, systems and other items of equipment that are an integral part of a particular aircraft configuration. (It is essentially a “dry” weight, including only those fluids contained in closed systems.)

Maximum Payload Maximum Zero Fuel Weight minus Operational Empty Weight.

Operational Empty Weight(OEW)

Basic Empty Weight or Fleet Empty Weight plus operational items.

JUL 19/2010

1-00-001SF RB (ALL)


PAGE 2 OF 5IAI 365-08-00-99626-GBA1


GENERAL INFORMATION (CONT)

Weight Limitation Terms

Operational Items Personnel, equipment and supplies necessary for a particular operation but not included in Basic Empty Weight. These items may vary for a particular aircraft and may include, but are not limited to the following:• Crew and Baggage• Manuals and navigational equipment• Removable service equipment for cabin, galley and bar• Food and beverage, including liquor• Usable fluids other than those in useful load• Life rafts, life vests and emergency transmitters• Aircraft unit load devices.

Operational Landing Weight (OLW)

Maximum authorized weight for landing. (It is subject to airport, operational and related restrictions. It must not exceed maximum certified landing weight.)

Operational Takeoff Weight (OTOW)

Maximum authorized weight for takeoff. (It is subject to airport, operational and related restrictions. This is the weight at start of takeoff run and must not exceed maximum certified takeoff weight.)

Payload Weight of the passengers, cargo and baggage. (These may be revenue and/or non-revenue.)

Standard Basic Empty Weight (SBEW)

Manufacturer's Empty Weight plus standard items.

Standard Items Equipment and fluids not considered an integral part of a particular aircraft and not a variation for the same type of aircraft. These items may include, but are not limited to, the following:• Unusable fuel and other unusable fluids• Engine oil• Toilet fluid and chemical• Fire extinguishers, pyrotechnics and emergency oxygen equipment• Structure in galley, buffet and bar• Supplementary electronic equipment.

Useful Load Difference between takeoff weight and Operational Empty Weight. (It includes payload, usable fuel and other usable fluids not included as operational items.)

Zero Fuel Weight Operational Empty Weight plus payload. (This weight must not exceed Maximum Zero Fuel Weight.)

Maximum Landing Weight (MLW)

Maximum weight for landing as limited by aircraft strength and airworthiness requirements.

Maximum Takeoff Weight (MTOW)

Maximum weight at brake release as limited by aircraft strength and airworthiness requirements.

Maximum Taxi Weight (MTW) Maximum weight for ground maneuver as limited by aircraft strength and airworthiness requirements. (It includes weight of taxi and run-up fuel.)

Maximum Zero Fuel Weight (MZFW)

Maximum weight allowed before usable fuel must be loaded in the aircraft as limited by strength and airworthiness requirements.

Minimum Flight Weight (MFW) Minimum weight for flight as limited by aircraft strength and airworthiness requirements.

JUL 19/2010

1-00-001SF RB (ALL)


PAGE 3 OF 5IAI 365-08-00-99626-GBA1



Balance Terms

Fuel Terms

Unusable Fuel Fuel remaining after a fuel run-out test has been completed in accordance with government regulations. (It includes drainable unusable fuel plus unusable portion of trapped fuel.)

Drainable Unusable Fuel Unusable fuel minus unusable portion of trapped fuel.

Trapped Unusable Fuel Unusable fuel remaining when aircraft is defueled by normal means using the procedures and attitudes specified for draining the tanks.

Usable Fuel Fuel available for aircraft propulsion.

Drainable Usable Fuel Usable fuel that can be drained from the aircraft by normal means using the procedures and attitudes specified for draining the tanks.

Trapped Usable Fuel Usable fuel remaining in the fuel feed and engine lines after standard tank defueling.

Curtailments

Cargo Location Variation Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable variations in cargo location when partially unrestricted cargo placement is permitted.

Fuel Density Variation Operational margin placed within the certified center of gravity limits to compensate for the effect of fuel density variation.

Fuel Usage Operational margin placed within the certified center of gravity limits to compensate for the effect of fuel management during the critical portions of flight.

Gear and Flap Movement Operational margin placed within the certified center of gravity limits to compensate for the effect of extending or retracting landing gear and flaps.

In-flight Movement Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable passenger, crew, and cart movement during flight.

Loading Schedule A hardcopy or computerized form used to record the aircraft’s weight, load distribution and other appropriate information; to calculate and check the weight and balance conditions of the aircraft against operational limitations; and to establish the stabilizer trim setting for takeoff.

Operational Empty Weight Variation

Operational margin placed within the certified center of gravity limits to compensate for the known variations in the standard and operational items.

Passenger Seating Variation Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable variations in passenger center of gravity when unrestricted seating is permitted.

Fleet Center-of-Gravity Average Basic Empty Weight center of gravity used for a fleet or group of aircraft of the same model and configuration. (The center of gravity of any fleet member shall not vary more than the maximum tolerance established by government regulations.)

JUL 19/2010

1-00-001SF RB (ALL)


PAGE 4 OF 5IAI 365-08-00-99626-GBA1


ABBREVIATIONS

The following terms, when necessary, will be abbreviated as shown below.

CONVERSION FACTORS

The data in this manual is provided in both English and Metric units. Unless otherwise stated, the conversionslisted below are used throughout this manual.

When totals or summations are required the English values are summed separately from the metric values.Differences may occur when comparing the English totals with the metric totals due to round off.

All metric values are converted from English values. When using the conversion factors in this manual, allresultants will be rounded except when the value is a weight limitation. For minimum or maximum weightlimitations the resultant metric values will be rounded up or truncated, whichever is more conservative.

UNIT ABBREVIATION UNIT ABBREVIATION

Pounds LB Inches IN.

Kilograms KG Feet FT

U. S. Gallons U.S. GAL. Square Feet SQ FT

Liters L Cubic Feet CU FT

Number NO. Inboard INBD

Forward FWD Outboard OUTBD

Balance Arm B.A. Mean Aerodynamic Chord MAC

Body Buttock Line B.B.L. Leading Edge of the MAC LEMAC

Water Line W.L. Center of Gravity C.G.

MULTIPLY BY TO OBTAIN

Pounds 0.45359237 Kilograms

U. S. Gallons 3.78541180 Liters

JUL 19/2010

1-00-001SF RB (ALL)


PAGE 5 OF 5IAI 365-08-00-99626-GBA1



CARGO TERMS AND DEFINITIONS

Cargo Compartment The single volume enclosed by the cargo floor, the forward cargo partition, theaft cargo partition, the cargo compartment ceiling and the cargo compartmentsidewalls.

Certified ULD A unit load device that has been manufactured in accordance to and receivedapproval by the appropriate governmental airworthiness authority indicatingthe airplane ULD meets their safety requirements.

Frangible Cargo Cargo consisting of items which will readily separate and conform to theairplane contour when subjected to a 9g forward load.

Frangible ULD Any ULD, when empty or when containing frangible cargo.

g The expression used to show the magnitude of a force in terms of the standardearth gravitational unit.

NAS 3610 A document which defines test conditions for certification of ULDs.

Non-Certified ULD A unit load device that has not received approval by the appropriategovernmental airwothiness authority indicating the airplane ULD meets theirsafety requirements.

Rigid Cargo Cargo consisting of an item or items which will not readily separate or whichwill not readily conform to the airplane contour when subjected to a 9g forwardload. examples include aircraft engines, machine tools, vehicles, automobileengines, pipes, large motors or generators, etc.

Tie-down Fitting An attachment device designed to transfer forces between a load bearingdevice (typically a net, strap, rope or bar) and a cargo track.

ULD Unit Load Device. An assembly of component comprising either of thefollowing:• pallet and pallet net• pallet and pallet net over an igloo• aircraft container.The purpose of the unit is to enable individual pieces of cargo to be assembled into a standard sized unit to facilitate rapid loading/unloading into the aircraft having compatible handling and restraint systems which interface directly with the unit.

JUL 19/2010

1-00-001SF RB (ALL)


PAGE 1 OF 3IAI 365-08-00-99626-GBA1


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS

CERTIFIED WEIGHT LIMITS - MTW 140000 LB (63502 KG)

The Maximum Certified Gross Weights and Center of Gravity Limits are shown graphically on pages 2 & 3.

These Center of Gravity Limits are for taxi, takeoff, flight and landing unless otherwise specified, and are theabsolute limits which must not be exceeded by the airplane center of gravity in any taxi, takeoff, flight, or landingconfiguration.

LIMITATIONS

The following limitations must be met in order to use the certified gross weight and center of gravity limits:

• Minimum Tire Size Required

• Nose Gear - 27X7.75-15/10 Ply Rating

• Main Gear - H40X14.5-19/24 Ply Rating or H42X16-19/24 Ply Rating.

• Refer to the Airplane Maintenance Manual Section 12-15-51 for minimum tire pressure requirements.

CERTIFIED GROSS WEIGHTS

LB KG

Maximum Taxi Weight (MTW) 140,000 63,502

Maximum Takeoff Weight (MTOW) 139,500 63,276

Maximum Landing Weight (MLW) 116,600 52,888

Maximum Zero Fuel Weight (MZFW) 109,600 49,713

Minimum Flight Weight (MFW) 63,400 28,757

JUL 19/2010

1-02-041SF RB (ALL)


PAGE 2 OF 3IAI 365-08-00-99626-GBA1


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS (Continued)

C.G. LIMITS - MTW 140000 LB, MLW 116600 LB, MZFW 109600 LB

The following diagram represents the certified Center of Gravity Limits in English units:

WARNING: REFER TO PAGE 1 OF THIS SUBJECT FOR LIMITATIONS TO THE C.G. LIMITS.

JUL 19/2010

1-02-041SF RB (ALL)


PAGE 3 OF 3IAI 365-08-00-99626-GBA1


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS (Continued)

C.G. LIMITS - MTW 63502 KG, MLW 52888 KG, MZFW 49713 KG

The following diagram represents the certified Center of Gravity Limits in Metric units:

WARNING: REFER TO PAGE 1 OF THIS SUBJECT FOR LIMITATIONS TO THE C.G. LIMITS.

JUL 19/2010

1-02-041SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


POTABLE WATER SYSTEM

TANK QUANTITIES AND LOCATIONS

Potable Water

All the potable water system (tanks, plumbing and water) has been removed from the airplane.

Any potable water in the airplane should be considered as payload.

JUL 19/2010

1-32-002SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


WASTE DISPOSAL SYSTEM

LAVATORY QUANTITIES AND LOCATION - 3 GALLON PRECHARGE

NOTE: Density used is 8.34 LB/U.S. GAL. (0.999 KG/L).Lavatory location is shown in the following diagram.

FLUID CATEGORYVOLUME WEIGHT

U.S. GAL. L LB KG

Lav. Precharge Fluid 3.0 11.4 25.0 11.3

LAVATORY LOCATION

LAVATORY DESIGNATION B.A. IN.

A 207.5

JUL 19/2010

1-34-002SF RB (ALL)


PAGE 1 OF 2IAI 365-08-00-99626-GBA1


INTERIOR ARRANGEMENT - MAIN DECK

FLIGHT DECK

The flight crew balance arms are defined as 7 IN. in front of the Seat Reference Point (SRP). The SRP is definedas the intersection of the seat bottom and the seat back. The crew locations represent the crew seated at takeoffpositions.

FLIGHT CREW (TWO OBSERVERS)

LOCATION B.A.IN.

Captain 150

First Officer 150

First Observer 185

Second Observer 178

JUL 19/2010

1-45-001SF RB (ALL)


PAGE 2 OF 2IAI 365-08-00-99626-GBA1


INTERIOR ARRANGEMENT - MAIN DECK (Cont)

Galleys

The galley weights listed in the following table represents the maximum allowable galley loading that can besustained by the basic monocoque structure for the galley footprints shown in the Main Deck SupernumerariesArea.

NOTE: Galleys installed on the aircraft may be further limited by the carrier and contents weight as shown on the galley capacity placards.

NOTE: For main deck cargo arrangement refer to CHAP-SEC 1-64-001.

CREW (TWO SUPERNUMERARIES)

LOCATION B.A.IN.

SUPERNUMERARY SEAT 237

SUPERNUMERARY SEAT 237

MAXIMUM ALLOWABLE GALLEY WEIGHT [a]

LOCATION LB KG

Galley No. 1 800 362

[a] These galley weights are based on an average passengerweight of 170 LB (77.1 KG)/Passenger.

JUL 19/2010

1-45-001SF RB (ALL)


PAGE 1 OF 2IAI 365-08-00-99626-GBA1


COMPARTMENT, LINEAR AND AREA LOAD LIMITS

The main deck and lower deck compartment loads listed below are the maximum loads that can be sustained bythe basic monocoque structure. These values are consistent with the airplane configuration described in thismanual.

COMPARTMENT AND FLOOR LIMITS

The four basic structural limitations that must be observed when loading payload are compartment, linear, areaand combined load limits. The maximum compartment, linear, area, and combined loads for the 737-300F areshown below.

NOTE: (1) Refer to Note (2) on page 2.(2) Compartment limitations must be observed.

MAXIMUM ALLOWABLE WEIGHT (1)

COMPARTMENT (2)TOTAL WEIGHT LINEAR LOADING AREA LOADING

LB KG LB/IN KG/IN LB/SQ FT KG/SQ FT

Main Deck Cargo 51170 23210

B.A. 290 to B.A 559.45 16800 7620 63.0 28.6 75 34.0

B.A. 559.45 to B.A 648.45 9167 4158 103.0 46.7 120 54.4

B.A. 648.45 to B.A 737.45 7387 3351 83.0 37.6 95 43.1

B.A. 737.45 to B.A 926 10747 4875 57.0 25.9 65 29.5

B.A. 926 to B.A 1015 4762 2160 53.5 24.3 50 22.7

B.A. 1015 to B.A 1116 1862 845 33.0 15.0 50 22.7

Fwd Cargo Hold 5002 2269

150 68B.A. 300 to B.A 358 1682 763 29 13.1

B.A. 358 to B.A 415 855 388 15.0 6.8

B.A. 415 to B.A 500 2465 1118 29.0 13.1

Aft Cargo Hold 7648 3469

150 68B.A. 731 to B.A 892 5152 2337 32.0 14.5

B.A. 892 to B.A 949 912 414 16.0 7.2

B.A. 949 to B.A 1048 1584 718 16.0 7.2

JUL 19/2010

1-60-002SF RB (ALL)


PAGE 2 OF 2IAI 365-08-00-99626-GBA1


COMPARTMENT, LINEAR AND AREA LOAD LIMITS (CONT)

COMPARTMENT AND FLOOR LIMITS (CONT)

When a unit load device overlaps two linear load zones, the lower of the two linear loads is used for the length ofthe entire unit load device to determine the allowable unit load device load. an exception is made when a unit loaddevice has less than 11.0 inches in the lower linear load zone in which case the higher linear load may be used forthe length of the unit load device.

Maximum Combined (Monocoque) Linear Load Limits

NOTE: (1) The load limits above include the weight of cargo and the Unit Load Devices.

(2) Each section may be loaded up to the allowed linear load limit, but the max load should not exceed the max combined linear load.

BALANCE ARMINCH MAIN DECK LOWER DECK MAXIMUM COMBINED

LINEAR LOAD

FROM TO LB/IN KG/IN LB/IN KG/IN LB/IN KG/IN

290 300 63 28.6 0 0 63 28.6

300 358 63 28.6 29 13.1 72 32.7

358 415 63 28.6 15 6.8 63 28.6

415 500 63 28.6 29 13.1 72 32.7

500 559.45 63 28.6 0 0 63 28.6

559.45 648.45 103 46.7 0 0 103 46.7

648.45 731 83 37.6 0 0 83 37.6

731 737.45 83 37.6 32 14.5 83 37.6

737.45 892 57 25.9 32 14.5 75 34.0

892 926 57 25.9 16 7.2 59 26.8

926 1015 53.5 24.3 16 7.2 59 26.8

1015 1048 33 15.0 16 7.2 33 15.0

1048 1116 33 15.0 0 0 33 15.0

JUL 19/2010

1-60-002SF RB (ALL)


PAGE 1 OF 2IAI 365-08-00-99626-GBA1


FORWARD AND AFT BODY CUMULATIVE LOAD LIMITS

FOREBODY CUMULATIVE LOAD LIMITS

The cumulative total load profile is computed forward to aft in the forebody and must not exceed load distributionlimitations shown in the table below:

NOTE: (1) IF ZFW IS LESS THAN 91,000 LB (41,277 KG) CUMULATIVE LOAD LIMIT AT EACH STATION OF THE FOREBODY FOR ALL ULD’S TYPE MUST BE REDUCED BY 600 LB (272 KG).

(2) THE CUMULATIVE LOAD AT THE SPECIFIED BALANCE ARM CONSISTS OF THE WEIGHT OF THE CARGO ON THE MAIN DECK PLUS THE CARGO IN THE HOLD BELOW.

(3) THE ULD LOAD LIMITS ARE DEFINED ON PAGE 1-65-001, PAGE 1.THE LOWER HOLD CARGO LIMITS ARE DEFINED ON PAGE 1-60-002.ULD POSITION 10 MAY BE A TYPE K, OR IATA OR LD-4.

(4) FOR INTERMEDIATE LOCATIONS USE LINEAR INTERPOLATION.

A TYPE ULD B TYPE ULD M TYPE ULD

ARM BA(IN)

CUMULATIVELOADINGLIMIT LB.

ARM BA(IN)


ARM BA(IN)


290.00 0 290.00 0 290.00 0

380.95 7379 380.95 7379 388.95 7922

469.95 13073 469.95 13073 485.95 14079

540.00 17480 540.00 17480 540.00 17480

558.95 18712 558.95 18525 582.95 19941


ARM BA(IN)

CUMULATIVELOADINGLIMIT KG.

ARM BA(IN)


ARM BA(IN)


290.00 0 290.00 0 290.00 0

380.95 3347 380.95 3347 388.95 3593

469.95 5930 469.95 5930 485.95 6386

540.00 7929 540.00 7929 540.00 7929

558.95 8488 558.95 8403 582.95 9044

JUL 19/2010

1-61-001SF RB (ALL)


PAGE 2 OF 2IAI 365-08-00-99626-GBA1


FORWARD AND AFTBODY CUMULATIVE LOAD LIMITS (Continued)

AFTBODY CUMULATIVE LOAD LIMITS

The cumulative total load profile is computed aft to forward in the aftbody and must not exceed load distributionlimitations shown in the table below:

NOTE: (1) THE CUMULATIVE LOAD AT THE SPECIFIED BALANCE ARM CONSISTS OF THE WEIGHT OF THE CARGO ON THE MAIN DECK PLUS THE CARGO IN THE HOLD BELOW.

(2) THE ULD LOAD LIMITS ARE DEFINED ON PAGE 1-65-001, PAGE 1.THE LOWER HOLD CARGO LIMITS ARE DEFINED ON PAGE 1-60-002.ULD POSITION 10 MAY BE A TYPE K, OR IATA OR LD-4.

(3) FOR INTERMEDIATE LOCATIONS USE LINEAR INTERPOLATION.


ARM BA(IN)


ARM BA(IN)


ARM BA(IN)


1116.00 0 1116.00 0 1116.00 0

1004.95 4953 1004.95 4953 1004.95 4953

915.95 10411 915.95 10411 874.95 13199

826.95 16549 826.95 16549 777.95 20430

737.95 22529 737.95 22529 680.95 23298

664.00 23444 664.00 23444 664.00 23444

648.95 24676 648.95 24506 583.95 30914


ARM BA(IN)


ARM BA(IN)


ARM BA(IN)


1116.00 0 1116.00 0 1116.00 0

1004.95 2247 1004.95 2247 1004.95 2247

915.95 4722 915.95 4722 874.95 5987

826.95 7507 826.95 7507 777.95 9267

737.95 10219 737.95 10219 680.95 10568

664.00 10634 664.00 10634 664.00 10634

648.95 11193 648.95 11116 583.95 14022

JUL 19/2010

1-61-001SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


CARGO COMPARTMENTS

GENERAL LOCATION AND ARRANGEMENT

The following airplane profile illustrates cargo compartment locations.

The following table provides cargo compartment locations, usable volumes and the corresponding volumetriccentroid arms.

CARGO COMPARTMENTLOCATION - B.A USABLE VOLUME

CU FTB.AINFROM TO

Main Deck 290 1116 4900 677

Forward hold 300 500 425 400.6

Aft hold 731 1048 643 864.2

Total 5968 677

JUL 19/2010

1-62-002SF RB (ALL)


PAGE 1 OF 6IAI 365-08-00-99626-GBA1


FORWARD CARGO COMPARTMENTS

FORWARD CARGO COMPARTMENT VOLUMES

The following figure shows forward cargo hold compartment boundaries.

Volumes and centroids for the above figure are provided in the following table.

VOLUMESCOMPARTMENTS

1A 1B 2

Forward Compartment VolumesCU FT 152 65 208

Total Forward Hold CU FT 425

Volumetric Centroids 329.0 386.2 457.4

B.A. - IN. 400.6

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 2 OF 6IAI 365-08-00-99626-GBA1


FORWARD CARGO COMPARTMENTS (CONT)

FORWARD CARGO COMPARTMENT CROSS SECTIONS

The figure below illustrates the general layout of the forward cargo compartments. The numbered labels andshaded panels correspond to the cross-sections provided on the next page.

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 3 OF 6IAI 365-08-00-99626-GBA1



The following cross-sections for compartments 1 and 2 can be used to determine ceiling clearances at variousforward cargo compartment balance arms. The relative location of the cross-sectional cut can be determined bycorrelating the cross-section number to the general layout on the previous page.

CROSS SECTIONNO.

B.A.IN

1 300.0

2 358.0

3 415.0

4 482.0

5 498.0

6 500.0

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 4 OF 6IAI 365-08-00-99626-GBA1



CARGO DOOR DIMENSIONS AND ALLOWABLE PACKAGE SIZES

This section provides dimensions of the maximum package sizes which will pass through the forward cargo dooropening. Individual tables are presented for two types of packages; “Heavy Packages Lift Assisted” and “LightPackages Hand Maneuvered”.

“Heavy Packages Lift Assisted” refers to packages which require the use of a fork lift or other loading device tomaneuver them through the door. The maximum length is restricted by the inward curve of the lower cargosidewall liner opposite the door. The table assumes the packages cannot be elevated to clear this interference.

“Light Packages Hand Maneuvered” refers to packages which may be elevated to clear the inward curve of thecargo sidewall liner opposite the door.

Package sizes are approximate. Tilting, twisting, bending and/or rotating packages through door openings willallow additional lengths in many cases, but should be determined for each situation. A trial loading isrecommended for packages with dimensions close to maximum dimensions indicated in the tables.

The height dimensions do not include allowances for items increasing package height such as fork lift tynethicknesses, pallet depths, skid tub heights, etc. Any such devices must be accounted for in the total height.

Tie-downs are required for any bulk cargo with a shape and/or density that could cause it to become a hazard,damage airplane structure, or cause a large change in airplane C.G. as a result of the cargo shifting underoperational loads (e.g. dense or piercing items that could become projectiles). Refer to CHP-SEC 1-68-00x fortie-down information.

Package Size Illustration

The following illustration shows package dimensioning used in the allowable package size tables.

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 5 OF 6IAI 365-08-00-99626-GBA1



Door Dimensions

The following figure provides the forward cargo door clearance dimensions.

Allowable Package Sizes

The following table is applicable for packages loaded aft from the forward cargo door (B.A. 386 IN.)

HEAVY PACKAGES LIFT ASSISTED [A]

HEIGHT IN.

WIDTH IN.

5 10 15 20 25 30 35 40 45

LENGTH IN.

5 143 137 113 96 84 74 64 56 50

10 143 122 106 94 84 74 64 56 50

12 139 119 105 94 84 74 64 56 50

14 135 117 105 94 84 74 64 56 50

16 132 116 104 94 84 74 64 56 50

18 130 115 104 94 84 74 64 56 50

20 128 115 104 94 84 74 64 56 50

22 127 115 104 94 84 74 64 56 50

24 126 114 104 94 84 74 64 56 50

26 126 114 104 94 84 74 64 56 50

28 125 114 104 94 84 74 64 56 50

30 125 114 104 94 84 74 64 56 50

32 125 114 104 94 84 74 64 56 50

34 125 114 104 94 84 74 64 56 50

NOTE: [a] Package length is limited to a maximum of 85 inches when transverse cargo nets are installed.

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 6 OF 6IAI 365-08-00-99626-GBA1



The following table is applicable for packages loaded aft from the forward cargo door (B.A. 386 IN.).

LIGHT PACKAGES HAND MANEUVERED [a]

HEIGHT IN.

WIDTH IN.

5 10 15 20 25 30 35 40 45

LENGTH IN.

5 175 143 121 106 95 84 74 65 58

10 155 132 116 105 95 84 74 65 58

12 150 130 116 105 95 84 74 65 58

14 147 129 115 105 95 84 74 65 58

16 144 127 115 105 95 84 74 65 58

18 142 126 115 105 95 84 74 65 58

20 140 126 115 105 95 84 74 65 58

22 139 125 115 105 95 84 74 65 58

24 138 125 115 105 95 84 74 65 58

26 137 125 115 105 95 84 74 65 58

28 137 125 115 105 95 84 74 65 58

30 136 125 115 105 95 84 74 65 58

32 136 125 115 105 95 84 74 65 58

34 136 125 115 105 95 84 74 65 58

NOTE: [a] Package length is limited to a maximum of 85 inches when transverse cargo nets are installed.

JUL 19/2010

1-62-042SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


MAIN DECK CARGO COMPARTMENT

MAIN DECK CARGO COMPARTMENT CROSS SECTIONS

The following drawing shows the cross sectional area with the maximum cargo dimensions in the main deckcompartment.

NOTE: For the maximum allowable contour of a cargo see CHAP-SEC 1-63-001, Page 2.

JUL 19/2010

1-62-101SF RB (ALL)


PAGE 1 OF 2IAI 365-08-00-99626-GBA1


UNIT LOAD DEVICE - MAIN DECK

A Unit Load Device (ULD) is a device for grouping and retaining cargo for transit. The ULD can refer to a palletand net, a pallet and net over and igloo, or a container. This Chapter-Section-Subject provides center of gravitylimits, dimensions for Side Code A, B, M, K and IATA LD-4 ULDs certified in conformance with TSO C90C.

NOTE: MIXED ULD’S CONFIGURATIONS ARE PERMITTED ON THE CONDITION THAT THE POSITION OF ULD’S HAS NOT CHANGED FROM THE APPROVED CONFIGURATIONS’ STATIONS AS DEFINED ON CHP-SEC 1-64-001.

For each ULD configuration the ULD position is fixed (See CHAP-SEC 1-64-001)

The allowable center of gravity range is based on the geometric center of the Unit Load Device base dimension.the vertical center of gravity is measured from the base of the container. Good judgement must be used indistributing the load within the ULD.

Use of ULDs that are not specified in this manual requires tie-downs for the ULD gross weight and the specifiedload factors.

[1] Container meeting the dimensions of IATA LD-4, certified for the loading capability and load factorsdefined in CHAP-SEC 1-65-001 Page 1.

ULD DESIGNATION ALLOWABLE CENTER OF GRAVITY RANGE (IN)

SIZE CODE NAS 3610 TYPE ULD SIZE VERTICAL LATERAL LONGITUDINAL

A

-2A1

88 X 125 36 ±12.5 ±8.8

-2A2

-2A3

-2A4

-2A5

-2A6

B

-1B5

88 X 108 36 ±10.8 ±8.8

-2B1

-2B2

-2B3

-2B4

-2B5

-2B6

M

-2M1

96 X 125 36 ±12.5 ±9.6-2M2

-2M3

K

-2K1

60.4 X 61.5 36 ±6.04 ±6.15-2K2

-2K3

IATA LD-3

[1] IATA LD-4 NOT APPLICABLE 60.4 X 96 36 ±6.04 ±9.6

JUL 19/2010

1-63-001SF RB (ALL)


PAGE 2 OF 2IAI 365-08-00-99626-GBA1


UNIT LOAD DEVICE - MAIN DECK (CONT)

UNIT LOAD DEVICES

The maximum allowable contour is shown below.

Rear View

JUL 19/2010

1-63-001SF RB (ALL)


PAGE 1 OF 3IAI 365-08-00-99626-GBA1


MAIN DECK UNIT LOAD DEVICE LOCATIONS

SIZE CODE A (88 X 125) AND POSITION 10

The illustration below shows the positions in the main deck compartment for size code A and position 10 unit loaddevices using the delivery restraint hardware configuration.

Assuming a uniformly distributed load for the positions shown in the above illustration, the following tabletabulates the fwd and aft edge for each individual position in balance ARM (B.A.).

NOTE: 1. Empty ULD’s position are permitted.

2. When carrying rigid cargo on the main deck, at least one cargo position forward to rigid cargo shall contain frangible cargo.

MAIN DECK COMPARTMENT UNIT LOAD DEVICE LOCATION

ULD POSITIONFWD EDGE AFT EDGE

B.A. (IN)

1A 292.95 380.95

2A 381.95 469.95

3A 470.95 558.95

4A 559.95 647.95

5A 648.95 736.95

6A 737.95 825.95

7A 826.95 914.95

8A 915.95 1003.95

10K 1004.95 1066.45

OR 10-LD-4 1004.95 1100.95

JUL 19/2010

1-64-001SF RB (ALL)


PAGE 2 OF 3IAI 365-08-00-99626-GBA1


MAIN DECK UNIT LOAD DEVICE LOCATIONS (CONT)

SIZE CODE B (88 X 108) AND POSITION 10

The illustration below shows the positions in the main deck compartment for size code B and position 10 unit loaddevices using the delivery restraint hardware configuration.






B.A. (IN)

1B 292.95 380.95

2B 381.95 469.95

3B 470.95 558.95

4B 559.95 647.95

5B 648.95 736.95

6B 737.95 825.95

7B 826.95 914.95

8B 915.95 1003.95

10K 1004.95 1066.45

OR 10-LD-4 1004.95 1100.95

JUL 19/2010

1-64-001SF RB (ALL)


PAGE 3 OF 3IAI 365-08-00-99626-GBA1


MAIN DECK UNIT LOAD DEVICE LOCATIONS (CONT)

SIZE CODE M (96 X 125) AND POSITION 10

The illustration below shows the positions in the main deck compartment for size code M and position 10 unit loaddevices using the delivery restraint hardware configuration.






B.A. (IN)

1M 292.95 388.95

2M 389.95 485.95

3M 486.95 582.95

4M 583.95 679.95

5M 680.95 776.95

6M 777.95 873.95

7M 874.95 970.95

10K 1004.95 1066.45

OR 10-LD-4 1004.95 1100.95

JUL 19/2010

1-64-001SF RB (ALL)


PAGE 1 OF 7IAI 365-08-00-99626-GBA1


MAIN DECK UNIT LOAD DEVICE LOAD LIMITS

SIZE CODE A, B, M, K AND LD-4 LOAD LIMITS

The load device contents must be loaded in such a manner that it is sufficiently secured to prevent it frombecoming a hazard or damaging the airplane structure due to shifting under operational loads.

[1] Container must be certified for the defined loading.

CAUTION: The maximum allowable payload on the main deck is: MZFW-OEW (per particular aircraft) but not to exceed 45,000 Lb and Limitations in CHP-SEC 1-60-003.The maximum load includes the tare weight of the unit load device.

NOTE: Load factors are ultimate.

ULD DESIGNATION POSITION WEIGHT

SIDE CODE NAS 3610 TYPE ULD SIZE UNIT 1 2 3 4 5 6 7 8 10

A

-2A1

88 X 125

-2A2-2A3 LB 5600 5600 5600 9000 7250 5000 5000 4700 ------2A4 KG 2540 2540 2540 4082 3288 2268 2268 2132 ------2A5-2A6

B

-1B5

88 X 108

-2B1-2B2 LB 4750 4750 4750 7500 6250 4300 4300 4050 ------2B3 KG 2155 2155 2155 3402 2835 1950 1950 1837 ------2B4-2B5-2B6

M-2M1

96 X 125-2M2 LB 5600 5600 5600 9000 7250 5000 5000 ----- ------2M3 KG 2540 2540 2540 4082 3289 2268 2268 ----- -----

K

-2K1

60.4 X 61.5-2K2-2K3 LB ----- ----- ----- ----- ----- ----- ----- ----- 2000IATA KG ----- ----- ----- ----- ----- ----- ----- ----- 907LD-3

IATA LD-4 [1] 60.4 X 96LB ----- ----- ----- ----- ----- ----- ----- ----- 2000

[1]KG ----- ----- ----- ----- ----- ----- ----- ----- 907

BODY ARM LOAD FACTOR

FROM TO UP / DOWN SIDE FWD AFT50 640 -2.6 / +5.6 +/-1.1 1.5 1.5640 1317 Linear Linear

-2.6 to -4.3 +1.1 to +2.7 1.5 1.5+5.6 to 7.3 -1.1 to -2.7

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 2 OF 7IAI 365-08-00-99626-GBA1



SIZE CODE A, B, M, K AND LD-4 LOAD LIMITS WITH MISSING/INOPERATIVE RESTRAINTS

Under the following conditions reduced or no loads are required with certain equipment missing/inoperable.

Restraint systems are defined as side restraint, forward/aft restraints and vertical restraints. Each restraintdirection is considered separately when missing/inoperative restraint equipment exists, (i.e. forward, aft, side left,side right and vertical loading).

Restrain symbols used in the schematic illustrations that follow are described below:

This symbol indicates restraint applied in two directions: vertical and side. The restraint hardware differs oninboard and outboard longitudinal edges:

• Outboard guide rail: side restraint is given by the guide rail; vertical restraint may be given by the manually operable side lock, or by the spring-loaded rotating vertical restraint

• Inboard longitudinal edge: both side and vertical restraint are given by the center guide restraint assembly.

•

This restraint symbol occurs along ULD leading and trailing edges. The hardware is manually retractableand end locks or pallet locks, which apply restraint in a vertical direction and a forward or at direction.

CAUTION: Care must be exercised during loading and unloading of unit load devices when equipment is missing/inoperable to prevent damage to airplane structure. It is advisable that malfunctioning equipment be repaired or replaced to prevent damage to operative equipment.

CAUTION: When a restraint is common to restrain more than one ULD, the missing restraint limit must be applied to all affected ULDs.

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 3 OF 7IAI 365-08-00-99626-GBA1



SIZE CODE A, B, M, K AND LD-4 LOAD LIMITS WITH MISSING/INOPERATIVE RESTRAINTS (Cont)

Allowable weight includes the weight of the ULD. Any load in excess of the allowables specified in thisChapter-Section must be restrained by additional tie-downs.

Missing/inoperative restraints cannot be adjacent to each other. Also two restraints adjacent to a common cornercan not be missing/inoperative.

The following equipment malfunctions do not constitute a load limit restriction:

• Jammed or missing sill and capstan rollers

• Jammed or missing balls in a ball mat

• Jammed or missing rollers in a roller tray

• Missing side guide rail

• Jammed or missing impact rollers at positions 1 or 8A.

A lock is considered to be fully effective at the corner of a ULD if the centerline of the lockhead lines up with thetangency point of the ULD corner radius.

NOTE: An empty ULD can be carried in any position provided at least one restraint is operable in each (forward, aft, left and right) direction. In addition, one vertical restraint on each edge (forward, aft, left and right) must be operable.

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 4 OF 7IAI 365-08-00-99626-GBA1




Size Code A Lateral (88 x 125 inches)

The following table is for one (1) missing or inoperative restraint per ULD only. This table shows the reducedmaximum weight of a particular ULD depending on the missing or inoperable end restraint and its location relativeto the ULD.

CAUTION: A position may not be loaded if more than one (1) of its restraints is missing or inoperative

For non-commonly restrained, adjacent ULDS, missing/Inoperative restraints shall not be side by side.

BASIC RESTRAINT CONFIGURATION

DIRECTION

POSITION

1A 2A - 6A8A 7A

NUMBER NUMBER NUMBER

Vertical 19 18 20

Side 4/5 4/4 5/5

Fwd 5 5 5

Aft 5 5 5

POSITION WEIGHTS (LB)

1 2 3 4 5 6 7 8

All Restraints MAX LOAD (LB) 5600 5600 5600 9000 7250 5000 5000 4700

One (1) Missing

FWD/AFT 4955 5600 5600 9000 7250 5000 5000 4700

RIGHT SIDE 5600 5600 5314 5899 5613 5000 5000 3810

LEFT SIDE 4001 5093 5314 5899 5613 5000 5000 3810

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 5 OF 7IAI 365-08-00-99626-GBA1




Size Code B Lateral (88 x 108 inches)



For non-commonly restrailed, adjacent ULDS, missing/Inoperative restraints shall not be side by side.


DIRECTION

POSITION

1B 2B - 6B8B 7B


Vertical 17 16 18

Side 4/5 4/4 5/5

Fwd 4 4 4

Aft 4 4 4


1 2 3 4 5 6 7 8

All Restraints MAX LOAD (LB) 4750 4750 4750 7500 6250 4300 4300 4050

One (1) Missing

FWD/AFT 3799 4750 4750 7273 6250 4300 4300 4050

RIGHT SIDE 4146 4107 4750 5785 5504 4300 4300 3737

LEFT SIDE 3623 4427 4750 5785 5504 4300 4300 3737

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 6 OF 7IAI 365-08-00-99626-GBA1




Size Code M Lateral (96 x 125 inches)



For non-commonly restrained, adjacent ULDS, missing/Inoperative restraints shall not be side by side.


DIRECTION

POSITION

1M 3M - 4M 2M5M - 7M


Vertical 19 18 20

Side 4/5 4/4 5/5

Fwd 5 5 5

Aft 5 5 5


1 2 3 4 5 6 7

All Restraints MAX LOAD (LB) 5600 5600 5600 9000 7250 5000 5000

One (1) Missing

FWD/AFT 4933 5600 5600 9000 7250 5000 5000

RIGHT SIDE 5600 5600 5600 5412 7250 5000 5000

LEFT SIDE 3524 5600 5600 5412 7250 5000 5000

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 7 OF 7IAI 365-08-00-99626-GBA1




Size Code K Longitudinal (60.4 x 64.5)

Size Code IATA LD-4 Longitudinal (60.4 x 96)



DIRECTION

POSITION

P10

NUMBER

Vertical 10

Side 2

Fwd 3

Aft 3


DIRECTION

POSITION

P10

NUMBER

Vertical 12

Side 3/3

Fwd 3

Aft 3


K (LD-3) LC-4 (LD-4)

All Restraints MAX LOAD (LB) 2000 2000

One (1) Missing

FWD/AFT 2000 2000

RIGHT SIDE N/A 764

LEFT SIDE N/A 764

JUL 19/2010

1-65-001SF RB (ALL)


PAGE 1 OF 1IAI 365-08-00-99626-GBA1


TIPPING LIMITATIONS

CRITERIA FOR PUTTING TAIL JACK IN PLACE

CAUTION: If at any time during aircraft loading the Nose Gear Load is less than 2000 lbs or C.G. of the aircraft is more than 44% MAC, tail must be in place to avoid tipping. In this case, check that load on tail jack is less than maximum allowable load as defined in Maintenance Manual or in Section 1-80-001 of Boeing Weight and Balance Control and Loading Manual Report D043A530-GBA1 and Highlights Revision No. 2.

JUL 19/2010

1-84-002SF RB (ALL)


Documents

Mantra: 365-08-00-99626-GBA1, Rev: A, RELEASED, 16-NOV-10 ... · 365-08-00-99626-gba1, for special freighter. all other chapters do not apply to the sf rb configurations. chapters