LIST OF EFFECTIVE PAGES - Login · 54−12−31 54−12−31 tailpipe skin and plating − structural identification 1 all general tailpipe skin and plating − allowable damage 101

54 − EffectivePages

1 * Apr 10/2011

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54 − Contents 1 Jun 10/20072 Jun 10/20073 Jun 10/20074 Jun 10/20075 Jun 10/20076 Jun 10/20077 May 10/20108 May 10/2010

54−00−00 1 Feb 18/20032 Feb 18/2003

54−00−00 101 Jun 22/2004102 Jun 22/2004103 Jun 22/2004104 Jun 22/2004105 Jun 22/2004106 Jun 22/2004

54−00−31 101 Dec 15/2004102 Dec 15/2004103 Dec 15/2004104 Dec 15/2004

54−10−00 1 Feb 18/20032 Feb 18/2003

54−10−00 101 Feb 18/2003102 Feb 18/2003103 Feb 18/2003104 Feb 18/2003105 Feb 18/2003106 Feb 18/2003107 Feb 18/2003

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54−10−27 101 Feb 18/2003

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54−10−31 101 Feb 18/2003102 Jun 22/2004103 Jun 22/2004104 Jun 22/2004

54−10−31 201 Feb 18/2003

54−11−00 1 Feb 18/2003

54−11−15 1 Feb 18/20032 Mar 10/20063 Mar 10/20064 Mar 10/20065 Mar 10/20066 Mar 10/20067 Mar 10/20068 Mar 10/20069 Mar 10/200610 Mar 10/200611 Feb 18/200312 Mar 10/200613 Mar 10/200614 Mar 10/2006

54−11−15 101 Jun 17/2003

54−11−15 201 Mar 10/2006

54−11−31 101 Jun 10/2007

54−11−31 201 Jul 10/2006

CSTRUCTURAL REPAIR MANUAL

NACELLES/PYLONSLIST OF EFFECTIVE PAGES

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Apr 10/2011

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PagesPage 4

Apr 10/2011

54−00−00 54−00−00

NACELLES/PYLONS − GENERAL 1 ALL

General

Structural Classification

Stations

NACELLES/PYLONS − ALLOWABLE DAMAGE 101 ALL

General

54−00−31 54−00−31

NACELLES/PYLONS SKIN AND PLATING −

ALLOWABLE DAMAGE

101 ALL

General

Allowable Damage

54−10−00 54−10−00

NACELLES INTERNAL STRUCTURE − GENERAL 1 ALL

General

Structural Identification

NACELLES INTERNAL STRUCTURE − ALLOWABLE

DAMAGE

101 ALL

General

54−10−27 54−10−27

NACELLE FITTINGS − GENERAL 1 ALL


NACELLE FITTINGS − ALLOWABLE DAMAGE 101 ALL

General


NACELLES/PYLONSTABLE OF CONTENTS

Subject

ChapterSectionSubject Page Effectivity

MasterEFFECTIVITY: ALL 54−Contents Page 1

Jun 10/2007

54−10−31 54−10−31

NACELLE − SKIN AND PLATING − GENERAL 1 ALL

General


NACELLE SKIN AND PLATING − ALLOWABLE

DAMAGE

101 ALL

General

Allowable Damage

NACELLE SKIN AND PLATING − REPAIRS 201 ALL

General

54−11−00 54−11−00

NOSE COWL − GENERAL 1 ALL

General

54−11−15 54−11−15

NOSE COWL FRAMES AND FORMERS −

STRUCTURAL IDENTIFICATION

1 ALL

General

NOSE COWL FRAMES AND FORMERS − ALLOWABLE

DAMAGE

101 ALL

General

NOSE COWL FRAMES AND FORMERS − REPAIRS 201 ALL

General

54−11−31 54−11−31

NOSE COWL SKIN AND PLATING − ALLOWABLE

DAMAGE

101 ALL

General

NOSE COWL SKIN AND PLATING − REPAIRS 201 ALL

General


Subject



Jun 10/2007

54−12−00 54−12−00

TAILPIPE − GENERAL 1 ALL

General

54−12−15 54−12−15

TAILPIPE FRAMES AND FORMERS − STRUCTURAL

IDENTIFICATION

1 ALL

General

TAILPIPE FRAMES AND FORMERS − ALLOWABLE

DAMAGE

101 ALL

General

TAILPIPE FRAMES AND FORMERS − REPAIRS 201 ALL

General

54−12−31 54−12−31

TAILPIPE SKIN AND PLATING − STRUCTURAL

IDENTIFICATION

1 ALL

General

TAILPIPE SKIN AND PLATING − ALLOWABLE DAMAGE 101 ALL

General

TAILPIPE SKIN AND PLATING − REPAIRS 201 ALL

General

54−13−15 54−13−15

THRUST REVERSER FRAMES AND FORMERS −

ALLOWABLE DAMAGE

101 ALL

General

THRUST REVERSER FRAMES AND FORMERS −

REPAIRS

201 ALL

General


Subject



Jun 10/2007

54−13−31 54−13−31

THRUST REVERSER SKINS AND PLATING −

ALLOWABLE DAMAGE

101 ALL

General

THRUST REVERSER SKINS AND PLATING − REPAIRS 201 ALL

General

54−14−00 54−14−00

ACCESS COWLS − STRUCTURAL IDENTIFICATION 1 ALL

General

ACCESS COWL − ALLOWABLE DAMAGE 101 ALL

General

ACCESS COWL − REPAIRS 201 ALL

General

54−16−15 54−16−15

CORE COWL FRAMES AND FORMERS − ALLOWABLE

DAMAGE

101 ALL

General

CORE COWL FRAMES AND FORMERS − REPAIRS 201 ALL

General

54−16−31 54−16−31

CORE COWL SKIN AND PLATING − ALLOWABLE

DAMAGE

101 ALL

General

CORE COWL SKIN AND PLATING − REPAIRS 201 ALL

General


Subject



Jun 10/2007

54−17−00 54−17−00

NACELLE/PYLON SERVICE STRUCTURE −


1 ALL

General

NACELLE/PYLON SERVICE STRUCTURE −

ALLOWABLE DAMAGE

101 ALL

General

NACELLE/PYLON SERVICE STRUCTURE − REPAIRS 201 ALL

General

54−18−00 54−18−00

EXHAUST NOZZLE − STUCTURAL IDENTIFICATION 1 ALL

General

EXHAUST NOZZLE − ALLOWABLE DAMAGE 101 ALL

General

EXHAUST NOZZLE − REPAIRS 201 ALL

General

54−50−00 54−50−00

PYLONS MAIN STRUCTURE − STRUCTURAL

IDENTIFICATION

1 ALL

General

PYLONS MAIN STRUCTURE − ALLOWABLE DAMAGE 101 ALL

General

Specific

54−51−14 54−51−14

PYLON BOX FRAMING STRUCTURE − STRUCTURAL

IDENTIFICATION

1 ALL

General

PYLON BOX FRAMING STRUCTURE − ALLOWABLE

DAMAGE

101 ALL


Subject



Jun 10/2007

General 101

Specific

PYLON BOX FRAMING STRUCTURE − REPAIRS 201 ALL

General

54−51−27 54−51−27

PYLON−BOX ATTACH/ATTACHED FITTINGS −

ALLOWABLE DAMAGE

101 ALL

General

PYLON−BOX ATTACH/ATTACHED FITTINGS −

REPAIRS

201 ALL

General

54−51−31 54−51−31

PYLON BOX SKIN AND PLATING − STRUCTURAL

IDENTIFICATION

1 ALL

General

PYLON BOX SKIN AND PLATING − ALLOWABLE

DAMAGE

101 ALL

General

Specific

PYLON BOX SKIN AND PLATING − REPAIRS 201 ALL

General

54−60−00 54−60−00

PYLON SECONDARY STRUCTURE − STRUCTURAL

IDENTIFICATION

1 ALL

General

PYLON SECONDARY STRUCTURE − ALLOWABLE

DAMAGE

101 ALL

General

Specific


Subject



Jun 10/2007

54−61−14 54−61−14

FORWARD STRUCTURE FRAMING − STRUCTURAL

IDENTIFICATION

1 ALL

General

FORWARD STRUCTURE FRAMING − ALLOWABLE

DAMAGE

101 ALL

General

Specific

FORWARD STRUCTURE FRAMING − REPAIRS 201 ALL

General

54−61−31 54−61−31

FORWARD STRUCTURE SKIN AND PLATING −


1 ALL

General


ALLOWABLE DAMAGE

101 ALL

General

Specific


REPAIRS

201 ALL

General

54−62−14 54−62−14

AFT STRUCTURE FRAMING − STRUCTURAL

IDENTIFICATION

1 ALL

General

PYLON AFT STRUCTURE FRAMING − ALLOWABLE

DAMAGE

101 ALL

General

Specific


Subject



May 10/2010

AFT STRUCTURE FRAMING − REPAIRS 201 ALL

General

54−62−31 54−62−31

AFT STRUCTURE SKIN AND PLATING − STRUCTURAL

IDENTIFICATION

1 ALL

General

AFT STRUCTURE SKIN AND PLATING − ALLOWABLE

DAMAGE

101 ALL

General

General Limitations

Specific Limitations

AFT STRUCTURE SKIN AND PLATING − REPAIRS 201 ALL

General


Subject



May 10/2010

NACELLES/PYLONS − GENERAL

1. General

Chapter 54 contains structural identification data, allowable damage limits and repairs for the nacellesand pylons.

Section 54−00 contains general data that is applicable to the nacelle and the pylon.

Section 54−10 contains data that is applicable only to the nacelle (power plant) structures.

Section 54−50 contains data that is applicable only to the pylon main structures.

Section 54−60 contains data that is applicable only to the pylon secondary structures.

2. Structural Classification

Refer to SRM 51−00−00.

3. Stations

Refer to Figure 1.


MasterEFFECTIVITY: ALL 54−00−00 Page 1

Feb 18/2003

FWL120.632FBL72.606 AT

YN97.750ZN112.780 AT

00.

0L

BP

00.

00

1N

Z3

84.

32

1B

F

FS736.00

FS718.00

FS711.40

FS700.00

FS682.00

FS672.20

FS663.40

FS654.50

FS640.00

FS625.30

FS621.00

FS614.00

FS605.00

FS59600

FS589.00

XN247.90

XN243.00

XN237.93

XN232.87

XN227.80

XN221.96

XN214.00

XN208.39XN205.70

XN200.00XN196.18

XN190.59

XN185.00

XN170.00

XN164.73

XN156.62

XN151.40

XN135.845

XN121.60

XN105.00

XN100.72

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, 12/

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Nacelle/Pylon StationsFigure 1


Feb 18/2003

NACELLES/PYLONS − ALLOWABLE DAMAGE

1. General

CAUTION: ALWAYS REFER TO PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE THE INCORRECT DATA.

A. Use the general allowable damage limits given in this subject when specific damage limits are notsupplied in the subject for a given structural element.

B. The allowable damage limits to the extruded, machined parts (other than fittings) and formedsheet metal parts of the Nacelles/Pylons are given in Figure 101 and Figure 102. The allowabledamage limits of the nacelle skins and the pylons skins are given in their related ATA subject.The allowable damage limits of fittings are given in the related ATA subject.



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RUN−OUT20XMIN

THE BOTTOM OF THE REMOVEDDAMAGE MUST HAVE A RADIUS

OF 1.0 in. (25.4 mm) MINIMUM

T X = DEPTH OF MATERIALREMOVAL = 10% THICKNESS

(T) MAXIMUM

TWO WEBELEMENTSAT A HOLE

FLANGE

CORNER

WEB

FREEFLANGE

BULB(EXTRUSIONS

ONLY)

AREA OF MATERIALREMOVAL MUST NOTBE MORE THAN 10%OF ELEMENT WIDTH

THE DISTANCE OF THEDAMAGE FROM A HOLE,FASTENERS OR EDGE

MUST NOT BE LESSTHAN 20X

REMOVALLIMIT

DAMAGEAREA



T

T1

2

T3

REMOVEDDAMAGE

Remove damage as shown for small edgedamage, detail A. T must be larger than Tafter damage removal.

2 For added data, refer to Sheet 3.

NOTES

3 2

MATERIAL

SKIN ELEMENT

15T 15T

T = SKIN THICKNESS

EXTRUDED SECTION

EXTRUDED AND MACHINEDSECTION ELEMENTS−EXAMPLE

SMALLEDGE DAMAGE

SURFACE DAMAGE

CORNER DAMAGE

X

TOTAL CROSS−SECTION(INCLUDES SKIN)


Extruded and Machined Parts (Other than Fittings) – Allowable Damage − GeneralFigure 101 (Sheet 1)


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RADIUS OFREMOVED DAMAGEIS FOUND BY THE

DAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM

FASTENER EDGEDISTANCE LIMIT

(EXAMPLE)

DEPTH X − MUSTNOT BE MORE THAN

FASTENER DIAMETEROR 10% OF ELEMENT

WIDTH

MATERIAL REMOVEDTO REMOVE DAMAGE

DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES

DO NOT HAVE OVERLAPS



WIDTH


HAVE OVERLAPS

EDGE DAMAGE

FASTENEREDGE DISTANCELIMIT (EXAMPLE)

LIMIT OF DAMAGEREMOVAL. RADIUS OFREMOVED DAMAGE IS

FOUND BY THEDAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM

For added data, refer to sheet 3.

NOTE




Jun 22/2004

DAMAGE REMARKS

Cracks

Cracks are not permitted in webs.

Cracks are permitted in flange edges if they are in material removal limits shown foredge damage.

Scratches,nicks, gougesand corrosion

Removed damage must not decrease the thickness (or the cross−section area) of agiven element by more than 10% (an extruded bulb is an element).

Dents Dents are not permitted.

Holes andpunctures

Holes and punctures are not permitted in attachment flanges.

You can plug holes thru 0.25 inch (6.35 mm) in diameter (refer to the Notes that follow)if they are not nearer than 4 X the repaired hole diameter to:

− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10%.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lite pins),contact Bombardier Aerospace Regional Aircraft Customer Support, (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer tothe data given for formed parts in Figure 102, (Sheet 1).

NOTE: Attached skins for a distance of 15 X the local skin thickness from theattachment row of fasteners are an element of the cross−section (refer to Sheet 1 of thisFigure).

If the part was shot peened when it was made, it must be shot peened again (refer toSRM 51−24−11) after damage removal.

NOTE: Approved repair or replacement of a member is necessary when more than 30% of its length isdamaged.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00. Use anapproved repair (refer to SRM 51−13−00) to repair damage that does not agree with the allowabledamage limits.

NOTE: Remove damage as shown in Sheets 1 and 2.


Extruded and Machined Parts (Other than Fittings) − Allowable Damage − GeneralFigure 101 (Sheet 3)


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ATTACHMENTFLANGE

LIP

WEB

FORMED SECTIONELEMENTS EXAMPLE

FLANGE

15T 15T

T = SKIN THICKNESS

SKIN ELEMENT

FORMEDSECTION

FREEFLANGE

Repaired areas must nothave an overlap.

2 For added data,

NOTES

refer to Sheet 3.

DENTS MUST BESMOOTH AND NOT

HAVE SHARP CREASES,GOUGES, OR CRACKS.

FOR DEPTH LIMITCALCULATION, REFER

TO SHEET 2

D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

AREA REPAIREDBEFORE

THE BOTTOM OF THEREMOVED DAMAGE MUSTHAVE A RADIUS OF 1.0 in.

(25.4 mm) MINIMUM

X = DEPTH OFDAMAGE REMOVAL

= 10% FLANGEWIDTH MAXIMUM

20XMINIMUMRUN−OUT


DENTS

REMOVAL OF NICK OR CRACKDAMAGE ON AN EDGE


Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 1)


Jun 22/2004

DAMAGE REMARKS

Cracks

Edge cracks are permitted only in free flanges. Cracks are not permitted in lippedflanges or in webs.

Remove damage as shown in (Sheet 1 of this figure).


Removed damage must not decrease the thickness or the cross−section area of a givenelement by more than 10%.

Dents

Dents are permitted in webs only.

Dents must be smooth and not have sharp creases, gouges, cracks, or signs ofdamaged or loose rivets.

W/D must not be less than 20 where:

W = Width of the minor axis of the dent

D = Depth of the dent from the initial contour.

Holes andpunctures



− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10%.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lite pins),contact Bombardier Aerospace Regional Aircraft Customer Support, (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer toSheet 1 of this Figure).

NOTE: Attached skins for a distance of 15 X the local skin thickness from theattachment row of fasteners are an element of the cross−section (refer to Sheet 1 ofthis Figure).

NOTE: Approved repair or replacement of a member is necessary when more than 30% of its length isdamaged.



Formed Parts − Allowable Damage − GeneralFigure 102 (Sheet 2)


Jun 22/2004

NACELLES/PYLONS SKIN AND PLATING − ALLOWABLE DAMAGE

1. General


CAUTION: MAKE SURE THAT THE REMOVED DAMAGE, INCLUDING ANY PREVIOUSDAMAGE REMOVAL, IS WITHIN ALLOWABLE LIMITS AT ANY SPECIFICLOCATION. RECORD DAMAGE REMOVAL LOCATION.

A. Use the allowable damage limits given in this subject when specific allowable damage limits arenot supplied in the subject for a given structural element.

B. The nacelle skin panels are of two general types; sheet metal and honeycomb compositestructures. The composite panels are of two types, as follows:

(1) Aluminum alloy facing skins on aluminum alloy honeycomb cores (Type A panels)

(2) Kevlar/epoxy and graphite/epoxy laminated facing skins on nylon (Nomex) honeycombcores (Type B panels). To provide lightning protection, these panels have fiberglass facingsheets, that are aluminum−coated, bonded to the external facing skin surfaces.

2. Allowable Damage

A. Composite Honeycomb Panels

(1) Scratched paint or primer is the only allowable damage permitted for honeycomb compositepanels. If the damage has not gone through the paint or primer, there is no limit on theamount of scratch damage. You must use approved typical, generic or specific repairs for allother damage (refer to SRM 51−13−00 and the applicable 201−999 page block).

B. Sheet Metal Panels

CAUTION: DO NOT FILL DENTS IN THE ENGINE AIR INTAKE AREA WITH SURFACEFILLER. IF THIS IS DONE, IT CAN CAUSE DAMAGE TO THE ENGINE.

(1) For general allowable damage limits for sheet metal skin and plating, refer to Figure 101.



Dec 15/2004

DAMAGE REMARKS

CracksEdge cracks that are within the material removal limits must be removed as shown inFigure 102. For cracks that are not within the specified limits, contact BombardierAerospace Regional Aircraft Customer Support.

Scratches, nicks,gouges andcorrosion

Blending or edge trimming is permitted as per Figure 102.

Removed corrosion damage must not be more than 10% of the local skin thickness.For the removal of corrosion damage, refer to SRM 51−21−06.

Dents must be smooth and not have sharp creases, gouges, cracks or signs ofdamaged or loose rivets.

Dents W1/D must not be less than 25 where:

− W1 = width of the minor axis of the dent

− D = depth of the dent from the initial contour

− X must be greater than W2 or 1 inch (25.40 mm)

− W2 = width of the major axis of the dent.

Holes andpunctures

Through holes 0.25 in. (6.35 mm) in diameter can be plugged with AD type rivets (referto SRM 51−12−00) if they are not closer than 4 times the repaired hole diameter to:

− Adjacent holes

− Skin edge

− Chem milled pocket radii

− Other damage.

GeneralNo Damage is allowed in the 2D area around the fasteners.


NOTE: Approved repair or replacement is necessary when more than 30% of the area of a panel isdamaged.



Wing Skin and Plating − Allowable Damage − GeneralFigure 101 (Sheet 1)


Dec 15/2004

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RADIUS OF REMOVEDDAMAGE IS FOUND BY


(EXAMPLE)

X DEPTH = 0.15 in.(3.81 mm) MAXIMUM

MATERIAL TRIMMEDTO REMOVE DAMAGE




HAVE OVERLAPS

EDGE DAMAGE


LIMIT OF DAMAGE REMOVAL. RADIUS OF REMOVED DAMAGE ISFOUND BY THE DAMAGE DEPTH (X).

R = 1.0 in. (25.4 mm) MINIMUM

1. For added data, refer to Table in this Figure.

NOTE

THE DAMAGE DEPTH (X)


R = 1.0 in. (25.4 mm) MINIMUM


Sheet Metal Skin and Plating − Allowable DamageFigure 102 (Sheet 1)


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D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

DENTS

0.100 in. (2.54 mm)MAXIMUM

RUN−OUT20X

MINIMUM

T = THICKNESS X = DEPTH OF MATERIALREMOVAL = 10% OF

THICKNESS (T) MAXIMUM

For added data, refer to Table in this Figure.

NOTES

A A

A

A

MAJOR AXIS OF THEREMOVED MATERIAL

MATERIALREMOVAL

LIMITDAMAGE

AREA



OF THE MATERIAL

The distance of the damage from a hole,fastener, edge or chem−mill radius must

2

1.

2

not be less than 20X.

No rework permitted in an area within

No rework permitted

2D

D

DAMAGEREMOVAL LIMIT 3

3a 2D radius around fasteners.


Sheet Metal Skin and Plating − Allowable DamageFigure 102 (Sheet 2)


Dec 15/2004

NACELLES INTERNAL STRUCTURE − GENERAL

1. General

This section contains data that is applicable to the power plant components, refer to Figure 1 fornacelle breakdown.

2. Structural Identification

A. Nose Cowl

The nose cowl directs airflow to the engine fan and over the engine nacelle. For the nose cowlframes and formers structural identification, refer to SRM 54−11−15.

B. Access Cowls

The upper and lower access cowls direct the airflow over the fan section and give access to thethrust reverser mechanism. For the Access Cowls structural identification, refer to SRM54−14−00.

C. Thrust Reverser

The thrust reverser is used during landing roll out and helps to stop the aircraft. For the thrustreverser frames and formers structural identification, refer to SRM 54−13−15.

D. Exhaust Nozzle

The exhaust nozzle tube is the outlet for exhaust gases from the turbine. For the exhaust nozzlestructural identification, refer to SRM 54−18−00−00.

E. Core Cowls

The core cowl doors are around the center section of the engine to give it protection. For the corecowl frames and formers structural identification, refer to SRM 54−16−15.

F. Tailpipe

The tailpipe fairing gives a smooth aerodynamic surface for external airflow and the control ofengine bypass air to keep satisfactory exhaust nozzle assembly temperature. For the tailpipeframes and formers structural identification, refer to SRM 54−12−15.

G. Nacelle/Pylon Service Structure

The nacelle/pylon service structure has the attachment points for the movable cowls, and all ofthe connections between the aircraft and the power plant. For the nacelle/pylon service structurestructural identification, refer to SRM 54−17−00.



Feb 18/2003

54−12−15TAILPIPE

COWLSCORE

COWLNOSE

54−16−15

54−11−15

54−13−15THRUST REVERSER

54−17−00

SERVICESTRUCTURE

NACELLE/PYLON

TAILPIPE54−12−15

54−18−00NOZZLE

EXHAUST

rsr5

4012

.dw

g , i

c, 1

8/09

/00


Nacelle BreakdownFigure 1


Feb 18/2003

NACELLES INTERNAL STRUCTURE − ALLOWABLE DAMAGE

1. General


A. Use the allowable damage limits given in this subject when specific damage limits are notsupplied in the subject for a given structural element.

B. For general allowable damage limits for the extruded, machined parts (other than fittings) andformed sheet metal parts of the nacelles, refer to Figure 101 and Figure 102. For generalallowable damage of the nacelle skins, refer to SRM 54−10−31. For allowable damage limits offittings, refer to the applicable subject in this chapter.



Feb 18/2003

rsr5

2001

, yfr

, 15/

07/9

9

RUN−OUT20XMIN



T X = DEPTH OF MATERIALREMOVAL = 10% THICKNESS

(T) MAXIMUM

TWO WEBELEMENTSAT A HOLE

FLANGE

CORNER

WEB

FREEFLANGE

BULB(EXTRUSIONS

ONLY)

AREA OF MATERIALREMOVAL MUST NOTBE MORE THAN 10%OF ELEMENT WIDTH



REMOVALLIMIT

DAMAGEAREA



T

T1

2

T3

REMOVEDDAMAGE

Remove damage as shown for small edgedamage, detail A. T must be larger than Tafter damage removal.

2 For added data, refer to Sheet 3.

NOTES

3 2

MATERIAL

SKIN ELEMENT

15T 15T

T = SKIN THICKNESS

EXTRUDED SECTION

EXTRUDED AND MACHINEDSECTION ELEMENTS−EXAMPLE

SMALLEDGE DAMAGE

SURFACE DAMAGE

CORNER DAMAGE

X





Feb 18/2003

rsr5

2002

, ic,

16/

08/9

9

RADIUS OFREMOVED DAMAGEIS FOUND BY THE

DAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM


(EXAMPLE)



WIDTH

MATERIAL REMOVEDTO REMOVE DAMAGE





WIDTH


HAVE OVERLAPS

EDGE DAMAGE



FOUND BY THEDAMAGE DEPTH (X).R = 1.0 in. (25.4 mm)

MINIMUM

For added data, refer to sheet 3.

NOTE




Feb 18/2003

DAMAGE REMARKS

Cracks

Cracks are not permitted in webs.

Cracks are permitted in flange edges if they are in material removal limits shown foredge damage.


Removed damage must not decrease the thickness (or the cross−section area) of agiven element by more than 10 percent (an extruded bulb is an element).

Dents Dents are not permitted.

Holes andpunctures


You can plug holes thru 0.25 inch (6.35 mm) in diameter (refer to the Notes that follow)if they are not nearer than 4 X repaired hole diameter to:

− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10 percent.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lok pins),contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer tothe data given for formed parts in Figure 102, (Sheet 1).



NOTE: Approved repair or replacement of a member is necessary when more than 30 percent of its lengthis damaged.


NOTE: Remove damage as shown in Sheets 1 and 2.


Extruded and Machined Parts (Other than Fittings) –− Allowable Damage − GeneralFigure 101 (Sheet 3)


Feb 18/2003

rsr5

2004

, yfr

, 15/

07/9

9

ATTACHMENTFLANGE

LIP

WEB

FORMED SECTIONELEMENTS EXAMPLE

FLANGE

15T 15T

T = SKIN THICKNESS

SKIN ELEMENT

FORMEDSECTION

FREEFLANGE

Repaired areas must nothave an overlap.

2 For added data,

NOTES

refer to Sheet 3.

DENTS MUST BESMOOTH AND NOT

HAVE SHARP CREASES,GOUGES, OR CRACKS.

FOR DEPTH LIMITCALCULATION, REFER

TO SHEET 2

D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

AREA REPAIREDBEFORE

THE BOTTOM OF THEREMOVED DAMAGE MUSTHAVE A RADIUS OF 1.0 in.

(25.4 mm) MINIMUM

X = DEPTH OFDAMAGE REMOVAL

= 10% FLANGEWIDTH MAXIMUM

20XMINIMUMRUN−OUT


DENTS

REMOVAL OF NICK OR CRACKDAMAGE ON AN EDGE




Feb 18/2003

DAMAGE REMARKS

Cracks

Edge cracks are permitted only in free flanges. Cracks are not permitted in lippedflanges or in webs.

Remove damage as shown in Sheet 1.


Removed damage must not decrease the thickness (or the cross−section area) of agiven element by more than 10 percent.

Dents

Dents are permitted in webs only.


W/D must not be less than 20 where:



Holes andpunctures



− Adjacent holes

− Part edges

− Corner radii

− Other damage.

NOTE: The hole must not decrease the cross−section area of a given element by morethan 10 percent.

NOTE: If the adjacent fasteners are rivets or clearance−fit fasteners, use an AD rivet toplug the hole. If the adjacent fasteners are interference−fit fasteners (e.g. Hi−Lok pins),contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM51−13−01).

General

Damage is permitted in only one element at a given cross−section. Removed damage atone element must not have an overlap on removed damage at another element (refer toSheet 1 of this Figure).





Feb 18/2003

DAMAGE REMARKS

NOTE: Approved repair or replacement of a member is necessary when more than 30 percent of its lengthis damaged.





Feb 18/2003

THIS PAGE INTENTIONALLY LEFT BLANK

NACELLE FITTINGS − GENERAL


A. The nacelles contain the power plants and have aerodynamic surfaces that direct the air into andover the engines. The nacelle consists of the following sections (refer to Figure 1 for the nacellebreakdown):

– Nose Cowl. Refer to SRM 54−11−00.

Access Cowls. Refer to SRM 54−14−00.

Thrust Reverser. Refer to SRM 54−13−00.

Core Cowls. Refer to SRM 54−16−00.

Exhaust Nozzle. Refer to SRM 54−18−00.

Tailpipe. Refer to SRM 54−12−00.

Nacelle/Pylon Service Structure. Refer to SRM 54−17−00.

B. The nose cowl directs airflow to the engine fan and over the engine nacelle. For the nose cowlfittings refer to SRM 54−11−15.

C. The upper and lower access cowls direct the airflow over the fan section and give access to thethrust reverser mechanism. For the access cowl fittings refer to SRM 54−14−00

D. The thrust reverser is used during landing roll out and helps to stop the aircraft. For the thrustreverser fittings refer to SRM 54−13−15.

E. The core cowl doors are around the center section of the engine to give it protection. For the corecowl fittings refer to SRM 54−16−15.

F. The exhaust nozzle tube is the outlet for exhaust gases from the turbine. For the exhaust nozzlefittings refer to SRM 54−18−00.

G. The tailpipe fairing gives a smooth aerodynamic surface for external airflow and the control ofengine bypass air to keep satisfactory exhaust nozzle assembly temperature. For the tailpipefittings refer to SRM 54−12−15.

H. The nacelle/pylon service structure has the attachment points for the movable cowls, and all ofthe connections between the aircraft and the power plant. For the nacelle/pylon service structurefittings refer to SRM 54−17−00.



Feb 18/2003


NACELLE FITTINGS − ALLOWABLE DAMAGE

1. General

For the allowable damage limits contact Short Brothers Technical Information and Support (TechnicalHelp Line 44 07850 770826).



Feb 18/2003


NACELLE − SKIN AND PLATING − GENERAL

1. General

This section contains data that is applicable to the power plant components.


A. General

(1) The nacelles contain the power plants and have aerodynamic surfaces that direct the airinto and over the engines. The nacelle consists of the following sections (refer to Figure 1for the nacelle skin and plating breakdown):

– Nose Cowl. Refer to SRM 54−11−00.

Access Cowls. Refer to SRM 54−14−00.

Thrust Reverser. Refer to SRM 54−13−00.

Core Cowls. Refer to SRM 54−16−00.

Exhaust Nozzle. Refer to SRM 54−18−00.

Tailpipe. Refer to SRM 54−12−00.

Nacelle/Pylon Service Structure. Refer to SRM 54−17−00.

(2) The nose cowl directs airflow to the engine fan and over the engine nacelle. For the NOSECOWL SKIN AND PLATING structural identification refer to SRM 54−11−31.

(3) The upper and lower access cowls direct the airflow over the fan section and give access tothe thrust reverser mechanism. For the ACCESS COWLS structural identification refer toSRM 54−14−00.

(4) The thrust reverser is used during landing roll out and helps to stop the aircraft. For theTHRUST REVERSER SKIN AND PLATING structural identification refer to SRM 54−13−31.

(5) The core cowl doors are around the center section of the engine to give it protection. For theCORE COWL SKIN AND PLATING structural identification refer to SRM 54−16−31.

(6) The tailpipe fairing gives a smooth aerodynamic surface for external airflow and the controlof engine bypass air to keep satisfactory exhaust nozzle assembly temperature. For theTAILPIPE SKIN AND PLATING structural identification refer to SRM 54−12−31.

(7) The nacelle/pylon service structure has the attachment points for the movable cowls, and allof the connections between the aircraft and the power plant. For the NACELLE/PYLONSERVICE STRUCTURE structural identification refer to SRM 54−17−00.



Feb 18/2003

rsr5

4039

.dg

, na,

24/

11/0

054−12−31TAILPIPE

COWLSCORE ACCESS COWLS COWL

NOSE

54−16−3154−14−00 54−11−31

54−13−31THRUST REVERSER

54−17−00

SERVICESTRUCTURE

NACELLE/PYLON


Nacelle Skin and Plating BreakdownFigure 1


Feb 18/2003

NACELLE SKIN AND PLATING − ALLOWABLE DAMAGE

1. General


A. Use the allowable damage limits given in this subject when specific allowable damage limits arenot supplied in the subject for a given structural element.

B. The nacelle skin panels are of two general types; sheet metal and honeycomb compositestructures. The composite panels are of two types, as follows:

(1) Aluminum alloy facing skins on aluminum alloy honeycomb cores (Type A panels)

(2) Kevlar/epoxy and graphite/epoxy laminated facing skins on nylon (Nomex) honeycombcores (Type B panels). To provide lightning protection, these panels have fiberglass facingsheets, that are aluminum−coated, bonded to the external facing skin surfaces.

2. Allowable Damage

A. Composite Honeycomb Panels

(1) Scratched paint or primer is the only allowable damage permitted for honeycomb compositepanels. If the damage has not gone through the paint or primer, there is no limit on theamount of scratch damage. You must use approved typical, generic or specific repairs for allother damage (refer to SRM 51−13−00 and the applicable 201−999 page block).

B. Sheet Metal Panels

CAUTION: DO NOT FILL DENTS IN THE ENGINE AIR INTAKE AREA WITH SURFACEFILLER. IF THIS IS DONE, IT CAN CAUSE DAMAGE TO THE ENGINE.

(1) For general allowable damage limits for sheet metal skin and plating, refer to Figure 101.



Feb 18/2003

rsr5

2007

.dg,

yfr

/lr, 1

7/12

/03

For added data, refer to sheet 3.NOTE


MATERIAL REMOVEDTO REMOVE DAMAGE RADIUS OF

REMOVED DAMAGEIS FOUND BY THE

DAMAGE DEPTH (X)


(EXAMPLE)


FOUND BY THEDAMAGE DEPTH (X)




HAVE OVERLAPS

EDGE DAMAGE



(EXAMPLE)


Sheet Metal Skin and Plating − Allowable Damage − GeneralFigure 101 (Sheet 1)


Jun 22/2004

rsr5

2008

.dg,

yfr

/lr, 1

7/12

/03

D(DEPTH OF DENT)

W(WIDTH OF MINOR

AXIS OF DENT)

INITIALCONTOUR

DENTS

0.100 in. (2.54 mm)

RUN−OUT20X

MINIMUM



X = DEPTH OFOF DAMAGE

THE DISTANCE OF THEEDGE OF THE REMOVED

DAMAGE FROM THE HOLES,FASTENERS OR SKIN EDGE

MUST NOT BE LESS THAN 20X

T = THICKNESSOF THE

SCRATCHES, NICKS, GOUGES AND CORROSION

(MAJOR AXIS OF THEREMOVED MATERIAL)

DAMAGEAREA

DAMAGEREMOVAL

LIMIT

Refer to sheet 3, for added data.NOTE

A

A

A

MAXIMUM

REMOVALMATERIAL




Jun 22/2004

DAMAGE REMARKS

CracksCracks are permitted only at the edges of the skins.

Remove damage as shown in Sheet 1.

Scratches, nicks,gouges and

corrosion

Removed damage must not be more than 10 percent of the local skin thickness.

Remove damage as shown in Sheet 2. For the removal of corrosion damage, refer toSRM 51−21−06.

If the part was shot peened when it was made, it must be shot peened again (refer toSRM 51−24−11).

Dents

Dents must be separated by one−half (1/2) the width of the largest adjacent dent.

Dents must be smooth and not have sharp creases, gouges, cracks, or signs ofdamaged or loose rivets. W/D must not be less than 25 where:



Depth limit given in Sheet 2 is applicable to all areas but does not include the engineair intake. If dents have a larger depth than permitted by the aerodynamic smoothnesslimits (refer to SRM 51−14−11), fill with surface filler (refer to SRM 51−12−00).

Depth of dents in the engine air intake area must agree with aerodynamic smoothnesslimits given in SRM 51−14−11. Dents in the engine air intake area must not be filledwith surface filler.

Holes andpunctures

Holes through 0.25 inch (6.35 mm) in diameter can be plugged with AD type rivets ifthey are not nearer than 4 X the repaired hole diameter to:

− Adjacent holes

− Skin edges

− Chem−milled pocket radii

− Other damage.

General edgedamage

There are no limits for the linear dimension of the removed damage if standard edgedistances are maintained (refer to SRM 51−40−06). A decreased edge distance of 1.5X fastener diameter is permitted for 10 percent of the linear dimension.

NOTE: Approved repair or replacement is necessary when more than 30 percent of the area of a panel isdamaged.





Jun 22/2004

NACELLE SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the nacelle skin and plating, refer to Shorts CMM, Nacelles.



Feb 18/2003


NOSE COWL − GENERAL

1. General

For the Nose Cowl Frames and Formers, refer to SRM 54−11−15.

For the Nose Cowl Skin and Plating, refer to SRM 54−11−31.



Feb 18/2003


NOSE COWL FRAMES AND FORMERS − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the nose cowl.



Feb 18/2003

rsr5

4013

.dg,

pl/r

m, 0

5/01

/06

NOTEThe structure is symmetricalabout the nacelle centerlines,unless shown differently. XN105.00

XN121.60

XN135.84

11

XN105.00

XN121.60

XN135.84


Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 1)


Mar 10/2006

rsr5

4014

.dg,

pl,/

rm, 0

5/01

/06

1

5

7

XN105.00

TYPICAL 4 PLACES

11 (REF)

XN121.60

XN105.00

10

8

2 4 20 55 24

212223

3103

8

510 1

32 (REF)

29 (REF)

43

54 (REF)

25 (REF)

XN125.94

9 (REF)




Mar 10/2006

rsr5

4023

.dg,

pl/r

m, 0

5/01

/06

28

26

54

27

XN121.604 PLACES

XN121.60

32 (REF)

36

61

4334

29 (REF)

25

XN125.94

XN125.94

34

39

43

66

64

37 (4 PLACES)

65

29 (REF)

XN121.60

EFFECTIVITY:

EFFECTIVITY:

7037 − 8400

7002 − 7036




Mar 10/2006

rsr5

4024

.dg,

pl/r

m, 1

9/12

/05

XN121.60

14

19

16

XN135.84

XN121.60

XN105.00

105

12

8 3

15

17

1854

213

4

8

106

1

310

9 (REF)

29 (REF)66

64

65

37

34

32 (REF)

XN121.60

29 (REF)

32 (REF)

34

43

613936 40

38

36

11 (REF)

XN125.94

XN125.94

EFFECTIVITY:EFFECTIVITY: 7037 − 84007002 − 7036




Mar 10/2006

rsr5

4025

.dg,

pl/r

m, 1

05/0

1/06

XN121.60

29 (REF)

32 (REF)

34

39

37

65

64

XN121.60

XN105.00

105

8310

3

4

2

13

1754

16

15

14

19

1

10

6

8

11 (REF)

6634 43 (REF)

61

32 (REF)

29 (REF)

XN121.6043 (REF)

XN125.94XN125.94

EFFECTIVITY: EFFECTIVITY: 7002 − 7036 7037 − 8400




Mar 10/2006

rsr5

4026

.dg,

rm

, 05/

01/0

6

30

30

31

31

31

31

31

33

33

35

41

42

42

36

36

36

35

35

35

31




Mar 10/2006

rsr5

4045

.dg,

ca,

11/

01/0

1

44

44

48 4862

57

57

57

57

575757

57

44

44

57

44

57

5857

60

57




Mar 10/2006

rsr5

4046

.dg,

ca/

rm, 0

5/01

/06

63

42 (REF)

47

51

5149

50

45

4852

56

49

53

56

48

46

48

56

50

XN121.60

XN135.8450

50

XN121.60

XN135.84

XN135.84

59

XN135.84

62 (REF)

14 (REF)

7002 − 72217230 − 7230 RH NACELLE7215 − 7215 LH NACELLE

7222 − 84007215 − 7215 RH NACELLE7230 − 7230 LH NACELLE

EFFECTIVITY: EFFECTIVITY:




Mar 10/2006

ITEM DESCRIPTION DRAWING MATERIALREFERENCE

FINISHCODE ♦ EFFECTIVITY

Bulkhead Instl,Fwd 228−50031

1 Frame 0.032 (0.81) Titaniumalloy ††

T002

2 Bracket 0.050 (1.27) Alclad2024−0 † ‡‡‡

A010

3 Spacer 0.125 (3.18) Alclad2024−T3 ‡‡‡

V004

4 Clip 0.050 (1.27) Alclad2024−0 † ‡‡‡

V004

5 Spacer 0.160 (4.06) Al alloy2024−0 † ‡‡

V005 7003−7236

0.160 (4.06) Al alloy7075−T6 ¶

V005 7237−8400

6 Doubler 0.032 (0.81) Titaniumalloy ††

T002

7 Splice 0.032 (0.81) Titaniumalloy ††

T002

8 Hi TemperatureGasket

0.022 (0.56) GlassFiber/Aramid §§

9 Insulation Kevlar/Epoxy FabricPrepreg ♦♦♦

10 Laminated Shim ♥

11 D Duct 228−50083 Titanium alloy ♥♥♥ V004 7003−7098

7100−7114

7116−7118

7133−7133

Titanium alloy ††† V004 7099−7099

7115−7115

7119−7132

7134−8400

12 Ejector Outlet 228−56452 CRES InvestmentCasting 17−4PH §§§

V004

Intercostal Instl,Lower

228−50077

13 Web 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003


Key to Figure 1 (Sheet 1)


Mar 10/2006

14 Tee Cap Extruded Al alloy2024−0 † ¶¶¶

V003

15 Stiffener 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

16 Doubler 0.050 (1.27) Alclad2024−T3 ‡‡‡

V003

17 Angle 0.040 (1.02) Alclad2024−0 † ‡‡‡

V003

18 Support 0.040 (1.02) Alclad2024−0 † ‡‡‡

V003


V003

Intercostal Instl,Upper

228−50076

20 Web 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

21 Tee Cap Extruded Al alloy2024−0 † ¶¶¶

V003


V003

23 Doubler 0.040 (1.02) Alclad2024−T3 ‡‡‡

V003

24 Angle 0.040 (1.02) Alclad2024−T3 ‡‡‡

V003

Intercostal Instl,Actuator Support

228−50078

25 Web 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

26 Cap 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

27 Angle 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003


V003

Bulkhead Assy,Aft

228−50055

29 Web 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

30 Web Splice 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003




Feb 18/2003

31 Doubler 0.063 (1.60) Alclad2024−0 † ♦♦

V003

32 Outer Cap Extruded Al alloy2024−0 † ¶¶¶

V002

33 Cap Splice 0.063 (1.60) Alclad2024−0 † ‡‡‡

V003

34 Doubler 0.050 (1.27) Alclad2024−0 † ♦♦

V003

35 Bracket 0.063 (1.60) CRES ♣ V024

36 Bracket 0.040 (1.02) Alclad2024−T3 ‡‡‡

V003

37 Filler Extruded Al alloy7075−T6 §§

V003

38 Support 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003 7037−8400

39 Bracket 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

40 Support 0.050 (1.27) Alclad2024−T3 ‡‡‡

V003 7003−7036

41 Support 0.080 (2.03) CRES ♣ V024

42 Bracket 0.050 (1.27) Al alloy2024−T3 ‡‡‡

V003

43 Filler Laminated Phenolicsheet ♣♣

Support Instl,Thrust ReverserActuator

228−50057

44 Cable Support 0.050 (1.27) Alclad2024−T3 ‡‡‡

V003

45 Support Beam 0.063 (1.60) Alclad2024−0 † ‡‡‡

V003

46 Support Beam Extruded Al alloy7075−T6 ¶¶¶

V003

47 Attach Angle 0.063 (1.60) Alclad2024−T3 ‡‡‡

V003

48 Bracket 0.063 (1.60) Alclad2024−T3 ‡‡‡

V003

49 Bracket 0.063 (1.60) Alclad2024−0 † ‡‡‡

V003




Mar 10/2006

50 Bracket 0.040 (1.02) Alclad2024−T3 ‡‡‡

V003

51 Filler 0.063 (1.60) Alclad2024−T3 ‡‡‡

V003

52 Filler 0.100 (2.54) Alclad2024−T3 ‡‡‡

V003

53 Shim 0.063 (1.60) Alclad2024−T3 ‡‡‡

V003

54 Bracket 0.050 (1.27) Alclad2024−0 † ‡‡‡ ♦♦

V003

55 Bracket 0.050 (1.27) Alclad2024−0 † ‡‡‡

V003

56 Attach Clip Extruded Al alloy7075−T6 ¶¶¶

V002

57 Support 228−50020 0.040 (1.02) Al alloy2024−T3 ‡‡‡

V003

58 Support 0.063 (1.60) Al alloy2024−T3 ‡‡‡

V003

− Packer 228−50020 0.063 (1.60) Al alloy2024−T3 ‡‡‡

7209−7209♣♣♣7213−7213

7214−7214♠♠♠7215−8400

59 Bracket 228−50745 0.040 (1.02) Al alloy2024−T3 ‡‡

V003

60 Support 228−50747 Al alloy 2024−T351 ‡‡ V001 ‡

61 Fitting 228−50084 Al alloy 7050−T7451 ¶¶§

V007 7037−8400

62 Ring 228−50056

228−50450

Forged Al alloy7075−T73 ♠

V002P

63 Cover 228–50072 Kevlar/Epoxy Prepreg♦♦♦, andGraphite/Epoxy Prepreg♥♥

64 Fitting 228−50051 0.375 (9.53) Al alloy7075−T7451 ¶¶

V007P 7003−7036

65 Fitting Strap 228−50071 0.160 (4.06) Al alloy7075−T76 ♠♠

V007P 7003−7036




Mar 10/2006

66 Fitting 228–50068 0.500 (12.70) Al alloy7050−T7451 ¶¶

V007P 7003−7036

− Item not shown.

♦ Refer to SHORTS CMM 20−21−16 for finish code identification.

♦♦ Alternate material is Alclad 2024−T3 per specification AMS−QQ−A−250/5.

♦♦♦ Specification Vought 207−7−464, Style 285.

† Heat treated to Cond T42 and aged to Cond T62 per specification AMS−H−6088.

†† Specification AMS−T−9046, Type III, Comp C.

††† Specification AMS−4901.

‡ Sulfuric acid anodized per specification MIL−A−8625, Type II.

‡‡ Specification AMS−QQ−A−250/4.

‡‡‡ Specification AMS−QQ−A−250/5.

¶ Specification AMS−QQ−A−250.

¶¶ Specification AMS−4050.

¶¶¶ Specification AMS−QQ−A−200.

§ Alternate material is Al alloy Bar 7050−T74511 per specification AMS−4342.

§§ Specification Vought 207−7−465.

§§§ Specification Vought CVA1−513, Class B.

♣ Specification AMS−5517, Type 301, Cond 1/4 Hard.

♣♣ Specification MIL−I−24768/9, Type NPG.

♣♣♣ RH nacelle only.

♠ Specification AMS−QQ−A−367.

♠♠ Specification AMS−QQ−A−250/24.

♠♠♠ LH nacelle only.

♥ Specification Vought 207−6−437, Class 2.

♥♥ Specification Vought 207−7−448, Type II, Style 1.

♥♥♥ Specification AMS−T−9046, Type I, Comp B or C.

NOTE: All dimensions are given in inches followed by millimeters in parentheses.




Mar 10/2006

NOSE COWL FRAMES AND FORMERS − ALLOWABLE DAMAGE

1. General

Refer to Shorts CMM 71−61−01for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).



Jun 17/2003


NOSE COWL FRAMES AND FORMERS − REPAIRS

1. General

A. For repairs to the nose cowl frames and formers, refer to Shorts CMM 71−61−01, Nose InletCowl, except for the REOs listed below.

B. List of REOs

The repairs listed below are applicable to this subject. Details of these repairs are found inappropriate chapters of the Structural Generic Repair Engineering Order (SGREO) Manual,CSP−A−092.

The SGREO Manual contains the latest issue of each repair. Repairs to an earlier issue remainvalid unless otherwise indicated on the current issue of the REO. Make sure that you record theissue of the REO that was used.

REO TITLE/DESCRIPTION EFFECTIVITY

601R−71−61−2207 Inlet cowl − replacement of peri−seal on anti−ice inlet

601R−71−61−2328 Removal of a cracked track support bracket on the noseinlet cowl

601R−71−61−2713 Inlet cowl − repair of chafe damage on rear bulkhead atanti−ice duct support brackets locations

601R−71−61−2843 Repair to chafe damage on ballscrew actuator supportassembly − nose cowl



Mar 10/2006


NOSE COWL SKIN AND PLATING − ALLOWABLE DAMAGE

1. General

A. Refer to Shorts CMM 71−61−01 for information pertaining to allowable damage limits and ifnecessary, contact Short Brothers Technical Information and Support (Technical Help Line 44 (0)7850 770826).



Jun 10/2007


NOSE COWL SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the nose cowl skin and plating, refer to Shorts CMM 71−61−01, Nose Inlet Cowl,except for the REOs listed below.

B. List of REOs




601R−71−61−2056 Nosecowl − lipskin thickness

601R−71−61−2129 Nosecowl − lipskin thickness

601R−71−61−2532 Nose cowl − pitting on lipskin

601R−71−61−2635 Inlet cowl − outer skin leading edge erosion/delamination −fly−on

601R−71−61−2862 Application of Ceram−Kote® to prevent further erosion tothe leading edge of the nose cowl outer−skin



Jul 10/2006


TAILPIPE − GENERAL

1. General

For the Tailpipe Frames and Formers, refer to SRM 54−12−15.

For the Tailpipe Skin and Plating, refer to SRM 54−12−31.



Feb 18/2003


TAILPIPE FRAMES AND FORMERS − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the tailpipe, refer to Figure 1.



Mar 10/2006

rsr5

4015

, cr,

13/

10/0

0

15

9

2

14

1819

16

9

10

111

12

3

2

10

24

4

8

25

15

21141

15

15

17XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

24

XN243.00XN247.90

XN237.93

1510

1515

22

23


Tailpipe Fairing Structure − Structural IdentificationFigure 1 (Sheet 1)


Feb 18/2003

rsr5

4016.c

gm

7

7

6

7

13

26

8

27

27

28

410

20

6

105


Tailpipe Fairing Structure − Structural IdentificationFigure 1 (Sheet 2)


Feb 18/2003

ITEM DESCRIPTION DRAWINGMATERIAL REFER-

ENCEFINISH

CODE ♦EFFECTIVI-

TY

Fairing Assy 228−50181

1 Frame SpliceChannel

0.050 (1.27) Alclad2024−0 † ¶

V004

2 Frame SpliceAngle

0.050 (1.27) Alclad2024−0 † ¶

V004

3 Frame Splice 0.050 (1.27) Alclad2024−0 † ¶

‡‡ 7003−7067

7069−7080

7381−8400

4 Intercostal 0.040 (1.02) Alclad2024−0 † ¶

V004

5 Intercostal 0.050 (1.27) Alclad2024−0 † ¶

V004

6 Bracket 0.080 (2.03) CRES17−4PH †† ¶¶¶

S010

7 Bracket 0.080 (2.03) CRES17−4PH †† ¶¶¶

T002

− ReceptacleBracket

0.100 (2.03) CRES17−4PH †† ¶¶¶

T002 7003−7067

7069−7114

7116−7119

7133−7133

0.100 (2.03) CRES17−7PH §

T002 7115−7115

7120−7132

7134−8400

8 Clip 0.040 (1.02) Alclad2024−0 † ¶

V004

9 Stiffener Extruded Al alloy2024−0 † ¶¶

V005

10 Stiffener 0.032 (0.81) Alclad2024−0 † ¶

V004


V004


V004

13 Plate 0.032 (0.81) Alclad2024−T3 ¶

V004

14 Seal (Upper,Lower)

Silicone rubber †††




Mar 10/2006


ENCEFINISH

CODE ♦EFFECTIVI-

TY

15 Strap 0.020 (0.51) Alclad2024−T3 ¶

V004

16 Stiffener 0.080 (2.03) CRES17−4PH †† ¶¶¶

T002

17 Receptacle 0.080 (2.03) CRES17−4PH †† ¶¶¶

T002

18 Clip 0.080 (2.03) CRES17−4PH †† ¶¶¶

T002 7003−7067

7071−7073

7075−7075

7077−7077

19 Bracket 0.080 (2.03) CRES17−4PH †† ¶¶¶

T002 7069−7070

7074−7074

7076−7076

7078−8400

20 Bracket 0.040 (1.02) Alclad2024−T3 ¶

V004

21 Panel 0.050 (1.27) CRES §§ T002

22 Splice Plate 0.032 (0.81) Alclad2024−T3 ¶

V004

23 Splice Plate 0.005 (0.13 ) CRES§§

T002

24 Retainer 0.020 (0.51) Alclad2024−T3 ¶

V004

Fitting Assy,Combustor FuelVent

228−53401

25 Plate 0.050 (1.27) CRES§§§

T002

− Stiffener 0.050 (1.27) CRES§§§

T002

26 Upper Support,Aft Tail Fairing

228−50185 CRES InvestmentCasting 17−4PH ‡ ♣

T002

− Lower Support,Aft Tail Fairing

228−50184 CRES InvestmentCasting 17−4PH ‡ ♣

T002

27 Link 228−50186 CRES InvestmentCasting 17−4PH ‡ ♣

T002




Mar 10/2006


ENCEFINISH

CODE ♦EFFECTIVI-

TY

28 Support 228−50188 Nickel Alloy Casting,Inconel 718C ♣♣

T002

− Item not shown.


† Heat treated per specification AMS−H−6088 to Cond T42, and aged to Cond T62.

†† Aged per specification CVA 1−372 to Cond H1025 (155 ksi).

††† Specification Vought 207−6−439, Type I, Grade 50.

‡ Homogenized and heat treated to 150 ksi minimum tensile strength per specification CVA 1−372.

‡‡ Apply heat resisting aluminum paint per specification Vought 208−9−87.


¶¶ Specification AMS−QQ−A−200.

¶¶¶ Specification AMS−5604.

§ Specification AMS−5529.

§§ Specification AMS−5516, Type 302, Cond A.

§§§ Specification AMS−5510, Type 321.

♣ Specification Vought CVA 1−513, Class B.

♣♣ Specification AMS−5383.





Mar 10/2006

TAILPIPE FRAMES AND FORMERS − ALLOWABLE DAMAGE

1. General

Refer to Shorts CMM 78−11−00 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).



Jun 17/2003


TAILPIPE FRAMES AND FORMERS − REPAIRS

1. General

A. For repairs to the tailpipe frames and formers, refer to Shorts CMM 78−11−00, Exhaust NozzleAssembly.



Feb 18/2003


TAILPIPE SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1for the structural identification of the tailpipe skin and plating.



Jun 17/2003

rsr5

4029

, na,

21/

11/0

0

−

LEGEND

12

t = 0.020/0.030 (0.508/0.762)t = 0.027/0.037 (0.686/0.940)

NOTEThe structure is symmetrical around the nacelle centerline, unless shown differently.

3t = 0.035/0.045 (0.889/1.143)

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1t1

t1

t1

t2

t3

1

t2t2

78

t2

ZN100.00

ZN100.00

2

CL

CL

t2t2


Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 1)


Jun 17/2003

rsr5

40

35

, n

a,

21

/11

/00

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1t1

t1

t1t3

t2 t2

t2

9

ZN100.00

2

t2t2




Jun 17/2003

rsr5

40

36

, n

a,

22

/11

/00

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1 t1 t1t1 t2t3

t2t2

t2

3

1

87ZN

100.00

t2

t2

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1t3

t2t1

t1t1

9

3

ZN100.00

t2t2

t2 t2




Jun 17/2003

rsr5

40

37

, n

a,

22

/11

/00

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1 t3 t2 t1 t1 t1

t2

t2

6

4

ZN100.00

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1

t3

t2t1

t1t1

t2

t2

6

10

ZN100.00

t2t2

t2t2




Jun 17/2003

rsr5

40

38

, n

a,

22

/11

/00

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t1t3t2t1t1t1

t2

t2

4

5

XN208.00

XN214.00

XN221.97

XN227.80

XN232.87

XN237.93

XN243.00

XN247.90

t2

t2

t1

t3

t2t1

t1t1

5

10

ZN100.00

ZN100.00

t2

t2

t2 t2




Jun 17/2003

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY

Skin Assy. Bonded 228−50181 V0117003−7067

7069−7163

1 Skin Chem−Mill UPR 0.050 (1.27) Alclad oneside 2024−0 sheet †

V011 7003−7067

7069−7163

2 Fire Shield UPR 0.005 (0.13) CRES sheet††

S010

3 Fire Shield UPR 0.005 (0.13) CRES sheet††

S010

Skin Assy. Bonded 228−50181 V0117003−7067

7069−7163

4 Skin Chem−Mill LWR 0.050 (1.27) Alclad oneside 2024−0 sheet † †††

V011 7003−7067

7069−7163

5 Fire Shield LWR 0.005 (0.13) CRES sheet††

S010

6 Fire Shield LWR 0.005 (0.13) CRES sheet††

S010

7 Doubler Shield 0.005 (0.13) CRES sheet††

S010

8 Panel 0.050 (1.27) CRES sheet††

S010

Skin Assy. Bonded 228−50181 V011 7164−8400

9 Skin Chem−Mill UPR 0.050 (1.27) Alclad oneside 2024−0 sheet †

V011 7164−8400

Skin Assy. Bonded 228−50181 V011 7164−8400

10 Skin Chem−Mill LWR 0.050 (1.27) Alclad oneside 2024−0 sheet † †††

V011 7164−8400


† Specification AMS–4077.

†† Specification MIL−S−5059, Type 302, Cond A.

††† Heat treat per MIL−H−6088 to Cond T42 and age to Cond T62.



Key to Figure 1


Mar 10/2006


TAILPIPE SKIN AND PLATING − ALLOWABLE DAMAGE

1. General




Jun 17/2003


TAILPIPE SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the tailpipe skins and plating, refer to Shorts CMM 78−11−00, Exhaust NozzleAssembly.



Feb 18/2003


THRUST REVERSER FRAMES AND FORMERS − ALLOWABLE DAMAGE

1. General

Check Shorts CMM 78−30−00 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).



Jun 22/2004


THRUST REVERSER FRAMES AND FORMERS − REPAIRS

1. General

A. For repairs to the thrust reverser frames and formers, refer to Shorts CMM 78−30−00, ThrustReverser.



Feb 18/2003


THRUST REVERSER SKINS AND PLATING − ALLOWABLE DAMAGE

1. General

Check Shorts CMM 78−30−00 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).



Jun 22/2004


THRUST REVERSER SKINS AND PLATING − REPAIRS

1. General

A. For repairs to the thrust reverser skins and plating, refer to Shorts CMM 78−30−00, ThrustReverser.



Feb 18/2003


ACCESS COWLS − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the access cowls internal structure.

Refer to Figure 2 for the structural identification of the access cowls skin and plating.



Feb 18/2003

rsr5

40

17

, lc

, 1

3/1

0/0

0

1

2

3

4


Access Cowls − Internal StructureFigure 1


Feb 18/2003


Cowl Assy, UpperAccess

228−50080

1 Upper Edge Extruded Al alloy 2024−0 †

‡

V002

2 Splice 0.063 (1.60) Alclad2024−T3 ‡‡

V003

Cowl Assy, LowerAccess

228−50081

3 Lower Edge Extruded Al alloy 2024−0 †‡

V002

4 Doubler 0.063 (1.60) Al alloy2024−T3 ‡‡

V002

− Filler 0.100 (2.54) Al alloy2024−T3 ‡‡

V002

− Item not shown.


† Heat treated per specification AMS−H−6088 to Cond T42, and aged to Cond T62.

‡ Specification AMS−QQ−A−200.

‡‡ Specification AMS−QQ−A−250.



Key to Figure 1


Jun 17/2003

rsr5

4030

, na,

06/

12/0

0

4435

3444

22

143

4

23

4444

12


Access Cowls − Skin and PlatingFigure 2 (Sheet 1)


Mar 10/2006

rsr5

40

31

, n

a,

06

/12

/00

4435

3444

22

143

4

23

4444

143

4

23

4435

2344




Feb 18/2003

rsr5

4032

.dg,

na/

rm, 1

9/12

/05

698

9

78

998

10

8999

77

9999

998

10

8999

77

9999

1198

9

78

998

10

899

77

9999

EFFECTIVITY: 7009 − 7047


998

10

899

77

9999


1198

9

7

87




Mar 10/2006


Panel Assy, Upper 228−50080 V001

1 Core0.375 (9.53)Aramid/Phenolichoneycomb ††

2 Al Coated FiberglassFabric, epoxy impregwoven glass fiber, Alcoated †††

3 Kevlar/Epoxy Fabric Fabric, epoxy impregwoven aramid fiber ‡

4 Graphite/Epoxy Fabric Fabric, epoxy impregwoven graphite fiber ‡‡

5 Fiberglass/EpoxyFabric

Fabric, epoxy impreg glassfiber ‡‡‡

Panel Assy, Lower 228−50081 V001


7 Al Coated FiberglassFabric, epoxy impregwoven glass fiber, Alcoated †††

8 Kevlar/Epoxy Fabric Fabric, epoxy impregwoven aramid fiber ‡

9 Graphite/Epoxy Fabric Fabric, epoxy impregwoven graphite fiber ‡‡

10 Fiberglass/EpoxyFabric

Fabric, epoxy impreg glassfiber ‡‡‡


12 Cover 228−50073 0.040 (1.02) Alclad 2024−0† V003

− Item not shown.


† Heat treated per specification AMS−H−6088 to Cond T42 and aged to Cond T62.

†† Specification Vought 207−8−411, Type I, Class 2, Grade 3.

††† Specification Vought 207−7−466, Type I.

‡ Specification Vought 207−7−464, Style 285.




Jun 17/2003


‡‡ Specification Vought 207−8−448, Type II, Style 1.

‡‡‡ Specification Vought 207−7−425, Type V.





Jun 17/2003

ACCESS COWL − ALLOWABLE DAMAGE

1. General

No damage is allowed on the Access Cowl. If necessary, contact Short Brothers Technical Informationand Support (Technical Help Line 44 07850 770826).



Jun 17/2003


ACCESS COWL − REPAIRS

1. General

A. For repairs to the access cowl, refer to Shorts CMM 71−14−01, Access Cowls, except for theREOs listed below.

B. List of REOs




601R−71−14−001 Fan access panel − repair

601R−71−14−002 Fan access panel chafing repair

601R−71−14−003 Fan access panel − alternate fasteners

601R−71−14−1899 Insertion of drain hole in lower access cowl

601R−71−14−2029 Access cowl door leading edge corrosion/delamination

601R−71−14−2607 Lower access cowl − PDU access panel − louversbent/deformed



Jul 10/2006


CORE COWL FRAMES AND FORMERS − ALLOWABLE DAMAGE

1. General




Jun 17/2003


CORE COWL FRAMES AND FORMERS − REPAIRS

1. General

A. For repairs to the core cowl frames and formers, refer to Shorts CMM 71−12−01, Core CowlDoors, except for the REOs listed below.

B. List of REOs




601R−71−61−003 STOW switch bracket − modification



Mar 10/2006


CORE COWL SKIN AND PLATING − ALLOWABLE DAMAGE

1. General




Jun 17/2003


CORE COWL SKIN AND PLATING − REPAIRS

1. General

For repairs to the core cowl skin and plating, refer to Shorts CMM 71−12−01, Core Cowl Doors, exceptfor the REOs listed below:

A. List of REOs

The repairs listed below are only applicable to this subject. Details of these repairs are found inappropriate chapters of the Structural Generic Engineering Orders (SGREO) Manual,CSP−A−092.



601R−71−12−2518 Upper and Lower Core Cowl Door − Cracked/Piece Missingfrom Aft Edge of Outer Skin



Jul 10/2006


NACELLE/PYLON SERVICE STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the nose cowl side panel internal structure.

Refer to Figure 2 for the structural identification of the nose cowl side panel skin and plating.

Refer to Figure 3 for the structural identification of the fixed core cowl internal structure.

Refer to Figure 4 for the structural identification of the fixed core cowl skin and plating.

Refer to Figure 5 for the structural identification of the service pylon internal structure.



Feb 18/2003

rsr5

40

19

, cr

, 1

3/1

0/0

0

1

14

4

3

2

2

3

4

4


Nose Cowl Side Panel Internal Structure − Structural IdentificationFigure 1


Feb 18/2003

ITEM DESCRIPTION DRAWING MATERIAL REFERENCE FINISHCODE ♦ EFFECTIVITY

Panel Assy 228−50082

1 Longeron Extruded Al alloy 2024−T3511 †† V002

2 Support 0.063 (1.60) Alclad 2024−0 † ¶¶ V003

3 Support 0.090 (2.29) Alclad 7075−T6 ¶ V003

4 Edge Extruded Al alloy 2024−T62 ‡ V002


† Heat treated to Cond T42, and aged to Cond T62, per specification MIL−H−6088.

†† Specification Vought CVC10013−164AD (AMS−QQ−A−200).

¶ Specification AMS−QQ−A−250/13.

¶¶ Specification AMS−QQ−A−250/5.

‡ Specification Vought CVC10052−14AA.



Key to Figure 1


Feb 18/2003

rsr5

4033

, na,

04/

12/0

0

PYLON

1

XN155.32

XN121.60

XN151.14

CL


Nose Cowl Side Panel Skin and Plating − Structural IdentificationFigure 2 (Sheet 1)


Feb 18/2003

rsr5

40

40

, n

a,

04

/12

/00

335

3323

43

3335

3333

43

3335

3333

43

335

3323

43

−

3335

3333

43

5

−

−

0.082 (2.08)0.074 (1.88)

0.082 (2.08)0.074 (1.88)




Feb 18/2003

rsr5

40

41

, n

a,

01

/12

/00

33

5

33

3

43

335

3233

43

−

−

3

33

33

3

3

3

333333

33

5

33

3

43

3

33

33

3

3

3

33333

33

5

3

33

43

3

3

0.196 (4.98)0.170 (4.32)

0.196 (4.98)0.170 (4.32)




Feb 18/2003

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE

♦EFFECTIVITY

Panel Inst’l 228−50082

1 Panel Assy V001

− Adhesive Film ‡

2 Core 0.250 (6.35) phenolicreinforced aramid †

3 Kevlar/Epoxy Fabric ‡‡

4 Aluminum CoatedFiberglass Prepreg

‡‡‡

5 Epoxy Fiberglass ††


† Specification Vought 207–8–411, Class 2, Type I (3/16” hex.cell), Grade 3 (3 lbs dens.).

Ciba−Geigy (199950), HMX 3/16–3.0, or Hexcel Corp.(436785), HRH−10−3/16−3.0.

†† Specification Vought 207–7–425, Type V (MIL−C−9084, Class 2, Type III)

The Fiberite Corp. (340649), MBX7701−120−Z−6040 or Hexcel Corp.(436785), 120−F155−8−F69.

‡ Specification Vought 207–8–420.

American Cyanamid Company (065548), FM−300/.08 PSF.

‡‡ Specification Vought 207–7–464, Style 285.

BASF Structural Materials, Inc.(108358), Fabric Prepreg Epox Resin.

‡‡‡ Specification Vought 207–7–466.

Hexcel Corp.(436785), Aluminized Fabric P.



Key to Figure 2


Feb 18/2003

rsr5

4020

, pl,

09/0

1/01

The structure is symmetricalabout the aircraft centerline,unless shown differently.

NOTE

7

7

XN206.39

XN204.20

XN190.59

XN175.20

XN164.73 XN158.285

SKIN (REF)


Fixed Core Cowl Internal Structure − Structural IdentificationFigure 3 (Sheet 1)


Feb 18/2003

rsr5

4021, pl,

09/0

1/0

1

XN206.39

XN204.20

XN190.59

XN175.20

XN158.28

XN164.73

7

7

2

2

12

1

3

3

3

54

4

6

17

18

SKIN (REF)

23

2

XN175.20

VIEW LOOKING OUTBOARD

13

2

1

21

3 (REF)

24




Feb 18/2003

rsr5

4043, pl,

09/0

1/0

1

14

2

23

2

19

15

2020

19

16

XN175.20

XN190.59

XN190.59

3 (REF)

3 (REF)

3 (REF)




Feb 18/2003

rsr5

4044

, pl,

09/0

1/01

LH SIDE NACELLE

RH SIDE NACELLE

22

8 9

922

9

9

99

9

11

10

XN190.59

XN190.59

XN175.20



9

SKIN (REF)

SKIN (REF)




Feb 18/2003


Cowl Assy 228−50121

1 Longeron 0.050 (1.27) CRESPH15−7MO † ¶¶¶

S022

2 Clip 0.050 (1.27) CRESPH15−7MO † ¶¶¶

S022

3 Frame 0.050 (1.27) CRESPH15−7MO † ¶¶¶

S022

4 Closure 0.025 (0.64) CRES ♣ S022

5 Duct 0.032 (0.81) Alclad 2024−0††† ¶¶

V003

6 Closure Extruded Al alloy 2024−0 ††♣♣♣

V002

7 Splice 0.050 (1.27) CRESPH15−7MO † ¶¶¶

S022

8 Clip 0.063 (1.60) Alclad 2024−T3¶¶

V003

9 Bracket 0.063 (1.60) Alclad2024−T3 ¶¶

V003

10 Bracket 0.063 (1.60) Alclad 2024−0†† ¶¶

V003

11 Plate 0.063 (1.60) Alclad 2024−T3¶¶

V003

− Shim 0.005 (0.13) CRES ♥♥♥

12 Frame 228−50582 Steel 4340 ¶ ♠♠ D010

13 Hinge Support, Upr,Fwd

228−50123 CRES Investment Casting17−4PH ‡ ♣♣

S022

14 Hinge Support, Lwr,Fwd

228−50125 CRES Investment Casting17−4PH ‡ ♣♣

S022

15 Hinge Support, Upr,Ctr

228−50127 CRES Investment Casting17−4PH ‡‡

S022

16 Hinge Support, Lwr,Ctr


S022

17 Hinge Support, Upr,Aft


S022

18 Hinge Support, Lwr,Aft


S022




Feb 18/2003

19 Radius Block 228−50595 0.190 (4.83) CRES 17−4PH♠

S022 7003−7147

20 Tee Clip 228−50585

228−50560 ♠♠♠CRES Investment Casting17−4PH ♣♣

S022

21 Side Retainer 228−50191 CRES ♣ S010

22 Bracket 228−55410 0.063 (1.60) Alclad 2024−T3¶¶

V004

23 Tee Clip 228−50586

228−50596 ♠♠♠CRES Investment Casting17−4PH ♣♣

S022

24 Filler 228−50121 0.050 (1.27) Alclad 2024−0††† ¶¶ ♠♠♠

V003 ♥


† Heat treated to Rockwell C41 to C47 Cond TH1050 (190 ksi) per specification Vought CVA1−372.

†† Heat treated to Cond T42 per specification AMS−H−6088.

††† Heat treated to Cond T42 and aged to Cond T62 per specification AMS−H−6088.

‡ Homogenized and heat treated to 150 000 psi minimum tensile strength.

‡‡ Aged to Cond H1000 per specification Vought CVA1−372.

‡‡‡ Aged to Cond H1025 per specification Vought CVA1−372.

¶ Heat treated to Rockwell 033−C38 (150 ksi) per specification Vought CVA1−372.


¶¶¶ Specification AMS−5520.

♣ Specification AMS−5513, Type 304, Cond A.

♣♣ Specification Vought CVA1−513, Class B.

♣♣♣ Specification AMS−QQ−A−200.

♠ Specification AMS−5604.

♠♠ Specification AMS−6359, Cond A.

♠♠♠ Acceptable alternate is 0.050 (1.27) Alclad 2024–T3, per specification AMS−QQ−A−250/5.

♥ RH effectivity is 7003 only, and LH effectivity is 7003−8400.

♥♥ Acceptable alternate is Machined CRES Bar 17−4PH, per specification Vought CVA1−372.

♥♥♥ Specification AMS−5524, Type 316 ,Cond A.





Mar 10/2006

rsr5

40

34

, n

a,

04

/12

/00

XN208.39

XN201.825

XN190.59

XN177.27

XN164.73

XN158.285

XN175.20

1

XN208.39

XN201.825

XN190.59

XN177.37

XN158.285

XN175.20

2

XN164.73


Fixed Core Cowl Skin and Plating − Structural IdentificationFigure 4 (Sheet 1)


Feb 18/2003

rsr5

40

42

, n

a,

18

/12

/00

XN208.39

XN201.825

XN190.59

XN

177.37XN158.285

XN175.20

XN164.73

3

XN208.39

XN201.825

XN190.59XN

158.285

XN175.20

XN164.73

XN177.27

3

4

5

LEGEND

12

t = 0.030 (0.762)t = 0.022 (0.559)

t1

t1

t2

t2



1

2


Fixed Core Cowl Skin and Plating − Structural IdentificationFigure 4 (Sheet 2)


Feb 18/2003


1

Skin 228−50121 0.050 (1.27) CRESPH15–7MO†

S022 ††† 7003−7134

Skin 228−50121 0.050 (1.27) Titanium alloy††

S022 ††† 7135−7285

2 Skin 0.050 (1.27) Titanium alloy††

S022 ††† 7286−8400

3 Doubler 0.050 (1.27) CRESPH15−7MO † ¶¶¶

S022

4 Doubler 0.032 (0.81) CRESPH15−7MO †

S022 7003−7013

5 Doubler 0.032 (0.81) CRESPH15−7MO †

S022 7014−8400


† Specification AMS−5520.

†† Specification AMS−T−9046

††† 1 coat, interior only.



Key to Figure 4


Mar 10/2006

rsr5

40

22

, n

a,

05

/12

/00

XN154.70

2

3

114

14 12

57

69

51

16

15

1685

5 10

1413

XN177.17

11

4

17


Service Pylon Internal Structure − Structural IdentificationFigure 5


Feb 18/2003


1 Support 228−50453 1.500 (38.10) Al alloy 7075−T651¶

V003 7003−7177

228−50453 1.500 (38.10) Al alloy 7075−T7351¶

V003 7178−8400

2 Support Angle 228−50300 0.032 (0.81) CRES ‡‡‡ V024

3 Firewall 228−50310 CRES ††† V024

4 Z−section 228−50310 0.032 (0.81) CRES ‡‡‡ V024

5 Seal Retainer 228−50310 0.063 (1.60) Alclad 2024−T3 ¶¶ V003

6 Retainer 228−50310 0.032 (0.81) Alclad 2024−T3 ¶¶ V003

− Seal 228−50310 ♣

7 Seal 228−50310 ♣♣

8 Seal 228−50310 ♣♣♣

9 Seal 228−50310 ♠

10 Seal 228−50310 ♠♠

11 Fire Seal 228−50310 §§§ 7003−7123

7133−7133

‡ 7124−7132

7134−8400

12 Strap 228−50310 0.040 (1.02) CRES ††† V024

− Clip 228−50310 0.063 (1.60) Alclad 2024−T3 ¶¶ V003

− Packer ‡‡ 228−50310 ♠♠♠ 7350−7368

7417−8400

13 Slider Block 228−50909 Tribon Material CompositionPolybon L ††

7003−7049

228–50919 Tribon Material CompositionPolybon L ††

7050−8400

− Eccentric Bushing 228−50908 Machined CRES Bar 17−4PH † § V025

14 Support Rail 228−50904 ♦♦ V003 7003−7049

228−50918 ♦♦ V002 7050−8400

15 Service Pylon 228−50900 Al Casting A−356−T6 ¶¶¶ V015

16 Auxiliary SliderBlock

228−50911 Plastic Sheet, Phenolic, NylonFiber §§




Mar 10/2006

17 Support 228–50452 2.500 (63.50) CRES Bar 17–4PH§

V024 7003−7036

228–50454 2.500 (63.50) CRES Bar 17–4PH§

V024 7037−8400

− Item not shown.


♦♦ Specification Vought CVC10010−110CH.

† Aged to Cond H1025 (155 ksi), per specification Vought CVA1−372.

†† Tribon Bearing Co., 5581 West 169 St, Cleveland, OHIO 44142.

††† Specification AMS−5518, Type 301, Cond 1/2 Hard.

‡ Made from part number 5−264 supplied by Chase−Walton Elastomers Inc.

‡‡ Finished using diester resistant primer per specification Vought 207−9−431 to 208−9−77, and withgloss enamel per specification Vought 207−9−414 to 208−9−19 on all exposed edges.

‡‡‡ Specification AMS−5517, Type 301, Cond 1/4 Hard.



¶¶¶ Specification AMS−A21180.

§ Specification AMS−5643.

§§ Specification MIL−I−24768/9.

§§§ Specification Vought CVC10091−61.

♣ Specification Vought CVC10091−54.

♣♣ Specification Vought CVC10091−56.

♣♣♣ Specification Vought CVC10091−57.

♠ Specification Vought CVC10091−58.

♠♠ Specification Vought CVC10091−59.

♠♠♠ Specification Vought CVC571−B−008−F−082−C, or CVC571−D−008−F−082−C.





Mar 10/2006


NACELLE/PYLON SERVICE STRUCTURE − ALLOWABLE DAMAGE

1. General




Jun 17/2003


NACELLE/PYLON SERVICE STRUCTURE − REPAIRS

1. General

A. For repairs to the nacelle/pylon service structure, refer to Shorts CMM 71−13−01, Fixed Cowlsand Service Pylon, except for the REOs listed below.

B. List of REOs




601R−71−61−2652 Engine intake lipskin type II finish standard



Mar 10/2006


EXHAUST NOZZLE − STUCTURAL IDENTIFICATION

1. General

Refer to Figure 1 for the structural identification of the exhaust nozzle.



Feb 18/2003

rsr5

40

18

, lc

, 1

2/1

0/0

0

2

2

1

3 2

2

1


Exhaust Nozzle Tube — Structural IdentificationFigure 1


Feb 18/2003


Nozzle Assy, EngineExhaust 228−55030

1 Duct Half 0.025 (0.64) Inconel 625 † S002

2 Stiffener Half 0.020 (0.51) Inconel 625 † S002

3 Flange 228−55400 1.250 (31.75) Inconel 625†† ‡

S002


† Specification AMS−5599.

†† Specification AMS−5666.

‡ Acceptable alternate is Nickel alloy plate Inconel 625 per specification AMS−5599.



Key to Figure 1


Feb 18/2003


EXHAUST NOZZLE − ALLOWABLE DAMAGE

1. General




Jun 17/2003


EXHAUST NOZZLE − REPAIRS

1. General

A. For repairs to the exhaust nozzle, refer to Shorts CMM 78−11−00, Exhaust Nozzle Assembly.



Feb 18/2003


PYLONS MAIN STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the pylons main structure, refer to Figure 1.



Jun 22/2004

rsr5

4053

.dg,

ds/

lr, 2

/03/

04

SKIN AND PLATING54−51−31

PYLON BOXFRAMING STRUCTURE

54−51−14



A

A


Pylon Main Structure − Structural IdentificationFigure 1


Jun 22/2004

PYLONS MAIN STRUCTURE − ALLOWABLE DAMAGE

CAUTION: ALWAYS REFER TO THE SUBJECT PAGE BLOCK 101−199 APPLICABLE TO A GIVENSTRUCTURAL ELEMENT FOR SPECIFIC ALLOWABLE DAMAGE LIMITS. IF THIS ISNOT DONE, IT IS POSSIBLE THAT YOU WILL USE INCORRECT DATA.

YOU MUST REFER TO THE CONTINUING AIRWORTHINESS INSPECTIONREQUIREMENTS TO DETERMINE IF ADDITIONAL DAMAGE TOLERANCEINSPECTIONS APPLY (REF. SRM 51−13−00).

1. General

When specific damage limits are not supplied in this subject for a given structural element, use thegeneral allowable damage limits, (refer to SRM 54−00−00, Page Block 101−199).

CAUTION: MAKE SURE THAT THE REMOVED DAMAGE, INCLUDING ANY PREVIOUS DAMAGEREMOVAL, IS WITHIN ALLOWABLE LIMITS AT ANY SPECIFIC LOCATION. RECORDDAMAGE REMOVAL LOCATION.

2. Specific

For the allowable damage limits, refer to Figure 101 and Figure 102.



May 10/2010

rsr5

4060

.dg,

lr, 2

/03/

04

D(DEPTH OF DENT)

W (MINOR)

INITIALCONTOUR

W (MAJOR)IN THE LONGDIRECTION

For dent spacing limits, refer to Table in this Figure.

NOTE

A

A

A A

W (MINOR)IN THE SHORT

DIRECTION

DENTS MUST BE SMOOTHAND NOT HAVE SHARP CREASES,

GOUGES, OR CRACKS. FORDEPTH LIMIT CALCULATION,

REFER TO TABLE IN THIS FIGURE.

T(THICKNESS)

C

C

C C

W1 S W2 X

LEGEND

W1. Measured along W (major).W2. Measured along W (major).

S. Distance between dents.X. Distance to fastener.

B

BB B

No damage permitted

2D

D

DAMAGEREMOVAL LIMIT


Pylons Main Structure − Allowable DamageFigure 101


Jun 22/2004

DAMAGE REMARKS

Dents

Refer to Figure 101 for definitions relating to dents.

Dents are not permitted on extruded or machined parts

Dents must be smooth and not have sharp creases, gouges, cracks,or signs of damaged or loose rivets.

W(MINOR)/D must not be less than 20.

D/T must not be greater than 2.

Maximum W(MAJOR) = 40 x T.

Minimum value for X = greater of W2 or 1 inch (25.4mm).

Minimum value of S = greater of W1 or W2.

BlendingIn the case of blending parts with multiple flanges, damage ispermitted on one flange only for both the flange that is attached toother structural elements as well as for the free flange.

General No rework permitted in an area within a 2D radius around fasteners,refer to Figure 101.



Pylons Main Structure − Allowable DamageFigure 102


Jun 22/2004


PYLON BOX FRAMING STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the pylon box framing structure, refer to Figure 1.



Jun 22/2004

682 PLACES

A

A

rsr5

4054

, ds,

11/

11/0

3

672 PLACES

29

47 73

2 PLACES

92 PLACES

74 PLACES

84 PLACES

59

55

243 PLACES

FS654.50

23

13

724 PLACES

FS605.00

FS614.10

7448

2 PLACES

FS625.30

4

6

26

17

11

FS640.00

162 PLACES

5

66

302 PLACES

49

21

337576 77

NOTE

The structure is symmetricalaround the aircraft centerline,unless shown differently.


Pylon Box Framing Structure − Structural IdentificationFigure 1 (Sheet 1)


Jun 22/2004

3169

104 PLACES

12

32

36

33

35

38

24

FS682.00

2

3

1

54

7833

FS654.50

27

FS672.20

3470

4 PLACES

72

2018

4337

3839

12

25

1215

22

6

6

51

50

1

6

716

2

16

B

B

5856

56

5857

1

19

rsr5

4056

, ds,

11/

11/0

3

28

C

C

NOTE





Jun 22/2004

A44

4119

40

46

42

6

6

45

D

E

D

E

64

62

63

52

1465

6061

rsr5

4057

, ds,

11/

11/0

3

79

NOTE





Jun 22/2004

ITEM DESCRIPTION DRAWING MATERIAL REFERENCE

FIN-ISH

CODE♦

EFFECTIVI-TY

Pylon StructuralAssembly

601−37003

1 Seal Retainer 601−37003 0.032 (0.81) Titanium Sheet † T002 7003−7067

7069−7449

1 Seal Retainer 601−37003 0.032 (0.81) Titanium Sheet †† T002 7450−8400

2 Seal Retainer 601−37003 0.032 (0.81) Titanium Sheet † T002

3 Seal Retainer 601−37003 0.040 (1.02) Titanium Sheet † T002

4 Seal Retainer 601−37003 0.040 (1.02) clad 2024−T42 ††† A010

5 Seal Retainer 601−37003 0.040 (1.02) clad 2024−T42 ††† A011

6 Seal 601−37003 8269−1, Hercules AircraftProducts

7 Laminated Shim, Rib,Forward

601−37003 0.063 (1.60) CRES Shim Stock ‡ X120

8 Laminated Shim, Brace,Aft

601−37003 0.063 (1.60) CRES Shim Stock ‡ X120

9 Laminated Shim, Brace,Fwd

601−37003 0.063 (1.60) CRES Shim Stock♣♣

X110

10 Laminated Shim, Rib,Aft

601−37003 0.032 (0.81) CRES Shim Stock ‡ X120

11 Angle 601−37003 0.050 (1.27) clad 2024−T42 ††† A010

12 Angle 601−37003 0.050 (1.27) clad 2024−T42 ††† A011

13 Angle 601−37003 0.050 (1.27) clad 7075−T62 ‡‡‡ A011

14 Web 601−37003 0.090 (2.28) clad 7075−T62 ‡‡‡ A011 7003−7067

7069−7909

15 Web 601−37003 0.040 (1.02) clad 2024−T3 ††† A011

16 Angle 601−37003 0.63 (0.81) clad 7075−T62 ‡‡‡ A010

17 Stiffener 601−37003 0.040 (1.02) clad 7075−T62 ‡‡‡ A010

18 Web 601−37003 0.040 (1.02) Titanium Sheet † T002

19 Angle 601−37003 0.040 (1.02) Titanium Sheet † §

20 Stiffener 601−37003 0.040 (1.02) Titanium Sheet † T002

21 Stiffener 601−37003 S−6547 (B0510073AA) extruded2024−T3511 Al Alloy

A012




Mar 10/2006


FIN-ISH

CODE♦

EFFECTIVI-TY

22 Shim 601−37003 0.050 (1.27) Titanium Sheet † T002/X040

23 Spacer 601−37003 0.125 (3.17) clad 2024−T42 ††† A010

24 Radius Block 601−37003 0.100 (2.54) CRES, Type 301,1/2 Hard, MIL−S−5059

S020

25 Stiffener 601−37003 0.063 (1.60) clad 7075−T62 ‡‡‡ A011

26 Angle 601−37003 0.063 (1.60) clad 2024−T42 ††† A011

27 Shim 601−37003 0.070 (1.78) Titanium Sheet † T002

28 Cover (LH Pylon only) 600−12089 0.200 (5.08) Al Alloy 6061−0 ♣♣ A100

29 Spar, Forward Member 601−37018 Machined 7075−T73651 Al alloyplate §§

A012

30 Bushing, Center 601−37050 15−5PH CRES Bar, AMS 5659,Cond H1000

S011

31 Spar 601−37025 S−4935 extruded Titanium,MIL−T−81556

T002 7003−7067

7069−7679

32 Stiffener 601−37007 0.063 (1.60) Titanium Sheet §§§ T002

33 Clip 601−37003 0.050 (1.27) clad 2024−T42 ††† A010

33A Clip 601−37003 0.050 (1.27) clad 2024−T42 ‡‡‡ A011

34 Cap Angle 601−37029 Machined Titanium Bar ¶ T002 7003−7067

7069−7160

35 Rib, Aft Engine Mount,Inboard

601−37009 Machined Titanium Bar ¶ T002

36 Angle, Upper 601−37023 Machined Titanium Bar ¶ T002

37 Web 601R37011 0.032 (0.81) Titanium Sheet ¶¶ T002

38 Cap 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002

39 Doubler 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002

40 Channel 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002

41 Shim 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002

42 Clip 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002

43 Stiffener 601−37011 0.032 (0.81) Titanium Sheet ¶¶ T002




Mar 10/2006


FIN-ISH

CODE♦

EFFECTIVI-TY

44 Angle 601−37011 0.063 (1.60) PH17−7 CRES,MIL−S−25043, COND H1050

S002


S002


S002

47 Drag Brace 601−37030 7075−T73651 Al Alloy Plate §§ A012 7003−7067

7069−7665

48 Angle, Pylon toFuselage, Upper

601−37051 0.080 (2.03) clad 2024−T42 ††† A010 7003−7067

7069−7098


601−37051 0.050 (1.27) Titanium Sheet §§§ T002

50 Bushing 601−37057 17−4PH CRES Bar, AMS 5622 S010

51 Washer 601−37058 CRES, Type 303, Cond A S010

52 Fitting 601−37060 Machined 7075−T73651 Al AlloyPlate §§

A012

53 Spar 601−37026 S4936 extruded Titanium,MIL−T−81556

T002/X040

7003−7067

7069−7679

54 Doubler 601−37003 0.050 (0.127) Titanium Sheet † T002/T020

55 Angle 601−37003 0.040 (1.02) clad 2024−T42 ††† A010

56 Separator 601R37138 0.032 (0.81) Titanium Sheet¶¶¶ T002

57 Clip 601R37138 0.032 (0.81) Titanium Sheet ¶¶¶ T002

58 Strip 601R37138 0.125 (3.18) PTFE Sheet Molded,AMS3367 Type 1

E002 7382−8400

59 Fitting, Splice 601−37031 Machined Titanium Bar ¶ T002/X040(2coats)

60 Angle 601−37003 0.050 (1.27) clad 2024−T42 ††† A010 7003−7067

7069−7909

61 Angle 601R350072 Machined 7475−7351 Al Alloyplate ‡‡

A012 7910−8400

62 Laminated Shim 601−37003 S10249−94−92−95C A010 7910−8400




Mar 10/2006


FIN-ISH

CODE♦

EFFECTIVI-TY



65 Web 601R350081 0.100 (2.54) clad 7075−T62 ‡‡‡ A010 7910−8400

66 Spar, Aft Member 601−37019 Machined 7075−T73651 Al Alloyplate §§

A012

67 Bushing, Upper 601−37038 15−5PH CRES Bar, AMS 5659,Cond H1000

S011

68 Bushing, Lower 601−37041 15−5PH CRES Bar, AMS 5659,Cond H1000

S011

69 Spar 601R37025 S−6407 extruded Titanium,MIL−T−81556

T002 7680−8400

70 Cap Angle 601−37029 S−5537 extruded Titanium,MIL−T−81556

T002 7161−7669

71 Rib, Aft Engine Mount,Outboard

601−37010 Machined Titanium Bar ¶ T002

72 Angle, Lower 601−37024 Machined Titanium Bar ¶ T002

73 Drag Brace 601−37030 7075−T73651 Al Alloy Plate §§ A013 7666−8400


601−37051 0.080 (2.03) 6013−T6 Al AlloySheet, AMS 4347

A010 7099−8400

75 Angle, Pylon toFuselage, Lower

601−37051 0.080 (2.03) clad 2024−T42 ††† A010 7003−7067

7069−7101


601−37051 0.080 (2.03) 6013−T6 Al AlloySheet, AMS 4347

A010 7102−8400


601−37051 0.063 (1.60) Titanium Sheet §§§ T002

78 Spar 601R37026 S−6408 extruded Titanium,MIL−T−81556

T001 7680−8400

79 Shim 601−37003 S10249−40−80−89C A010

♦ Refer to SRM 51−21−16

− ITEM not shown

† Specification MIL−T−9046, Type III, Comp C, Cond A

†† Specification MIL−T−9046, Comp CP−1

††† Specification QQ−A−250/5




Mar 10/2006


FIN-ISH

CODE♦

EFFECTIVI-TY

‡ Specification MIL−S−22499 Comp 3, Type I, Class 2

‡‡ Bombardier Specification CMS 516−02 (BAMS 516−002)

‡‡‡Specification QQ−A−250/13

§ T002 followed by X040

§§ Bombardier Specification CMS 516−03 (BAMS 516−003)

§§§ Specification MIL−T−9046, Type I, Comp B, Annealed

¶ Bombardier Specification CMS 514−02 (BAMS 514−002)

¶¶ Specification MIL−T−9046, Type III, Comp AB−1, Cond A

¶¶¶ Specification MIL−T−9046, Comp CP−1, Annealed

♣ Specification MIL−S−22499 Comp 1, Type I, Class 2

♣♣ Specification QQ−A−250/11

NOTE: All dimensions are in inches (millimeters) unless otherwise specified.




Mar 10/2006


PYLON BOX FRAMING STRUCTURE − ALLOWABLE DAMAGE



1. General

When specific damage limits are not supplied in the subject for a given structural element, use thegeneral allowable damage limits given in this chapter (refer to SRM 54−00−00, Page Block 101−199).


2. Specific

For the allowable damage limits, refer to Figure 101.



May 10/2010

rsr5

4004

.dg,

ds/

lr, 1

1/03

/04

A

A

2

FS654.50

B

FS682.00

FS605.00

1

BNOTE

2D

D

DAMAGEREMOVAL LIMIT

1 No rework permitted in an area withina 2D radius around fasteners.

1

No damage permitted


Pylon Box Framing Structure − Allowable DamageFigure 101


Jun 22/2004

ITEM DESCRIPTION REMARKS

1 Firewall− upper and lower caps No blending is permitted on the upper andlower caps.

2 Spar web at FS 654.50 No material removal permitted.

NOTE: No rework permitted in an area within a 2D radius around fasteners. Refer to Figure 101.



Jun 22/2004


PYLON BOX FRAMING STRUCTURE − REPAIRS

1. General

A. For repairs to the pylon box framing structure, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01), except for the REOs listed below.

B. List of REOs




601R−54−50−006 Repair to forward engine mount spar, left and right sides

601R−54−50−036 Damage to production riser of the aft engine mount

601R−54−50−047 Deviation to REO 601R−54−50−036, alternate procedure forsolid film lubricant



Mar 10/2006


PYLON−BOX ATTACH/ATTACHED FITTINGS − ALLOWABLE DAMAGE

1. General

A. For the allowable damage limits for the pylon−box attach/attached fittings, contact BombardierAerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003


PYLON−BOX ATTACH/ATTACHED FITTINGS − REPAIRS

1. General

A. For repairs to the pylon box attached fittings, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003


PYLON BOX SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the pylon box skin and plating, FS605.00 to FS682.00, refer to Figure1.



Jun 22/2004

rsr5

4052

.dg,

om

, 10/

12/0

3

VIEW LOOKING UP

1

1

1

2

5

4

3

2

63

6

7

3

88

8

FS682.00

FS605.00


Pylon Box Skin and Plating − Structural IdentificationFigure 1


Jun 22/2004


FINISHCODE

♦EFFEC-TIVITY

Pylon Structural Assy 601−37003

1 Skin, Chem−milled 601−37003 0.080 (2.03) Titanium Sh,MIL−T−9046, Type III, Comp C,Cond A

†

2 Door, Chem−milled 601−37003 0.090 (2.28) Titanium Sh,MIL−T−9046, Type III, Comp C,Cond A

†

3 Door, Chem−milled 601−37003 0.090 (2.28) Titanium,MIL−T−9046, Type AB−1,Annealed

†

4 Door, Chem−milled 601−37003 0.090 (2.28) clad 2024−T3 †† A010

5 Skin, Chem−milled 601−37003 0.080 (2.03) clad 2024−T3 †† A010

6 Door, Chem−milled 601−37003 0.080 (2.03) Titanium Sh,MIL−T−9046, Type III, Comp C,Cond A

†

7 Door, Chem−milled 601−37003 0.080 (2.03) clad 2024−T3 †† A010

8 Angle 601−37003 0.032 (0.81) Titanium,MIL−T−9046, Type CP−1,Annealed

T002

♦ Refer to SRM 51−21−16.

† Inner surface − T002, outer surface − sandblasted and finished with one layer of green epoxy primer(CMS 565−01 (BAMS 565−001)).

†† Specification QQ−A−250/5.

††† Specification QQ−A−250/13.

NOTE: All dimensions are in inches (millimeters) unless specified otherwise .


Key to Figure 1


Jun 22/2004


PYLON BOX SKIN AND PLATING − ALLOWABLE DAMAGE



1. General

When specific damage limits are not supplied in the subject for a given structural element, use thegeneral allowable damage limits in this chapter (refer to SRM 54−00−00, Page Block 101−199).


2. Specific




May 10/2010

rsr5

4006

.dg,

ds/

lr, 1

0/03

/04

A

A

FS605.00

FS619.18

FS640.00FS625.30

FS654.50

FS682.00

REMARKS

Maximum blend depth permitted

Refer to SRM 51−13−01

DAMAGE DEPTHCODE

in.

0.005

mm

0.13

− −

General Dents are not permitted on any structure. For fullinstructions on treatment of allowable damage,refer to SRM 51−12−00.

FS672.20

UPPERSKIN

UPPERSKIN

UPPERSKIN

LOWERSKIN

LOWERSKIN

LOWERSKIN


Pylon Box Skin and Plating − Allowable DamageFigure 101


Jun 22/2004

PYLON BOX SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the pylon box skins and plating, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003


PYLON SECONDARY STRUCTURE − STRUCTURAL IDENTIFICATION

1. General

A. The structural identification of the Pylon Secondary Structure is given in Figure 1.



Dec 22/2003

rsr5

4051

.dg,

yf,

23/1

0/03

A

A

54−62−31

54−62−14

54−50−00 (REF)

54−61−14

54−61−31

54−62−31


Pylon Secondary Structure − Structural IdentificationFigure 1


Dec 22/2003

PYLON SECONDARY STRUCTURE − ALLOWABLE DAMAGE



1. General

When specific damage limits are not supplied in the subject for a given structural element, use thegeneral allowable damage limits given in this chapter (refer to SRM 54−00−00, Page Block 101−199).


2. Specific




May 10/2010

rsr5

4060

.dg,

lr, 2

/03/

04

D(DEPTH OF DENT)

W (MINOR)

INITIALCONTOUR

W (MAJOR)IN THE LONGDIRECTION

For dent spacing limits, refer to Table in this Figure.

NOTE

A

A

A A

W (MINOR)IN THE SHORT

DIRECTION

DENTS MUST BE SMOOTHAND NOT HAVE SHARP CREASES,

GOUGES, OR CRACKS. FORDEPTH LIMIT CALCULATION,

REFER TO TABLE IN THIS FIGURE.

T(THICKNESS)

C

C

C C

W1 S W2 X

LEGEND

W1. Measured along W (major).W2. Measured along W (major).

S. Distance between dents.X. Distance to fastener.

B

BB B

No damage permitted

2D

D

DAMAGEREMOVAL LIMIT


Pylon Secondary Structure − Allowable DamageFigure 101 (Sheet 1)


Jun 22/2004

DAMAGE REMARKS

Dents

Refer to sheet 1 for definitions relating to dents.

Dents are not permitted on extruded or machined parts.


W(MINOR)/D must not be less than 20.

D/T must not be greater than 2.

Maximum W(MAJOR) = 40 x T.

D = Depth of dent.

T = Thickness of material.

W = Width of dent.

Minimum value for X = greater of W2 or 1 inch (25.4mm).

Minimum value of S = greater of W1 or W2.

BlendingIn the case of blending parts with multiple flanges, damage is permitted on one flangeonly for both the flange that is attached to other structural elements as well as for thefree flange.

General No rework permitted in an area within a 2D radius around fasteners, refer to Figure 101.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00. Use anapproved repair (refer to SRM 51−13−00), to repair damage that does not agree with the allowabledamage limits.


Pylons Secondary Structure − Formed Parts − Allowable DamageFigure 101 (Sheet 2)


Jun 22/2004


FORWARD STRUCTURE FRAMING − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the pylon forward structure framing, refer to Figure 1.



Jun 22/2004

rsr5

4047

.dg,

rm

/lr, 1

3/01

/04

1

2

45

6

7

8(2 PLACES)

9(2 PLACES)

10

11

FS589.00

FS596.60

FS605.00

3

5

2

2

1

12 62

1617

11

14

2

13

7

15

7

147

2

12


NOTE

PBL−8.340

PBL−3.000


Forward Structure Framing − Structural IdentificationFigure 1


Jun 22/2004


Nose Assembly − PylonStructure

601−37004

1 Rib 601−37004 0.040 (1.02) clad 2024−T42 A010

2 Angle 601−37004 0.040 (1.02) clad 2024−T42 A010

3 Angle 601−37004 0.040 (1.02) Alclad 2024−T42 A010 7003−7067

7069−7239

4 Angle 601−37004 0.040 (1.02) Alclad 2024−T42 A010 7240−8400

5 Channel 601−37004 0.040 (1.02) Alclad 7075−T62 A010


7 Angle 601−37004 0.050 (1.27) Alclad 7075−T62 A010

8 Clip 601−37004 0.040 (1.02) Alclad 2024−T42 A010


10 Shim 601−37004 0.040 (1.02) Alclad 2024−T42 A010

11 Fitting 601−37048 7050−T7451 Al Alloy PlateCMS 516−03

A012

12 Fuselage Attach Angle 601−37051 0.040 (1.02) Alclad 2024−T42 A010

13 Support 601−37004 0.040 (1.02) Alclad 2024−T42 A010

14 Support 601−37004 0.040 (1.02) Alclad 2024−T42 A010 7003−7067

7069−7196

15 Support 601−37004 0.040 (1.02) Alclad 2024−T42 A010 7197−8400

16 Doubler 601−37004 0.050 (1.27) Alclad 2024−T42 A010

Nut Plate 601−37004 RM52LHA3006M−4−02

Nut Plate 601−37004 MS21059L3

Nut Plate 601−37004 NAS1870CL3−5

17 Tee 601−37004 S−6737−V Extd 2024−T62 Al.Alloy

A010

18 Seal Retainer 601−37004 0.032 (0.81) Alclad 2024−T42 A010

19 Seal 601−37049(SCD)

Armet Part No. AEJ 1282−3

20 Seal Retainer 601−37004 0.040 (1.02) Alclad 2024−T42 A010

21 Seal Support 601−37004 0.313 (7.95), Nylon 6/6 perL−P−410−A




Mar 10/2006






Mar 10/2006

FORWARD STRUCTURE FRAMING − ALLOWABLE DAMAGE



1. General

When specific damage limits are not supplied for a given structural element, use the general allowabledamage limits given in this chapter (refer to SRM 54−00−00, Page Block 101−199).


2. Specific

For the general allowable damage limits, refer to Figure 101.



May 10/2010

rsr5

4002

.dg,

yf/l

r, 1

8/03

/04

A

B − B

NOTESThe structure is symmetrical around theaircraft centerline, unless shown differently.

2 No rework permitted in an area within a 2D

1.

radius around fasteners.

2

No damage permitted

FS589.00

FS596.60

FS605.00

1

B

B

2D

D

DAMAGEREMOVAL LIMIT


Forward Structure Framing − Allowable DamageFigure 101 (Sheet 1)


Jun 22/2004

ITEM DESCRIPTION DRAWING REMARKS

1 Channel FS589.00 601−37004 No damage permitted for the whole channel atFS589.00.

No rework permitted in an area within a 2D radius around fasteners, refer to Figure 101.

NOTE: Refer to SRM 54−00−00 for all instructions on treatment of allowable damage limits not supplied inthis subject.


Forward Structure Framing − Allowable DamageFigure 101 (Sheet 2)


Jun 22/2004


FORWARD STRUCTURE FRAMING − REPAIRS

1. General

A. For repairs to the forward structure framing, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01).



Feb 18/2003


FORWARD STRUCTURE SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

For the structural identification of the forward structure skin and plating, refer to Figure 1.



Jun 22/2004

rsr5

4062

.dg,

yf/l

r, 2

6/01

/04

A

54−61−14 (REF)

A

1

1


Forward Structure Skin and Plating − Structural IdentificationFigure 1


Jun 22/2004

ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISH

CODE ♦ EFFECTIVITY

Nose assembly pylonstructure

601−37004

1 Skin 601−37004 0.090 (2.29) Alclad2024−T42 †

A010


† Specification QQ−A−250/5.



Key to Figure 1


Jun 22/2004


FORWARD STRUCTURE SKIN AND PLATING − ALLOWABLE DAMAGE



1. General

The general allowable damage limits of 10% given in SRM 54−00−00, Page Block 101−199, may notapply to this section. You must replace the general limits of 10% with the limits specified for each itemidentified in Section 2 below. For the allowable damage limits for any items not specified in Section 2,contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01).


2. Specific




May 10/2010

rsr5

4008

.dg,

yf/l

r, 1

1/03

/04

A

54−61−14 (REF)

A1

1

NOTESThe structure is symmetrical around theaircraft centerline, unless shown differently.

2 No rework permitted in an area within a 2D

1.

radius around fasteners.

No damage permitted

2D

D



Forward Structure Skin and Plating − Allowable DamageFigure 101 (Sheet 1)


Jun 22/2004

ITEM DESCRIPTION DAMAGE REMARKS

1 Skin

Scratches, nicks, gougesand corrosion

Maximum blend depth is 0.005 (0.13).

Cracks Not permitted

Dents

Permitted. Maximum depth of dent is 0.080(2.03). Refer to SRM 54−60−00, Page Block101−199. Maximum depth of dent is 0.080(2.03).

Holes and punctures Permitted. Refer to SRM 54−00−00, PageBlock 101−199.

NOTE: For full instructions on the treatment of allowable damage, refer to SRM 51−12−00.

NOTE: For the removal of corrosion damage, refer to SRM 51−21−06.

NOTE: All dimensions are given in inches followed by millimeters in parenthesis.

NOTE: No rework permitted in an area within a 2D radius around fasteners. Refer to Figure 101.


Forward Structure Skin and Plating – Allowable DamageFigure 101 (Sheet 2)


Jun 22/2004


FORWARD STRUCTURE SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the forward structure skin and plating, contact Bombardier Aerospace RegionalAircraft, Customer Support (refer to SRM 51−13−01).



Feb 18/2003


AFT STRUCTURE FRAMING − STRUCTURAL IDENTIFICATION

1. General

A. For the structural identification of the aft structure framing in this section, refer to figures asfollows:

Refer toFigure 1 for the Kevlar aft structure framing.

Refer to Figure 2 for the graphite aft structure framing.



May 10/2010

rsr5

4084

.dg,

sd,

jun3

0/20

08

20

2

12

14

24

17

16

13

1

5

7

3

4

8

96

11

15

18

19

NOTE


10

23

22

21

FWD


Pylon Aft Structure Framing − Structure IdentificationFigure 1 (Sheet 1)


May 10/2010

37

36

32

33

35

rsr5

4085

.dg,

st/s

r, a

pr09

/200

8

41

46

39

48

45

4038

4742

43

44

49

2526272829303134




May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY

Rear Assembly −Pylon Structure

601−37112−1009,−1010

†


601−37112−1011,−1012

††


601−37112−1013,−1014

‡


601−37112−1015,−1016

‡‡

1 Channel 601−37012−15,−16

Kevlar CMS532−03Type I

NA Ψ

2 Channel 601−37112−37,−38


NA Ψ

3 Channel Rib 601−37112−7, −8 Kevlar CMS532−03Type I

NA Ψ

4 Channel Rib 601−37112−9, −10 Kevlar CMS532−03Type I

NA Ψ

5 Channel 601−37112−11,−12


NA Ψ

6 Angle 601−37012−97,−98

0.063 (1.60) 2024−T42AL Alloy Clad SheetQQ−A−250/5

A010 Ψ

7 Backing Strip 601−37012−113,−114


A010 Ψ

8 Backing Strip 601−37012−115 0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5

A010 Ψ

9 Clip 601−37012−17,−18


A010 Ψ

10 Clip 601−37012−19,−20


A010 Ψ

11 Clip 601−37012−25,−26


A010 Ψ

12 Clip 601−37012−27,−28


A010 Ψ




May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY

13 Seal, Top 601−37012−79,−80

Silicone Rubber Haveg#7093 CMPD−H−406Dacron Fabric F−799Plain Weave

NA Ψ

14 Seal, Lower Fwd 601−37012−81,−82


NA Ψ

15 Seal, Lower Aft 601−37012−83,−84


NA Ψ

16 Seal Retainer, Top 601−37012−85,−86


A010 Ψ

17 Seal Retainer,Lower Fwd

601−37012−87,−88


A010 Ψ

18 Seal Retainer,Lower Aft

601−37012−89,−90


A010 Ψ

19 Plate 601−37012−107 0.016 (0.40) AMS5510Comp 321 orAMS5512 Comp 347

S010 Ψ

20 Plate 601−37012− 109 0.032 (0.81) AMS5510Comp 321 orAMS5512 Comp 347

S010 Ψ

21 Fitting 601−37053−1, −2 4130 Alloy Steel PlateMIL−S−18729 Cond N

D013 Ψ

22 Radius Block 601−37012−21,−22


A010 Ψ

23 Radius Block 601−37012−23,−24


A010 Ψ

24 Clip 601−37012−77,−78


A010 Ψ

Pylon StructureAssembly AftDetachable

601−37066−1, −2 7003−7067

7069−7135




May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY


601−37066−101,−102

7136−7863


601−37066−31,−32

7864−7990

8000−8037


601−37066−89,−90

8038−8400

25 Skin (1 lam.) 601−37066−13 CMS532−05 Class I NA 7003−7067

7069−7863

25A Skin (1 lam.) 601−37066−41 CMS532−19 Class II NA 7864−7990

8000−8400


7069−7863


8000−8400


7069−7863


8000−8400


7069−7135

28A Skin (1 lam.) 601−37066−29 CMS532−05 Class I NA 7136−7863

28B Skin (1 lam.) 601−37066−53 CMS532−19 Class II NA 7864−7990

8000−8400


7069−7863


8000−8400


7069−7863


8000−8400




May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY


7069−7863


8000−8400

32 Channel (4 lams.) 601−37066−7, −8 CMS532−05 Class I NA 7003−7067

7069−7863

32A Channel (4 lams.) 601−37066−37,−38

CMS532−19 Class II NA 7864−7990

8000−8037

32B Channel (4 lams.) 601−37066−95,−96

CMS532−19 Class II NA 8038−8400

33 Channel (4 lams.) 601−37066−9, −10 CMS532−05 Class I NA 7003−7067

7069−7863

33A Channel (4 lams.) 601−37066−39,−40

CMS532−19 Class II NA 7864−7990

8000−8400

34 Shell 601−37066−5, −6 NA NA 7003−7067

7069−7135

34A Shell 601−37066−105,−106

NA NA 7136−7863

34B Shell 601−37066−35,−36

NA NA 7864−7990

8000−8400

35 Block 601−37066−27 CMS 533−01 5%Carbon added,(TEFLO) Etched OneSide

NA 7003−7067

7069−7990

8000−8037

35A Block 601R37162−1 0.375 (9.53)MIL−1−24768/18

¶ 8038−8400

36 Seal 601−37005−29,−30

Make From No.8269−1 Seal−FirewallNode

NA

37 Seal 601−37005−31,−32

Make From No.8269−1 Seal−FirewallNode

NA

Trailing EdgeAssembly − PylonStructure

601−37013−1, −2




May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY

38 Seal 601−37013−21,−22

Silicone Rubber CMPDH406 Dacron FabricF−799 Haveg 7093

NA

39 Honeycomb Core 601−37013−9, −10 1.50 (38.10)Honeycomb (Nomex)CMS539−01 Type I

NA

40 Filler Block 601−37013−17,−18

0.620 (15.75)Phenolic−Cotton SheetMIL−P−15035 TypeFBG

NA

41 Filler Block 601−37013−23,−24

0.620 (15.75)Phenolic−Cotton SheetMIL−P−15035 TypeFBG

NA

42 Doubler 601−37013−19 0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5

A010

43 Skin, Lower 601−37013−3, −4 Kevlar FabricCMS532−01 Type IClass II

E002/E104¶¶

44 Screen (120 mesh) 601−37013−11,−12

0.004 (0.10) DiameterWire 5056 RR−W−360Aluminum Screen 120Mesh Type I Class II

NA

45 Skin, Upper 601−37013−5, −6 Kevlar FabricCMS532−01 Type IClass II

E002/E104¶¶

46 Screen (120 mesh) 601−37013−13,−14

0.004 (0.10) DiameterWire 5056 RR−W−360Aluminum Screen 120Mesh Type I Class II

NA

47 Closeout Rib 601−37013−15,−16

Kevlar FabricCMS532−01 Type IClass II

E002/E104¶¶

48 Closeout Rib 601−37013−25,−26

Kevlar FabricCMS532−01 Type IClass II

E002/E104¶¶

49 Channel 601−37013−7, −8 Kevlar FabricCMS532−01 Type IClass II

− Item not shown.





May 10/2010


ENCEFINISH

CODE ♦EFFECTIV-

ITY

† 7045−7045, 7047−7047, 7049−7049, 7051−7051, 7054−7054, 7058−7058, 7060−7060, 7065−7065,7071−7071, 7074−7074, 7078−7078, 7082−7083, 7087−7087, 7089−7089, 7095−7098, 7107−7107,7112−7112, 7115−7115, 7118−7118, 7120−7120, 7124−7124

†† 7003−7044, 7046−7046, 7048−7048, 7050−7050, 7052−7053, 7055−7057, 7059−7059, 7061−7064,7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7081, 7084−7086, 7088−7088, 7090−7094,7099−7106, 7108−7111, 7113−7114, 7116−7117, 7119−7119, 7121−7123, 7125−7135

‡ 7172−7173, 7175−7175, 7178−7178, 7181−7181, 7185−7185, 7191−7191, 7195−7195, 7202−7202,7208−7208, 7217−7218

‡‡ 7136−7171, 7174−7174, 7176−7177, 7179−7180, 7182−7184, 7186−7190, 7192−7194, 7196−7201,7203−7207, 7209−7216, 7219−7810, 7812−7833, 7835−7847, 7849−7869

Ψ 7003−7067,7069−7810,7812−7833, 7835−7847, 7849−7869

¶ Abrade surface with fine grid sand paper (180 or finer), solvent clean per BAPS 180−009, apply 1 coatof primer/BAMS 565−001 per BAPS 138−043.

¶¶ Finish Inside−E002, Finish Outside−E104

Notes: All dimensions are given in inches followed by millimeters in parentheses.




May 10/2010

rsr5

4086

.dg,

sd,

jun3

0/20

0839

40

44

FWD

43

48

45

38

41

1

4649

21

42

12

34

27

50

47

NOTE


5351

52




May 10/2010

rsr5

4087

.dg,

sd,

jun2

9/20

07

4578

10

TOOL FACE

345678

TOOL FACE11




May 10/2010

rsr5

4088

.dg,

sd,

jun3

0/20

08

4578

3457811

34567811

3457811

4578

457811

4578

245789TOOL FACE

TOOL FACE




May 10/2010

rsr5

4089

.dg,

sd,

jun3

0/20

08

181615141318

191314151619

TOOL FACE




May 10/2010

171314151620

TOOL FACE

13141516

rsr5

4090

.dg,

vh,

jun3

0/20

08




May 10/2010

2223242526

TOOL FACE

TOOL FACE

232425

rsr5

4091

.dg,

vh,

jun3

0/20

08




May 10/2010

rsr5

4092

.dg,

vh,

jun3

0/20

08

31302928

333130292832

TOOL FACE

TOOL FACE




May 10/2010

353637

TOOL FACE

rsr5

4093

.dg,

vh,

jun3

0/20

08




May 10/2010


ENCEFINISH

CODE ♦EFFECTIVI-

TY


601R37139−1, −2 7811−7811

7834−7834

7848−7848

7870−7990

8000−8062


601R37139−121,−122

8063−8400

1 Rib, Inboard 601R37142−1, −2 E002 7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

1A Rib, Inboard 601R37142−23, −24 E002 8077−8400

2 Glass Fabric 601R37142−003,−004

CMS532−06 Style 120 NA Ψ

3 Glass Fabric 601R37142−005,−006

CMS532−06 Style 120 NA 7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

3A Glass Fabric 601R37142−025,−026

CMS532−06 Style 120 NA 8077−8400

4 Graphite Fabric 601R37142−007,−008

CMS532−19 Class II NA Ψ




CMS532−19 Class II NA 7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

6A Graphite Fabric 601R37142−027,−028

CMS532−19 Class II NA 8077−8400






May 10/2010


ENCEFINISH

CODE ♦EFFECTIVI-

TY



9 Glass Fabric 601R37142−017,−018


10 Glass Fabric 601R37142−019,−020


11 Glass Fabric 601R37142−021,−022

CMS532−06 Style 120 NA 7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

11A Glass Fabric 601R37142−029,−030

CMS532−06 Style 120 NA 8077−8400

12 Rib, Outboard 601R37143−1, −2 E002 Ψ









17 Glass Fabric 601R37143−011,−012


18 Copper Foil 601R37143−013,−014

CMS553−01 Class IIType II GR 4

NA Ψ

19 Copper Foil 601R37143−015,−016

CMS553−01 Class IIType II GR 4

NA Ψ

20 Glass Fabric 601R37143−021,−022


21 Spar, Fwd 601R37144−1, −2 E002 Ψ

22 Glass Fabric 601R37144−003,−004









May 10/2010


ENCEFINISH

CODE ♦EFFECTIVI-

TY





27 Spar, Mid 601R37145−1, −2 E002 Ψ









32 Glass Fabric 601R37145−011,−012


33 Glass Fabric 601R37145−013,−014


34 Spar, Aft 601R37146−1, −2 E002 Ψ







38 Angle 601−37012−19, −20 0.063 (1.60)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

39 Radius Block 601R37013−1, −2 0.160 (4.06)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

40 Radius Block 601−37012−23, −24 0.160 (4.06)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

41 Clip 601R37128−1, −2 0.063 (1.60)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ




May 10/2010


ENCEFINISH

CODE ♦EFFECTIVI-

TY

42 Clip 601R37129−1, −2 0.063 (1.60)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

43 Angle 601−37012−97, −98 0.063 (1.60)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

− Shim 601−37012−103 0.032 (0.81) ALMIL−S−22499 Comp 1Type I Class II

X110 Ψ

− Shim 601−37012−105 0.032 (0.81) ALMIL−S−22499 Comp 1Type I Class II

X110 Ψ

44 Fitting 601R37053−1, −2 4130 Alloy SteelMIL−S−18729 Cond N

D013 Ψ

45 Seal, Top 601R37154−1, −2 Rubber ZZ−R−765,Class 3B, Grade 50

NA Ψ

46 Seal, Lower Fwd 601R37155−3, −4 Rubber ZZ−R−765,Class 3B, Grade 50

NA Ψ

47 Seal, Lower Aft 601R37156−1, −2 Rubber ZZ−R−765,Class 3B, Grade 50

NA Ψ

48 Seal Backing,Top

601R37157−1 0.020 (0.51)MIL−T−9046 TY CP−3Cond A

T002 Ψ

49 Seal Backing,Lower Fwd

601R37158−3, −4 0.032 (0.81) 2024−T3AL Alloy Clad SheetQQ−A−250/5

A011 Ψ

50 Seal Backing,Lower Aft

601R37159−1, −2 0.020 (0.51)MIL−T−9046 TY CP−3Cond A

T002 Ψ

51 Angle Rear Spar,Inboard

601R37150−1 0.040 (1.02)MIL−T−9046 TY CP−3Cond A

T002 Ψ

52 Angle Rear Spar,Outboard

601R37151−1 0.040 (1.02)MIL−T−9046 TY CP−3Cond A

T002 Ψ

53 Angle 601R37012−1, −2 0.040 (1.02)2024−T42 AL AlloyClad SheetQQ−A−250/5

A010 Ψ

− Item not shown.




May 10/2010


ENCEFINISH

CODE ♦EFFECTIVI-

TY


Ψ 7811−7811, 7834−7834, 7848−7848, 7870−7990, 8000−8400





May 10/2010

PYLON AFT STRUCTURE FRAMING − ALLOWABLE DAMAGE



1. General

When specific damage limits are not supplied in the subject for a given structure element, use thegeneral allowable damage limits given in this chapter (refer to SRM 54−00−00, Page Block 101−199).


2. Specific

A. No rework permitted in an area within a 2D radius around fasteners (refer to Figure 101).

B. For the allowable damage limits for composite parts, contact Bombardier Aerospace RegionalAircraft, Customer Support (refer to SRM 51−13−01).



May 10/2010

rsr5

4063

.dg,

lr, 1

1/03

/04

NOTE1 No rework permitted in an area within

a 2D radius around fasteners.

No damage permitted

2D

D



Pylon Aft Structure Framing − Allowable DamageFigure 101


Jun 22/2004

AFT STRUCTURE FRAMING − REPAIRS

1. General

A. For repairs to the aft structure framing, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01), except for the REOs listed below.

B. List of REOs




601R−54−62−005 Repair to pylon fire separator panel

601R−54−62−054 Repair to pylon aft detachable part



Mar 10/2006


AFT STRUCTURE SKIN AND PLATING − STRUCTURAL IDENTIFICATION

1. General

A. For the structural identification of the aft structure skin and plating in this section, refer to figuresas follows:

Refer to Figure 1 for the Kevlar aft structure skin and plating.

Refer to Figure 2 for the graphite aft structure skin and plating.



May 10/2010

rsr5

4048

.dg,

om

/vh,

jun1

8/20

07

2

3

4

1

NOTE



Aft Structure Skin and Plating − Structure IdentificationFigure 1


May 10/2010


CODE ♦EFFECTIVI-

TY

Rear Assembly− PylonStructure

601−37112−1009,−1010

†


601−37112−1011,−1012

††


601−37112−1013,−1014

‡


601−37112−1015,−1016

‡‡

1 Skin Panel,Upper

601−37112−3, −4 Kevlar Fabric (CMS532−03 Type 1), CoreMaterial−NomexHoneycomb(CMS539−01, Type I)

E002/E109 ¶ ♥

1A Skin Panel,Upper

601−37112−75,−76

Kevlar Fabric (CMS532−03 Type 1), CoreMaterial−NomexHoneycomb(CMS539−01, Type I)

E002/E109 ¶ ♥♥

2 Skin Panel,Lower

601−37112−55,−56


E002/E109 ¶ ♥

2A Skin Panel,Lower

601−37112−83,−84


E002/E109 ¶ ♥♥

3 Cover 601−37102−117,−118

Kevlar CMS 532−03 TypeI

E002/E109 ¶ Ψ

4 Door 601−37112−67 Kevlar Fabric, CMS532−03 Type I

E002/E109 ¶ Ψ

− Item not shown.


† 7045−7045, 7047−7047, 7049−7049, 7051−7051, 7054−7054, 7058−7058, 7060−7060, 7065−7065,7071−7071, 7074−7074, 7078−7078, 7082−7083, 7087−7087, 7089−7089, 7095−7098, 7107−7107,7112−7112, 7115−7115, 7118−7118, 7120−7120, 7124−7124




May 10/2010


CODE ♦EFFECTIVI-

TY

†† 7003−7044, 7046−7046, 7048−7048, 7050−7050, 7052−7053, 7055−7057, 7059−7059, 7061−7064,7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7081, 7084−7086, 7088−7088, 7090−7094,7099−7106, 7108−7111, 7113−7114, 7116−7117, 7119−7119, 7121−7123, 7125−7135

‡ 7172−7173, 7175−7175, 7178−7178, 7181−7181, 7185−7185, 7191−7191, 7195−7195, 7202−7202,7208−7208, 7217−7218

‡‡ 7136−7171, 7174−7174, 7176−7177, 7179−7180, 7182−7184, 7186−7190, 7192−7194, 7196−7201,7203−7207, 7209−7216, 7219−7810, 7812−7833, 7835−7847, 7849−7869

♥ 7045−7045, 7047−7047, 7049−7049, 7051−7051, 7054−7054, 7058−7058, 7060−7060, 7065−7065,7071−7071, 7074−7074, 7078−7078, 7082−7083, 7087−7087, 7089−7089, 7095−7098, 7107−7107,7112−7112, 7115−7115, 7118−7118, 7120−7120, 7124−7124, 7172−7173, 7175−7175, 7178−7178,7181−7181, 7185−7185, 7191−7191, 7195−7195, 7202−7202, 7208−7208, 7217−7218

♥♥ 7003−7044, 7046−7046, 7048−7048, 7050−7050, 7052−7053, 7055−7057, 7059−7059, 7061−7064,7066−7067, 7069−7070, 7072−7073, 7075−7077, 7079−7081, 7084−7086, 7088−7088, 7090−7094,7099−7106, 7108−7111, 7113−7114, 7116−7117, 7119−7119, 7121−7123, 7125−7171, 7174−7174,7176−7177, 7179−7180, 7182−7184, 7186−7190, 7192−7194, 7196−7201, 7203−7207, 7209−7216,7219−7810, 7812−7833, 7835−7847, 7849−7869

Ψ 7003−7067,7069−7810,7812−7833, 7835−7847, 7849−7869

¶ Finish Inside−E002, Finish Outside−E109





May 10/2010

65

rsr5

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NOTE


1

37

81

73


Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 1)


May 10/2010

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VIEW LOOKING UP




May 10/2010

3

TOOL FACE

489323334

238932363133

2928261312113631

93230

238

33

389

1620243233

rsr5

4069

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jun3

0/20

08




May 10/2010

TOOL FACE

389

1721253233

38

1093233

389

1620243233

rsr5

4070

.dg,

vh,

jun3

0/20

08

21

20




May 10/2010

TOOL FACE

389

1721253233

38

1093233

378

1093233

rsr5

4071

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jun3

0/20

08




May 10/2010

TOOL FACE

358932333435

3893233

389

1418223233

rsr5

4072

.dg,

st,

jun3

0/20

08




May 10/2010

TOOL FACE

389

1418223233

2389

14182232363133

238932363133

238932363133

389

1519233233

2389

15192332363133

rsr5

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.dg,

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jun3

0/20

08




May 10/2010

389

1519233233

38

109

15192332273334

368

10932273334

TOOL FACE

rsr5

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sd,

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0/20

08




May 10/2010

389323633

23893230292826131211363133

389323633 3

68

10932273334

TOOL FACE

rsr5

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jun3

0/20

08




May 10/2010

3589323334

389

1620243233

35

rsr5

4076

.dg,

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un30

/200

8

TOOL FACE




May 10/2010

58932333435

TOOL FACE

389

1721253233

3

rsr5

4077

.dg,

js, j

un30

/200

8




May 10/2010

389

1620243233

38

109

16202432273334

368

10932273334

TOOL FACE

rsr5

4078

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jun3

0/20

08




May 10/2010

389

1721253233

38

109

17212532273334

368

10932273334

TOOL FACE

rsr5

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js, j

un30

/200

8




May 10/2010

4549383942435152

4538395361574243

45473839404243

4538395462584243

454838394041424351

TOOL FACE

rsr5

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08




May 10/2010

TOOL FACE

4546

39424351

38

4538

4243

39

4547

39404243

38

4538

55635942

39

43

4538

56646042

39

43

4550

39404442

38

43

rsr5

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08




May 10/2010

TOOL FACE

7266677071

72666770687169

72666770687169

rsr5

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0/20

08

75747677787980




May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY


601R37139−1,−2

7811−7811

7834−7834

7848−7848

7870−7990

8000−8062


601R37139−121,−122

8063−8400

1 Skin, TopCompositeAssembly, AftPylon Structure

601R37140−81,−82

E002/E100 †

Ψ

2 Glass Fabric 601R37140−003,−004


3 Copper Foil 601R37140−007,−008

CMS553−01 Type II GR 4 NA Ψ

4 Copper Foil 601R37140−009,−010


5 Copper Foil 601R37140−011,−012


6 Copper Foil 601R37140−013,−014


7 Copper Foil 601R37140−015,−016

















May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY

14 Adhesive Film 601R37140−031,−032

CMS551−09 Class II FM−M GR 4 NA Ψ

15 Adhesive Film 601R37140−033,−034


16 Adhesive Film 601R37140−035,−036


17 Adhesive Film 601R37140−037,−038


18 HoneycombCore

601R371401−1,−2

0.375 (9.53) CMS539−01 Type I E002 Ψ

19 HoneycombCore

601R371402−1,−2

0.375 (9.53) CMS539−01 Type I E002 Ψ

20 HoneycombCore

601R371403−1,−2

0.375 (9.53) CMS539−01 Type I E002 Ψ

21 HoneycombCore

601R371404−1,−2

0.250 (6.35) CMS539−01 Type I E002 Ψ

22 Adhesive Film 601R37140−047,−048


23 Adhesive Film 601R37140−049,−050


24 Adhesive Film 601R37140−051,−052


25 Adhesive Film 601R37140−053,−054

















May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY





34 Glass Fabric 601R37140−071,−072


35 Glass Fabric 601R37140−073,−074




37 Skin, BottomCompositeAssembly, AftPylon Structure

601R37141−1,−2

E002/E100 †

Ψ













44 Ud Preform 601R37141−017,−018

CMS532−20 NA Ψ

45 Copper Foil 601R37141−019,−020

CMS553−01 Class I Type II GR 4 NA Ψ

46 Copper Foil 601R37141−021,−022


47 Copper Foil 601R37141−023,−024


48 Copper Foil 601R37141−025,−026





May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY

49 Copper Foil 601R37141−027,−028


50 Copper Foil 601R37141−029,−030


51 Glass Fabric 601R37141−031,−032


52 Glass Fabric 601R37141−033,−034


53 Adhesive Film 601R37141−037,−038


54 Adhesive Film 601R37141−039,−040


55 Adhesive Film 601R37141−041,−042


56 Adhesive Film 601R37141−043,−044


57 Adhesive Film 601R37141−045,−046


58 Adhesive Film 601R37141−047,−048


59 Adhesive Film 601R37141−049,−050


60 Adhesive Film 601R37141−051,−052


61 HoneycombCore

601R371411−1,−2

0.250 (6.35) CMS539−01 Type I E002 Ψ

62 HoneycombCore

601R371412−1,−2

0.250 (6.35) CMS539−01 Type I E002 Ψ

63 HoneycombCore

601R371413−1,−2

0.250 (6.35) CMS539−01 Type I E002 Ψ

64 HoneycombCore

601R371414−1,−2

0.250 (6.35) CMS539−01 Type I E002 Ψ




May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY

65 DoorCompositeAssembly,Lower Skin, AftPylonAssembly

601R37148−1,−2

E002/E214††

7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

65A DoorCompositeAssembly,Lower Skin, AftPylonAssembly

601R37148−17,−18

E002/E214††

8077−8083

65B DoorCompositeAssembly,Lower Skin, AftPylonAssembly

601R37148−23,−24

E002/E214††

8084−8400











71 Copper Foil 601R37148−013,−014

CMS553−01 Class I Type II GR 4 NA 7811−7811

7834−7834

7848−7848

7870−7990

8000−8076


CMS532−19 Class II NA 8077−8083

71B Graphite Fabric 601R37148−025,−026

CMS532−19 Class II NA 8084−8400




May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY

72 Copper Foil 601R37148−015,−016


7834−7834

7848−7848

7870−7990

8000−8076

72A CopperFoil/Surf. Film

601R37148−021,−022

CMS553−01 Class II Type II GR4

NA 8077−8400

73 CoverCompositeAssembly,Lower Skin, AftPylonAssembly

601R37149−1,−2

E002/E214††

7811−7811

7834−7834

7848−7848

7870−7990

8000−8076

73A CoverCompositeAssembly,Lower Skin, AftPylonAssembly

601R37149−17,−18

E002/E214††

8077−8400

74 Copper Foil 601R37149−003,−004


7834−7834

7848−7848

7870−7990

8000−8076


CMS532−19 Class II NA 8077−8400

75 Copper Foil 601R37149−005,−006


7834−7834

7848−7848

7870−7990

8000−8076

75A Surf Film 601R37149−021,−022

BAMS 551−010 NA 8077−8400








May 10/2010


FIN-ISH

CODE♦ EFFECTIVITY







81 Doubler 601R37153−1 0.040 (1.02) MIL−T−9046 TYCP−3 Cond A

T002 Ψ

− Item not shown.


Ψ 7811−7811, 7834−7834, 7848−7848, 7870−7990, 8000−8400

† Finish Inside−E002, Finish Outside−E100, Polyurethane top coat, Color Grey, #16473 Per FED Std.595.

†† Finish Inside−E002, Finish Outside−E214





May 10/2010


AFT STRUCTURE SKIN AND PLATING − ALLOWABLE DAMAGE

1. General

A. The allowable damage limits given in this procedure are only for the pylon trailing edge structure,part numbers 601−37013−1 and 601−37013−2. These allowable limits must not be used for anyother part numbers.

B. Contact Bombardier Aerospace Regional Aircraft, Customer Support (refer to SRM 51−13−01)when:

– there is damage that is more than the limits that follow

– the part number (or dash number) of the damaged part is not given above.

2. General Limitations

There are no general limitations.

3. Specific Limitations



Apr 10/2005

COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS

TYPE OFDAMAGE

LOCATION OFDAMAGE LIMITS REMARKS

Fasteners

All areas It is acceptable for one in tenfasteners to be ineffectiveprovided:

− the end three fasteners remaineffective.

− at least three fasteners remaineffective either side of theineffective fastener.

Replace ineffective fastener atnext ’A’ check.

Cracks

Bonded edge Not allowed Contact Bombardier AerospaceRegional Aircraft, CustomerSupport (refer to SRM51−13−01).

Free edge The maximum crack length (L)allowed is 1.00 in. (25.4 mm)provided:

− the distance from any structuralfastener or unrepaired damage is3L minimum.

− there are no more than twocracks per square foot.

Apply speed tape to thedamaged areas (Refer to SRM51−27−15).

Do a detailed visual inspection atevery subsequent ’A’ check fordamage propagation and speedtape integrity. Replace the speedtape as necessary.

Do a permanent repair no laterthan the next ’C’ check.Less than 3L from a

structural fastenerThe maximum crack length (L)allowed is 1.00 in. (25.4 mm)provided:

− the structural fastener is one ina row of ten or more fastenerswith three fastener locations oneither side (if they exist)undamaged.

− not more than one fastenerlocation in ten is damaged.

− the structural fastener locationis not at the end of a row or atthe corner of the fairing.


TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 1)


Apr 10/2005


TYPE OFDAMAGE


Cracks

(Cont’d)

All other areas The maximum crack length (L)allowed is 2.00 in. (50.8 mm)provided:

− the distance from anyunrepaired damage or structuralfastener is 3L minimum.

− there are no more than twocracks per square foot.



Do a permanent repair no laterthan the next ’C’ check.

Holes andpunctures

All areas The maximum puncture diameter(D) allowed is 2.00 in. (50.8 mm)provided:

− the distance from anyunrepaired damage or structuralfastener is 3D minimum.

− there are no more than twopunctures per square foot.

− the distance from any edge is3D minimum.

Do a tap test around hole edgeand repeat at every subsequent’A’ check for delamination. Ifthere is delamination, refer to thelimits for delamination.




Dents ordepressions

All areas Dent does not penetrate skin andis less than 0.040 in. (1.02 mm)deep.

No repair necessary.

Dent is more than 0.040 in. (1.02mm) deep but is less than fullpenetration.

Treat as hole of 0.500 in. (12.70mm).

Do a tap test and check fordelamination and disbonding andrepeat at every subsequent ’A’check. If there is delamination,refer to the limits fordelamination.




Apr 10/2005


TYPE OFDAMAGE


Dents ordepressions

(Cont’d)

Laminate The maximum dent diameter (D)allowed is 2.00 in (50.8 mm)provided:


− there are no more than threedents per square foot.

− the distance from any bondedjoint is 3D minimum.

Do a tap test in way of the dent.If there is fiber damage, cracks,delamination or disbonding oneither surface of the structure,refer to the relevant damage typefor limits.

Repeat the tap test at everysubsequent ’A’ check.

No repair necessary.

Sandwich The maximum dent diameter (D)allowed is 2.00 in. (50.8 mm)provided:


− there are no more than threedents per square foot.

Do a tap test in way of the dentto check for delamination anddisbond. If there is fiber damage,cracks, delamination ordisbonding on either surface ofthe structure, refer to the relevantdamage type for limits.

Repeat the tap test at everysubsequent ’A’ check.


Scratches

All areas The maximum damage length (L)is 4.0 in. (101.6 mm) provided:

− the damage is limited to onlyone ply (0.009 in. (0.22 mm)maximum depth), otherwise referto allowable damage limits forcrack.

− the distance from anyunrepaired damage is a minimumof 3L or 4.00 in. (101.6 mm).

Do a detailed visual inspection atevery subsequent ’A’ check fordamage propagation.





Apr 10/2005


TYPE OFDAMAGE


Nicks orgouges

Bonded edge Not allowed. Contact Bombardier AerospaceRegional Aircraft, CustomerSupport (refer to SRM51−13−01).

All other areas The maximum area of damageshall be 1.0 square inchprovided:

− the maximum damage length(L) is 2.00 in. (50.8 mm).

− the distance from anyunrepaired damage is a minimumof 3L or 4.00 in. (101.6 mm).


Do a tap test around the nick orgouge to check for delaminationand disbond. If there isdelamination or disbonding oneither surface of the structure,refer to the relevant damage typefor limits.



Delaminationsand

Disbonds

Free or bondededge

Not allowed. Contact Bombardier AerospaceRegional Aircraft, CustomerSupport (refer to SRM51−13−01).

All other areas The maximum delaminationlength (L) allowed is 1.50 in.(38.1 mm) provided:

− the distance from anyunrepaired damage or structuralfastener is 3L minimum.

− there are no more than threedelaminations per square foot.

− the maximum area is 1.50 x1.50 in (38.1 x 38.1 mm).

No temporary repair necessary.

Do a tap test at everysubsequent ’A’ check for damagepropagation.





Apr 10/2005


TYPE OFDAMAGE


Erosion

Free edge Edge erosion is acceptableprovided:

− the damage is limited to oneply maximum.

− the damage length in the winddirection does not exceed 4.00in. (101.6 mm).

− the damage does not exceedmore than two attachments in thecrosswind direction.




All other areas Maximum erosion of one ply shallbe treated as a scratch provided:

− the maximum area of one plyerosion is not more than 6.00square inches.

More than one ply removed isassessed as a puncture hole.




Apr 10/2005

AFT STRUCTURE SKIN AND PLATING − REPAIRS

1. General

A. For repairs to the aft structure skin and plating, contact Bombardier Aerospace Regional Aircraft,Customer Support (refer to SRM 51−13−01), except for the REOs listed below.

B. List of REOs




601R−54−62−022 Temporary repair to pylon T/E upper and lower panels



Mar 10/2006


Documents

LIST OF EFFECTIVE PAGES - Login · 54−12−31 54−12−31 tailpipe skin and plating − structural identification 1 all general tailpipe skin and plating − allowable damage 101