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54 − EffectivePages
1 * Apr 10/2011
2 Jul 10/20083 * Apr 10/20114 * Apr 10/2011
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
54−10−27 1 Feb 18/2003
54−10−27 101 Feb 18/2003
54−10−31 1 Feb 18/20032 Feb 18/2003
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
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NACELLES/PYLONSLIST OF EFFECTIVE PAGES
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54−17−00 101 Jun 17/2003
54−17−00 201 Mar 10/2006
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54−18−00 1 Feb 18/20032 Feb 18/20033 Feb 18/2003
54−18−00 101 Jun 17/2003
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54−50−00 1 Jun 22/20042 Jun 22/2004
54−50−00 101 May 10/2010102 Jun 22/2004103 Jun 22/2004
54−51−14 1 Jun 22/20042 Jun 22/20043 Jun 22/20044 Jun 22/20045 Mar 10/20066 Mar 10/20067 Mar 10/20068 Mar 10/20069 Mar 10/2006
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54−60−00 1 Dec 22/20032 Dec 22/2003
54−60−00 101 May 10/2010102 Jun 22/2004103 Jun 22/2004
54−61−14 1 Jun 22/20042 Jun 22/20043 Mar 10/20064 Mar 10/2006
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54−61−31 201 Feb 18/2003
54−62−14 1 May 10/20102 May 10/20103 May 10/20104 May 10/20105 May 10/20106 May 10/20107 May 10/2010
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8 May 10/20109 May 10/201010 May 10/201011 May 10/201012 May 10/201013 May 10/201014 May 10/201015 May 10/201016 May 10/201017 May 10/201018 May 10/201019 May 10/201020 May 10/201021 May 10/201022 May 10/2010
54−62−14 101 May 10/2010102 Jun 22/2004
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54−62−31 1 May 10/20102 May 10/20103 May 10/20104 May 10/20105 May 10/20106 May 10/20107 May 10/20108 May 10/20109 May 10/201010 May 10/201011 May 10/201012 May 10/201013 May 10/201014 May 10/201015 May 10/201016 May 10/201017 May 10/201018 May 10/201019 May 10/201020 May 10/201021 May 10/201022 May 10/2010
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54−62−31 101 Apr 10/2005102 Apr 10/2005103 Apr 10/2005104 Apr 10/2005105 Apr 10/2005106 Apr 10/2005
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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
Structural Identification
NACELLE FITTINGS − ALLOWABLE DAMAGE 101 ALL
General
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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
Structural Identification
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
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Subject
ChapterSectionSubject Page Effectivity
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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
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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
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54−17−00 54−17−00
NACELLE/PYLON SERVICE STRUCTURE −
STRUCTURAL IDENTIFICATION
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
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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
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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 −
STRUCTURAL IDENTIFICATION
1 ALL
General
FORWARD STRUCTURE SKIN AND PLATING −
ALLOWABLE DAMAGE
101 ALL
General
Specific
FORWARD STRUCTURE SKIN AND PLATING −
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
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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
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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.
CSTRUCTURAL REPAIR MANUAL
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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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0
CSTRUCTURAL REPAIR MANUAL
Nacelle/Pylon StationsFigure 1
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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
THE DISTANCE OF THEDAMAGE FROM A HOLE,FASTENERS OR EDGE
MUST NOT BE LESSTHAN 20X
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)
CSTRUCTURAL REPAIR MANUAL
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
DEPTH X − MUSTNOT BE MORE THAN
FASTENER DIAMETEROR 10% OF ELEMENT
WIDTH
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
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
CSTRUCTURAL REPAIR MANUAL
Extruded and Machined Parts (Other than Fittings) – Allowable Damage − GeneralFigure 101 (Sheet 2)
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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.
CSTRUCTURAL REPAIR MANUAL
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
TOTAL CROSS−SECTION(INCLUDES SKIN)
DENTS
REMOVAL OF NICK OR CRACKDAMAGE ON AN EDGE
CSTRUCTURAL REPAIR MANUAL
Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 1)
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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).
Scratches,nicks, gougesand corrosion
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
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 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.
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.
CSTRUCTURAL REPAIR MANUAL
Formed Parts − Allowable Damage − GeneralFigure 102 (Sheet 2)
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NACELLES/PYLONS SKIN AND PLATING − 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.
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.
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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.
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 is necessary when more than 30% of the area of a panel 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.
CSTRUCTURAL REPAIR MANUAL
Wing Skin and Plating − Allowable Damage − GeneralFigure 101 (Sheet 1)
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RADIUS OF REMOVEDDAMAGE IS FOUND BY
FASTENER EDGEDISTANCE LIMIT
(EXAMPLE)
X DEPTH = 0.15 in.(3.81 mm) MAXIMUM
MATERIAL TRIMMEDTO REMOVE DAMAGE
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
DO NOT HAVE OVERLAPS
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
HAVE OVERLAPS
EDGE DAMAGE
FASTENEREDGE DISTANCELIMIT (EXAMPLE)
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)
X DEPTH = 0.15 in.(3.81 mm) MAXIMUM
R = 1.0 in. (25.4 mm) MINIMUM
CSTRUCTURAL REPAIR MANUAL
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
THE BOTTOM OF THE REMOVEDDAMAGE MUST HAVE A RADIUS
OF 1.0 in. (25.4 mm) MINIMUM
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.
CSTRUCTURAL REPAIR MANUAL
Sheet Metal Skin and Plating − Allowable DamageFigure 102 (Sheet 2)
MasterEFFECTIVITY: ALL 54−00−31 Page 104
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−10−00 Page 1
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
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Nacelle BreakdownFigure 1
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Feb 18/2003
NACELLES INTERNAL STRUCTURE − 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 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.
CSTRUCTURAL REPAIR MANUAL
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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
THE DISTANCE OF THEDAMAGE FROM A HOLE,FASTENERS OR EDGE
MUST NOT BE LESSTHAN 20X
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)
CSTRUCTURAL REPAIR MANUAL
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
DEPTH X − MUSTNOT BE MORE THAN
FASTENER DIAMETEROR 10% OF ELEMENT
WIDTH
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
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
CSTRUCTURAL REPAIR MANUAL
Extruded and Machined Parts (Other than Fittings) – Allowable Damage − GeneralFigure 101 (Sheet 2)
MasterEFFECTIVITY: ALL 54−10−00 Page 103
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.
Scratches,nicks, gougesand corrosion
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
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 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: 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 percent of its lengthis damaged.
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.
CSTRUCTURAL REPAIR MANUAL
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
TOTAL CROSS−SECTION(INCLUDES SKIN)
DENTS
REMOVAL OF NICK OR CRACKDAMAGE ON AN EDGE
CSTRUCTURAL REPAIR MANUAL
Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 1)
MasterEFFECTIVITY: ALL 54−10−00 Page 105
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.
Scratches,nicks, gougesand corrosion
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.
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
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 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).
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).
CSTRUCTURAL REPAIR MANUAL
Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 2)
MasterEFFECTIVITY: ALL 54−10−00 Page 106
Feb 18/2003
DAMAGE REMARKS
NOTE: Approved repair or replacement of a member is necessary when more than 30 percent of its lengthis damaged.
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.
CSTRUCTURAL REPAIR MANUAL
Formed Parts – Allowable Damage – GeneralFigure 102 (Sheet 3)
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NACELLE FITTINGS − GENERAL
1. Structural Identification
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.
CSTRUCTURAL REPAIR MANUAL
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NACELLE FITTINGS − ALLOWABLE DAMAGE
1. General
For the allowable damage limits contact Short Brothers Technical Information and Support (TechnicalHelp Line 44 07850 770826).
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NACELLE − SKIN AND PLATING − GENERAL
1. General
This section contains data that is applicable to the power plant components.
2. Structural Identification
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−10−31 Page 1
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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
CSTRUCTURAL REPAIR MANUAL
Nacelle Skin and Plating BreakdownFigure 1
MasterEFFECTIVITY: ALL 54−10−31 Page 2
Feb 18/2003
NACELLE SKIN AND PLATING − 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 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.
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For added data, refer to sheet 3.NOTE
X DEPTH = 0.15 in.(3.81 mm) MAXIMUM
MATERIAL REMOVEDTO REMOVE DAMAGE RADIUS OF
REMOVED DAMAGEIS FOUND BY THE
DAMAGE DEPTH (X)
FASTENER EDGEDISTANCE LIMIT
(EXAMPLE)
LIMIT OF DAMAGEREMOVAL. RADIUS OFREMOVED DAMAGE IS
FOUND BY THEDAMAGE DEPTH (X)
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
DO NOT HAVE OVERLAPS
DAMAGE REMOVALWHERE THE FASTENER EDGE DISTANCES
HAVE OVERLAPS
EDGE DAMAGE
X DEPTH = 0.15 in.(3.81 mm) MAXIMUM
FASTENER EDGEDISTANCE LIMIT
(EXAMPLE)
CSTRUCTURAL REPAIR MANUAL
Sheet Metal Skin and Plating − Allowable Damage − GeneralFigure 101 (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)
RUN−OUT20X
MINIMUM
THE BOTTOM OF THE REMOVEDDAMAGE MUST HAVE A RADIUS
OF 1.0 in. (25.4 mm) 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
CSTRUCTURAL REPAIR MANUAL
Sheet Metal Skin and Plating − Allowable Damage − GeneralFigure 101 (Sheet 2)
MasterEFFECTIVITY: ALL 54−10−31 Page 103
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:
W = Width of the minor axis of the dent
D = Depth of the dent from the initial contour.
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.
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.
CSTRUCTURAL REPAIR MANUAL
Sheet Metal Skin and Plating − Allowable Damage − GeneralFigure 101 (Sheet 3)
MasterEFFECTIVITY: ALL 54−10−31 Page 104
Jun 22/2004
NACELLE SKIN AND PLATING − REPAIRS
1. General
A. For repairs to the nacelle skin and plating, refer to Shorts CMM, Nacelles.
CSTRUCTURAL REPAIR MANUAL
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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.
CSTRUCTURAL REPAIR MANUAL
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NOSE COWL FRAMES AND FORMERS − STRUCTURAL IDENTIFICATION
1. General
Refer to Figure 1 for the structural identification of the nose cowl.
CSTRUCTURAL REPAIR MANUAL
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NOTEThe structure is symmetricalabout the nacelle centerlines,unless shown differently. XN105.00
XN121.60
XN135.84
11
XN105.00
XN121.60
XN135.84
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 1)
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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)
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 2)
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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
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 3)
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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
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 4)
MasterEFFECTIVITY: ALL 54−11−15 Page 5
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
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 5)
MasterEFFECTIVITY: ALL 54−11−15 Page 6
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
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 6)
MasterEFFECTIVITY: ALL 54−11−15 Page 7
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
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 7)
MasterEFFECTIVITY: ALL 54−11−15 Page 8
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:
CSTRUCTURAL REPAIR MANUAL
Nose Inlet Cowl — Structural IdentificationFigure 1 (Sheet 8)
MasterEFFECTIVITY: ALL 54−11−15 Page 9
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−11−15 Page 10
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
19 Stiffener 0.040 (1.02) Alclad2024−0 † ‡‡‡
V003
Intercostal Instl,Upper
228−50076
20 Web 0.050 (1.27) Alclad2024−0 † ‡‡‡
V003
21 Tee Cap Extruded Al alloy2024−0 † ¶¶¶
V003
22 Stiffener 0.050 (1.27) Alclad2024−0 † ‡‡‡
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
28 Stiffener 0.050 (1.27) Alclad2024−0 † ‡‡‡
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−11−15 Page 11
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−11−15 Page 12
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 4)
MasterEFFECTIVITY: ALL 54−11−15 Page 13
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.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 5)
MasterEFFECTIVITY: ALL 54−11−15 Page 14
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−11−15 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−11−15 Page 201
Mar 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−11−31 Page 101
Jun 10/2007
THIS PAGE INTENTIONALLY LEFT BLANK
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
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−71−61−2056 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
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−11−31 Page 201
Jul 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−00 Page 1
Feb 18/2003
THIS PAGE INTENTIONALLY LEFT BLANK
TAILPIPE FRAMES AND FORMERS − STRUCTURAL IDENTIFICATION
1. General
For the structural identification of the tailpipe, refer to Figure 1.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−15 Page 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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Fairing Structure − Structural IdentificationFigure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−12−15 Page 2
Feb 18/2003
rsr5
4016.c
gm
7
7
6
7
13
26
8
27
27
28
410
20
6
105
CSTRUCTURAL REPAIR MANUAL
Tailpipe Fairing Structure − Structural IdentificationFigure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−12−15 Page 3
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
11 Stiffener 0.050 (1.27) Alclad2024−0 † ¶
V004
12 Stiffener 0.040 (1.02) Alclad2024−0 † ¶
V004
13 Plate 0.032 (0.81) Alclad2024−T3 ¶
V004
14 Seal (Upper,Lower)
Silicone rubber †††
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−12−15 Page 4
Mar 10/2006
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−12−15 Page 5
Mar 10/2006
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIVI-
TY
28 Support 228−50188 Nickel Alloy Casting,Inconel 718C ♣♣
T002
− Item not shown.
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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−250.
¶¶ 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−12−15 Page 6
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−15 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−15 Page 201
Feb 18/2003
THIS PAGE INTENTIONALLY LEFT BLANK
TAILPIPE SKIN AND PLATING − STRUCTURAL IDENTIFICATION
1. General
Refer to Figure 1for the structural identification of the tailpipe skin and plating.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−31 Page 1
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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−12−31 Page 2
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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−12−31 Page 3
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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−12−31 Page 4
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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 4)
MasterEFFECTIVITY: ALL 54−12−31 Page 5
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
CSTRUCTURAL REPAIR MANUAL
Tailpipe Skin and Plating – Structural IdentificationFigure 1 (Sheet 5)
MasterEFFECTIVITY: ALL 54−12−31 Page 6
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
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
MasterEFFECTIVITY: ALL 54−12−31 Page 7
Mar 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
TAILPIPE SKIN AND PLATING − 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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−31 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−12−31 Page 201
Feb 18/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−13−15 Page 101
Jun 22/2004
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−13−15 Page 201
Feb 18/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−13−31 Page 101
Jun 22/2004
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−13−31 Page 201
Feb 18/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−14−00 Page 1
Feb 18/2003
rsr5
40
17
, lc
, 1
3/1
0/0
0
1
2
3
4
CSTRUCTURAL REPAIR MANUAL
Access Cowls − Internal StructureFigure 1
MasterEFFECTIVITY: ALL 54−14−00 Page 2
Feb 18/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY
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.
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
MasterEFFECTIVITY: ALL 54−14−00 Page 3
Jun 17/2003
rsr5
4030
, na,
06/
12/0
0
4435
3444
22
143
4
23
4444
12
CSTRUCTURAL REPAIR MANUAL
Access Cowls − Skin and PlatingFigure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−14−00 Page 4
Mar 10/2006
rsr5
40
31
, n
a,
06
/12
/00
4435
3444
22
143
4
23
4444
143
4
23
4435
2344
CSTRUCTURAL REPAIR MANUAL
Access Cowls − Skin and PlatingFigure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−14−00 Page 5
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
EFFECTIVITY: 7002 − 7008
998
10
899
77
9999
EFFECTIVITY: 7048 − 8400
1198
9
7
87
CSTRUCTURAL REPAIR MANUAL
Access Cowls − Skin and PlatingFigure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−14−00 Page 6
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY
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
6 Core0.375 (9.53)Aramid/Phenolichoneycomb ††
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 ‡‡‡
11 Core0.500 (12.70)Aramid/Phenolichoneycomb ††
12 Cover 228−50073 0.040 (1.02) Alclad 2024−0† V003
− Item not shown.
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−14−00 Page 7
Jun 17/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY
‡‡ Specification Vought 207−8−448, Type II, Style 1.
‡‡‡ Specification Vought 207−7−425, Type V.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−14−00 Page 8
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−14−00 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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
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−71−14−001 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
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−14−00 Page 201
Jul 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
CORE COWL FRAMES AND FORMERS − ALLOWABLE DAMAGE
1. General
Refer to Shorts CMM 71−12−01 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−16−15 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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
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−71−61−003 STOW switch bracket − modification
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−16−15 Page 201
Mar 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
CORE COWL SKIN AND PLATING − ALLOWABLE DAMAGE
1. General
Refer to Shorts CMM 71−12−01 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−16−31 Page 101
Jun 17/2003
THIS PAGE INTENTIONALLY LEFT BLANK
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.
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−71−12−2518 Upper and Lower Core Cowl Door − Cracked/Piece Missingfrom Aft Edge of Outer Skin
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−16−31 Page 201
Jul 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−17−00 Page 1
Feb 18/2003
rsr5
40
19
, cr
, 1
3/1
0/0
0
1
14
4
3
2
2
3
4
4
CSTRUCTURAL REPAIR MANUAL
Nose Cowl Side Panel Internal Structure − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−17−00 Page 2
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
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
MasterEFFECTIVITY: ALL 54−17−00 Page 3
Feb 18/2003
rsr5
4033
, na,
04/
12/0
0
PYLON
1
XN155.32
XN121.60
XN151.14
CL
CSTRUCTURAL REPAIR MANUAL
Nose Cowl Side Panel Skin and Plating − Structural IdentificationFigure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−17−00 Page 4
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)
CSTRUCTURAL REPAIR MANUAL
Nose Cowl Side Panel Skin and Plating − Structural IdentificationFigure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−17−00 Page 5
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)
CSTRUCTURAL REPAIR MANUAL
Nose Cowl Side Panel Skin and Plating − Structural IdentificationFigure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−17−00 Page 6
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 ††
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2
MasterEFFECTIVITY: ALL 54−17−00 Page 7
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)
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Internal Structure − Structural IdentificationFigure 3 (Sheet 1)
MasterEFFECTIVITY: ALL 54−17−00 Page 8
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
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Internal Structure − Structural IdentificationFigure 3 (Sheet 2)
MasterEFFECTIVITY: ALL 54−17−00 Page 9
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)
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Internal Structure − Structural IdentificationFigure 3 (Sheet 3)
MasterEFFECTIVITY: ALL 54−17−00 Page 10
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
VIEW LOOKING OUTBOARD
VIEW LOOKING OUTBOARD
9
SKIN (REF)
SKIN (REF)
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Internal Structure − Structural IdentificationFigure 3 (Sheet 4)
MasterEFFECTIVITY: ALL 54−17−00 Page 11
Feb 18/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE FINISHCODE ♦ EFFECTIVITY
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
228−50128 CRES Investment Casting17−4PH ‡‡
S022
17 Hinge Support, Upr,Aft
228−50311 CRES Investment Casting17−4PH ‡‡
S022
18 Hinge Support, Lwr,Aft
228−50312 CRES Investment Casting17−4PH ‡‡
S022
CSTRUCTURAL REPAIR MANUAL
Key to Figure 3 (Sheet 1)
MasterEFFECTIVITY: ALL 54−17−00 Page 12
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 ♥
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† 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−QQ−A−250/5.
¶¶¶ 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 3 (Sheet 2)
MasterEFFECTIVITY: ALL 54−17−00 Page 13
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
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Skin and Plating − Structural IdentificationFigure 4 (Sheet 1)
MasterEFFECTIVITY: ALL 54−17−00 Page 14
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
VIEW LOOKING OUTBOARD
VIEW LOOKING OUTBOARD
1
2
CSTRUCTURAL REPAIR MANUAL
Fixed Core Cowl Skin and Plating − Structural IdentificationFigure 4 (Sheet 2)
MasterEFFECTIVITY: ALL 54−17−00 Page 15
Feb 18/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE FINISHCODE ♦ EFFECTIVITY
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
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† Specification AMS−5520.
†† Specification AMS−T−9046
††† 1 coat, interior only.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 4
MasterEFFECTIVITY: ALL 54−17−00 Page 16
Mar 10/2006
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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
CSTRUCTURAL REPAIR MANUAL
Service Pylon Internal Structure − Structural IdentificationFigure 5
MasterEFFECTIVITY: ALL 54−17−00 Page 17
Feb 18/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE FINISHCODE ♦ EFFECTIVITY
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 §§
CSTRUCTURAL REPAIR MANUAL
Key to Figure 5 (Sheet 1)
MasterEFFECTIVITY: ALL 54−17−00 Page 18
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.
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
♦♦ 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−QQ−A−250.
¶¶ Specification AMS−QQ−A−250/5.
¶¶¶ 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.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 5 (Sheet 2)
MasterEFFECTIVITY: ALL 54−17−00 Page 19
Mar 10/2006
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NACELLE/PYLON SERVICE STRUCTURE − ALLOWABLE DAMAGE
1. General
Refer to Shorts CMM 71−13−01 for information pertaining to allowable damage limits and if necessary,contact Short Brothers Technical Information and Support (Technical Help Line 44 07850 770826).
CSTRUCTURAL REPAIR MANUAL
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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
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−71−61−2652 Engine intake lipskin type II finish standard
CSTRUCTURAL REPAIR MANUAL
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EXHAUST NOZZLE − STUCTURAL IDENTIFICATION
1. General
Refer to Figure 1 for the structural identification of the exhaust nozzle.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−18−00 Page 1
Feb 18/2003
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18
, lc
, 1
2/1
0/0
0
2
2
1
3 2
2
1
CSTRUCTURAL REPAIR MANUAL
Exhaust Nozzle Tube — Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−18−00 Page 2
Feb 18/2003
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE FINISHCODE ♦ EFFECTIVITY
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
♦ Refer to SHORTS CMM 20−21−16 for finish code identification.
† Specification AMS−5599.
†† Specification AMS−5666.
‡ Acceptable alternate is Nickel alloy plate Inconel 625 per specification AMS−5599.
NOTE: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
MasterEFFECTIVITY: ALL 54−18−00 Page 3
Feb 18/2003
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EXHAUST NOZZLE − 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).
CSTRUCTURAL REPAIR MANUAL
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Jun 17/2003
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EXHAUST NOZZLE − REPAIRS
1. General
A. For repairs to the exhaust nozzle, refer to Shorts CMM 78−11−00, Exhaust Nozzle Assembly.
CSTRUCTURAL REPAIR MANUAL
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Feb 18/2003
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PYLONS MAIN STRUCTURE − STRUCTURAL IDENTIFICATION
1. General
For the structural identification of the pylons main structure, refer to Figure 1.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−50−00 Page 1
Jun 22/2004
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SKIN AND PLATING54−51−31
PYLON BOXFRAMING STRUCTURE
54−51−14
SKIN AND PLATING54−51−31
SKIN AND PLATING54−51−31
A
A
CSTRUCTURAL REPAIR MANUAL
Pylon Main Structure − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−50−00 Page 2
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−50−00 Page 101
May 10/2010
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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
CSTRUCTURAL REPAIR MANUAL
Pylons Main Structure − Allowable DamageFigure 101
MasterEFFECTIVITY: ALL 54−50−00 Page 102
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.
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.
CSTRUCTURAL REPAIR MANUAL
Pylons Main Structure − Allowable DamageFigure 102
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Jun 22/2004
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PYLON BOX FRAMING STRUCTURE − STRUCTURAL IDENTIFICATION
1. General
For the structural identification of the pylon box framing structure, refer to Figure 1.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−51−14 Page 1
Jun 22/2004
682 PLACES
A
A
rsr5
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, ds,
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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.
CSTRUCTURAL REPAIR MANUAL
Pylon Box Framing Structure − Structural IdentificationFigure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−51−14 Page 2
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
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, ds,
11/
11/0
3
28
C
C
NOTE
The structure is symmetricalaround the aircraft centerline,unless shown differently.
CSTRUCTURAL REPAIR MANUAL
Pylon Box Framing Structure − Structural IdentificationFigure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−51−14 Page 3
Jun 22/2004
A44
4119
40
46
42
6
6
45
D
E
D
E
64
62
63
52
1465
6061
rsr5
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, ds,
11/
11/0
3
79
NOTE
The structure is symmetricalaround the aircraft centerline,unless shown differently.
CSTRUCTURAL REPAIR MANUAL
Pylon Box Framing Structure − Structural IdentificationFigure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−51−14 Page 4
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−51−14 Page 5
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−51−14 Page 6
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦
EFFECTIVI-TY
44 Angle 601−37011 0.063 (1.60) PH17−7 CRES,MIL−S−25043, COND H1050
S002
45 Radius Block 601−37011 0.125 (3.18) CRES, Type 301,1/2 Hard, MIL−S−5059
S002
46 Radius Block 601−37011 0.090 (2.29) CRES, Type 301,1/2 Hard, MIL−S−5059
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
49 Angle, Pylon toFuselage, Upper
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−51−14 Page 7
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦
EFFECTIVI-TY
63 Laminated Shim 601−37003 S10249−63−92−118C A010 7910−8400
64 Laminated Shim 601−37003 S10249−94−92−331C A010 7910−8400
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
74 Angle, Pylon toFuselage, Upper
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
76 Angle, Pylon toFuselage, Lower
601−37051 0.080 (2.03) 6013−T6 Al AlloySheet, AMS 4347
A010 7102−8400
77 Angle, Pylon toFuselage, Lower
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 4)
MasterEFFECTIVITY: ALL 54−51−14 Page 8
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
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.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 5)
MasterEFFECTIVITY: ALL 54−51−14 Page 9
Mar 10/2006
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PYLON BOX FRAMING 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 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).
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−51−14 Page 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
CSTRUCTURAL REPAIR MANUAL
Pylon Box Framing Structure − Allowable DamageFigure 101
MasterEFFECTIVITY: ALL 54−51−14 Page 102
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−51−14 Page 103
Jun 22/2004
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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
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−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
CSTRUCTURAL REPAIR MANUAL
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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).
CSTRUCTURAL REPAIR MANUAL
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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).
CSTRUCTURAL REPAIR MANUAL
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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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−51−31 Page 1
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VIEW LOOKING UP
1
1
1
2
5
4
3
2
63
6
7
3
88
8
FS682.00
FS605.00
CSTRUCTURAL REPAIR MANUAL
Pylon Box Skin and Plating − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−51−31 Page 2
Jun 22/2004
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
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 .
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
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PYLON BOX SKIN AND PLATING − 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 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).
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.
CSTRUCTURAL REPAIR MANUAL
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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
CSTRUCTURAL REPAIR MANUAL
Pylon Box Skin and Plating − Allowable DamageFigure 101
MasterEFFECTIVITY: ALL 54−51−31 Page 102
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).
CSTRUCTURAL REPAIR MANUAL
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Feb 18/2003
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PYLON SECONDARY STRUCTURE − STRUCTURAL IDENTIFICATION
1. General
A. The structural identification of the Pylon Secondary Structure is given in Figure 1.
CSTRUCTURAL REPAIR MANUAL
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A
A
54−62−31
54−62−14
54−50−00 (REF)
54−61−14
54−61−31
54−62−31
CSTRUCTURAL REPAIR MANUAL
Pylon Secondary Structure − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−60−00 Page 2
Dec 22/2003
PYLON SECONDARY 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 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).
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.
CSTRUCTURAL REPAIR MANUAL
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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
CSTRUCTURAL REPAIR MANUAL
Pylon Secondary Structure − Allowable DamageFigure 101 (Sheet 1)
MasterEFFECTIVITY: ALL 54−60−00 Page 102
Jun 22/2004
DAMAGE REMARKS
Dents
Refer to sheet 1 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 ofdamaged 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.
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.
CSTRUCTURAL REPAIR MANUAL
Pylons Secondary Structure − Formed Parts − Allowable DamageFigure 101 (Sheet 2)
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FORWARD STRUCTURE FRAMING − STRUCTURAL IDENTIFICATION
1. General
For the structural identification of the pylon forward structure framing, refer to Figure 1.
CSTRUCTURAL REPAIR MANUAL
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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
The structure is symmetricalaround the aircraft centerline,unless shown differently.
NOTE
PBL−8.340
PBL−3.000
CSTRUCTURAL REPAIR MANUAL
Forward Structure Framing − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−61−14 Page 2
Jun 22/2004
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY
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
6 Channel 601−37004 0.050 (1.27) 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
9 Channel 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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−61−14 Page 3
Mar 10/2006
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISHCODE EFFECTIVITY
NOTE: All dimensions are in inches (millimeters) unless otherwise specified.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−61−14 Page 4
Mar 10/2006
FORWARD STRUCTURE FRAMING − 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 for a given structural element, use the general allowabledamage limits given in this chapter (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 general allowable damage limits, refer to Figure 101.
CSTRUCTURAL REPAIR MANUAL
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May 10/2010
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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
CSTRUCTURAL REPAIR MANUAL
Forward Structure Framing − Allowable DamageFigure 101 (Sheet 1)
MasterEFFECTIVITY: ALL 54−61−14 Page 102
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.
CSTRUCTURAL REPAIR MANUAL
Forward Structure Framing − Allowable DamageFigure 101 (Sheet 2)
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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).
CSTRUCTURAL REPAIR MANUAL
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FORWARD STRUCTURE SKIN AND PLATING − STRUCTURAL IDENTIFICATION
1. General
For the structural identification of the forward structure skin and plating, refer to Figure 1.
CSTRUCTURAL REPAIR MANUAL
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A
54−61−14 (REF)
A
1
1
CSTRUCTURAL REPAIR MANUAL
Forward Structure Skin and Plating − Structural IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−61−31 Page 2
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
♦ Refer to SRM 51−21−16.
† Specification QQ−A−250/5.
NOTE: All dimensions are in inches (millimeters) unless otherwise specified.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1
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FORWARD STRUCTURE SKIN AND PLATING − 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
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).
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.
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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
DAMAGEREMOVAL LIMIT 2
CSTRUCTURAL REPAIR MANUAL
Forward Structure Skin and Plating − Allowable DamageFigure 101 (Sheet 1)
MasterEFFECTIVITY: ALL 54−61−31 Page 102
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.
CSTRUCTURAL REPAIR MANUAL
Forward Structure Skin and Plating – Allowable DamageFigure 101 (Sheet 2)
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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).
CSTRUCTURAL REPAIR MANUAL
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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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−62−14 Page 1
May 10/2010
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0/20
08
20
2
12
14
24
17
16
13
1
5
7
3
4
8
96
11
15
18
19
NOTE
The structure is symmetricalaround the aircraft centerline,unless shown differently.
10
23
22
21
FWD
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−14 Page 2
May 10/2010
37
36
32
33
35
rsr5
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st/s
r, a
pr09
/200
8
41
46
39
48
45
4038
4742
43
44
49
2526272829303134
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−14 Page 3
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIV-
ITY
Rear Assembly −Pylon Structure
601−37112−1009,−1010
†
Rear Assembly −Pylon Structure
601−37112−1011,−1012
††
Rear Assembly −Pylon Structure
601−37112−1013,−1014
‡
Rear Assembly −Pylon Structure
601−37112−1015,−1016
‡‡
1 Channel 601−37012−15,−16
Kevlar CMS532−03Type I
NA Ψ
2 Channel 601−37112−37,−38
Kevlar CMS532−03Type I
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
Kevlar CMS532−03Type I
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
0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5
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
0.040 (1.01) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
10 Clip 601−37012−19,−20
0.040 (1.01) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
11 Clip 601−37012−25,−26
0.050 (1.27) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
12 Clip 601−37012−27,−28
0.063 (1.60) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−14 Page 4
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
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
Silicone Rubber Haveg#7093 CMPD−H−406Dacron Fabric F−799Plain Weave
NA Ψ
15 Seal, Lower Aft 601−37012−83,−84
Silicone Rubber Haveg#7093 CMPD−H−406Dacron Fabric F−799Plain Weave
NA Ψ
16 Seal Retainer, Top 601−37012−85,−86
0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
17 Seal Retainer,Lower Fwd
601−37012−87,−88
0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
18 Seal Retainer,Lower Aft
601−37012−89,−90
0.032 (0.81) 2024−T42AL Alloy Clad SheetQQ−A−250/5
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
0.160 (4.06) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
23 Radius Block 601−37012−23,−24
0.160 (4.06) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
24 Clip 601−37012−77,−78
0.063 (1.60) 2024−T42AL Alloy Clad SheetQQ−A−250/5
A010 Ψ
Pylon StructureAssembly AftDetachable
601−37066−1, −2 7003−7067
7069−7135
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−14 Page 5
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIV-
ITY
Pylon StructureAssembly AftDetachable
601−37066−101,−102
7136−7863
Pylon StructureAssembly AftDetachable
601−37066−31,−32
7864−7990
8000−8037
Pylon StructureAssembly AftDetachable
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
26 Skin (1 lam.) 601−37066−15 CMS532−05 Class I NA 7003−7067
7069−7863
26A Skin (1 lam.) 601−37066−43 CMS532−19 Class II NA 7864−7990
8000−8400
27 Skin (1 lam.) 601−37066−17 CMS532−05 Class I NA 7003−7067
7069−7863
27A Skin (1 lam.) 601−37066−45 CMS532−19 Class II NA 7864−7990
8000−8400
28 Skin (1 lam.) 601−37066−19 CMS532−05 Class I NA 7003−7067
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
29 Skin (1 lam.) 601−37066−21 CMS532−05 Class I NA 7003−7067
7069−7863
29A Skin (1 lam.) 601−37066−47 CMS532−19 Class II NA 7864−7990
8000−8400
30 Skin (1 lam.) 601−37066−23 CMS532−05 Class I NA 7003−7067
7069−7863
30A Skin (1 lam.) 601−37066−49 CMS532−19 Class II NA 7864−7990
8000−8400
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−14 Page 6
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIV-
ITY
31 Skin (1 lam.) 601−37066−25 CMS532−05 Class I NA 7003−7067
7069−7863
31A Skin (1 lam.) 601−37066−51 CMS532−19 Class II NA 7864−7990
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−14 Page 7
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
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.
♦ Refer to SRM 51−21−16.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−14 Page 8
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
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.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 6)
MasterEFFECTIVITY: ALL 54−62−14 Page 9
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
The structure is symmetricalaround the aircraft centerline,unless shown differently.
5351
52
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−14 Page 10
May 10/2010
rsr5
4087
.dg,
sd,
jun2
9/20
07
4578
10
TOOL FACE
345678
TOOL FACE11
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−14 Page 11
May 10/2010
rsr5
4088
.dg,
sd,
jun3
0/20
08
4578
3457811
34567811
3457811
4578
457811
4578
245789TOOL FACE
TOOL FACE
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−14 Page 12
May 10/2010
rsr5
4089
.dg,
sd,
jun3
0/20
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181615141318
191314151619
TOOL FACE
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−14 Page 13
May 10/2010
171314151620
TOOL FACE
13141516
rsr5
4090
.dg,
vh,
jun3
0/20
08
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−14 Page 14
May 10/2010
2223242526
TOOL FACE
TOOL FACE
232425
rsr5
4091
.dg,
vh,
jun3
0/20
08
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 6)
MasterEFFECTIVITY: ALL 54−62−14 Page 15
May 10/2010
rsr5
4092
.dg,
vh,
jun3
0/20
08
31302928
333130292832
TOOL FACE
TOOL FACE
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 7)
MasterEFFECTIVITY: ALL 54−62−14 Page 16
May 10/2010
353637
TOOL FACE
rsr5
4093
.dg,
vh,
jun3
0/20
08
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Structure IdentificationFigure 2 (Sheet 8)
MasterEFFECTIVITY: ALL 54−62−14 Page 17
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIVI-
TY
Rear Assembly −Pylon Structure
601R37139−1, −2 7811−7811
7834−7834
7848−7848
7870−7990
8000−8062
Rear Assembly −Pylon Structure
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
5 Graphite Fabric 601R37142−009,−010
CMS532−19 Class II NA Ψ
6 Graphite Fabric 601R37142−011,−012
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
7 Graphite Fabric 601R37142−013,−014
CMS532−19 Class II NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−14 Page 18
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIVI-
TY
8 Graphite Fabric 601R37142−015,−016
CMS532−19 Class II NA Ψ
9 Glass Fabric 601R37142−017,−018
CMS532−06 Style 120 NA Ψ
10 Glass Fabric 601R37142−019,−020
CMS532−06 Style 120 NA Ψ
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
13 Graphite Fabric 601R37143−003,−004
CMS532−19 Class II NA Ψ
14 Graphite Fabric 601R37143−005,−006
CMS532−19 Class II NA Ψ
15 Graphite Fabric 601R37143−007,−008
CMS532−19 Class II NA Ψ
16 Graphite Fabric 601R37143−009,−010
CMS532−19 Class II NA Ψ
17 Glass Fabric 601R37143−011,−012
CMS532−06 Style 120 NA Ψ
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
CMS532−06 Style 120 NA Ψ
21 Spar, Fwd 601R37144−1, −2 E002 Ψ
22 Glass Fabric 601R37144−003,−004
CMS532−06 Style 120 NA Ψ
23 Graphite Fabric 601R37144−005,−006
CMS532−19 Class II NA Ψ
24 Graphite Fabric 601R37144−007,−008
CMS532−19 Class II NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−14 Page 19
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIVI-
TY
25 Graphite Fabric 601R37144−009,−010
CMS532−19 Class II NA Ψ
26 Graphite Fabric 601R37144−011,−012
CMS532−19 Class II NA Ψ
27 Spar, Mid 601R37145−1, −2 E002 Ψ
28 Graphite Fabric 601R37145−003,−004
CMS532−19 Class II NA Ψ
29 Graphite Fabric 601R37145−005,−006
CMS532−19 Class II NA Ψ
30 Graphite Fabric 601R37145−007,−008
CMS532−19 Class II NA Ψ
31 Graphite Fabric 601R37145−009,−010
CMS532−19 Class II NA Ψ
32 Glass Fabric 601R37145−011,−012
CMS532−06 Style 120 NA Ψ
33 Glass Fabric 601R37145−013,−014
CMS532−06 Style 120 NA Ψ
34 Spar, Aft 601R37146−1, −2 E002 Ψ
35 Graphite Fabric 601R37146−003,−004
CMS532−19 Class II NA Ψ
36 Graphite Fabric 601R37146−005,−006
CMS532−19 Class II NA Ψ
37 Graphite Fabric 601R37146−007,−008
CMS532−19 Class II NA 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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−14 Page 20
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
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.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−14 Page 21
May 10/2010
ITEM DESCRIPTION DRAWINGMATERIAL REFER-
ENCEFINISH
CODE ♦EFFECTIVI-
TY
♦ Refer to SRM 51−21−16.
Ψ 7811−7811, 7834−7834, 7848−7848, 7870−7990, 8000−8400
Notes: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−14 Page 22
May 10/2010
PYLON AFT STRUCTURE FRAMING − 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 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).
CAUTION: MAKE SURE THAT THE REMOVED DAMAGE, INCLUDING ANY PREVIOUS DAMAGEREMOVAL, IS WITHIN ALLOWABLE LIMITS AT ANY SPECIFIC LOCATION. RECORDDAMAGE REMOVAL LOCATION.
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).
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−62−14 Page 101
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
DAMAGEREMOVAL LIMIT 1
CSTRUCTURAL REPAIR MANUAL
Pylon Aft Structure Framing − Allowable DamageFigure 101
MasterEFFECTIVITY: ALL 54−62−14 Page 102
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
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−54−62−005 Repair to pylon fire separator panel
601R−54−62−054 Repair to pylon aft detachable part
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−62−14 Page 201
Mar 10/2006
THIS PAGE INTENTIONALLY LEFT BLANK
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.
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−62−31 Page 1
May 10/2010
rsr5
4048
.dg,
om
/vh,
jun1
8/20
07
2
3
4
1
NOTE
The structure is symmetricalaround the aircraft centerline,unless shown differently.
CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 1
MasterEFFECTIVITY: ALL 54−62−31 Page 2
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISH
CODE ♦EFFECTIVI-
TY
Rear Assembly− PylonStructure
601−37112−1009,−1010
†
Rear Assembly− PylonStructure
601−37112−1011,−1012
††
Rear Assembly− PylonStructure
601−37112−1013,−1014
‡
Rear Assembly− PylonStructure
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
Kevlar Fabric (CMS532−03 Type 1), CoreMaterial−NomexHoneycomb(CMS539−01, Type I)
E002/E109 ¶ ♥
2A Skin Panel,Lower
601−37112−83,−84
Kevlar Fabric (CMS532−03 Type 1), CoreMaterial−NomexHoneycomb(CMS539−01, Type I)
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.
♦ Refer to SRM 51−21−16.
† 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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−31 Page 3
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCEFINISH
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
Notes: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 1 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−31 Page 4
May 10/2010
65
rsr5
4067
.dg,
vh,
jun3
0/20
08
NOTE
The structure is symmetricalaround the aircraft centerline,unless shown differently.
1
37
81
73
CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−31 Page 5
May 10/2010
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vh,
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VIEW LOOKING UP
CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−31 Page 6
May 10/2010
3
TOOL FACE
489323334
238932363133
2928261312113631
93230
238
33
389
1620243233
rsr5
4069
.dg,
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−31 Page 7
May 10/2010
TOOL FACE
389
1721253233
38
1093233
389
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21
20
CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−31 Page 8
May 10/2010
TOOL FACE
389
1721253233
38
1093233
378
1093233
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−31 Page 9
May 10/2010
TOOL FACE
358932333435
3893233
389
1418223233
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4072
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 6)
MasterEFFECTIVITY: ALL 54−62−31 Page 10
May 10/2010
TOOL FACE
389
1418223233
2389
14182232363133
238932363133
238932363133
389
1519233233
2389
15192332363133
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 7)
MasterEFFECTIVITY: ALL 54−62−31 Page 11
May 10/2010
389
1519233233
38
109
15192332273334
368
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 8)
MasterEFFECTIVITY: ALL 54−62−31 Page 12
May 10/2010
389323633
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 9)
MasterEFFECTIVITY: ALL 54−62−31 Page 13
May 10/2010
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 10)
MasterEFFECTIVITY: ALL 54−62−31 Page 14
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58932333435
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 11)
MasterEFFECTIVITY: ALL 54−62−31 Page 15
May 10/2010
389
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38
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 12)
MasterEFFECTIVITY: ALL 54−62−31 Page 16
May 10/2010
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 13)
MasterEFFECTIVITY: ALL 54−62−31 Page 17
May 10/2010
4549383942435152
4538395361574243
45473839404243
4538395462584243
454838394041424351
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 14)
MasterEFFECTIVITY: ALL 54−62−31 Page 18
May 10/2010
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39424351
38
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38
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 15)
MasterEFFECTIVITY: ALL 54−62−31 Page 19
May 10/2010
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CSTRUCTURAL REPAIR MANUAL
Aft Structure Skin and Plating − Structure IdentificationFigure 2 (Sheet 16)
MasterEFFECTIVITY: ALL 54−62−31 Page 20
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦ EFFECTIVITY
Rear Assembly− PylonStructure
601R37139−1,−2
7811−7811
7834−7834
7848−7848
7870−7990
8000−8062
Rear Assembly− PylonStructure
601R37139−121,−122
8063−8400
1 Skin, TopCompositeAssembly, AftPylon Structure
601R37140−81,−82
E002/E100 †
Ψ
2 Glass Fabric 601R37140−003,−004
CMS532−06 Style 120 NA Ψ
3 Copper Foil 601R37140−007,−008
CMS553−01 Type II GR 4 NA Ψ
4 Copper Foil 601R37140−009,−010
CMS553−01 Type II GR 4 NA Ψ
5 Copper Foil 601R37140−011,−012
CMS553−01 Type II GR 4 NA Ψ
6 Copper Foil 601R37140−013,−014
CMS553−01 Type II GR 4 NA Ψ
7 Copper Foil 601R37140−015,−016
CMS553−01 Type II GR 4 NA Ψ
8 Graphite Fabric 601R37140−017,−018
CMS532−19 Class II NA Ψ
9 Graphite Fabric 601R37140−019,−020
CMS532−19 Class II NA Ψ
10 Graphite Fabric 601R37140−021,−022
CMS532−19 Class II NA Ψ
11 Graphite Fabric 601R37140−025,−026
CMS532−19 Class II NA Ψ
12 Graphite Fabric 601R37140−027,−028
CMS532−19 Class II NA Ψ
13 Graphite Fabric 601R37140−029,−030
CMS532−19 Class II NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−31 Page 21
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
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
CMS551−09 Class II FM−M GR 4 NA Ψ
16 Adhesive Film 601R37140−035,−036
CMS551−09 Class II FM−M GR 4 NA Ψ
17 Adhesive Film 601R37140−037,−038
CMS551−09 Class II FM−M GR 4 NA Ψ
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
CMS551−09 Class II FM−M GR 4 NA Ψ
23 Adhesive Film 601R37140−049,−050
CMS551−09 Class II FM−M GR 4 NA Ψ
24 Adhesive Film 601R37140−051,−052
CMS551−09 Class II FM−M GR 4 NA Ψ
25 Adhesive Film 601R37140−053,−054
CMS551−09 Class II FM−M GR 4 NA Ψ
26 Graphite Fabric 601R37140−055,−056
CMS532−19 Class II NA Ψ
27 Graphite Fabric 601R37140−057,−058
CMS532−19 Class II NA Ψ
28 Graphite Fabric 601R37140−059,−060
CMS532−19 Class II NA Ψ
29 Graphite Fabric 601R37140−061,−062
CMS532−19 Class II NA Ψ
30 Graphite Fabric 601R37140−063,−064
CMS532−19 Class II NA Ψ
31 Graphite Fabric 601R37140−065,−066
CMS532−19 Class II NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−31 Page 22
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦ EFFECTIVITY
32 Graphite Fabric 601R37140−067,−068
CMS532−19 Class II NA Ψ
33 Graphite Fabric 601R37140−069,−070
CMS532−19 Class II NA Ψ
34 Glass Fabric 601R37140−071,−072
CMS532−06 Style 120 NA Ψ
35 Glass Fabric 601R37140−073,−074
CMS532−06 Style 120 NA Ψ
36 Graphite Fabric 601R37140−079,−080
CMS532−19 Class II NA Ψ
37 Skin, BottomCompositeAssembly, AftPylon Structure
601R37141−1,−2
E002/E100 †
Ψ
38 Graphite Fabric 601R37141−003,−004
CMS532−19 Class II NA Ψ
39 Graphite Fabric 601R37141−005,−006
CMS532−19 Class II NA Ψ
40 Graphite Fabric 601R37141−007,−008
CMS532−19 Class II NA Ψ
41 Graphite Fabric 601R37141−011,−012
CMS532−19 Class II NA Ψ
42 Graphite Fabric 601R37141−013,−014
CMS532−19 Class II NA Ψ
43 Graphite Fabric 601R37141−015,−016
CMS532−19 Class II NA 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
CMS553−01 Class I Type II GR 4 NA Ψ
47 Copper Foil 601R37141−023,−024
CMS553−01 Class I Type II GR 4 NA Ψ
48 Copper Foil 601R37141−025,−026
CMS553−01 Class I Type II GR 4 NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−31 Page 23
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦ EFFECTIVITY
49 Copper Foil 601R37141−027,−028
CMS553−01 Class I Type II GR 4 NA Ψ
50 Copper Foil 601R37141−029,−030
CMS553−01 Class I Type II GR 4 NA Ψ
51 Glass Fabric 601R37141−031,−032
CMS532−06 Style 120 NA Ψ
52 Glass Fabric 601R37141−033,−034
CMS532−06 Style 120 NA Ψ
53 Adhesive Film 601R37141−037,−038
CMS551−09 Class II FM−M GR 4 NA Ψ
54 Adhesive Film 601R37141−039,−040
CMS551−09 Class II FM−M GR 4 NA Ψ
55 Adhesive Film 601R37141−041,−042
CMS551−09 Class II FM−M GR 4 NA Ψ
56 Adhesive Film 601R37141−043,−044
CMS551−09 Class II FM−M GR 4 NA Ψ
57 Adhesive Film 601R37141−045,−046
CMS551−09 Class II FM−M GR 4 NA Ψ
58 Adhesive Film 601R37141−047,−048
CMS551−09 Class II FM−M GR 4 NA Ψ
59 Adhesive Film 601R37141−049,−050
CMS551−09 Class II FM−M GR 4 NA Ψ
60 Adhesive Film 601R37141−051,−052
CMS551−09 Class II FM−M GR 4 NA Ψ
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
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−31 Page 24
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
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
66 Graphite Fabric 601R37148−003,−004
CMS532−19 Class II NA Ψ
67 Graphite Fabric 601R37148−005,−006
CMS532−19 Class II NA Ψ
68 Graphite Fabric 601R37148−007,−008
CMS532−19 Class II NA Ψ
69 Graphite Fabric 601R37148−009,−010
CMS532−19 Class II NA Ψ
70 Graphite Fabric 601R37148−011,−012
CMS532−19 Class II NA Ψ
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
71A Graphite Fabric 601R37148−019,−020
CMS532−19 Class II NA 8077−8083
71B Graphite Fabric 601R37148−025,−026
CMS532−19 Class II NA 8084−8400
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−31 Page 25
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦ EFFECTIVITY
72 Copper Foil 601R37148−015,−016
CMS553−01 Class I Type II GR 4 NA 7811−7811
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
CMS553−01 Class I Type II GR 4 NA 7811−7811
7834−7834
7848−7848
7870−7990
8000−8076
74A Graphite Fabric 601R37149−019,−020
CMS532−19 Class II NA 8077−8400
75 Copper Foil 601R37149−005,−006
CMS553−01 Class I Type II GR 4 NA 7811−7811
7834−7834
7848−7848
7870−7990
8000−8076
75A Surf Film 601R37149−021,−022
BAMS 551−010 NA 8077−8400
76 Graphite Fabric 601R37149−007,−008
CMS532−19 Class II NA Ψ
77 Graphite Fabric 601R37149−009,−010
CMS532−19 Class II NA Ψ
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 6)
MasterEFFECTIVITY: ALL 54−62−31 Page 26
May 10/2010
ITEM DESCRIPTION DRAWING MATERIAL REFERENCE
FIN-ISH
CODE♦ EFFECTIVITY
78 Graphite Fabric 601R37149−011,−012
CMS532−19 Class II NA Ψ
79 Graphite Fabric 601R37149−013,−014
CMS532−19 Class II NA Ψ
80 Graphite Fabric 601R37149−015,−016
CMS532−19 Class II NA Ψ
81 Doubler 601R37153−1 0.040 (1.02) MIL−T−9046 TYCP−3 Cond A
T002 Ψ
− Item not shown.
♦ Refer to SRM 51−21−16.
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
Notes: All dimensions are given in inches followed by millimeters in parentheses.
CSTRUCTURAL REPAIR MANUAL
Key to Figure 2 (Sheet 7)
MasterEFFECTIVITY: ALL 54−62−31 Page 27
May 10/2010
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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
CSTRUCTURAL REPAIR MANUAL
MasterEFFECTIVITY: ALL 54−62−31 Page 101
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.
CSTRUCTURAL REPAIR MANUAL
TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 1)
MasterEFFECTIVITY: ALL 54−62−31 Page 102
Apr 10/2005
COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS
TYPE OFDAMAGE
LOCATION OFDAMAGE LIMITS REMARKS
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.
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.
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.
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.
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.
CSTRUCTURAL REPAIR MANUAL
TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 2)
MasterEFFECTIVITY: ALL 54−62−31 Page 103
Apr 10/2005
COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS
TYPE OFDAMAGE
LOCATION OFDAMAGE LIMITS REMARKS
Dents ordepressions
(Cont’d)
Laminate The maximum dent 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 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:
− the distance from anyunrepaired damage or structuralfastener is 3D minimum.
− 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.
Do a permanent repair no laterthan the next ’C’ 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.
Do a permanent repair no laterthan the next ’C’ check.
CSTRUCTURAL REPAIR MANUAL
TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 3)
MasterEFFECTIVITY: ALL 54−62−31 Page 104
Apr 10/2005
COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS
TYPE OFDAMAGE
LOCATION OFDAMAGE LIMITS REMARKS
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).
Apply speed tape to thedamaged areas (Refer to SRM51−27−15).
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.
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.
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.
Do a permanent repair no laterthan the next ’C’ check.
CSTRUCTURAL REPAIR MANUAL
TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 4)
MasterEFFECTIVITY: ALL 54−62−31 Page 105
Apr 10/2005
COMPOSITE STRUCTURE—ALLOWABLE DAMAGE LIMITS
TYPE OFDAMAGE
LOCATION OFDAMAGE LIMITS REMARKS
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.
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.
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.
CSTRUCTURAL REPAIR MANUAL
TRAILING EDGE COMPOSITE STRUCTURE, PYLON—Allowable DamageFigure 101 (Sheet 5)
MasterEFFECTIVITY: ALL 54−62−31 Page 106
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
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−54−62−022 Temporary repair to pylon T/E upper and lower panels
CSTRUCTURAL REPAIR MANUAL
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