THIS MATERIAL CONTAINS PROPRIETARY INFORMATION OF LOCKHEED MARTIN AERONAUTICS COMPANY. DISCLOSURE TO OTHERS, USE OR COPYING WI THOUT EXPRESS WRITTEN AUTHORIZATION OF LOCKHEED MARTIN AERONAUTICS COMPANY IS STRICTLY PROHIBITED.

© 2008 LOCKHEED MARTIN CORPOR ATION. ALL RIGHTS RESERVED. 

# 093-57-207

August 24, 1989 Page 1 of 31 Revision 5, November 14, 2008 WINGS - PYLON SUPPORT STRUCTURE – INSPECTION AND REPAIR/REPLACEMENT OF RIB CAPS AT IWS 503, 529 AND 555

1. PLANNING INFORMATION

A. EFFECTIVITY

NOTE : This service bulletin is applicable to the following L-1011 aircraft models:

L-1011-385-1 L-1011-385-1-14 L-1011-385-1-15 L-1011-385-3

(1) Aircraft Affected
Lockheed Serial No. 193A through Y and 293A through F: -1002 through -1250.

(2) Aircraft Ownership and Registration

Service Bulletin 093-11-126 lists L-1011 aircraft wh ich have been sold by the original operator and provides information on the cu rrent ownership and registration numbers for those aircraft. The bulletin also lists model and current regi stration numbers for all existing aircraft.
(3) Spares Affected
Lockheed supplied spares are not affected.

B. REASON
Several operators have reported finding cracked ri b cap castellations on a number of L-1011-385-1, 430,000 pound GTOW aircraft. The predominance of cracked castellation s have been found on the upper cap at IWS 555.0 which is the area modified by Service Bulletin 093-57-157 for L-1011-385-1-15 aircraft. Cracked castellations were also found on th e lower cap at IWS 555.0, and at a few locations on the upper caps at IWS 529.4 and 503.76. Crac ked clips were found on the closeout bulkhead. Cracking on one aircraft was so extensive that t he upper rib cap at IWS 555.0 required replacement.
One operator has reported that on inspection of one L-1011-385-1-15 aircraft which was modified in accordance with Service Bulletin 093-57-157, t he rib cap castellations were cracked but the modification doublers were not cracked.
Castellation cracks may propagate into the rib cap proper, and with several castellations cracked and the rib cap severed, fail safe capability cannot be analytically proven. Continued operation in this condition can result in severe additional damage and loss of stiffness in the pylon back-up structure creating a potential flutter hazard.
This service bulletin supersedes Servic e Bulletin 093-57-157 in its entirety.

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August 24, 1989 Page 2 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT C. DESCRIPTION

(1) Inspection of Aircraft

The No. 2L & 2R outboard fuel tanks are def ueled and purged, pylon aft fairing panels are removed and lower surface access panels 532AB, 532BB, 532CB, 632AB, 632BB, and 632CB are removed.
IWS 503, 529, and 555 upper and lower ribs are insp ected at the castellations, skin clips, and stringer clips. (See Figure 1 for inspection ar ea). Pylon back-up torque box stub ribs and closeout bulkhead are inspected at several locations. Upper and lower wing skins are inspected at fastener holes at IWS 503, 529, and 555 ribs. The pylon drag strut aft fitting attachments are inspected.

(2) Repair of Aircraft
Cracked clips should be replaced. A single cracke d castellation with a crack no longer than 3/4 inches may be stop drilled as a temporary repair provided that two adjacent castellations on either side are crack free. If more than two consecut ive castellations are cracked, modification of the aircraft as described below should be considered.

(3) Modification of Aircraft
The wing engines must be supported or removed. The No. 2L & 2R outboard fuel tanks are defueled and purged. Lower surface access panels 532AB, 532BB, 532CB, 632AB, 632BB, and 632CB are removed.

NOTE : It may be necessary to remove pylon fairi ng panels to disconnect the pylon drag strut aft attachment bolt so that the drag strut may be lowered out of the way.
The 1647070-101 kit provides the necessary parts to replace the upper rib caps at IWS 503, 529, 555, the lower rib caps at IWS 555, and the vertical support at IWS 503 for -1 aircraft serials -1002 through -1188.
The 1647070-141 kit provides the necessary parts to replace the lower rib caps at IWS 555 and the vertical support at IWS 503 for -3 aircraft serials -1157 through -1250.
The 1647070-103 through -125 kits provide the necessary parts to replace rib caps at their respective location, refer to Section 3 for application.

The 1647070-143 and -145 kits install a ne w forward section of the 1527033-703/-704 upper rib cap without removing the 1528402 fitting at IWS 555.
The 1647070-155 kit is a supplemental kit to be added to the -101 kit to permit alternate location of the cap splice installation (if preferred) wh en the 1527033-703 (IWS 555 rib) upper cap only is installed.

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August 24, 1989 Page 3 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT NOTE : (1) On L-1011-385-1 aircraft serial numbers 193Y -1189 and up, heavier duty upper rib caps were installed during production at IWS 555.
(2) On L-1011-385-3 aircraft serial numbers -1157 and up, heavier duty upper rib caps were installed during production at IWS 503, 529, and 555.
(3) No cracks have been reported in the lower rib caps at IWS 503 and 529. However, replacement kits have been designed for these locations. (See Section 1.G) They are identified in this service bulletin and on drawing No. 1647070, together with installation instructions. If these caps are found to be cracked contact Lockheed Martin Aeronautics Company. (See Section 1.M)

The 1527479-107/-108 tee extrusions on the rib cap installation are replaced with back-to-back sheet metal angles in the torque box area at t he forward end of IWS 503. The existing vertical support is removed and the new back-to-back sheet metal angles are installed. Designated upper cap fasteners are removed and holes are drilled a nd reamed for installation of new fasteners, caps, angles and splices. The fuel tanks are resealed and access doors installed.

D. COMPLIANCE
For L-1011-385-1 and L-1011-385-3 aircraft S/N -1002 through -1250 it is recommended that the rib caps be inspected in accordance with Section 2.A. at a threshold of 15,000 flights or 27,000 flight hours, whichever occurs first, and repeat inspection interval s of 3,600 flights or 7,200 flight hours, whichever occurs first. Upon receipt of this service bulletin, aircraft which have exceeded the inspection threshold should be inspected within 1,800 flights or 3, 600 flight hours, whichever occurs first.

NOTE : If the intent of this inspection has been accompli shed prior to receipt of this service bulletin, reinspection is not required until 3,600 flights or 7,200 flight hours, whichever occurs first.
Cracked or damaged structure must be repaired or re placed before further flights. Modification of the aircraft may also be accomplished in accordance with Section 2.B of this service bulletin. Modification of a particular rib cap resets the inspection threshol d for that rib cap to the interval defined above. After the reset threshold has been exceeded, the repeat inspection intervals defined above are again effective for that rib cap.

E. APPROVAL
The EFFECTIVITY information of Section 1, Par agraph A. (1) and the technical content of the ACCOMPLISHMENT INSTRUCTIONS of Section 2 of this service bulletin are FAA approved.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT F. MANPOWER

Accomplishment of this modification will require the following man-hours:

M/Hrs per Aircraft

Gain Access 16.0 M/Hrs Modification (See chart below) Return Aircraft to Operations 16.0 M/Hrs

Total * 32.0

* Man-Hours shown do not include modification time. Refer to chart below.

M/Hrs M/Hrs Kit Cap Installation Per Wing Per Aircraft

1647070-101 Cap Installation 384.0 768.0 1647070-103 Lower, IWS 503.76, LH 48.0 96.0 1647070-105 Upper, IWS 503.76, LH 48.0 96.0 1647070-107 Lower, IWS 503.76, RH 48.0 96.0 1647070-109 Upper, IWS 503.76, RH 48.0 96.0 1647070-111 Lower, IWS 529.40, LH 48.0 96.0 1647070-113 Upper, IWS 529.40, LH 48.0 96.0 1647070-115 Lower, IWS 529.40, RH 48.0 96.0 1647070-117 Upper, IWS 529.40, RH 48.0 96.0 1647070-119 Lower, IWS 555.00, LH 48.0 96.0 1647070-121 Upper, IWS 555.00, LH 48.0 96.0 1647070-123 Lower, IWS 555.00, RH 48.0 96.0 1647070-125 Upper, IWS 555.00, RH 48.0 96.0 1647070-127 Vertical Angle IWS 503 36.0 72.0 1647070-133 Vertical Angle IWS 503 36.0 72.0 1647070-141 Cap Installation 132.0 264.0 1647070-143 Upper, IWS 555.00, LH 24.0 48.0 1647070-145 Upper, IWS 555.00, RH 24.0 48.0 1647070-155 Upper, IWS 555.00, L&RH 24.0 48.0
It is estimated that incorporation of the 1647070-101 kit, with two men working on each wing, will require eight days down time.
It is estimated that incorporation of the 1647070-141 kit, with two men working on each wing, will require three days down time.

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August 24, 1989 Page 5 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT G. MATERIAL - COST AND AVAILABILITY
Refer to Section 1, EFFECTIVITY, for complete kit effectivity. Refer to Section 3, MATERIAL INFORMATION, for deta ils of kit parts.
The following kits are applicable for this modification:

Kit No. Per Kit Availability

1647070-101 * * 1647070-103 * * 1647070-105 * * 1647070-107 * * 1647070-109 * * 1647070-111 * * 1647070-113 * * 1647070-115 * * 1647070-117 * * 1647070-119 * * 1647070-121 * * 1647070-123 * * 1647070-125 * * 1647070-127 * * 1647070-133 * * 1647070-141 * * 1647070-143 * * 1647070-145 * * 1647070-155 * *

* For Pricing and Availability Contact:
Hi-Tech Aero Spares 9436 Meridian Way West Chester, OH 45069

Phone: 513-942-4541

Fax: 513-942-6581 Email: htassales@argoturbo.com

H. TOOLING - PRICE AND AVAILABILITY

None.

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August 24, 1989 Page 6 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT I. WEIGHT AND BALANCE
The estimated weight and balance change as a result of the complete installation of the applicable kit is as follows (see Section 3, MATERIAL INFORMATION, for kit effectivity):
Weight Moment Kit Pounds (Inch-Pounds)

1647070-101 Plus 44.0 Plus 56,012 1647070-103 Plus 6.7 Plus 8,442 1647070-105 Plus 9.2 Plus 11,592 1647070-107 Plus 6.7 Plus 8,442 1647070-109 Plus 7.9 Plus 9,954 1647070-111 Plus 5.2 Plus 6,604 1647070-113 Plus 6.2 Plus 7,874 1647070-115 Plus 5.5 Plus 6,985 1647070-117 Plus 6.8 Plus 8,636 1647070-119 Plus 2.4 Plus 3,072 1647070-121 Plus 2.5 Plus 3,200 1647070-123 Plus 3.0 Plus 3,840 1647070-125 Plus 3.0 Plus 3,840 1647070-127 Plus 3.0 Plus 3,810 1647070-133 Plus 3.0 Plus 3,810 1647070-141 Plus 8.4 Plus 10,727 1647070-143 Plus 2.5 Plus 3,200 1647070-145 Plus 3.0 Plus 3,840 1647070-155 Plus 5.5 Plus 7,040

J. ELECTRICAL LOAD DATA None.

K. REFERENCES

Service Bulletins: 093-11-126 093-57-157

Maintenance Manual: 6-40-00 12-17-00 28-11-00 28-22-00 28-41-01 28-41-24 54-00-03 54-00-04 54-24-01 54-51-54 54-51-55 54-51-56 57-33-01 71-00-01 Drawing: 1647070
Structural Repair Manual: 57-12-00

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT L. OTHER PUBLICATIONS AFFECTED

None.

M. CORRESPONDENCE

Attn: Lockheed Mart in Aeronautics Company Continuing Airworthiness Project 86 South Cobb Drive Marietta, GA 30063-0579

Telephone hotline (770) 494-5444 Facsimile telephone (770) 494-5445

Email: l1011.support@lmco.com

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August 24, 1989 Page 8 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT 2. ACCOMPLISHMENT INSTRUCTIONS

A. INSPECTION AND REPAIR OF AIRCRAFT

WARNING : VERIFY THAT THE AIRCRAFT AND EQ UIPMENT USED IN FUEL SYSTEM OPERATIONS ARE STATICALLY GROUNDED IN ACCORDANCE WITH APPROVED PROCEDURES. OBSERVE ALL SAFETY REGULATIONS, REFERENCE MAINTENANCE MANUAL 12-17-00 AND 28-11-00.
(1) Defuel, drain and purge the number 2L and num ber 2R outboard fuel tanks, reference Maintenance Manual 28-11-00 and 28-22-00.
(2) Remove lower wing surface access panels 532AB, 532BB, 532CB, 632AB, 632BB and 632CB, reference Maintenance Manual 6-40-00 and 57-33-01.
(3) Remove and store for reinstallation the quantity probes, sight gages and housings for accessibility to perform service bulletin work, reference Maintenance Manual 28-41-01 and 28-41-24.
(4) Remove pylon aft fairing panels.
(5) Inspect the wing box pylon back-up structure, fr ont spar to rear spar, for castellation and/or skin clips cracked between stringers and cracked stringer clips, at the following locations:
IWS 503.76 rib, upper/lower cap IWS 529.40 rib, upper/lower cap IWS 555.00 rib, upper/lower cap
Refer to Figure 1 for inspections and Figure 2 for repairs.
(6) Inspect the

. pylon backup torque box structure. Pe rform a general inspection for cracks in the two stub ribs and P/N 1527807-101 closeout bulkhead and associated clips. Inspect for cracks at the rib/torque box vertical attach tee P/N 1527479-107/-108 and the closeout bulkhead P/N 1527807-101 at the cuto ut for the upper skin stringer.
(7) Visually inspect the wing box external areas at the drag brace aft wing fitting,

. paying close attention to the following: (a) Inspect the pylon drag strut aft lug bolt head for cracks or failure.
(b) Inspect the six Hi-Tigues attaching the drag strut aft support fitting, P/N 1527342, to the wing pylon support skates.
(8) Inspect the outer surface of the wing upper and lower skins for cracks along the rib attachment at the fastener holes. Also look for cracks that do not originate from fastener holes but are oriented in the forward and aft di rections between the two rows of attachments.

NOTE : A single cracked castellation with a crack no longer than 3/4 inches may be stop drilled as a temporary repair limited to 3,600 flights or 7,200 flight hours, whichever occurs first, provided two adjacent castellations on either side are crack free (i.e. every third castellation may be cracked and stop drilled). Repair cracked castellations in accordance with Figure 2. (NOTE: If more than two consecutive castellations are cracked, modification in accordance with Section 2.B should be considered). If two or more adjacent castellations are cracked and repair rather than modification is planned, replacement of a segment of the ribcap using typical cap splices shown on DWG 1647070 should be considered. Cracked clips should be replaced. All other damaged structural items should be repaired in accordance with the best shop practices, following procedures in Structural Repair Manual 57-12-00. Advise Lockheed Martin Aeronautics Company of all such repairs.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT (9) Return aircraft to operations as follows:
(a) Reinstall wing lower surface access panel and pylon aft fairing panels.
(b) Reinstall quantity probes, sight gages and housings, reference Maintenance Manual 28-41-01 and 28-41-24.

B. MODIFICATION OF AIRCRAFT

WARNING : VERIFY THAT THE AIRCRAFT AND EQ UIPMENT USED IN FUEL SYSTEM OPERATIONS ARE STATICALLY GROUNDED IN ACCORDANCE WITH APPROVED PROCEDURES. OBSERVE ALL SAFETY REGULATIONS, REFERENCE MAINTENANCE MANUAL 12-17-00 AND 28-11-00.
(1) Prepare aircraft for modification as follows:
(a) Defuel, drain and purge the number 2L and num ber 2R outboard fuel tanks, reference Maintenance Manual 28-11-00 and 28-22-00.
(b) Remove lower wing surface access panels 532AB, 532BB, 532CB, 632AB, 632BB and 632CB, reference Maintenance Manual 6-40-00 and 57-33-01.
(c) Remove and retain the quantity probes, sight gages and housings for accessibility, reference Maintenance Manual 28-41-01 and 28-41-24.
(d) Support engine in accordance with Maintenance Manual 54-00-03.

NOTE : Step (e) below is optional, and may be performed for accessibility purposes at the operator's discretion. (e) Remove engine in accordance with Maintenance Manual 71-00-01 and 54-00-04.

CAUTION : LIMIT REMOVAL OF FASTENERS TO ONE RIB CAP PER WING AT ANY ONE TIME TO PREVENT STRUCTURE MISALIGNMENT. (2) Modify 1527031 rib installation IWS 503.76 LH/RH as follows, refer to SMID 1647070 Sheet 3:

NOTE : Use the following kits for IWS 503.76 cap modifications: (Refer to Section 3 for kit effectivity)
1647070-103 LH lower cap 1647070-105 LH upper cap 1647070-107 RH lower cap 1647070-109 RH upper cap
(a) Remove 1527031-355/-356 or -357/-358 Lower Cap. Cut old cap just aft of STGR 18 as shown in Zone 3D16 and View H, Zone 3A13. Do not remove section forward of STGR 18.

NOTE : Original cap may be cut into several pieces to facilitate removal.
(b) Install 1527031-501/-502 Lower Cap LH/RH using noted hardware and observing delta notes 53 and 54.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT NOTE : New cap may be cut into two pieces to facilitate installation, if required to cut cap into two pieces, cut so that splice will be located at STGR 13, refer to View J, Zone 3A10.
If new cap can be installed as one pi ece the splice at STGR 13 will not be required.
It may be necessary to trim excess material from cap in the area of STGR 6 to provide clearance from existing clip (-500 A/C only).
(c) Install the splice at STGR 18 as sh own in View H, Zone 3A13, using the following parts:
1527031-525 Strap 1527031-527/-528 Angle 1527031-523/-524 Angle
(d) If splice at STGR 13 is required, install as shown in View J, Zone 3A10, using the following parts:
1527031-505/-506 Splice Angle 1527031-509 Strap

NOTE : Steps (e) through (i) below are applicable to Serial No. 193A,B,C,E,K,L,M,N,P,R,S,T,U: - 1002 through -1187.
(e) Remove 1527031-287/-288 or -337/-338 Upper Cap. Cut old cap just forward of STGR 24 as shown in Zone 3E16 and View N, Zone 3G14. Do not remove section forward of STGR 24.

NOTE : Original cap may be cut into severa l pieces to facilitate removal.
(f) Remove and retain for reuse 1527031-241/-242 Doubler, refer to Zone 3D14.

1 Locate 1527031-513 Spacer and existing doubler in same location as shown in section P-P Zone 3G12. Drill holes in spacer locating from existing holes, refer to Zone 3D14 for fasteners.
(g) Install 1527031-503/-504 Upper C ap LH/RH using noted hardware and observing delta notes 53 and 54.

NOTE : New cap may be cut into two pieces to facilitate installation. If required to cut cap into two pieces, cut so that splic e will be located at STGR 18, refer to View K, Zone 3F8.
If new cap can be installed as one piec e the splice at STGR 18 will not be required.
(h) Install the splice at STGR 24 as shown in View N, Zone 3G14, using the following parts:
1527031-517 Angle Spacer 1527031-515 pacer/Filler 1647070-153 Shim 1527031-521 Angle 1527031-519/-520 Angle
(i) If splice at STGR 18 is required, install as shown in View K, Zone 3F8, using the following parts:
1527031-507/-508 Splice Angle 1527031-511 Strap

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August 24, 1989 Page 11 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT (j) Modify the vertical angle at fo rward end of rib using the following kits, refer to sheet 2 for details: (Refer to Section 3 for kit effectivity)
1647070-127 Vertical Angle 1647070-133 Vertical Angle (3) Modify 1527032 Rib installation IWS 529.40 LH/RH as follows, refer to SMID 1647070 Sheet 4:

NOTE : Use the following kits for IWS 529 .40 cap modifications: (Refer to Section 3 for kit effectivity)
1647070-111 LH Lower Cap 1647070-113 LH Upper Cap 1647070-115 RH Lower Cap 1647070-117 RH Upper Cap
(a) Remove 1527032-355/-356 or -357/-358 Lower Cap.

NOTE : Original cap may be cut into several pieces to facilitate removal.
(b) Install 1527032-501/-502 Lower Cap LH/RH using noted hardware and observing delta notes 53 and 54.

NOTE : Cut new cap into two pieces to fac ilitate installation. Cut so that splice will be located at STGR 13, re fer to View U, Zone 4A12.
It may be necessary to trim excess materi al from cap in the area of STGR's 10, 11, 13, 14 to provide clearance from existing clip (-500 A/C only).
(c) Install the splice at STGR 13 as shown in View U, Zone 4A12, using the following parts:
1527032-509 Strap 1527032-505/-506 Splice Angle

NOTE : Steps (d) through (f) below are applicable to Serial No. 193A,B,C,E,K,L,M,N ,P,R,S,T,U; -1002 through -1187.
(d) Remove 1527032-285/-286 or -307/-308 Upper Cap.

NOTE : Original cap may be cut into several pieces to facilitate removal.
(e) Install 1527032-503/-504 Upper Cap LH/RH using noted hardware and observing delta notes 53 and 54.

NOTE : Cut new cap into two pieces to fa cilitate installation. Cut so that splice will be located at STGR 18, refer to View V, Zone 4F11.
(f) Install the splice at STGR 18 as shown in View V, Zone 4F11, using the following parts:
1527032-511 Strap 1527032-507/-508 Splice Angle (4) Modify 1527033 Rib installation IWS 555.00 LH/RH as follows, refer to SMID 1647070 Sheet 5.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT NOTE : Use the following kits for IWS 555.00 cap modifications: (Refer to Section 3 for kit effectivity) 1647070-119 LH Lower Cap 1647070-121 LH Upper Cap 1647070-123 RH Lower Cap 1647070-125 RH Upper Cap 1647070-143 LH Upper Cap 1647070-145 RH Upper Cap 1647070-155 LH & RH Upper Cap
The -143/-145 Kits may be used to install a new forward section of the 1527033-703/-704 Upper Cap (STGR 13 to front spar - one piece) without removing the 1528402 Outboard Pylon Support Fitting; conversely, this fitting must be removed to install the -121/-125 and/or -119/-123 Kits. Presently, the -121/-125 Kits are the recommended installations. The -155 Kit includes parts from both the -143/-145 Kits without any -123/-125 Kit parts. Kits -143, -145, and -155 are not required for aircraft that have already had -101 or -141 Kits installed in their entirety or -121 and -125 Kits individually installed.
If installing the -143, -145 or -155 Kit only, go to Step (j); otherwise, continue with step (a).
(a) Remove the 1528402 fitting if required as follows:

1 Remove the two outboard retaining nuts fo r the 0.625 diameter bolts, that secure the aft pylon drag strut to the lower wing surface and the fitting.

2 Drive the bolts down carefully until the bolt head s contact the aft clevis lugs of the pylon drag strut.

3 Remove all fasteners attaching the fitting to the rib structure, refer to Sheet 5, Zone F4.

4 With all fasteners removed, lift the fitti ng up and outboard of the two protruding bolts.

NOTE : If the fitting can be removed at this point, go to Step (b); otherwise continue with Step (a)5 through (a)10

. 5 Remove small access plate No. 452FL and 462FL on left hand side of pylon, reference Maintenance Manual 6-40-00.

6 Remove trailing edge wedge fairing No. 453H and 463H, reference Maintenance Manual 54-51-56 and 6-40-00.

7 Remove glove fairing No. 453B and 463B, reference Maintenance Manual 54-51-54 and 6-40-00.

8 Remove wing pylon trailing edge assembly No. 453C and 463C, reference Maintenance Manual 54-24-01 and 6-40-00.

9 Remove Skirt Fairing No. 453JL and 463JL, reference Maintenance Manual 54-51-55 and 6-40-00.

NOTE : Disconnect and cap hydraulic lines as necessary.

10 Remove Drag Strut aft attachment bolt. Lower strut until the 1528402 Fitting can be removed (approx. 6 inches), refere nce Maintenance Manual 54-00-03.
(b) Remove 1527033-303/-304 Forward Lower Cap.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT NOTE : Original cap may be cut into seve ral pieces to facilitate removal. Do not remove section of cap between rear spar and STGR 8.
(c) Install 1527033-701/-702 Lower Cap LH /RH using noted har dware and observing delta notes 53, 54, and 62.

NOTE : Cut new cap into two pieces to facilitate installation. Cut so that splice will be located at STGR 14, refer to View W, Zone 5A10. It may be necessary to trim excess material from cap in the area of STGR's 9, 10, 11 to provide clearance from existing clips (-500 A/C only).
(d) Install the splice at STGR 14 as shown in View W, Zone 5A10, using the following parts: 1527033-709 Strap 1527033-705/-706 Splice Angle 1527033-713 Block

NOTE : Steps (e) through (g) below are applicable to Serial No. 193A,B,C,E,K,L,M,N,P,R,S,T,U: -1002 through -1187.
(e) Remove 1527033-519/-520 Upper Cap.

NOTE : Original cap may be cut into seve ral pieces to facilitate removal.
(f) Install 1527033-703/-704 Upper Cap LH /RH using noted har dware and observing delta notes 53 and 54.

NOTE : Cut new cap into two pieces to facilitate installation. Cut so that splice will be located at STGR 18, refer to View Y, Zone 5A5.
(g) Install the splice at STGR 18 as shown in View Y, Zone 5A5, using the following parts: 1527033-711 Strap 1527033-707/-708 Splice Angle (h) Reinstall the 1528402 Fitting using noted hardware, refer to Zone 5F4.
(i) Reattach drag strut and assemble all hydraulic lines.

NOTE : Steps (j) through (l) are applicable to the -143, -145, and -155 Kits.
(j) Remove 1527033-519/-520 Upper Cap from STRG 13 to the front spar as shown on drawing 1647070.

NOTE : Original cap may be cut into seve ral pieces to facilitate removal.
(k) Install 1527033-703/-704 Upper Cap LH/RH usi ng noted hardware and observing delta note 61.
(l) Install the upper splice at STGR 12, 13, and 14 as shown on 1647070, View AB using the following parts: 1647070-147/-148 Angle Splice L&RH 1647070-149 Plate-Splice 1647070-151 Strap-Splice
(5) Return aircraft to operational status.
(a) Remove all tools and debris from fuel tanks.
(b) Reinstall all quantity probes, sight gages and housings, reference Maintenance Manual 28-41-01 and 28-41-24.
(c) Reinstall all access panels.

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT Figure 1. Typical Rib Cap Castellation Cracks (Sheet 1 of 2)

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT Figure 1. Typical Rib Cap Castellation Cracks (Sheet 2 of 2)

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT Figure 2. Cracked Castellation Repair (Sheet 1 of 3)

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT Figure 2. Cracked Castellation Repair (Sheet 2 of 3)

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USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT PARTS REQUIRED FOR REPAIR:

SPLICE PLATE: 7075-T6 AL. 0.190 IN. THK.

ANGLE: 7075-T6 AL SHT. (FORM IN 0 CONDITION). 0.090 IN. THK.

ANGLE: 7075-T6 AL SHT. (FORM IN 0 CONDITION). 0.090 IN. THK.

FILLER: 7075-T6 AL, THICKNESS AS NEC ESSARY BETWEEN EXISTING STIFFENER AND

FILLER: 7075-T6 AL, THICKNESS AS NE CESSARY BETWEEN EXISTING CLIP AND

FILLERS: 7075-T6 AL, THICKNESS AS NE CESSARY BETWEEN EXISTING WEB AND

FILLER: 7075-T6 AL, THICKN ESS AS NECESSARY BETWEEN EXISTING WEB AND STIFFENER

NEW FASTENERS: HLT-314-6's OR EQUIVALENT, MIN. SPACING OF 4D, MIN. ED OF 2D

NEW FASTENERS: HLT-314-X'S OR EQUIVALENT; MI N. SPACING OF 4D. THESE FASTENERS ARE TO BE

THE SAME DIAMETER AS, AND IN LINE WITH EXISTING ADJACENT FASTENERS ( ). MIN ED OF 2D

+ EXISTING FASTENERS. WHEN REMOVED, REPLACE WI TH HLT-414-X's OR EQUIVALENT.

NOTE

STOP DRILL CRACK, 3/16 DIA. HOLE. VERIFY RE MOVAL OF CRACK TIP. COLD WORKING THE HOLE

IS RECOMMENDED.

FINISH PER MAINTENANCE MANUAL, CHAPTER 51.

WET INSTALL, P1 FIT.

4 THIS REPAIR MAY BE EXTENDED TO COVER MULTIPLE CRACKS IN ADJACENT CASTELLATIONS: HOWEVER, IF MORE THAN TWO CONSECUTIVE CASTELLATIONS ARE CR ACKED, MODIFICATION PER SECTION 2(B) SHOULD BE CO NSIDERED. IF TWO OR MORE ADJACENT CASTELLATIONS ARE CRACKED AND REPAIR RATHER THAN MODIFICA TION IS PLANNED, REPLACEMENT OF A SEGMENT OF THE RIBCAP USING TYPICAL CAP SPLICES SHOWN ON DWG 1647070 SHOULD BE CONSIDERED.

5 FILLER REQUIREMENTS MAY VARY FROM TH OSE SHOWN, DEPENDING ON THE RELATIVE THICKNESSES OF ALL TH E PARTS INVOLVED.

Figure 2. Cracked Castellation Repair (Sheet 3 of 3)

# 093-57-207

August 24, 1989 Page 19/20 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT 3. MATERIAL INFORMATION

A. 1647070-101 Kit is applicable to Serial No. 193A, B, C, E, K, L, M, N, P, R, S, T, U: -1002 through -1187. Service Mod installation incorpor ating kits -105, 109, -113, -117 through -127.

1647070-103 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap, IWS 503.76 L/H.

1647070-105 Kit is applicable to Serial No. 193A, B, C, E, G, H, J, K, L, M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 503.76 L/H.

1647070-107 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap IWS 503.76 R/H.

1647070-109 Kit is applicable to Serial No. 193A, B, C, E, G, H, J, K, L, M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 503.76 R/H.

1647070-111 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap IWS 529.40 L/H.

1647070-113 Kit is applicable to Serial No. 193A, B, C, E, G, H, J, K, L, M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 529.40 L/H.

1647070-115 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap IWS 529.40 R/H.

1647070-117 Kit is applicable to Serial No. 193A, B, C, E, G, H, J, K, L, M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 529.40 R/H.

1647070-119 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap IWS 555.00 L/H.

1647070-121 Kit is applicable to Serial No. 193A, B, C, E, G, H, J, K, L, M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 555.00 L/H.

1647070-123 Kit is applicable to Serial No. 193A through Y and 293A through F: -1002 through -1250. Service Mod inst allation, Lower Cap IWS 555.00 R/H.

1647070-125 Kit is applicable to Serial No. 193A, B, C, E, G, J, K, L, N M, N, P, R, S, T, U, V, W, Y: -1002 through -1188. Service Mod inst allation, Upper Cap, IWS 555.00 R/H.

1647070-127 Kit is applicable to Serial No. 193A, B, C, E, K, L, M, N, P, R, S, T: -1002 through -1187. Service mod inst allation, Vertical Angle, IWS 503.76.

1647070-133 Kit is applicable to Serial No. 193B, C, G, H, J, N, S, U, W, Y, and 293A through F: -1189 through -1250. Service mod inst allation, Vertical Angle, IWS 503.76.

1647070-141 Kit is applicable to Serial No. 193G, H, J, V, W, Y; 293A, B, F: -1157 through -1250 and 193B, C, N, U, S; 293C: -1189 through -1250. Service Mod installation incorporating Kits -119, -123 and -133.

1647070-143 Kit is applicable to Serial No. 193A through Y: -1002 through -1188. Service Mod installation, Upper Cap IWS 555.00 L/H without removing the 1582402 fitting.

1647070-145 Kit is applicable to Serial No. 193A th rough Y: -1002 through -1188. Service Mod installation, Upper Cap IWS 555.00 R/H without removing the 1582402 fitting.

1647070-155 Kit is applicable to Serial No. 193A through Y: -1002 through -1188. A supplemental kit to be added to the -101 Kit to permit alternate location of the cap splice installation (if preferred) when the 1527033-7 03 (IWS 555 Rib) Upper Cap only is installed.093-57-207August 24, 1989Page 21/22Revision 5, November 14, 2008USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENTQuantityPART NUMBER-101-103-105-107-109-111-113-115-117-119-121-123-125-127-133-141-143-145-155UnitList KeywordInstructionDispositionAN960D10 200 50 50 50 50 50 50 50 50 50 50 50 50 50 - 100 50 50 - (2) WasherAN960D416 20 - - - - - 4 - 4 50 50 50 50 - - - 50 50 - (2) WasherAN960D516 200 50 50 50 50 50 50 50 50 50 50 50 50 50 - 100 50 50 - (2) WasherAN960D616 160 40 40 40 40 40 40 40 4 40 40 40 40 40 - 80 40 40 - (2) WasherAN960D816 100 25 25 25 25 25 25 25 25 25 25 25 25 25 - 50 25 25 - (2) WasherHLT109-6-5 4 - - - - - - - - 2 - 2 - - - 4 - - - (2) PinHLT109-6-6 2 - - - - - - - - 1 - 1 - - - 2 - - - (2) PinHLT109-6-11 - 2 - - - - - - - - - - - - - - - - - (2) PinHLT109-6-13 2 - 2 - - - - - - - - - - - - - - - - (2) PinHLT109-12-11 - 2 - - - - - - - - - - - - - 2 - - - (2) PinHLT109-12-13 - - 2 - - - - - - - - - - - - - - - - (2) PinHLT110-6-3 30 - - - - - - - - - - - - 30 30 30 - - - (2) PinHLT110-6-4 4 - - - - - - - - - - - - 4 4 4 - - - (2) PinHLT110-6-5 106 60 43 60 43 50 - 50 - 9 - 9 - 2 2 20 - - - (2) PinHLT110-6-6 194 46 42 46 42 34 37 34 37 18 - 18 - - - 36 - - - (2) PinHLT110-6-7 138 47 49 47 49 13 6 13 6 10 2 10 2 4 4 144 2 2 - (2) PinHLT110-6-8 14 2 7 2 7 - - - - - - - - - - - 3 3 6 (2) PinHLT110-6-9 8 - 4 - 4 - - - - - - - - - - - 7 7 14 (2) PinHLT110-6-10 8 2 4 2 4 2 - 2 - - - - - - - - - - - (2) PinHLT110-8-5 94 16 15 16 15 20 - 20 - 12 8 12 8 24 24 48 8 8 - (2) PinHLT110-8-6 378 91 132 91 132 70 39 70 39 17 1 17 1 - - 34 1 1 - (2) PinHLT110-8-7 158 45 25 45 25 22 6 22 6 41 43 41 43 - - 46 43 43 - (2) PinHLT110-8-8 188 24 47 24 47 18 15 18 15 9 5 9 5 - - 98 5 5 - (2) PinHLT110-8-9 92 19 15 19 15 9 6 9 6 1 24 1 24 - - 2 30 30 12 (2) PinHLT110-8-10 102 4 3 4 3 2 - 2 - 31 44 31 44 - - 8 44 44 - (2) PinHLT110-8-11 40 - - - - - - - - 4 18 4 18 - - 4 18 18 - (2) PinHLT110-8-12 4 - - - - - - _ - 1 2 1 2 - - - 7 7 10 (2) PinHLT110-8-13 10 - - - - - - - - 1 5 1 5 - - - 5 5 - (2) PinHLT110-8-14 12 - - - - - - - - 4 4 4 4 - - 4 4 4 - (2) Pin093-57-207August 24, 1989Page 23/24Revision 5, November 14, 2008USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENTQuantityPART NUMBER-101-103-105-107-109-111-113-115-117-119-121-123-125-127-133-141-143-145-155UnitListKeywordInstructionDispositionHLT110-10-5 - 3 - 3 - 3 - 3 - - - - - - - - - - - (2) PinHLT110-10-6 130 8 9 8 9 6 - 6 - 35 21 35 21 - - 70 21 21 - (2) PinHLT110-10-7 66 9 - 9 - 9 - 9 - 6 3 6 3 24 24 36 3 3 - (2) PinHLT110-10-8 18 1 1 1 1 1 - 1 - 6 2 6 2 - - 12 2 2 - (2) PinHLT110-10-9 26 6 1 6 1 7 - 7 - 10 8 4 2 - - 8 8 2 - (2) PinHLT110-10-10 8 4 - 4 - 4 - 4 - 2 2 2 2 - - 4 2 2 - (2) PinHLT110-10-11 2 - - - - - - - - - 1 - 7 - - - 1 7 - (2) PinHLT110-12-6 12 - - - - - - - - 2 4 2 4 - - 4 4 4 - (2) PinHLT210-10-10 2 - - - - - - - - - 1 - 1 - - - 1 1 - (2) PinHLT210-10-12 12 - - - - - - - - 6 6 6 6 - - - 6 6 - (2) PinHLT210-10-6 60 - - - - - - - - - 30 - 30 - - 30 30 - (2) PinHLT210-10-8 2 - - - - - - - - - 1 - 1 - - - 1 1 - (2) PinHLT210-6-5 8 - - - - - - - - - 4 - 4 - - - 4 4 - (2) PinHLT210-6-6 38 - - - - - - - - - 19 - 19 - - - 19 19 - (2) PinHLT210-6-7 4 - - - - - - - - - 2 - 2 - - - 2 2 - (2) PinHLT210-8-6 6 - - - - - - - - - 3 - 3 - - - 3 3 - (2) PinHLT210-8-7 6 - - - - - - - - - 3 - 3 - - - 3 3 - (2) PinHLT210-8-8 18 - - - - - - - - - 9 - 9 - - - 9 9 - (2) PinHLT210-8-10 8 - - - - - - - - - 4 - 4 - - - 4 4 - (2) PinHLT210-8-11 12 - - - - - - - - - 6 - 6 - - - 6 6 - (2) PinHLT210-8-12 16 - - - - - - - - 8 8 8 8 - - - 8 8 - (2) PinHLT210-8-15 4 - - - - - - - - 2 2 2 2 - - - 2 2 - (2) PinHLT210-12-12 4 - - - - - - - - 2 2 2 2 - - - 2 2 - (2) PinHLT210-12-6 8 - - - - - - - - - 4 - 4 - - - 4 4 - (2) PinHLT271-6A 4 - - - - - - - - - - - - 4 4 4 - - - (2) CollarHLT271-6W 4 - - - - - - - - - - - - 4 4 4 - - - (2) WasherHLT271-8A 4 - - - - - - - - - - - - 4 4 4 - - - (2) CollarHLT271-8W 4 - - - - - - - - - - - - 4 4 4 - - - (2) WasherHLT277-6 456 161 153 157 149 - - - - 52 27 52 27 40 40 144 37 37 20 (2) CollarHLT277-8 894 199 237 199 237 - - - - 70128 70 128 24 24 164139139 22 (2) CollarHLT277-10 316 31 11 31 11 - - - - 53 82 53 82 24 24130 82 82 - (2) CollarHLT277-12 32 4 - - - - - - - 2 14 2 14 - - 4 14 14 - (2) Collar093-57-207August 24, 1989Page 25/26Revision 5, November 14, 2008USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENTQuantityPART NUMBER-101-103-105-107-109-111-113-115-117-119-121-123-125-127-133-141-143-145-155UnitList KeywordInstructionDispositionHLT294LP6 6 3 - 3 - - - - - 3 - 3 - - - 3 - - - (2) Collar -HLT294LP8 - 1 - 1 - - - - - - - - - - - - - - - (2) Collar -HLT294LP20 6 - - - - - - - - 3 - 3 - - - 6 - - - (2) Collar -HLT410-6-5 - - - - - 3 - 3 - - - - - - - - - - - (2) Pin -HLT410-6-6 22 7 7 7 7 7 - - - 4 - 4 - - - 8 - - - (2) Pin -HLT410-6-7 44 17 16 17 16 8 - 8 - 6 - 6 - - - 12 - - - (2) Pin -HLT410-6-8 16 8 8 8 8 - - - - - - - - - - 16 - - - (2) Pin -HLT410-8-7 - 4 - 4 - - - - - - - - - - - - - - - (2) Pin -HLT410-8-9 - 1 - - - - - - - - - - - - - - - - - (2) Pin -HLT411-6-7 4 - - - - - - - - 2 - 2 - - - 4 - - - (2) Pin -HLT414-8-9 - 1 - 1 - 1 - 1 - - - - - - - - - - - (2) Pin -HLT414-10-11 16 - - - - - - - - - 8 - 8 - - - 8 8 - (2) Pin -HLT414-10-14 10 - - - - - - - - - 5 - 5 - - - 5 5 - (2) Pin -HLT414-12-11 12 - - - - - - - - - 6 - 6 - - - 6 6 - (2) Pin -HLT414-20-12 2 - - - - - - - - 1 - 1 - - - 2 - - - (2) Pin -HLT414-20-14 4 - - - - - - - - 2 - 2 - - - 4 - - - (2) Pin -HLT77-6 62 32 31 32 31 - - - - - - - - - - - - - - (2) Collar -HLT77-8 - 5 - 5 - - - - - - - - - - - - - - - (2) Collar -C-37-1348(U-1315)1 pt 1 pt 1 pt 1 pt 1pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1pt 1 pt 1 pt 1 pt 1 pt (1) Thinner (3)LCM37-1035(02-GN-28)1 pt 1 pt 1 pt 1 pt 1pt 1 pt 1 pt 1 pt 1 pt 1 pt - 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt (1) Primer (4)LCM40-2180(Type II)1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt - 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt (1) Sealant (5)LCM40-2180(Type I)1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt - 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt (1) Sealant (6)MS21042L4 8 - - - - - 4 - 4 - - - - - - - - - - (2) Nut -MS20470DD6-9 70 29 35 29 35 - - - - - - - - - - - - - - (2) Rivet -MS20470DD6-11 70 32 35 32 35 - - - - - - - - - - - - - - (2) Rivet -NAS6404U5 8 - - - - - 4 - 4 - - - - - - - - - - (2) Bolt -SR-40 or ES-125 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt 1 pt (1) Cleaner (7)093-57-207August 24, 1989Page 27/28Revision 5, November 14, 2008USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENTQuantityPART NUMBER-101-103-105-107-109-111-113-115-117-119-121-123-125-127-133-141-143-145-155UnitListKeywordInstructionDisposition1527031-501 - 1 - - - - - - - - - - - - - - - - - (2)Cap1527031-502 - - - 1 - - - - - - - - - - - - - - - (2)Cap1527031-503 1 - 1 - - - - - - - - - - - - - - - (2)Cap1527031-504 1 - - - 1 - - - - - - - - - - - - - - (2)Cap1527031-505 - 1 - - - - - - - - - - - - - - - - - (2)Splice1527031-506 - - - 1 - - - - - - - - - - - - - - - (2)Splice1527031-507 1 - 1 - - - - - - - - - - - - - - - - (2)Splice1527031-508 1 - - - 1 - - - - - - - - - - - - - - (2)Splice1527031-509 - 1 - 1 - - - - - - - - - - - - - - - (2)Strap1527031-511 2 - 1 - 1 - - - - - - - - - - - - - - (2)Strap1527031-513 2 - 1 - 1 - - - - - - - - - - - - - - (2)Doubler1527031-515 2 - 1 - 1 - - - - - - - - - - - - - - (2)Filler1527031-517 2 - 1 - 1 - - - - - - - - - 1 1 - - - (2)Angle1527031-519 1 - 1 - - - - - - - - - - - - - - - - (2)Angle1527031-520 1 - - - 1 - - - - - - - - - - 1 - - - (2)Angle1527031-521 2 - 1 - 1 - - - - - - - - - - 1 - - - (2)Angle1527031-523 - 1 - - - - - - - - - - - - - - - - - (2)Angle1527031-524 - - - 1 - - - - - - - - - - - - - - - (2)Angle1527031-525 - 1 - 1 - - - - - - - - - - - - - - - (2)Strap1527031-527 - 1 - - - - - - - - - - - - - - - - - (2)Angle1527031-528 - - - 1 - - - - - - - - - - - - - - - (2)Angle1527032-501 - - - - - 1 - - - - - - - - - - - - - (2)Cap1527032-502 - - - - - - - 1 - - - - - - - - - - - (2)Cap1527032-503 1 - - - - - 1 - - - - - - - - - - - - (2)Cap1527032-504 1 - - - - - - - 1 - - - - - - - - - - (2)Cap1527032-505 - - - - - 1 - - - - - - - - - - - - - (2)Splice1527032-506 - - - - - - - 1 - - - - - - - - - - - (2)Splice1527032-507 1 - - - - - 1 - - - - - - - - - - - - (2)Splice1527032-508 1 - - - - - - - 1 - - - - - - - - - - (2)Splice1527032-509 - - - - - 1 - 1 - - - - - - - - - - - (2)Strap1527032-511 2 - - - - - 1 - 1 - - - - - - - - - - (2)Strap1527033-513 2 - - - - - 1 - 1 - - - - - - - - - - (2)Spacer1527033-701 1 - - - - - - - - 1 - - - - - 1 - - - (2)Cap093-57-207August 24, 1989Page 29/30Revision 5, November 14, 2008USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENTQuantityPART NUMBER-101-103-105-107-109-111-113-115-117-119-121-123-125-127-133-141-143-145-155UnitListKeywordInstructionDisposition1527033-702 1 - - - - - - - - - - 1 - - - 1 - - - (2) Cap1527033-703 1 - - - - - - - - - 1 - - - - - 1 - - (2) Cap1527033-704 1 - - - - - - - - - - - 1 - - - - 1 - (2) Cap1527033-705 1 - - - - - - - - 1 - - - - - 1 - - - (2) Splice1527033-706 1 - - - - - - - - - - 1 - - - 1 - - - (2) Splice1527033-707 1 - - - - - - - - - 1 - - - - - - - - (2) Splice1527033-708 1 - - - - - - - - - - - 1 - - - - - - (2) Splice1527033-709 2 - - - - - - - - 1 - 1 - - - 2 - - - (2) Strap1527033-711 2 - - - - - - - - - 1 - 1 - - - - - - (2) Strap1527033-713 2 - - - - - - - - 1 - 1 - - - 2 - - - (2) Block1527479-141 2 - - - - - - - - - - - - 2 - - - - - (2) Filler1647070-129 1 - - - - - - - - - - - - 1 - - - - - (2) Angle1647070-130 1 - - - - - - - - - - - - 1 - - - - - (2) Angle1647070-131 1 - - - - - - - - - - - - 1 - - - - - (2) Angle1647070-132 1 - - - - - - - - - - - - 1 - - - - - (2) Angle1647070-135 - - - - - - - - - - - - - - 1 1 - - - (2) Angle1647070-136 - - - - - - - - - - - - - - 1 1 - - - (2) Angle1647070-137 - - - - - - - - - - - - - - 1 1 - - - (2) Angle1647070-138 - - - - - - - - - - - - - - 1 1 - - - (2) Angle1647070-139 - - - - - - - - - - - - - - 2 2 - - - (2) Filler1647070-147 - - - - - - - - - - - - - - - - 1 - 1 (2) Angle-Splice1647070-148 - - - - - - - - - - - - - - - - - 1 1 (2) Angle-Splice1647070-149 - - - - - - - - - - - - - - - - 1 1 2 (2) Plate-Splice1647070-151 - - - - - - - - - - - - - - - - 1 1 2 (2) Strap-Splice1647070-153 2 - 1 - 1 - - - - - - - - - - - - - - (2) Shim

# 093-57-207

August 24, 1989 Page 31 Revision 5, November 14, 2008

USE AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT 3. Material Information (Cont.)
(1) Not Supplied with Kit.
(2) See Section 1, Paragraph G for price information.
(3) White High Gloss Interior Polyurethane Coating (C-37-1348) may be procured from:
Sterling Lacquer Manufacturing Company (60003) 3150 Brannon Avenue St. Louis, Missouri 63139-1422
(4) Phosphate Ester Resistant Epoxy Primer (LCM37-1035) may be procured from:
Deft Incorporated (33461) Chemical Coating Division 17451 Von Karman Avenue Irvine, California 92714-6205
(5) Brush Consistency Integral Fuel Ta nk Sealing Compound (LCM40-2180 Type II) may be procured from:

Products Research and Chem ical Corporation (83574) Coating and Sealants Division 5430 San Fernando Road P.O. Box 1800 Glendale, California 91209 P/N PR1422A-2
(6) Fillet Consistency Integral Fuel Tank Sealing Compound (LCM40-2180, Type I) may be procured from:

Products Research and Chem ical Corporation (7D294) Coating and Sealants Division 5454 San Fernando Road P.O. Box 1800 Glendale, California 91203-1521 P/N PR14223
(7) Solvent Cleaner SR-40 AXON Products, Inc. 307 Echelon Rd Greenville, SC 29605

or

ES-125 Eldorado Chemical CO, Inc 14350 Lookout Road San Antonio, TX 78233