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Commercial Airplanes 737 Service Bulletin
SPECIAL ATTENTION Number: 737-53-1065 Original Issue: January 04, 1985 Revision 3: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Aft Skin - Inspection, Repair, and Skin Panel Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 1989 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 1 of 206
4.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 2 of 206 BOEING SERVICE BULLETIN 737-53-1065
BLANK PAGE
Table of Contents
Revision Transmittal Sheet7
S u m m a r y ..................................................... 1 1
1. PLANNING INFORMATION ........................................ 1 5 A . E f f e c t i v i t y ............................................... 1 5
1. Airplanes ............................................ 1 5 2 . S p a r e s A f f e c t e d ........................................ 2 7 B. Concurrent Requirements ...................................... 2 7 C. Reason ................................................ 2 8 D. Description .............................................. 2 9 E. Compliance .............................................. 3 0 F . A p p r o v a l ............................................... 4 0 G. Manpower .............................................. 4 1 H. Weight and Balance Changes .................................... 4 5 I. Electrical Load Data ......................................... 4 5 J . R e f e r e n c e s .............................................. 4 5
1. Existing Data: ......................................... 4 5
2. Data Supplied with this Service Bulletin: ........................... 4 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 7 K. Publications Affected ........................................ 4 8 L. Interchangeability and Intermixability of Parts ........................... 4 8 M. Software Accomplishment Summary ................................ 4 8
2. MATERIAL INFORMATION ........................................ 4 9 A. Material - Price and Availability ................................... 4 9 B. Industry Support Information .................................... 4 9 C. Parts Necessary for Each Airplane ................................. 5 0 1 . K i t s / P a r t s ............................................ 5 0
2. Parts and Materials Supplied by the Operator ........................ 6 8
3. Parts Modified and Reidentified ................................ 7 0
4. Parts Removed and Not Replaced .............................. 7 0 D. Parts Necessary to Change Spares ................................. 7 0 E. Special Tooling - Price and Availability ............................... 7 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 7 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 7 1 A. GENERAL INFORMATION ..................................... 7 1 B. WORK INSTRUCTIONS ....................................... 7 3 FIGURE 1: INSPECTION ZONES - LEFT SIDE BS 727 TO BS908, S-14L TO S-20L [Group 2-28] . . 86 FIGURE 2: INSPECTION ZONES - LEFT SIDE BS 727 TO BS908, S-20L TO S-25L [Group 2-28] . . 87 FIGURE 3: INSPECTION ZONES - LEFT SIDE BS 727 TO BS908, S-14L TO S-20L [Group 29-40] . 88 FIGURE 4: INSPECTION ZONES - LEFT SIDE BS 727 TO BS908, S-20L TO S-25L [Group 29-40] . 90 FIGURE 5: INSPECTION ZONES - LEFT SIDE BS 908 TO BS 1016, S-14L TO S-20L [Group 2-40] . 91 FIGURE 6: INSPECTION ZONES - LEFT SIDE BS 908 TO BS 1016, S-20L TO S-25L [Group 2-40] . 92 FIGURE 7: INSPECTION ZONES - RIGHT SIDE BS 727 TO BS 908, S-14R TO S-25R [Group 2-40] . 93 FIGURE 8: INSPECTION ZONES - RIGHT SIDE BS 908 TO BS 1016, S-14R TO S20R [Group 2-40] . 96 FIGURE 9: INSPECTION ZONES - RIGHT SIDE BS 908 TO BS 1016, S-20R TO S25R [Group 2-40] . 97 FIGURE 10: EXTERNAL OR INTERNAL INSPECTION [Group 2-40] ................... 9 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 3 of 206 BOEING SERVICE BULLETIN 737-53-1065
FIGURE 11: INTERNAL INSPECTION [Group 2-40] ........................... 1 0 3 F I G U R E 1 2 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 0 7 F I G U R E 1 3 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 0 8 F I G U R E 1 4 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 0 9 F I G U R E 1 5 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 0 F I G U R E 1 6 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 1 F I G U R E 1 7 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 2 F I G U R E 1 8 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 3 F I G U R E 1 9 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 4 F I G U R E 2 0 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 5 F I G U R E 2 1 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 6 F I G U R E 2 2 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 7 F I G U R E 2 3 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 8 F I G U R E 2 4 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 1 9 F I G U R E 2 5 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 0 F I G U R E 2 6 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 1 F I G U R E 2 7 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 2 F I G U R E 2 8 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 3 F I G U R E 2 9 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 4 F I G U R E 3 0 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 5 F I G U R E 3 1 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 6 F I G U R E 3 2 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 7 F I G U R E 3 3 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 8 F I G U R E 3 4 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 2 9 F I G U R E 3 5 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 0 F I G U R E 3 6 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 1 F I G U R E 3 7 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 2 F I G U R E 3 8 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 3 F I G U R E 3 9 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 4 F I G U R E 4 0 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 5 F I G U R E 4 1 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 6 F I G U R E 4 2 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 7 F I G U R E 4 3 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 8 F I G U R E 4 4 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 3 9 F I G U R E 4 5 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 0 F I G U R E 4 6 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 1 F I G U R E 4 7 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 2 F I G U R E 4 8 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 3 F I G U R E 4 9 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 4 F I G U R E 5 0 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 5 F I G U R E 5 1 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 6 F I G U R E 5 2 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 7 F I G U R E 5 3 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 8 F I G U R E 5 4 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 4 9 F I G U R E 5 5 : T H I S F I G U R E W A S D E L E T E D A T R E V I S I O N 3 ...................... 1 5 0 FIGURE 56: TIME LIMITED SKIN REPAIR [Group 2-40] ......................... 1 5 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 4 of 206 BOEING SERVICE BULLETIN 737-53-1065
FIGURE 57: OPTION 1 MODIFICATION OF PERMANENT REPAIR INSTALLED IN ACCORDANCE WITH REVISION 2 OF THIS SERVICE BULLETIN [Group 2-40] ................. 1 5 6 FIGURE 58: OPTION 2 MODIFICATION OF PERMANENT REPAIR INSTALLED IN ACCORDANCE WITH REVISION 2 OF THIS SERVICE BULLETIN [Group 2-40] ................. 1 6 1 FIGURE 59: OPTION 1 PERMANENT REPAIR INSTALLATION FOR TIME LIMITED REPAIRS INSTALLED IN ACCORDANCE WITH REVISION 2 OF THIS SERVICE BULLETIN [Group 2-40] . . . 167 FIGURE 60: OPTION 2 PERMANENT REPAIR INSTALLATION FOR TIME LIMITED REPAIRS INSTALLED IN ACCORDANCE WITH REVISION 2 OF THIS SERVICE BULLETIN [Group 2-40] . . . 172 FIGURE 61: OPTION 1 PERMANENT REPAIR INSTALLATION FOR AIRPLANES WITH A TIME LIMITED REPAIR INSTALLED WITH REVISION 3 OF THIS SERVICE BULLETIN [Group 2-40] . 178 FIGURE 62: OPTION 2 PERMANENT REPAIR INSTALLATION FOR AIRPLANES WITH A TIME LIMITED REPAIR INSTALLED IN ACCORDANCE WITH REVISION 3 OF THIS SERVICE BULLETIN [Group 2-40] .......................................... 1 8 3 FIGURE 63: POST REPAIR EXTERNAL LFEC INSPECTION OF OPTION 1 PERMANENT REPAIR [Group 2 - 4 0 ] .............................................. 1 8 9 FIGURE 64: POST REPAIR EXTERNAL LFEC INSPECTION OF OPTION 2 PERMANENT REPAIR [Group 2 - 4 0 ] .............................................. 1 9 1 APPENDIX A: SKIN PANEL INSTALLATION DRAWINGS ......................... 1 9 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 5 of 206 BOEING SERVICE BULLETIN 737-53-1065
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 6 of 206 BOEING SERVICE BULLETIN 737-53-1065
BLANK PAGE
Commercial Airplanes 737 Service Bulletin
SPECIAL ATTENTION Revision Transmittal SheetNumber: 737-53-1065Original Issue: January 04, 1985 Revision 3: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Aft Skin - Inspection, Repair, and Skin Panel Replacement This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-13-30, AD 89-09-03 and AD 90-06-02 are related to this service bulletin. The effective date of AD 2005-13-30 is August 1, 2005.
The Federal Aviation Administration (FAA) will possibly release an additional AD related to this service bulletin.
The AD will make the compliance tasks and times given in this service bulletin mandatory.
More work is necessary on airplanes changed in accordance with the Original Issue, Revision 1 or Revision 2 of this service bulletin. Operators must do new inspection requirements and skin panel replacement in accordance with Revision 3 of this service bulletin. Inspections are not required on skin panels that have been replaced using production skin panels after 59,000 total flight cycles. If the operator has record that a skin panel was replaced with a production skin panel prior to 59,000 total flight cycles, contact The Boeing Company for work instructions and do the work. If the operator does not have record that a skin panel was replaced with a production skin panel before 59,000 total flight cycles, inspections and skin panel replacement are required on that skin panel in accordance with this service bulletin. The time limited repair has additional inspection requirements and two options to make the repair permanent. If the time limited repair was done in accordance with Revision 2 of this service bulletin, it must be made permanent in accordance with Revision 3 of this service bulletin.
Additionally, if a permanent repair was done in accordance with Revision 2 of this service bulletin, it must be modified or replaced in accordance with Revision 3 of this service bulletin.
Installation of the stiffener modification and the subsequent one time subsurface eddy current inspection is no longer terminating action for the repeat inspections. Operators that have installed the stiffener modification must continue to do the repeat inspection in that area in accordance with Revision 3 of this service bulletin.
REASON FOR REVISION This revision is sent to provide new and additional inspection requirements, add requirement to replace skin panels, change compliance time requirements, change time limited repair and permanent repair requirements, remove the options to install stiffener modification, and change airplane grouping.
The inspection areas have changed from three zones to two zones. In Revision 2, Zones 1, 2, and 3 consisted of bonded doublers with pockets fully chem-milled to the bond line. The new zones include all previously inspected areas from the Original Issue, Revision 1 or Revision 2 of this service bulletin and additional areas where cracking could be found. Due to the change in zone definition, inspection criteria has been changed to allow for early detection of cracks.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 7 of 206
The Option of doing detailed inspections every 2,000 flight cycles from Revision 2 has been removed because of reliability issues at a reasonable inspection interval.
In order to mitigate Widespread Fatigue Damage (WFD) concerns, compliance and inspection requirements have changed as shown in the following two tables.
Revision 2 Compliance Summary Threshold/Repeat IntervalsInspection Zone 16,000/3,600 flight cycles (External Inspections) or 2,000 flight cycles (External Inspections) Zone 1 (a) 16,000/4,500 flight cycles (External Inspections)Zone 2 (b) 16,000/4,500 flight cycles (External Inspections)Zone 3 (c)
(a) Zone 1: Areas under the fairing which have a history of cracking.
(b) Zone 2: Areas that have similar loading and structural configuration as Zone 1 and Zone 3 but have no history of cracks.
(c) Zone 3: Areas outside of fairing with history of cracking.
Revision 3 Compliance Summary Threshold/Repeat IntervalsInspection Zone 16,000/3,700 flight cycles (Internal or External Inspections)Zone 1 (a) 34,000/7,500 flight cycles (External Inspections)Zone 2 (b)
(a) Zone 1: Skin/bonded doubler with the bonded doubler chem-milled to the bond line in the pocket.
(b) Zone 2: Skin/bonded doubler with a chem-milled pocket thickness of 0.050 inches (bonded doubler partially chem-milled).
Airplane grouping has been changed as follows:
Airplane ModelRevision 3 GroupRevision 2 Group 737-10011 thru 7 737-200 Passenger18 thru 21 737-200 Passenger2 and 422 737-200 Passenger10 thru 1323 737-200 Passenger3, 5 thru 8, 14, 1524 737-200 Passenger925 737-200 Passenger16 thru 24, 26 thru 2826 737-200 Passenger2527 737-200 Cargo128 thru 34 737-200 Cargo2935 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 8 of 206 BOEING SERVICE BULLETIN 737-53-1065
Airplane ModelRevision 3 GroupRevision 2 Group 737-200 Cargo3036 737-200 Cargo3137 737-200 Cargo3338 737-200 Cargo32 and 3539 737-200 Cargo34, 36 and 3740 737-200 Cargo3841 737-200 Cargo39 and 4042 These sections were changed:
1. Summary - BACKGROUND: Information updated, body panel table added and planning table added.
2. Summary - ACTION: Information updated.
3. Summary - COMPLIANCE: Federal Aviation Administration (FAA) Airworthiness Directive (AD) statement added.
4. Paragraph 1.A. Effectivity: Groups changed for new skin panel numbers.
5. Paragraph 1.C. Reason: Revision information added.
6. Paragraph 1.D. Description: Information and table updated.
7. Paragraph 1.E. Compliance: Compliance tables changed to incorporate Non-Destructive Inspections (NDI), revised threshold and grace times and new tables added for time limited repairs and skin panel replacement.
8. Paragraph 1.F. Approval: Information updated to show new AD's, new AD paragraph references and updated text.
9. Paragraph 1.G. Manpower: New tables added for new inspections.
10. Paragraph 1.H. Weight and Balance: Two tables added.
11. Paragraph 2.A. Material and Price Availability: Existing kits removed and new skin panel part locations added.
12. Paragraph 2.C. Parts Necessary for Each Airplane: Kits removed and new skin panel part number/groups added.
13. Paragraph 3.A. General Information: New notes added.
14. Paragraph 3.B. Work Instructions: Parts changed from Roman Numerals to Numeric. Part 1 Inspection updated for new inspection process, Part 5 Skin Panel Replacement added.
15. Figure 1 thru Figure 9 revised for new inspection areas/zones.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 9 of 206 BOEING SERVICE BULLETIN 737-53-1065
16. Figure 10 and Figure 11 new graphic added to illustration and new information added to step tables.
17. Figure 12 thru Figure 54 deleted.
18. Figure 57 thru Figure 64 added.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY January 04, 1985Original Issue:
October 12, 1989Revision 1:
April 19, 2001Revision 2:
June 30, 2015Revision 3:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 10 of 206 BOEING SERVICE BULLETIN 737-53-1065
Commercial Airplanes 737 Service Bulletin
SPECIAL ATTENTION SummaryNumber: 737-53-1065Original Issue: January 04, 1985 Revision 3: June 30, 2015 ATA System: 5360 SUBJECT: FUSELAGE - Aft Skin - Inspection, Repair, and Skin Panel Replacement BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
CONCURRENT REQUIREMENTS None.
BACKGROUND Operators have reported wrinkling and cracks in the fuselage side skins in the area just aft of the main wheelwell.
Typically the cracks are in the skin only and are adjacent to the longitudinal edges of the bonded waffle doubler.
Some cracks have been found in the tearstraps and visible only from the interior. The skin cracks are caused by fatigue from cyclic shear stresses due to cyclic wrinkling of the skin. At skin panel locations from Station (STA) 727 to STA 1016 (S-14 L/R to S-25 L/R), the cyclic wrinkling of the skin could cause a condition where skin cracks could form along the longitudinal edges of the bonded doubler. If not corrected, such skin cracking could adversely affect the structural integrity of the airplane.
Before 1990, the only reported cracking was in zone1 of group 2 airplanes in revision 1 of this bulletin. However, since 1990, there have been cracks reported in zone 2 of group 2 airplanes and cracks reported on group 1 airplanes both of revision 1 of this bulletin. Because of this, the inspection area for all groups has been increased.
One operator reported a 737-200 airplane beyond line number 920 that had a crack in the new inspection area.
As a result, 737-200 and 737-200C airplanes after line number 920 were added to the bulletin effectivity as group 26,27, 41 and 42 airplanes in revision 2.
One operator reported cracks in the skin where reinforcing angles had been installed. These cracks likely existed, but were undetectable when the stiffeners were installed. As a result, additional inspections are required in areas that have been previously modified with stiffeners.
Since the release of Revision 2 of this bulletin, Boeing have completed a Widespread Fatigue Damage (WFD) assessment. Also, chem mill step cracks have been discovered while completing inspections in accordance with Revision 2 of this bulletin.
This service bulletin gives instructions for inspections, repair, and replacement of skin panels where cracking can occur between Stringer S-14 and Stringer S-25 and from STA 727 to STA 1016 on the left and right side of the airplane. The inspection in accordance with this service bulletin will allow early detection of cracks in the skin panels. The repair of cracks in accordance with this service bulletin will restore structural integrity of the skin panel. Replacement of the skin panels is terminating action for repetitive inspection at the locations where the skin panels were replaced using production skin panels on airplanes with more than 59,000 total flight cycles.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 11 of 206
Section 46 lower lobe skin panels addressed in this service bulletin have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD).
NOTE: Skin Panel at BS 908 - BS 1016 (S-14R to S-20R) does not have to be replaced.
Boeing Service Related Problem (SRP) 737-SRP-53-0413 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph
1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Group 1:
Boeing endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated under FAA jurisdiction.
As such, Boeing no longer provides maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line numbers 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Group 2-40:
This service bulletin provides instructions for the inspection and repair of the skin panels between STA 727 and STA 1016 and between Stringers S-14 and S-25. This service bulletin also provides instructions for skin panel replacement. Skin panel replacement is required at the following locations:
– STA 727 to STA 908, S-14L to S-20L – STA 727 to STA 908, S-20L to S-25L – STA 727 to STA 908, S-14R to S-20R – STA 727 to STA 908, S-20R to S-25R – STA 908 to STA 1016, S-14L to S-20L – STA 908 to STA 1016, S-20L to S-25L – STA 908 to STA 1016, S-20R to S-25R Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 04, 1985 737-53-1065Revision 3: June 30, 2015 12 of 206 BOEING SERVICE BULLETIN 737-53-1065