# Boeing Alert Service Bulletin 737-53A1355: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0766; AD 2018-04-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-53A1355](https://openairdocs.org/service-documents/boeing/737-53a1355.md) - Title as filed: SB-737-53A1355 R00 - BOEING - Pages: 100 - PDF: https://openairdocs.org/files/sha256/85/c0/85c0cd9d16b6d80a4c95c614f1a3cc2afb228e3630d0a56450e992a7013e0c3d - Page: https://openairdocs.org/service-documents/boeing/737-53a1355/file/85c0cd9d16b6 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1355 Original Issue: March 10, 2017 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Station 1016 Aft Pressure Bulkhead - Gore Webs Inspection and Repair 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 © 2017 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 Unpublished Work.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: March 10, 2017 737-53A1355 1 of 100 2.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 2 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT BLANK PAGE ### Page 3 Table of Contents S u m m a r y ...................................................... 5 1. PLANNING INFORMATION ........................................ 1 1 A . E f f e c t i v i t y ............................................... 1 1 1. Airplanes ............................................ 1 1 2 . S p a r e s A f f e c t e d ........................................ 2 3 B. Concurrent Requirements ...................................... 2 3 C. Reason ................................................ 2 3 D. Description .............................................. 2 4 E. Compliance .............................................. 2 6 F . A p p r o v a l ............................................... 4 1 G. Manpower .............................................. 4 2 H. Weight and Balance Changes .................................... 4 4 I. Electrical Load Data ......................................... 4 4 J . R e f e r e n c e s .............................................. 4 4 1. Existing Data: ......................................... 4 4 2. Data Supplied with this Service Bulletin: ........................... 4 4 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 5 K. Publications Affected ........................................ 4 5 L. Interchangeability and Intermixability of Parts ........................... 4 5 M. Software Accomplishment Summary ................................ 4 5 2. MATERIAL INFORMATION ........................................ 4 7 A. Material - Price and Availability ................................... 4 7 B. Industry Support Information .................................... 4 7 C. Parts Necessary for Each Airplane ................................. 4 7 1 . K i t s / P a r t s ............................................ 4 7 2. Parts and Materials Supplied by the Operator ........................ 4 7 3. Parts Modified and Reidentified ................................ 4 7 4. Parts Removed and Not Replaced .............................. 4 7 D. Parts Necessary to Change Spares ................................. 4 7 E. Special Tooling - Price and Availability ............................... 4 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 7 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 9 A. GENERAL INFORMATION ..................................... 4 9 B. WORK INSTRUCTIONS ....................................... 5 1 FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 [Group 2] ................. 5 6 FIGURE 2: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES - ZONE 2 [Group 2] ......... 6 1 FIGURE 3: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SRM SINGLE GORE WEB REPAIR [Group 2] .................................... 6 8 FIGURE 4: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE SRM ALL GORE WEB REPAIR [Group 2] .................................................. 7 3 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1 [Group 2, Configuration 1 ] ................................................ 7 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 3 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 4 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2 [Group 2, Configuration 2 ] ................................................ 8 2 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3 [Group 2] ...... 8 7 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4 [Group 2] ...... 9 4 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 5 [Group 2] ...... 9 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 4 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 5 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1355Original Issue: March 10, 2017 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Station 1016 Aft Pressure Bulkhead - Gore Webs Inspection and Repair THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin gives instructions to do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, of the aft pressure bulkhead at Station (STA) 1016 from the center of the aft pressure bulkhead to the second tear strap, not including the fastener locations under the second tear strap. This service bulletin also gives instructions to do detailed, HFEC, and LFEC inspections for any crack in the gore webs and repair webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, common to existing Structural Repair Manual (SRM) single gore web repair or SRM all gore web repair. Accomplishment of this service bulletin will mitigate the safety issue associated with the cracking in the gore webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, of the aft pressure bulkhead and make sure that any crack is found and repaired before the crack grows to a critical length. If not corrected, cracking in the gore web lap splices of the aft pressure bulkhead can result in possible rapid decompression and loss of structural integrity. The inspection of the gore webs in the apex area of the aft pressure bulkhead was added to Revision 3 of Boeing Service Bulletin (SB) 737-53A1214. Since the release of Revision 3 of SB 737-53A1214, operators have reported cracks in the aft pressure bulkhead at STA 1016, in the critical fastener rows of the gore web lap splices, outside the apex area. These cracks were found during Supplemental Structural Inspection Document (SSID) inspections of Structural Significant Item (SSI) F-30C (LFEC inspection of the hidden gore web critical fastener rows) and SSI F-30D (HFEC inspection of the visible gore web critical fastener rows). Cracks were also found during accomplishment of repair in accordance with SB 737-53A1214. The cracks found in the gore web lap splices of the aft pressure bulkhead are due to fatigue caused by cyclic pressure loading of the fuselage. Boeing determined that the existing inspection programs are not sufficient to find such cracks before they could lead to a decompression event. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 5 of 100 ### Page 6 Boeing received reports of a total of ten airplanes on which cracks were found in critical fastener rows of the gore web lap splices that are not included in the inspection area of SB 737-53A1214, which extends approximately seven inches radially outboard from the center of the aft pressure bulkhead. Cracks in the critical lap splice fastener rows of the hidden forward gore web were found on eight airplanes between approximately 37,000 and 66,000 total flight cycles, and the maximum reported tip-to-tip crack length was 0.766 inch, growing from opposite sides of a fastener hole. Cracks in the critical lap splice fastener rows of the visible aft gore web were found on four airplanes between approximately 42,000 and 62,000 total flight cycles, but crack lengths were not reported. This service bulletin supersedes the inspection of the aft pressure bulkhead gore webs in the apex area addressed by PART IV - NDT INSPECTION OF THE DOME CAP AT THE CENTER OF THE BULKHEAD of SB 737-53A1214, Revision 5. The gore web lap splices of the aft pressure bulkhead have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). This service bulletin provides alternative inspections for SSIs F-30C and F-30D for some areas that are affected by the SRM repairs. For the remaining areas affected by the SRM repairs, the alternative inspections for SSIs F-30C and F-30D are contained in the SRM repairs. SRM single gore web repairs: – 737-100/200 SRM 53-10-11, Figure 13, for 737-200 and 737-200C airplanes – 737-300/400/500 SRM 53-80-08, Repair 9, for 737-300/400/500 airplanes SRM all gore web repairs: – 737-100/200 SRM 53-10-11, Figure 14, for 737-200 and 737-200C airplanes – 737-300/400/500 SRM 53-80-08, Repair 10, for 737-300/400/500 airplanes Boeing Service Related Problem (SRP) 737-SRP-53-0500 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 53-15002 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 Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 6 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 7 ReferenceAffectedPlanning Data Paragraph 2.C.2., Parts and Materials Supplied by the Operator NoOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Group 1: Boeing endorses the 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: 1. Get access to the aft side of the aft pressure bulkhead at Station (STA) 1016 and do the actions that follow: 2. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices and outside the lap splices) of the aft pressure bulkhead in Zone 1. If any crack is found in Zone 1, do the repair in accordance with this service bulletin. If no crack is found, repeat the inspections. NOTE: Zone 1 includes all fastener locations within 7 inches from the center of the aft pressure bulkhead, measured radially outboard. This includes the first six fastener rows of the gore web lap splices and the fastener locations on the gore web within the first 7 inches that are outside the gore web lap splices. Zone 1 of this service bulletin is the same as the inspection area of PART IV of SB 737-53A1214 at the center of the aft pressure bulkhead. 3. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices only) of the aft pressure bulkhead in Zone 2. If any crack is found in Zone 2, contact The Boeing Company for repair instructions and do the repair. If no crack is found, repeat the inspections. NOTE: Zone 2 includes all fastener locations of the gore web radial lap splices from the seventh fastener row to the second tear strap (thirty-ninth fastener row), counted radially outboard from the center of the aft pressure bulkhead. Some airplane configurations have two fastener rows common to the first (inner) tear strap and some airplane configurations have three fastener rows common to the first tear strap. It is required to inspect the gore web lap splices common to all fastener rows under the first tear strap. 4. For airplanes with any SRM single gore web repair or a SRM all gore web repair, do detailed inspections, HFEC inspections, and LFEC inspections for any crack in the gore webs (lap splices only) and in the repair webs (lap splices and outside the lap splices), of each SRM single gore web repair or a SRM all gore web repair. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If no crack is found, repeat the inspections. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 7 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 8 EFFECTIVITY All 737-100/200/200C/300/400/500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directives AD 98-11-04 R1, AD 2008-08-23, AD 2008-09-13 and AD 2012-18-13 R1 are related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 8 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 9 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT STA 1016 DO DETAILED, HFEC AND LFEC INSPECTIONS FOR ANY CRACK IN THE GORE WEBS (LAP SPLICES AND OUTSIDE THE LAP SPLICES) IN ZONE 1 AND LAP SPLICES IN ZONE 2. IF ANY CRACK IS FOUND, DO THE REPAIR IN ACCORDANCE WITH THIS SERVICE BULLETIN, IF NO CRACK IS FOUND, REPEAT THE INSPECTIONS. BL 0 GORE WEB LAP SPLICE (7 LOCATIONS) DO DETAILED, HFEC AND S-7L S-7R LFEC INSPECTIONS FOR ANY CRACK IN THE GORE WEBS (LAP SPLICES ONLY) AND REPAIR WEBS (LAP SPLICES AND OUTSIDE THE ZONE 2 LAP SPLICES) OF EACH SRM SINGLE GORE WEB REPAIR OR A SRM ALL GORE WEB REPAIR. IF ANY CRACK IS FOUND, DO THE REPAIR IN ACCORDANCE WITH THIS SERVICE BULLETIN. IF NO CRACK IS FOUND, REPEAT THE INSPECTIONS. S-15L - • S-15R ZONE 1 S-23L S-23R AFT PRESSURE BULKHEAD (AFT SIDE) 2481363 A-A Original Issue: March 10, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1355 Work - See page 1 for details. 9 of 100 ### Page 10 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT - ZONE 1 TYPICAL CRACK IN VISIBLE AFT GORE WEB (LAP SPLICE AND OUTSIDE LAP SPLICE) - TYPICAL CRACK IN HIDDEN FWD GORE WEB (LAP SPLICE ONLY) TYPICAL CRACKS IN GORE WEBS (AFT SIDE) 2534523 Original Issue: March 10, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1355 Work - See page 1 for details. 10 of 100 ### Page 11 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1355 Original Issue: March 10, 2017 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Station 1016 Aft Pressure Bulkhead - Gore Webs Inspection and Repair THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is applicable to all 737-100/200/200C/300/400/500 Airplanes, in 2 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 737-100/200/200C Airplanes, line numbers 1 thru 291.-1 737-200/200C/300/400/500 Airplanes, line numbers 292 thru 3132.-2 Airplanes on which an inspection of the gore webs in the apex area at the center of the bulkhead was done in accordance with PART IV of Boeing Service Bulletin (SB) 737-53A1214. 1 Airplanes on which an inspection of the gore webs in the apex area at the center of the bulkhead was not done in accordance with PART IV of Boeing Service Bulletin (SB) 737-53A1214. 2 Airplane Models: 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 11 of 100 ### Page 12 GroupVariable Number 1PA001 - PA022 1PA099 1PA231 - PA232 1PC001 - PC005 1PG001 - PG075 1PG199 1PG201 - PG230 1PG251 - PG255 1PG271 - PG279 1PG301 - PG314 1PG331 - PG332 1PG351 - PG356 1PG375 1PG401 - PG403 1PG431 - PG442 1PG471 - PG475 1PG501 - PG505 1PG571 - PG583 2PG584 - PG586 1PG621 - PG630 1PG651 - PG652 1PG701 - PG705 2PH001 2PH011 - PH013 2PH021 - PH024 1PH701 - PH715 1PH731 - PH732 1PH741 - PH742 2PH743 1PJ001 - PJ002 2PJ003 - PJ009 1PJ031 - PJ032 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 12 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 13 GroupVariable Number 1PJ071 - PJ072 1PJ101 - PJ104 2PJ105 - PJ119 2PJ201 - PJ219 2PJ301 - PJ302 2PJ551 - PJ561 2PJ601 - PJ615 2PJ811 2PJ816 - PJ817 2PK026 - PK029 2PK041 - PK053 2PK061 - PK070 2PK081 - PK082 2PK091 - PK099 2PK101 - PK103 2PK111 - PK120 2PK141 - PK146 2PK201 - PK204 2PK211 - PK223 2PK231 - PK241 2PK251 - PK258 2PK271 - PK274 2PK281 - PK289 2PK291 2PK301 - PK318 2PK341 2PK351 - PK361 2PK391 2PK431 - PK433 2PK451 - PK452 2PK461 - PK469 2PK495 2PK501 - PK504 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 13 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 14 GroupVariable Number 2PK511 - PK515 2PK519 2PK521 - PK528 2PK541 - PK565 2PK581 2PK591 - PK599 2PK601 - PK617 2PK621 - PK637 2PK641 - PK642 2PK661 - PK666 2PK671 - PK681 2PK691 - PK697 2PK711 - PK716 2PK731 - PK765 2PK771 - PK779 2PK801 - PK804 2PK819 - PK827 2PK830 2PK861 - PK863 2PK871 - PK874 2PK881 - PK884 2PK901 - PK938 2PK971 - PK974 2PL001 - PL028 2PL061 2PL081 2PL101 - PL113 2PL151 2PL171 - PL172 2PL201 - PL203 2PL221 2PL401 - PL417 2PL421 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 14 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 15 GroupVariable Number 2PL441 2PL451 - PL456 2PL471 2PL491 2PL501 - PL506 2PL551 - PL562 2PL581 2PL601 - PL603 2PL611 2PL621 - PL626 2PL631 - PL632 1PL711 - PL712 1PL716 2PL717 - PL747 2PL756 2PL758 2PL761 - PL770 2PL781 - PL788 2PL793 1PL801 - PL803 2PM001 - PM006 2PM016 - PM017 2PM021 - PM023 2PM051 - PM066 2PM101 - PM119 2PM141 - PM142 2PM171 2PM181 2PM251 - PM255 2PM281 - PM283 2PM381 - PM399 2PM401 - PM417 2PM541 - PM564 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 15 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 16 GroupVariable Number 2PN001 - PN002 2PN021 - PN043 2PN081 - PN086 2PN101 - PN117 2PN131 - PN163 2PN401 - PN420 2PN431 - PN433 2PN451 - PN456 2PN471 - PN474 2PN481 2PN491 - PN493 2PN501 - PN502 2PN511 - PN512 2PN521 2PP001 - PP054 2PP101 - PP169 2PP181 - PP199 2PP201 - PP205 2PP221 2PP231 - PP243 2PP281 - PP286 2PP301 - PP305 2PP351 - PP353 2PP376 - PP384 2PP391 - PP393 2PP401 - PP440 2PP471 - PP475 2PP501 - PP522 2PP631 - PP634 2PP651 - PP652 2PP671 - PP699 2PP701 - PP733 2PP771 - PP779 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 16 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 17 GroupVariable Number 2PP801 - PP808 2PP821 - PP827 2PP831 - PP848 2PP851 - PP852 2PP861 - PP877 2PP891 - PP899 2PP901 - PP936 2PP946 - PP948 2PP951 - PP952 2PP961 - PP967 2PP981 - PP991 2PP993 2PQ001 - PQ016 2PQ026 - PQ041 2PQ051 - PQ092 2PQ101 - PQ199 2PQ201 - PQ202 2PQ221 - PQ237 2PQ241 - PQ243 2PQ251 - PQ267 2PQ281 - PQ299 2PQ301 - PQ307 2PQ331 - PQ332 2PQ341 - PQ348 2PQ361 - PQ373 2PQ391 - PQ395 2PQ401 - PQ418 2PQ421 2PQ431 - PQ438 2PQ447 - PQ448 2PQ451 2PQ454 2PQ471 - PQ475 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 17 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 18 GroupVariable Number 2PQ479 - PQ481 2PQ486 - PQ487 2PQ491 - PQ493 2PQ771 - PQ772 2PQ791 - PQ793 2PQ801 - PQ805 2PQ931 - PQ935 2PQ951 2PQ971 - PQ997 2PR001 - PR017 2PR021 - PR034 2PR041 - PR045 2PR061 - PR072 2PR077 - PR082 2PR091 - PR092 2PR096 2PR101 2PR121 - PR122 2PR131 - PR132 2PR141 - PR143 2PR161 - PR172 2PR181 2PS601 - PS631 2PS636 - PS638 2PS641 - PS644 2PS651 - PS657 2PS666 - PS669 2PS691 - PS692 2PS701 - PS706 2PS751 - PS799 2PS811 2PS836 - PS837 2PS841 - PS846 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 18 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 19 GroupVariable Number 2PS851 - PS852 2PS856 2PS861 - PS863 2PS866 - PS868 2PS871 - PS874 2PS896 - PS897 2PS901 - PS941 2PS956 - PS957 2PS961 - PS963 2PS971 - PS978 2PT001 - PT015 2PT021 - PT031 2PT041 - PT064 2PT101 - PT105 2PT121 - PT138 2PT146 - PT148 2PT161 - PT170 2PT181 - PT188 2PT211 - PT220 2PT295 2PT301 - PT309 2PT331 - PT360 2PT381 - PT399 2PT401 - PT438 2PT501 - PT517 2PT561 - PT565 2PT581 - PT586 2PT611 - PT621 2PT641 - PT644 2PT651 - PT656 2PT671 - PT672 2PT681 - PT685 2PT701 - PT703 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 19 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 20 GroupVariable Number 2PT716 - PT717 2PT721 - PT725 2PT801 - PT834 2PT851 - PT854 2PT871 - PT886 2PT901 - PT930 2PT971 - PT973 2PT981 - PT985 2PT996 2PU001 - PU025 2PU301 2PU311 - PU313 2PV001 - PV055 2PV201 - PV209 2PV226 - PV229 2PV231 - PV237 2PV271 - PV272 2PV281 - PV287 2PV296 2PV301 - PV302 2PV351 2PV356 - PV357 2PW001 - PW054 2PW061 - PW068 2PW072 2PW086 - PW088 2PW091 - PW094 2PW101 - PW102 2PW106 2PW111 - PW120 2PW156 - PW157 2PW161 - PW171 2PW201 - PW252 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 20 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 21 GroupVariable Number 2PW261 - PW268 2PW271 - PW276 2PW278 2PW281 - PW293 2PW296 2PW301 - PW327 2PW401 - PW408 2PW411 - PW418 2PW421 - PW424 2PW431 - PW435 2PW441 - PW450 2PW461 - PW467 2PW501 - PW504 2PW511 - PW522 2PW524 - PW550 2PW556 - PW557 2PW561 - PW564 2PW571 - PW576 2PW591 - PW596 2PW611 - PW622 2PW631 - PW637 2PW661 - PW662 2PW681 - PW683 2PW701 - PW702 2PW711 - PW717 2PW741 - PW742 2PW761 2PW771 2PW831 2PW851 - PW856 1PX071 1PX701 1PY001 - PY008 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 21 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 22 GroupVariable Number 1PY021 2PY022 1PY031 2PY036 - PY037 2PY046 - PY048 2PY051 - PY053 2PY056 - PY057 2PY101 - PY103 2PY111 - PY113 2PY131 - PY135 2PY141 - PY143 2PY151 - PY154 2PY156 - PY157 2PY161 - PY162 2PY166 2PY191 2PY201 2PY221 - PY222 2PY231 2PY241 - PY244 2PY270 - PY275 2PY281 2PY286 1PY301 - PY304 1PY321 - PY323 1PY341 - PY346 1PY361 - PY362 1PY381 2PY401 2PY409 - PY411 2PY421 - PY422 2PY441 2PY451 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 22 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 23 GroupVariable Number 2PY461 - PY463 2PY591 - PY595 2PY611 - PY612 2PY621 2PY631 2PY651 2PY671 - PY672 2PY721 2PY741 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, of the aft pressure bulkhead at Station (STA) 1016 from the center of the aft pressure bulkhead to the second tear strap, not including the fastener locations under the second tear strap. This service bulletin also gives instructions to do detailed, HFEC, and LFEC inspections for any crack in the gore webs and repair webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, common to existing Structural Repair Manual (SRM) single gore web repair or SRM all gore web repair. Accomplishment of this service bulletin will mitigate the safety issue associated with the cracking in the gore webs, in the lap splices and in some fastener locations in the apex area outside the lap splices, of the aft pressure bulkhead and make sure that any crack is found and repaired before the crack grows to a critical length. If not corrected, cracking in the gore web lap splices of the aft pressure bulkhead can result in possible rapid decompression and loss of structural integrity. The inspection of the gore webs in the apex area of the aft pressure bulkhead was added to Revision 3 of Boeing Service Bulletin (SB) 737-53A1214. Since the release of Revision 3 of SB 737-53A1214, operators have reported cracks in the aft pressure bulkhead at STA 1016, in the critical fastener rows of the gore web lap splices, outside the apex area. These cracks were found during Supplemental Structural Inspection Document (SSID) inspections of Structural Significant Item (SSI) F-30C (LFEC inspection of the hidden gore web critical fastener rows) and SSI F-30D (HFEC inspection of the visible gore web critical fastener rows). Cracks were also found during accomplishment of repair in accordance with SB 737-53A1214. The cracks found in the gore web lap splices of the aft pressure bulkhead are due to fatigue caused by cyclic pressure loading of the fuselage. Boeing determined that the existing inspection programs are not sufficient to find such cracks before they could lead to a decompression event. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 23 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 24 Boeing received reports of a total of ten airplanes on which cracks were found in critical fastener rows of the gore web lap splices that are not included in the inspection area of SB 737-53A1214, which extends approximately seven inches radially outboard from the center of the aft pressure bulkhead. Cracks in the critical lap splice fastener rows of the hidden forward gore web were found on eight airplanes between approximately 37,000 and 66,000 total flight cycles, and the maximum reported tip-to-tip crack length was 0.766 inch, growing from opposite sides of a fastener hole. Cracks in the critical lap splice fastener rows of the visible aft gore web were found on four airplanes between approximately 42,000 and 62,000 total flight cycles, but crack lengths were not reported. This service bulletin supersedes the inspection of the aft pressure bulkhead gore webs in the apex area addressed by PART IV - NDT INSPECTION OF THE DOME CAP AT THE CENTER OF THE BULKHEAD of SB 737-53A1214, Revision 5. The gore web lap splices of the aft pressure bulkhead have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). This service bulletin provides alternative inspections for SSIs F-30C and F-30D for some areas that are affected by the SRM repairs. For the remaining areas affected by the SRM repairs, the alternative inspections for SSIs F-30C and F-30D are contained in the SRM repairs. SRM single gore web repairs: – 737-100/200 SRM 53-10-11, Figure 13, for 737-200 and 737-200C airplanes – 737-300/400/500 SRM 53-80-08, Repair 9, for 737-300/400/500 airplanes SRM all gore web repairs: – 737-100/200 SRM 53-10-11, Figure 14, for 737-200 and 737-200C airplanes – 737-300/400/500 SRM 53-80-08, Repair 10, for 737-300/400/500 airplanes Boeing Service Related Problem (SRP) 737-SRP-53-0500 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 53-15002 is related to this service bulletin. D. Description Group 1: Boeing endorses the 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: 1. Get access to the aft side of the aft pressure bulkhead at Station (STA) 1016 and do the actions that follow: 2. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices and outside the lap splices) of the aft pressure bulkhead in Zone 1. If any crack is found in Zone 1, do the repair in accordance with this service bulletin. If no crack is found, repeat the inspections. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 24 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 25 NOTE: Zone 1 includes all fastener locations within 7 inches from the center of the aft pressure bulkhead, measured radially outboard. This includes the first six fastener rows of the gore web lap splices and the fastener locations on the gore web within the first 7 inches that are outside the gore web lap splices. Zone 1 of this service bulletin is the same as the inspection area of PART IV of SB 737-53A1214 at the center of the aft pressure bulkhead. 3. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices only) of the aft pressure bulkhead in Zone 2. If any crack is found in Zone 2, contact The Boeing Company for repair instructions and do the repair. If no crack is found, repeat the inspections. NOTE: Zone 2 includes all fastener locations of the gore web radial lap splices from the seventh fastener row to the second tear strap (thirty-ninth fastener row), counted radially outboard from the center of the aft pressure bulkhead. Some airplane configurations have two fastener rows common to the first (inner) tear strap and some airplane configurations have three fastener rows common to the first tear strap. It is required to inspect the gore web lap splices common to all fastener rows under the first tear strap. 4. For airplanes with any SRM single gore web repair or a SRM all gore web repair, do detailed inspections, HFEC inspections, and LFEC inspections for any crack in the gore webs (lap splices only) and in the repair webs (lap splices and outside the lap splices), of each SRM single gore web repair or a SRM all gore web repair. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If no crack is found, repeat the inspections. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 7-1, 2-20737-100, 737-200, 737-200C Group 2: Affected Maintenance Zones ZoneModel 7-1, 2-20737-200, 737-200C Group 2: Affected Maintenance Zones ZoneModel 220, 701737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 25 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 26 E. Compliance Federal Aviation Administration (FAA) Airworthiness Directives AD 98-11-04 R1, AD 2008-08-23, AD 2008-09-13 and AD 2012-18-13 R1 are related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. This service bulletin supersedes the inspection of the aft pressure bulkhead gore webs in the apex area addressed by PART IV - NDT INSPECTION OF THE DOME CAP AT THE CENTER OF THE BULKHEAD of SB 737-53A1214, Revision 5. The inspections in this service bulletin are terminating action to the SB 737-53A1214, PART IV inspections. Accomplish the required actions, based on the applicable conditions in Tables 1 through 5, in accordance with Paragraph 3. Accomplishment Instructions. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D and APPENDIX E. Group 1: Boeing endorses the 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 26 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 27 Group 2, Configuration 1: Table 1: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 6,000 flight cycles after the most recent inspection of the gore webs in the apex area at the cen- ter of the bulkhead was done in accordance with PART IV of SB 737-53A1214, or within 4,500 flight cycles after the original issue date of this service bulletin, whichever occurs first. Do PART 1: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. (a) All Airplanes (c) -Before 54,000 total flight cycles, or within 4,500 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do PART 2: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. (c) (b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 27 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 28 Group 2, Configuration 1: Table 1: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.OPTION 1 (ACTION 1): Do PART 5: SINGLE GORE WEB REPAIR. CONDITION 1: ANY CRACK FOUND IN ZONE 1 during PART 1 inspection 6,000 flight cycles. (c) -OPTION 1 (ACTION 2): Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack in unrepaired areas. (a) -Within 4,500 flight cycles after the installation of the SRM single gore web repair. OPTION 1 (ACTION 3): Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. -Before further flight.OPTION 2 (ACTION 1): Do PART 6: ALL GORE WEB REPAIR. -Within 30,000 flight cycles after the installation of the SRM all gore web repair. OPTION 2 (ACTION 2): Do PART 4: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR for any crack. 6,000 flight cycles. (c) -Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. CONDITION 2: NO CRACK FOUND IN ZONE 1 during PART 1 inspection (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 28 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 29 Group 2, Configuration 1: Table 1: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 3 (ACTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 3: ANY CRACK FOUND IN ZONE 2 during PART 2 inspection 6,000 flight cycles. (c) -CONDITION 3 (ACTION 2): Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack in unrepaired areas. (b) 6,000 flight cycles. (c) -Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. CONDITION 4: NO CRACK FOUND IN ZONE 2 during PART 2 inspection (b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR REPAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection 4,500 flight cycles.-Repeat PART 3: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 29 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 30 Group 2, Configuration 1: Table 1: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition 4,500 flight cycles.-Repeat PART 4: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack. CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection (a) For aft pressure bulkheads with existing repairs that are in the PART 1 inspection area, PART 1 inspections are applicable to the gore webs outside the repair area. (b) For aft pressure bulkheads with existing repairs that are in the PART 2 inspection area, PART 2 inspections are applicable to the gore webs outside the repair area. (c) The inspections in Table 3 are required at the compliance times specified in Table 3 to satisfy the Widespread Fatigue Damage (WFD) requirements. The PART 1 and PART 2 inspections in Table 3 are terminating action to the initial and repeat PART 1 and PART 2 inspections in Table 1 and Table 2. Group 2, Configuration 2: Table 2: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 30,000 total flight cycles.Do PART 1: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. All Airplanes (c) (a) -Before 54,000 total flight cycles, or within 4,500 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do PART 2: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. (c) (b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 30 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 31 Group 2, Configuration 2: Table 2: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.OPTION 1 (ACTION 1): Do PART 5: SINGLE GORE WEB REPAIR. CONDITION 1: ANY CRACK FOUND IN ZONE 1 during PART 1 inspection 6,000 flight cycles. (c) -OPTION 1 (ACTION 2): Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack in unrepaired areas. (a) -Within 4,500 flight cycles after the installation of the SRM single gore web repair. OPTION 1 (ACTION 3): Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. -Before further flight.OPTION 2 (ACTION 1): Do PART 6: ALL GORE WEB REPAIR. -Within 30,000 flight cycles after the installation of the SRM all gore web repair. OPTION 2 (ACTION 2): Do PART 4: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR for any crack. 6,000 flight cycles. (c) -Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. CONDITION 2: NO CRACK FOUND IN ZONE 1 during PART 1 inspection (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 31 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 32 Group 2, Configuration 2: Table 2: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 3 (ACTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 3: ANY CRACK FOUND IN ZONE 2 during PART 2 inspection 6,000 flight cycles. (c) -CONDITION 3 (ACTION 2): Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack in unrepaired areas. (b) 6,000 flight cycles. (c) -Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. CONDITION 4: NO CRACK FOUND IN ZONE 2 during PART 2 inspection (b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR REPAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection 4,500 flight cycles.-Repeat PART 3: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 32 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 33 Group 2, Configuration 2: Table 2: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance TimeActionCondition 4,500 flight cycles.-Repeat PART 4: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack. CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection (a) For aft pressure bulkheads with existing repairs that are in the PART 1 inspection area, PART 1 inspections are applicable to the gore webs outside the repair area. (b) For aft pressure bulkheads with existing repairs that are in the PART 2 inspection area, PART 2 inspections are applicable to the gore webs outside the repair area. (c) The inspections in Table 3 are required at the compliance times specified in Table 3 to satisfy the Widespread Fatigue Damage (WFD) requirements. The PART 1 and PART 2 inspections in Table 3 are terminating action to the initial and repeat PART 1 and PART 2 inspections in Table 1 and Table 2. Group 2: Table 3: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 - Widespread Fatigue Damage (WFD) Requirements Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 66,000 total flight cycles.Do PART 1: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. Airplanes on which no in- spection of Structural Significant Item (SSI) F- 30C and SSI F-30D was done in accordance with the SSID (c) (a) (d) (e) AND Do PART 2: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. (b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 33 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 34 Group 2: Table 3: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 - Widespread Fatigue Damage (WFD) Requirements Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 9,000 flight cycles after the most recent inspection of SSI F-30C was done in accordance with the SSID, Do PART 1: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. 737-200/200C Airplanes on which at least one in- spection of SSI F-30C and SSI F-30D was done in accordance with the SSID (c) (d) (f) or within 6,000 flight cycles after the most recent inspection of the gore webs in the apex area at the center of the bulkhead was done in accor- dance with PART IV of SB 737- 53A1214, (a) AND Do PART 2: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. (d) (c) or within 4,500 flight cycles after the original issue date of this service bulletin, (b) (c) whichever occurs first. -Within 8,000 flight cycles after the most recent inspection of SSI F-30C was done in accordance with the SSID, Do PART 1: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. 737-300/400/500 Air- planes on which at least one inspection of SSI F- 30C and SSI F-30D was done in accordance with the SSID (c) (e) (g) or within 6,000 flight cycles after the most recent inspection of the gore webs in the apex area at the center of the bulkhead was done in accor- dance with PART IV of SB 737- 53A1214, (a) AND Do PART 2: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. (e) (c) or within 4,500 flight cycles after the original issue date of this service bulletin, (b) (c) whichever occurs first. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 34 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 35 Group 2: Table 3: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 - Widespread Fatigue Damage (WFD) Requirements Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.OPTION 1 (ACTION 1): Do PART 5: SINGLE GORE WEB REPAIR. CONDITION 1: ANY CRACK FOUND IN ZONE 1 during PART 1 inspection 4,500 flight cy- cles. (c) -OPTION 1 (ACTION 2): Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack in unrepaired areas. (a) -Within 4,500 flight cycles after the in- stallation of the SRM single gore web repair. OPTION 1 (ACTION 3): Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. -Before further flight.OPTION 2 (ACTION 1): Do PART 6: ALL GORE WEB REPAIR. -Within 30,000 flight cycles after the installation of the SRM all gore web repair. OPTION 2 (ACTION 2): Do PART 4: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR for any crack. 4,500 flight cy- cles. (c) -Repeat PART 1: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. CONDITION 2: NO CRACK FOUND IN ZONE 1 during PART 1 inspection (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 35 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 36 Group 2: Table 3: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 - Widespread Fatigue Damage (WFD) Requirements Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 3 (ACTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 3: ANY CRACK FOUND IN ZONE 2 during PART 2 inspection 4,500 flight cy- cles. (c) -CONDITION 3 (ACTION 2): Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack in unrepaired areas. (b) 4,500 flight cy- cles. (c) -Repeat PART 2: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. CONDITION 4: NO CRACK FOUND IN ZONE 2 during PART 2 inspection (b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection 4,500 flight cy- cles. -Repeat PART 3: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR during PART 3 inspection -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR during PART 4 in- spection Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 36 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 37 Group 2: Table 3: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs of the aft pressure bulkhead at Station (STA) 1016 - Widespread Fatigue Damage (WFD) Requirements Repeat Interval (Not to Exceed) Compliance TimeActionCondition 4,500 flight cy- cles. -Repeat PART 4: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack. CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR during PART 4 in- spection (a) For aft pressure bulkheads with existing repairs that are in the PART 1 inspection area, PART 1 inspections are applicable to the gore webs outside the repair area. (b) For aft pressure bulkheads with existing repairs that are in the PART 2 inspection area, PART 2 inspections are applicable to the gore webs outside the repair area. (c) The inspections in Table 3 are required at the compliance times specified in Table 3 to satisfy the WFD requirements. The PART 1 and PART 2 inspections in Table 3 are terminating action to the initial and repeat PART 1 and PART 2 inspections in Table 1 and Table 2. (d) For 737-200/200C airplanes, the term "SSID" identifies Boeing Document D6-37089, "Supplemental Structural Inspection Document for Model 737-100/200/200C Airplanes". (e) For 737-300/400/500 airplanes, the term "SSID" identifies Boeing Document D6-82669, "Supplemental Structural Inspection Document Models 737-300/400/500 Airplanes". (f) The interval of 9,000 flight cycles provides the required Damage Tolerance Rating (DTR) of 10 for SSI F-30C in accordance with the SSID as required by AD 98-11-04 R1 for 737-200 airplanes and AD 2008- 08-23 for 737-200C airplanes. (g) The interval of 8,000 flight cycles provides the required Damage Tolerance Rating (DTR) of 10 for SSI F-30C in accordance with the SSID as required by AD 2008-09-13 for 737-300/400/500 airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 37 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 38 Group 2: Table 4: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs and repair webs of existing Structural Repair Manual (SRM) single gore web repair on the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 4,500 flight cycles af- ter the original issue date of this service bul- letin. Before 66,000 total flight cy- cles. Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. Airplanes which have an existing single gore web repair, as of the original is- sue date of this service bulletin, that was done in accordance with 737- 100/200 SRM 53-10-11, Figure 13, or 737- 300/400/500 SRM 53-80- 08, Repair 9, and on which no inspection of Structural Significant Item (SSI) F- 30C and SSI F-30D was done in accordance with the SSID (a) (b) (c) -Within 4,500 flight cycles af- ter the original issue date of this service bul- letin. Within 9,000 flight cycles af- ter the most re- cent inspection of SSI F-30C was done in ac- cordance with the SSID. Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. (a) 737-200/200C Airplanes which have an existing sin- gle gore web repair, as of the original issue date of this service bulletin, that was done in accordance with 737-100/200 SRM 53- 10-11, Figure 13, and on which at least one inspec- tion of SSI F-30C and SSI F-30D was done in accor- dance with the SSID (b) (d) (b) -Within 4,500 flight cycles af- ter the original issue date of this service bul- letin. Within 8,000 flight cycles af- ter the most re- cent inspection of SSI F-30C was done in ac- cordance with the SSID. Do PART 3: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE GORE WEBS AND RE- PAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. (a) 737-300/400/500 Airplanes which have an existing sin- gle gore web repair, as of the original issue date of this service bulletin, that was done in accordance with 737-300/400/500 SRM 53-80-08, Repair 9, and on which at least one inspec- tion of SSI F-30C and SSI F-30D was done in accor- dance with the SSID (c) (e) (c) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 38 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 39 Group 2: Table 4: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs and repair webs of existing Structural Repair Manual (SRM) single gore web repair on the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR REPAIR WEBS OF THE SINGLE GORE WEB REPAIR dur- ing PART 3 inspection 4,500 flight cycles.-Repeat PART 3: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND RE- PAIR WEBS OF THE SIN- GLE GORE WEB REPAIR during PART 3 inspection (a) (a) PART 3 inspections are applicable to a 737-100/200 SRM 53-10-11, Figure 13, or 737-300/400/500 SRM 53-80-08, Repair 9 single gore web repair without deviations. PART 3 inspections are also applicable to any other repair installed, provided the repair meets all of the requirements that follow: 1. The installed repair was approved with a FAA Form 8100-9 by a Boeing company Authorized Representative (AR) who was authorized by the FAA to make such findings. 2. The cut line extends beyond the ninth fastener row but does not extend beyond the twelfth fas- tener row of the gore web lap splices, counted radially outboard from the center of the aft pressure bulkhead. The twelfth fastener row is not cut out. The repair doubler extends two rows on either side of the cut line in the radial direction common to the lap splices. 3. Deviations to fastener type, size, and pitch are permitted only for fasteners not common to the lap splices. 4. The repair meets all other requirements of 737-100/200 SRM 53-10-11, Figure 13, or 737- 300/400/500 SRM 53-80-08, Repair 9 not specifically referred to above. (b) For 737-200/200C airplanes, the term "SSID" identifies Boeing Document D6-37089, "Supplemental Structural Inspection Document for Model 737-100/200/200C Airplanes". (c) For 737-300/400/500 airplanes, the term "SSID" identifies Boeing Document D6-82669, "Supplemental Structural Inspection Document Models 737-300/400/500 Airplanes". (d) The interval of 9,000 flight cycles provides the required Damage Tolerance Rating (DTR) of 10 for SSI F-30C in accordance with the SSID as required by AD 98-11-04 R1 for 737-200 airplanes and AD 2008- 08-23 for 737-200C airplanes. (e) The interval of 8,000 flight cycles provides the required Damage Tolerance Rating (DTR) of 10 for SSI F-30C in accordance with the SSID as required by AD 2008-09-13 for 737-300/400/500 airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 39 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 40 Group 2: Table 5: Detailed inspections, High Frequency Eddy Current (HFEC) inspections and Low Frequency Eddy Current (LFEC) inspections for any crack in the repair webs of existing Structural Repair Manual (SRM) all gore web repair on the aft pressure bulkhead at Station (STA) 1016 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,500 flight cycles af- ter the original issue date of this service bul- letin. Within 30,000 flight cycles af- ter the installa- tion of the SRM all gore web re- pair. Do PART 4: DETAILED, HFEC AND LFEC IN- SPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB RE- PAIR for any crack. Airplanes which have an existing all gore web repair, as of the original issue date of this service bulletin, that was done in accordance with 737-100/200 SRM 53- 10-11, Figure 14, or 737- 300/400/500 SRM 53-80- 08, Repair 10 (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection 4,500 flight cycles.-Repeat PART 4: DE- TAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack. CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR during PART 4 inspection (a) (a) PART 4 inspections are applicable to a 737-100/200 SRM 53-10-11, Figure 14, or 737-300/400/500 SRM 53-80-08, Repair 10 all gore web repair without deviations. PART 4 inspections are also applicable to any other repair installed, provided the repair meets all of the requirements that follow: 1. The installed repair was approved with a FAA Form 8100-9 by a Boeing company Authorized Representative (AR) who was authorized by the FAA to make such findings. 2. The cut line extends beyond the ninth fastener row but does not extend beyond the twelfth fas- tener row of the gore web lap splices, counted radially outboard from the center of the aft pressure bulkhead. The twelfth fastener row is not cut out. All seven gore webs are cut out at the same location with regards to the fastener row. 3. Deviations to fastener type, size, and pitch are permitted only for fasteners not common to the lap splices. 4. The repair meets all other requirements of 737-100/200 SRM 53-10-11, Figure 14, or 737- 300/400/500 SRM 53-80-08, Repair 10 not specifically referred to above. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 40 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 41 F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. In addition, the Manager of the FAA, Seattle Aircraft Certification Office, approves accomplishment of the inspections, methods, and repairs at the compliance times and repeat intervals defined in Paragraph 1.E., Compliance, for Zone 1, as an Alternative Method of Compliance (AMOC) to the inspections and corrective actions required by paragraph (o) of AD 2012-18-13 R1. All provisions of AD 2012-18-13 R1 that are not specifically referenced above remain fully applicable and must be complied with accordingly. The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as an Alternative Method of Compliance (AMOC) to paragraph (c) of AD 98-11-04 R1 for the inspection of Structural Significant Items (SSIs) F-30C, F-30D, and F-30E of Supplemental Structural Inspection Document (SSID) D6-37089. This AMOC only applies to the areas inspected in accordance with this service bulletin and to those airplanes identified in this service bulletin. All provisions of AD 98-11-04 R1 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as a Method of Compliance (MOC) to paragraph (g) of AD 98-11-04 R1 for the inspection of Structural Significant Items (SSIs) F-30C and F-30D of Supplemental Structural Inspection Document (SSID) D6-37089, affected by 737-100/200 SRM 53-10-11, Figure 13 and Figure 14. This MOC applies only to these SSIs and only for the area covered by the repair as defined in this service bulletin, and to the airplanes identified in this service bulletin. All provisions of AD 98-11-04 R1 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as an Alternative Method of Compliance (AMOC) to paragraphs (g) and (h) of AD 2008-08-23 for the inspection of Structural Significant Items (SSIs) F-30C, F-30D, and F-30E of Supplemental Structural Inspection Document (SSID) D6-37089. This AMOC only applies to the areas inspected in accordance with this service bulletin and to those airplanes identified in this service bulletin. All provisions of AD 2008-08-23 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 41 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 42 The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as an Alternative Method of Compliance (AMOC) to paragraphs (g) and (h) of AD 2008-08-23 for the inspection of Structural Significant Items (SSIs) F-30C and F-30D of Supplemental Structural Inspection Document (SSID) D6-37089, affected by 737-100/200 SRM 53-10-11, Figure 13 and Figure 14. This AMOC applies only to these SSIs and only for the area covered by the repair as defined in this service bulletin, and to the airplanes identified in this service bulletin. All provisions of AD 2008-08-23 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as an Alternative Method of Compliance (AMOC) to paragraphs (g) and (h) of AD 2008-09-13 for the inspection of Structural Significant Items (SSIs) F-30C, F-30D, F-30E, and F-30F of Supplemental Structural Inspection Document (SSID) D6-82669. This AMOC only applies to the areas inspected in accordance with this service bulletin and to those airplanes identified in this service bulletin. All provisions of AD 2008-09-13 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. The Manager of the FAA Seattle Aircraft Certification Office approves the inspection methods, compliance times, and repeat intervals defined in Paragraph 1.E., Compliance, as an Alternative Method of Compliance (AMOC) to paragraphs (g) and (h) of AD 2008-09-13 for the inspection of Structural Significant Items (SSIs) F-30C and F-30D of Supplemental Structural Inspection Document (SSID) D6-82669, affected by 737-300/400/500 SRM 53-80-08, Repair 9 and Repair 10. This AMOC applies only to these SSIs and only for the area covered by the repair as defined in this service bulletin, and to the airplanes identified in this service bulletin. All provisions of AD 2008-09-13 that are not specifically referenced above remain fully applicable and must be complied with accordingly. If operators choose this AMOC, then they must revise their FAA-approved maintenance or inspection program with these alternative inspections. G. Manpower The tables below show an estimate of the task hours necessary to do this inspection for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 42 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 43 Group 2: Detailed, High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections of the gore webs on the aft pressure bulkhead at STA 1016 Elapsed HoursTask HoursNumber of PersonsTask 0.250.251Open Access 8.00 (a)8.00 (a)1FIGURE 1 18.75 (a)37.50 (a)2FIGURE 2 0.250.251Close Access 27.25 (a)46.00 (a)TOTAL FOR EACH AIRPLANE (a) The estimates given are the task hours and elapsed hours necessary for in- spections of the aft pressure bulkhead without SRM repairs. Group 2: Detailed, HFEC and LFEC inspections of the gore webs and repair webs of each SRM single gore web repair on the aft pressure bulkhead at STA 1016 Elapsed HoursTask HoursNumber of PersonsTask 0.250.251Open Access 7.00 (a)7.00 (a)1FIGURE 3 0.250.251Close Access 7.50 (a)7.50 (a)TOTAL FOR EACH AIRPLANE (a) The estimate given is the task hours and elapsed hours that are necessary for inspections of the aft pressure bulkhead with a typical SRM single gore web repair installed. Group 2: Detailed, HFEC and LFEC inspections of the repair webs of the SRM all gore web repair on the aft pressure bulkhead at STA 1016 Elapsed HoursTask HoursNumber of PersonsTask 0.250.251Open Access 9.00 (a)9.00 (a)1FIGURE 4 0.250.251Close Access 9.50 (a)9.50 (a)TOTAL FOR EACH AIRPLANE (a) The estimate given is the task hours and elapsed hours that are necessary for inspections of the aft pressure bulkhead with a typical SRM all gore web repair installed. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 43 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 44 H. Weight and Balance Changes Weight and Balance changes affected by incorporation of this service bulletin are dependent on the type and number of repairs done on each particular airplane. Weight and Balance are to be calculated by the operator by weighing parts installed or removed. Operators should make necessary revisions to the appropriate weight and balance report. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 737-53A1214 b. Boeing Service Letter 737-SL-51-042 c. Boeing Service Related Problem (SRP) 737-SRP-53-0500 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2008-08-23, 2008-09-13, 2012-18-13 R1, 98-11-04 R1 e. Service Bulletin Index D6-19567 f. 737 Fleet Team Digest (FTD) 53-15002 g. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-11-52 h. 737-100/200 Aircraft Maintenance Manual (AMM) 12-31-41 i. 737-100/200 Structural Repair Manual (SRM) 53-10-11 j. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-31-41 k. 737-300 Structural Repair Manual (SRM) 53-80-08 l. 737-400 Structural Repair Manual (SRM) 53-80-08 m. 737-500 Structural Repair Manual (SRM) 53-80-08 n. 737-100/200/200C Supplemental Structural Inspection Document (SSID) D6-37089 Structural Significant Items (SSIs) F-30C, F-30D, and F-30E o. 737-300/400/500 Supplemental Structural Inspection Document (SSID) D6-82669 Structural Significant Items (SSIs) F-30C, F-30D, F-30E, and F-30F 2. Data Supplied with this Service Bulletin: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 44 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 45 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number BULKHEAD INSTALLATION STATION 101665-46568 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-SectionPublication 53-10737-100/200 Structural Repair Manual 53-80737-300 Structural Repair Manual 53-80737-400 Structural Repair Manual 53-80737-500 Structural Repair Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS and there are new DTI requirements for structure affected. – New DTI, required for safety, are contained in Paragraph 1.E., Compliance of this service bulletin. – New DTI, which may be used in support of compliance with 14 Code of Federal Regulations (CFR), Section 121.1109 or 129.109, are contained in 737-100/200 SRM 53-10-11, Figure 13 and 14, for 737-200/200C airplanes, and in 737-300/400/500 SRM 53-80-08, Repair 9 and 10, for 737-300/400/500 airplanes. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 45 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 46 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 46 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT BLANK PAGE ### Page 47 2. MATERIAL INFORMATION A. Material - Price and Availability None. B. Industry Support Information Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator No special parts or materials are necessary to do the change in this service bulletin. But, parts and materials in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 47 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 48 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 48 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT BLANK PAGE ### Page 49 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 737 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 737 Aircraft Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 737 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 49 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 50 7. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 8. Refer to APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D and APPENDIX E for logic diagrams. Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 9. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 11. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 12. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 14. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled "RC Exempt," then the RC requirement is removed from that step or sub-step. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 50 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 51 including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. B. WORK INSTRUCTIONS Group 1: 1. Boeing endorses the 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: 1. Open stabilizer trim access door 3701L to get access to the aft side of the aft pressure bulkhead at Station (STA) 1016. Refer to 737-100/200 AMM 12-31-41 or 737-300/400/500 AMM 12-31-41 for access door location. 2. RC - Do PART 1: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack. NOTE: Zone 1 includes all fastener locations within 7 inches from the center of the aft pressure bulkhead, measured radially outboard. This includes the first six fastener rows of the gore web lap splices and the fastener locations on the gore web within the first 7 inches that are outside the gore web lap splices. Zone 1 of this service bulletin is the same as the inspection area of PART IV of SB 737-53A1214 at the center of the aft pressure bulkhead. NOTE: For aft pressure bulkheads with existing repairs that are in the PART 1 inspection area, PART 1 inspections are applicable to the gore webs outside the repair area. a. CONDITION 1: ANY CRACK FOUND IN ZONE 1 (1) OPTION 1: (a) OPTION 1 (ACTION 1): Do PART 5: SINGLE GORE WEB REPAIR. (b) OPTION 1 (ACTION 2): Repeat PART 1: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack in unrepaired areas, at the times specified in Paragraph 1.E., Compliance. (c) OPTION 1 (ACTION 3): Do PART 3: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. 1) CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR REPAIR WEBS OF THE SINGLE GORE WEB REPAIR a) Contact The Boeing Company for repair instructions and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 51 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 52 2) CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR a) Repeat PART 3: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. (2) OPTION 2: (a) OPTION 2 (ACTION 1): Do PART 6: ALL GORE WEB REPAIR. (b) OPTION 2 (ACTION 2): Do PART 4: DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. 1) CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR a) Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR a) Repeat PART 4: DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. b. CONDITION 2: NO CRACK FOUND IN ZONE 1 (1) Repeat PART 1: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 for any crack, at the times specified in Paragraph 1.E., Compliance. 3. RC - Do PART 2: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack. NOTE: Zone 2 includes all fastener locations of the gore web radial lap splices from the seventh fastener row to the second tear strap (thirty-ninth fastener row), counted radially outboard from the center of the aft pressure bulkhead. Some airplane configurations have two fastener rows common to the first (inner) tear strap and some airplane configurations have three fastener rows common to the first tear strap. It is required to inspect the gore web lap splices common to all fastener rows under the first tear strap. NOTE: For aft pressure bulkheads with existing repairs that are in the PART 2 inspection area, PART 2 inspections are applicable to the gore webs outside the repair area. a. CONDITION 3: ANY CRACK FOUND IN ZONE 2 (1) CONDITION 3 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) CONDITION 3 (ACTION 2): Repeat PART 2: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack in unrepaired areas, at the times specified in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 52 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 53 b. CONDITION 4: NO CRACK FOUND IN ZONE 2 (1) Repeat PART 2: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 for any crack, at the times specified in Paragraph 1.E., Compliance. 4. RC - For airplanes which have an existing single gore web repair that was done in accordance with 737-100/200 SRM 53-10-11, Figure 13, or 737-300/400/500 SRM 53-80-08, Repair 9, do PART 3: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack. NOTE: PART 3 inspections are applicable to a 737-100/200 SRM 53-10-11, Figure 13, or 737-300/400/500 SRM 53-80-08, Repair 9 single gore web repair without deviations. PART 3 inspections are also applicable to any other repair installed, provided the repair meets all of the requirements that follow: 1. The installed repair was approved with a FAA Form 8100-9 by a Boeing company Authorized Representative (AR) who was authorized by the FAA to make such findings. 2. The cut line extends beyond the ninth fastener row but does not extend beyond the twelfth fastener row of the gore web lap splices, counted radially outboard from the center of the aft pressure bulkhead. The twelfth fastener row is not cut out. The repair doubler extends two rows on either side of the cut line in the radial direction common to the lap splices. 3. Deviations to fastener type, size, and pitch are permitted only for fasteners not common to the lap splices. 4. The repair meets all other requirements of 737-100/200 SRM 53-10-11, Figure 13, or 737-300/400/500 SRM 53-80-08, Repair 9 not specifically referred to above. a. CONDITION 5: ANY CRACK FOUND IN THE GORE WEBS OR REPAIR WEBS OF THE SINGLE GORE WEB REPAIR (1) Contact The Boeing Company for repair instructions and do the repair. b. CONDITION 6: NO CRACK FOUND IN THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR (1) Repeat PART 3: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. 5. RC - For airplanes which have an existing all gore web repair that was done in accordance with 737-100/200 SRM 53-10-11, Figure 14, or 737-300/400/500 SRM 53-80-08, Repair 10, do PART 4: DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 53 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 54 NOTE: PART 4 inspections are applicable to a 737-100/200 SRM 53-10-11, Figure 14, or 737-300/400/500 SRM 53-80-08, Repair 10 all gore web repair without deviations. PART 4 inspections are also applicable to any other repair installed, provided the repair meets all of the requirements that follow: 1. The installed repair was approved with a FAA Form 8100-9 by a Boeing company Authorized Representative (AR) who was authorized by the FAA to make such findings. 2. The cut line extends beyond the ninth fastener row but does not extend beyond the twelfth fastener row of the gore web lap splices, counted radially outboard from the center of the aft pressure bulkhead. The twelfth fastener row is not cut out. All seven gore webs are cut out at the same location with regards to the fastener row. 3. Deviations to fastener type, size, and pitch are permitted only for fasteners not common to the lap splices. 4. The repair meets all other requirements of 737-100/200 SRM 53-10-11, Figure 14, or 737-300/400/500 SRM 53-80-08, Repair 10 not specifically referred to above. a. CONDITION 7: ANY CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR (1) Contact The Boeing Company for repair instructions and do the repair. b. CONDITION 8: NO CRACK FOUND IN THE REPAIR WEBS OF THE ALL GORE WEB REPAIR (1) Repeat PART 4: DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR for any crack, at the times specified in Paragraph 1.E., Compliance. 6. Close stabilizer trim access door 3701L. Refer to 737-100/200 AMM 12-31-41 or 737-300/400/500 AMM 12-31-41 for access door location. 7. Put the airplane back to a serviceable condition. Group 2: PART 1: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS IN ZONE 1 1. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices and outside the lap splices) of the aft pressure bulkhead in Zone 1, in accordance with FIGURE 1. Group 2: PART 2: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEB LAP SPLICES IN ZONE 2 1. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices only) of the aft pressure bulkhead in Zone 2, in accordance with FIGURE 2. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 54 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 55 Group 2: PART 3: DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS AND REPAIR WEBS OF THE SINGLE GORE WEB REPAIR 1. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the gore webs (lap splices only) and in the repair webs (lap splices and outside the lap splices), of each SRM single gore web repair, in accordance with FIGURE 3. Group 2: PART 4: DETAILED, HFEC AND LFEC INSPECTIONS OF THE REPAIR WEBS OF THE ALL GORE WEB REPAIR 1. Do detailed inspections, High Frequency Eddy Current (HFEC) inspections, and Low Frequency Eddy Current (LFEC) inspections for any crack in the repair webs (lap splices and outside the lap splices), of a SRM all gore web repair, in accordance with FIGURE 4. Group 2: PART 5: SINGLE GORE WEB REPAIR 1. Do a single gore web repair in accordance with the applicable SRM in the table below: NOTE: PART 5 repair is only applicable to repair a crack found in Zone 1 of this service bulletin. Single Gore Web RepairAirplane 737-100/200 SRM 53-10-11, Figure 13737-200 737-100/200 SRM 53-10-11, Figure 13737-200C 737-300 SRM 53-80-08, Repair 9737-300 737-400 SRM 53-80-08, Repair 9737-400 737-500 SRM 53-80-08, Repair 9737-500 Group 2: PART 6: ALL GORE WEB REPAIR 1. Do the all gore web repair in accordance with the applicable SRM in the table below: NOTE: PART 6 repair is only applicable to repair a crack found in Zone 1 of this service bulletin. All Gore Web RepairAirplane 737-100/200 SRM 53-10-11, Figure 14737-200 737-100/200 SRM 53-10-11, Figure 14737-200C 737-300 SRM 53-80-08, Repair 10737-300 737-400 SRM 53-80-08, Repair 10737-400 737-500 SRM 53-80-08, Repair 10737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 55 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT ### Page 56 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT This Figure applies only to: Group 2. STA 1016 A WITHOUT SRM REPAIR BLO B WITH SEM SINGL • GORE WEB REPAI S-7L S-15L S-15R GORE WEB LAP SPLICE (7 LOCATIONS) S-23L S-23R AFT PRESSURE BULKHEAD (AFT SIDE) 2481367 A-A FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 (SHEET 1 OF 5) Original Issue: March 10, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1355 Work - See page 1 for details. 56 of 100 ### Page 57 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT TYPICAL 4 O TYPICAL S-7L _S-7R B • ZONE 1 S-15L - • S-15R TYPICAL (IF EXISTING) 2 3 TYPICAL S-23L S-23R + VISIBLE AFT GORE WEB CRITICAL FASTENER ROW * HIDDEN FWD GORE WEB CRITICAL FASTENER ROW • FASTENER LOCATIONS AFT PRESSURE BULKHEAD OUTSIDE GORE WEB LAP (WITHOUT SRM REPAIR) SPLICES (AFT SIDE) * FASTENER LOCATION THAT IS NOT IN ALL AFT PRESSURE BULKHEAD CONFIGURATIONS 2499119 FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 (SHEET 2 OF 5) Original Issue: March 10, 2017 Export Controlled ECCN: 9E991 - BOEING 737-53A1355 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 100 ### Page 58 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT TYPICAL 4 BL O 1 TYPICAL —S-7R S-15L $-15R ZONE 1 TYPICAL (IF EXISTING) 3) TYPICAL S-23R S-23L + VISIBLE AFT GORE WEB CRITICAL FASTENER ROW + HIDDEN FWD GORE WEB CRITICAL FASTENER ROW AFT PRESSURE BULKHEAD • FASTENER LOCATIONS (WITH SRM SINGLE GORE WEB REPAIR) OUTSIDE GORE WEB LAP (AFT SIDE) SPLICES TYPICAL SRM SINGLE * FASTENER LOCATION THAT IS NOT GORE WEB REPAIR AREA IN ALL AFT PRESSURE BULKHEAD CONFIGURATIONS FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 (SHEET 3 OF 5) Original Issue: March 10, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1355 Work - See page 1 for details. 58 of 100 ### Page 59 (OCR) BOEING SERVICE BULLETIN 737-53A1355 ALERT ALERT - ZONE 1 TYPICAL CRACK IN VISIBLE AFT GORE WEB (LAP SPLICE AND OUTSIDE INBD LAP SPLICE) -O- TYPICAL CRACK IN HIDDEN FWD GORE WEB (LAP SPLICE ONLY) TYPICAL CRACKS IN GORE WEB (AFT SIDE) RADIAL HIDDEN FWD GORE - STIFFENER WEB CRITICAL FASTENER ROW HIDDEN FWD GORE WEB VISIBLE AFT GORE WEB • VISIBLE AFT GORE WEB CRITICAL FASTENER ROW TYPICAL GORE WEB LAP SPLICE B-B 2500370 FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 (SHEET 4 OF 5) Original Issue: March 10, 2017 Export Controlled ECCN: 9E991 - BOEING 737-53A1355 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 100 ### Page 60 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQtyIdentificationNameTaskStep (a) (e) (f)--VISIBLE AFT GORE WEB CRITICAL FAS- TENER ROW Inspect1 (b) (e) (f)--FASTENER LOCA- TION THAT IS NOT IN ALL AFT PRESSURE BULKHEAD CONFIGU- RATIONS Inspect2 (c) (e) (f)--FASTENER LOCA- TIONS OUTSIDE GORE WEB LAP SPLICES Inspect3 (d) (e) (f)--HIDDEN FWD GORE WEB CRITICAL FAS- TENER ROW Inspect4 (a) Do a detailed inspection and a High Frequency Eddy Current (HFEC) inspection for any crack in the visible aft gore web around each critical fastener location of all gore web lap splices, in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23. (b) If this fastener is installed in one or more gore web lap splices, do a detailed inspection and a HFEC in- spection for any crack around each existing fastener location, in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23. (c) Do a detailed inspection and a HFEC inspection for any crack in the gore webs around each fastener lo- cation outside the gore web lap splices, in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23. (d) Do a Low Frequency Eddy Current (LFEC) inspection for any crack in the hidden forward gore web around each critical fastener location of all gore web lap splices, in accordance with 737 NDT Manual Part 6, 53- 11-52, Figure 2, and a HFEC inspection for any crack in the gore webs along the edges of the visible aft gore webs, in accordance with 737 NDT Manual Part 6, 53-11-52, Figure 2. (e) For aft pressure bulkheads with existing repairs that are in the PART 1 inspection area, PART 1 inspections are applicable to the gore webs outside the repair area. (f) Zone 1 includes all fastener locations within 7 inches from the center of the aft pressure bulkhead, measured radially outboard. This includes the first six fastener rows of the gore web lap splices and the fastener locations on the gore web within the first 7 inches that are outside the gore web lap splices. Zone 1 of this service bulletin is the same as the inspection area of PART IV of SB 737-53A1214 at the center of the aft pressure bulkhead. FIGURE 1: STA 1016 - AFT PRESSURE BULKHEAD - AFT SIDE - DETAILED, HFEC AND LFEC INSPECTIONS OF THE GORE WEBS - ZONE 1 (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 10, 2017 737-53A1355 60 of 100 BOEING SERVICE BULLETIN 737-53A1355 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/737-53a1355/file/85c0cd9d16b6.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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