# Boeing Alert Service Bulletin 757-53A0012: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0778; AD 2018-06-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 757-53A0012](https://openairdocs.org/service-documents/boeing/757-53a0012.md) - Title as filed: SB-757-53A0012-R1 - Pages: 169 - PDF: https://openairdocs.org/files/sha256/1f/fb/1ffbfd140f0f925b32aea112a44abd0051ea16a23fa1f3005cf5cdfad40dbad4 - Page: https://openairdocs.org/service-documents/boeing/757-53a0012/file/1ffbfd140f0f ## 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 757 Service Bulletin ALERT Number: 757-53A0012 Original Issue: October 05, 1984 Revision 1: January 25, 2017 ATA System: 5363 SUBJECT: FUSELAGE - Section 46 - Structure - Cargo Deck Attachment Inspection and Modification Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 1989 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 1 of 169 5.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 2 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 S u m m a r y ...................................................... 9 1. PLANNING INFORMATION ........................................ 1 3 A . E f f e c t i v i t y ............................................... 1 3 1. Airplanes ............................................ 1 3 2 . S p a r e s A f f e c t e d ........................................ 1 4 B. Concurrent Requirements ...................................... 1 4 C. Reason ................................................ 1 4 D. Description .............................................. 1 5 E. Compliance .............................................. 1 6 F . A p p r o v a l ............................................... 3 0 G. Manpower .............................................. 3 0 H. Weight and Balance Changes .................................... 3 2 I. Electrical Load Data ......................................... 3 2 J . R e f e r e n c e s .............................................. 3 2 1. Existing Data: ......................................... 3 2 2. Data Supplied with this Service Bulletin: ........................... 3 2 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 2 K. Publications Affected ........................................ 3 3 L. Interchangeability and Intermixability of Parts ........................... 3 3 M. Software Accomplishment Summary ................................ 3 3 2. MATERIAL INFORMATION ........................................ 3 5 A. Material - Price and Availability ................................... 3 5 B. Industry Support Information .................................... 3 5 C. Parts Necessary for Each Airplane ................................. 3 5 1 . K i t s / P a r t s ............................................ 3 5 2. Parts and Materials Supplied by the Operator ........................ 3 8 3. Parts Modified and Reidentified ................................ 3 8 4. Parts Removed and Not Replaced .............................. 3 8 D. Parts Necessary to Change Spares ................................. 3 8 E. Special Tooling - Price and Availability ............................... 3 8 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 8 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9 A. GENERAL INFORMATION ..................................... 3 9 B. WORK INSTRUCTIONS ....................................... 4 1 FIGURE 1: DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF FRAME INNER CHORD FROM STA 1200 TO STA 1620 [Group 1, 3] ......... 5 4 F I G U R E 2 : T H I S F I G U R E I S D E L E T E D.................................. 5 6 FIGURE 3: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME [Group 1, 3] ..... 5 7 FIGURE 4: MODIFICATION OF SIDE PANEL, FRAME, AND INTERCOSTAL AT STA 1380 ..... 6 2 FIGURE 5: MODIFICATION OF SIDE PANEL ATTACHMENT FROM STA 1200 TO STA 1300 . . . 71 FIGURE 6: MODIFICATION OF SIDE PANEL ATTACHMENT FROM STA 1320 TO STA 1620 [Group 1, 3 ] ................................................ 7 4 FIGURE 7: REMOVE SIDE PANEL SPLICE AND CARGO TIEDOWN FITTING ATTACH SCREWS . 77 FIGURE 8: INSTALL SIDE PANEL SPLICE AND CARGO TIEDOWN FITTING ............ 8 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 3 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 4 FIGURE 9: GENERAL VISUAL INSPECTION FOR MODIFICATION [Group 1] ............ 8 6 FIGURE 10: GENERAL VISUAL INSPECTION FOR MODIFICATION [Group 2] ............ 9 4 FIGURE 11: MODIFICATION OF SIDE PANEL, FRAME, AND INTERCOSTAL AT STA 1440 [Group 2] . 103 FIGURE 12: DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF FRAME INNER CHORD FROM STA 1200 TO STA 1580 [Group 2] ......... 1 1 2 FIGURE 13: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME [Group 2] ...... 1 1 4 FIGURE 14: MODIFICATION OF SIDE PANEL ATTACHMENT FROM STA 1320 AND STA 1580 [Group 2] ................................................. 1 1 7 FIGURE 15: SIDE PANEL ATTACH TAB AND FRAME AT 1380 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION .................. 1 2 0 FIGURE 16: SIDE PANEL ATTACH TAB AND FRAME AT 1440 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 2-3] ........... 1 2 2 FIGURE 17: FRAME AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1 , 3 ] .............................................. 1 2 4 FIGURE 18: FRAME AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 2 ] ................................................ 1 2 6 FIGURE 19: GENERAL VISUAL INSPECTION FOR MODIFICATION [Group 3] ............ 1 2 8 FIGURE 20: SIDE PANEL, STANCHION, AND INTERCOSTAL MODIFICATION FROM STA 1440 TO STA 1500 [Group 3] ........................................ 1 3 9 APPENDIX A: TABLE 1: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 [Group 1] ................ 1 4 9 APPENDIX B: TABLE 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 [Group 2] ................ 1 5 5 APPENDIX C: TABLE 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 [Group 3] ................ 1 6 2 APPENDIX D: BOEING PART DEMAND INTENT .............................. 1 6 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 4 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 5 Commercial Airplanes 757 Service Bulletin ALERT Revision Transmittal SheetNumber: 757-53A0012Original Issue: October 05, 1984 Revision 1: January 25, 2017 ATA System: 5363 SUBJECT: FUSELAGE - Section 46 - Structure - Cargo Deck Attachment Inspection and Modification This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Effects of this Revision on airplanes on which the Original Issue was previously done: ActionConditionGroup Do a general visual inspection to make sure that the modifications are complete. All airplanes.1, 2, 3 Airplanes line numbers 37 to 49 and 51 were added to Group 1, and airplane line number 50 was added to Group 2 of this service bulletin effectivity. Airplanes line numbers 2 to 5 were removed from Group 1 and airplane line number 1 to 5 were added to new Group 3. REASON FOR REVISION Revision 1 is sent to add a general visual inspection to verify modification status and if the modification is not complete, do Low Frequency Eddy Current (LFEC) inspections and a mandatory modification that is required to comply with the Widespread Fatigue Damage (WFD) rule. The release classification of this service bulletin has been changed to Alert Service Bulletin. These sections were changed: 1. In Summary, Background, the paragraph has been updated, a Widespread Fatigue Damage (WFD) statement, a reference to Boeing Fleet Team Digest, and a Summary evaluation table have been added. 2. In Summary, Action, the paragraph has been updated. 3. In Summary, Compliance, a paragraph has been added. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 5 of 169 ### Page 6 4. In Summary, Industry Support Information, a paragraph has been added. 5. In Summary, Manpower, a paragraph has been updated and tables have been added. 6. In Summary, Material Information, the paragraph has been updated. 7. In Summary, the illustration has been updated. 8. In Paragraph 1.A., Effectivity, line numbers 37 to 49 and 51 have been added to Group 1, and line number 50 has been added to Group 2, line numbers 2 to 5 were removed from Group 1, and line numbers 1 to 5 were added to new Group 3. 9. In Paragraph 1.C., Reason, the paragraph has been updated, and a Widespread Fatigue Damage (WFD) statement, and a reference to Boeing Fleet Team Digest have been added. 10. In Paragraph 1.D., Description, paragraph has been updated, a group configuration table, and a maintenance zone table have been added. 11. In Paragraph 1.E., Compliance, compliance tables have been added. 12. In Paragraph 1.F., Approval, the paragraph has been updated. 13. In Paragraph 1.G., Manpower, manpower tables have been added. 14. In Paragraph 1.J., References, the reference list has been updated. 15. In Paragraph 1.K.1., Publications, a paragraph has been added. 16. In Paragraph 1.K.2., Damage Tolerance Based Structural Inspections, a paragraph has been added. 17. In Paragraph 1.L., Interchangeability and Intermixability of parts, paragraph has been added. 18. In Paragraph 1.M., Software Accomplish Summary, a paragraph has been added. 19. In Paragraph 2.A., Material - Price and Availability, the paragraphs and table have been updated. 20. In Paragraph 2.B., Industry Support Information, a paragraph has been added. 21. In Paragraph 2.C.1., Kits/Parts, the table has been updated. 22. In Paragraph 2.C.2., Parts and Materials Supplied by the operator, table has been updated. 23. In Paragraph 2.C.3., Parts Modified and Reidentified, a paragraph has been added. 24. In Paragraph 2.C.4., Parts Removed and Not Replaced, a paragraph has been added. 25. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, the paragraph has been updated. 26. In Paragraph 3.A., General Information, paragraphs have been updated and notes have been added. 27. In Paragraph 3.B., Work Instructions, new work instructions have been added. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 6 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 7 28. In Figures 1, 3, 4, 5, 6, 7 and 8, the Illustrations have been updated and step tables added. 29. Figure 2 has been deleted. 30. Figure 9 has been added do inspection for modification on Group 1 airplanes. 31. Figure 10 has been added do inspection for modification on Group 2 airplanes. 32. Figure 11 has been added to do modification of the side panel, frame, and intercostal at STA 1440 for Group 2 airplanes. 33. Figure 12 has been added to do inspection of frame inner chord for Group 2 airplanes. 34. Figure 13 has been added to do modification of aft wall at STA 1640 for Group 2 airplanes. 35. Figure 14 has been added to do modification of side panel attachment from STA 1320 to STA 1580 for Group 2 airplanes. 36. Figure 15 has been added to do inspection of side panel attach tabs and frame at STA 1380. 37. Figure 16 has been added to do inspection of side panel attach tabs and frame at STA 1440 for Group 2 and Group 3 airplanes. 38. Figure 17 has been added to do inspection of frame at STA 1640 for Group 1 and Group 3 airplanes. 39. Figure 18 has been added to do inspection of frame at STA 1640 for Group 2 airplanes. 40. Figure 19 has been added do inspection for modification on Group 3 airplanes. 41. Figure 20 has been added to do modification of the side panel, stanchions, and intercostals from STA 1440 to STA 1500 on Group 3 airplanes. 42. Appendix A, new Logic Diagram has been added for Group 1 airplanes. 43. Appendix B, new Logic Diagram has been added for Group 2 airplanes. 44. Appendix C, new Logic Diagram has been added for Group 3 airplanes. 45. Appendix D, Boeing Part Demand Intent added. The data given in Notice of Status Change 757-53-0012 NSC1 is included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY October 05, 1984Original Issue: January 25, 2017Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 7 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 8 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT BLANK PAGE ### Page 9 Commercial Airplanes 757 Service Bulletin ALERT SummaryNumber: 757-53A0012Original Issue: October 05, 1984 Revision 1: January 25, 2017 ATA System: 5363 SUBJECT: FUSELAGE - Section 46 - Structure - Cargo Deck Attachment Inspection and Modification 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 inspect that a modification to the aft cargo side panel attach tabs and frames; STA 1640 frame; and STA 1380 and STA 1440 intercostals, clips and angles is complete. If modification is not complete, this service bulletin gives instructions to inspect for any crack on the frames from STA 1200 to STA 1640 at the cargo floor interfaces between stringers S-26 and S-27; and to modify the attachments between the frames and the cargo floor. Accomplishment of the work in this service bulletin will make sure that the modification of the body frames at the aft cargo compartment panel attach points and intercostals are complete, to reduce the probability of cracks in the lower lobe frames and side panels. If the work given in this service bulletin is not accomplished, a frame crack at the panel attach point may go undetected and grow in length. An undetected crack could result in reduced structural integrity of the body frames at the aft cargo panel attachment points. Failure of multiple frames could lead to rapid decompression of the airplane. Fatigue testing of two 757 airframes indicates body frames in the aft cargo compartment may crack at the side panel to frame attachment. In one fatigue test airframe, numerous fractured cargo compartment side panel attach fasteners, cracked side panel attach tabs at right side STA 1380, cracked frames at left side STA 1320, 1400, 1500, 1540, 1560 and right side STA 1540 were found at 34,600 equivalent flight cycles. In the second fatigue test airframe, several fractured side panel attach fasteners and cracked frames at right side STA 1580 and 1600 were found at 62,500 equivalent flight cycles. These frame cracks originated at the side panel to frame attach fastener rivet hole and propagated from fastener hole to fastener hole through the frame inner chord, web and fail-safe chord. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 9 of 169 ### Page 10 Cracks have already been reported in fuselage frames in the aft cargo compartment at STA 1340, 1400, 1420, 1500, 1520 and 1580 between S-26 and S-27 on the left and right sides, at the intersection with the side cargo compartment panel installation. The cracking has been attributed to fatigue at the associated frame attachment fastener hole, as a result of an unmodified or de-modified interface between the affected frame and the cargo floor. These cracks may be associated with airplanes that have had the modification removed. Widespread Fatigue Damage (WFD) analysis identified the need for the inspections and modifications of frames from STA 1320 through STA 1620. The modification as given in the original issue of this service bulletin was not mandated, and has been removed on two airplanes that were converted, and may have been removed on more. Airplane line numbers 37 - 51 should have been reworked in production but the rework may not have been accomplished or may have been de-modified. The fuselage frames from STA 1320 through STA 1620 in this service bulletin have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Boeing Fleet Team Digest (FTD) 757 FTD 53-14001 is related to this service bulletin. Boeing Service Related Problem (SRP) 757-SRP-53-0488 is related to this service bulletin. 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 ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications 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/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 53068-R) Do a general visual inspection to make sure that a modification has been done and remains complete. If no modification has been done, or is not complete, do a Low Frequency Eddy Current (LFEC) inspection for any crack and do the modification of the aft cargo compartment side panel to frame attachments. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If the modification has been done, and remains complete, no further inspection or modification is required. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 10 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 11 Group 1 airplanes, which have two cargo doors, have the E-6 electrical equipment rack aft of the number 2 cargo door and do not require inspection or modification of side panel attach tabs at STA 1440 right side. Group 2 airplanes, which have three cargo doors, have the E-6 rack aft of the number 3 cargo door and do not require inspection or modification on the right side, aft of STA 1520. Group 3 airplanes are similar to Group 1 airplanes, and also require inspection or modification of the side panel, stanchions, stringer clips, and intercostals from STA 1440 right side, to STA 1500 right side. EFFECTIVITY 757-200 Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an 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 This service bulletin was first released before October of 1994. Thus industry support for affected airplanes depends upon whether the operator previously filed a warranty claim with Boeing on this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 11 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 12 (OCR) BOEING SERVICE BULLETIN 757-53A0012 ALERT ALERT NO. 2 CARGO DOOR NO. 3 CARGO DOOR STA 1380 SIDEWALL LINING SIDE PANEL STA 1440 CARGO STA DECK 1460 STA 1480 STA 1500 SIDE PANEL TO FRAME ATTACHMENT (40 LOCATIONS ON GROUP 1 AND GROUP 3) (33 LOCATIONS ON GROUP 2) NO. 2 SIDE PANEL AND INTERCOSTAL CARGO DOOR ATTACHMENT SIDE PANEL, STANCHION AND INTERCOSTAL (GROUP 3 ONLY) DO A GENERAL VISUAL INSPECTION OF THE SIDE PANELS, SIDE PANEL ATTACH TABS, FRAME INNER COMPLETEND INTERCOSTALS IN THE CARGO COMPARTMENT, TO MAKE SURE THAT MODIFICATION IS IF THE MODIFICATION IS NOT COMPLETE, DO A LOW FREQUENCY EDDY CURRENT INSPECTION FOR ANY FRAME CRACK, AND DO THE MODIFICATION IF ANY CRACK IS FOUND, CONTACT THE BOEING COMPANY FOR REPAIR INSTRUCTIONS AND DO THE RETHE MODIFICATION IS COMPLETE, NO FURTHER INSPECTION OR MODIFICATIONIS REQUIRED. 2450205 Original Issue: October 05, 1984 Revision 1: January 25, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 757-53A0012 Work - See page 1 for details. 12 of 169 ### Page 13 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-53A0012 Original Issue: October 05, 1984 Revision 1: January 25, 2017 ATA System: 5363 SUBJECT: FUSELAGE - Section 46 - Structure - Cargo Deck Attachment Inspection and Modification 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 757-200 Airplanes, line numbers 1 thru 51 in 3 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 757-200 Airplanes, line numbers 6-8, 12, 15, 17-22, 26-28, 31, 35-49, 51 without no.3 cargo door. -1 757-200 Airplanes, line numbers 9-11, 13-14, 16, 23-25, 29-30, 32-34, 50 with no.3 cargo door. -2 757-200 Airplanes, line numbers 1-5 without no.3 cargo door.-3 Airplane Models: 757-200 GroupVariable Number 3NA001 - NA005 1NA006 - NA021 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 13 of 169 ### Page 14 GroupVariable Number 1NA191 - NA192 2NA201 - NA215 1NA401 - NA403 1NA501 - NA506 1NB001 - NB004 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to inspect that a modification to the aft cargo side panel attach tabs and frames; STA 1640 frame; and STA 1380 and STA 1440 intercostals, clips and angles is complete. If modification is not complete, this service bulletin gives instructions to inspect for any crack on the frames from STA 1200 to STA 1640 at the cargo floor interfaces between stringers S-26 and S-27; and to modify the attachments between the frames and the cargo floor. Accomplishment of the work in this service bulletin will make sure that the modification of the body frames at the aft cargo compartment panel attach points and intercostals are complete, to reduce the probability of cracks in the lower lobe frames and side panels. If the work given in this service bulletin is not accomplished, a frame crack at the panel attach point may go undetected and grow in length. An undetected crack could result in reduced structural integrity of the body frames at the aft cargo panel attachment points. Failure of multiple frames could lead to rapid decompression of the airplane. Fatigue testing of two 757 airframes indicates body frames in the aft cargo compartment may crack at the side panel to frame attachment. In one fatigue test airframe, numerous fractured cargo compartment side panel attach fasteners, cracked side panel attach tabs at right side STA 1380, cracked frames at left side STA 1320, 1400, 1500, 1540, 1560 and right side STA 1540 were found at 34,600 equivalent flight cycles. In the second fatigue test airframe, several fractured side panel attach fasteners and cracked frames at right side STA 1580 and 1600 were found at 62,500 equivalent flight cycles. These frame cracks originated at the side panel to frame attach fastener rivet hole and propagated from fastener hole to fastener hole through the frame inner chord, web and fail-safe chord. Cracks have already been reported in fuselage frames in the aft cargo compartment at STA 1340, 1400, 1420, 1500, 1520 and 1580 between S-26 and S-27 on the left and right sides, at the intersection with the side cargo compartment panel installation. The cracking has been attributed to fatigue at the associated frame attachment fastener hole, as a result of an unmodified or de-modified interface between the affected frame and the cargo floor. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 14 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 15 These cracks may be associated with airplanes that have had the modification removed. Widespread Fatigue Damage (WFD) analysis identified the need for the inspections and modifications of frames from STA 1320 through STA 1620. The modification as given in the original issue of this service bulletin was not mandated, and has been removed on two airplanes that were converted, and may have been removed on more. Airplane line numbers 37 - 51 should have been reworked in production but the rework may not have been accomplished or may have been de-modified. The fuselage frames from STA 1320 through STA 1620 in this service bulletin have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Boeing Fleet Team Digest (FTD) 757 FTD 53-14001 is related to this service bulletin. Boeing Service Related Problem (SRP) 757-SRP-53-0488 is related to this service bulletin. Revision 1 is sent to add a general visual inspection to verify modification status, Low Frequency Eddy Current (LFEC) inspections, and a mandatory modification that is required to comply with the Widespread Fatigue Damage (WFD) rule. This is required only in locations with no modification. The release classification of this service bulletin has been changed to Alert Service Bulletin. The data given in Notice of Status Change 757-53-0012 NSC1 is included in this revision. D. Description Do a general visual inspection to make sure that a modification has been done and remains complete. If no modification has been done, or is not complete, do a Low Frequency Eddy Current (LFEC) inspection for any crack and do the modification of the aft cargo compartment side panel to frame attachments. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If the modification has been done, and remains complete, no further inspection or modification is required. Group 1 airplanes, which have two cargo doors, have the E-6 electrical equipment rack aft of the number 2 cargo door and do not require inspection or modification of side panel attach tabs at STA 1440 right side. Group 2 airplanes, which have three cargo doors, have the E-6 rack aft of the number 3 cargo door and do not require inspection or modification on the right side, aft of STA 1520. Group 3 airplanes are similar to Group 1 airplanes, and also require inspection or modification of the side panel, stanchions, stringer clips, and intercostals from STA 1440 right side, to STA 1500 right side. Revision 1 - Effects of this Revision on airplanes on which the Original Issue was previously done: ActionConditionGroup Do a general visual inspection to make sure that the modifications are complete. All airplanes.1, 2, 3 Airplanes line numbers 37 to 49 and 51 were added to Group 1, and airplane line number 50 was added to Group 2 of this service bulletin effectivity. Airplanes line numbers 2 to 5 were removed from Group 1 and airplane line number 1 to 5 were added to new Group 3. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 15 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 16 The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones ZoneModel 153, 154, 161, 162757-200 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX A, APPENDIX B, and APPENDIX C. Do the required actions 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. Group 1: Table 1: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 24 months after the Revision 1 date of this service bulletin, whichever occurs first. Before 31,000 Total Flight Cy- cles. Do PART 3: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, AND STA 1640 - GENERAL VISUAL IN- SPECTION to make sure the modifications are complete. All Airplanes. --No further inspection or modi- fication is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1620. CONDITION 1: MODIFI- CATIONS ARE COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 16 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 17 Group 1: Table 1: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 2: MODIFI- CATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. -Before Further Flight.CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 2.1: ANY CRACK IS FOUND DURING PART 6 IN- SPECTION. 3,000 Flight Cy- cles. (a) -CONDITION 2.1 (ACTION 2): Repeat PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack at the unrepaired areas. -Before 52,000 Total Flight Cycles.CONDITION 2.1 (ACTION 3): Do PART 9: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION at ar- eas with no crack. 3,000 Flight Cy- cles. (a) -CONDITION 2.2 (ACTION 1): Repeat PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 2.2: NO CRACK IS FOUND DURING PART 6 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 2.2 (ACTION 2): Do PART 9: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 17 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 18 Group 1: Table 1: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. CONDITION 3: MODIFI- CATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1380 RIGHT SIDE. -Before Further Flight.Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TION for any crack. CONDITION 4: MODIFI- CATION IS NOT COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1380 RIGHT SIDE. -Before Further Flight.CONDITION 4.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 4.1: ANY CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 4.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. 3,000 Flight Cy- cles. (b) -CONDITION 4.2 (ACTION 1): Repeat PART 12: SIDE PAN- EL TO FRAME ATTACH- MENT AT STA 1380 RIGHT SIDE - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 4.2: NO CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 4.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachments at STA 1640. CONDITION 5: MODIFI- CATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1640. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 18 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 19 Group 1: Table 1: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 17: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 6: MODIFI- CATION IS NOT COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1640. -Before Further Flight.CONDITION 6.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 6.1: ANY CRACK IS FOUND DURING PART 17 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 6.1 (ACTION 2): Do PART 20: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION. 3,000 Flight Cy- cles. (c) -CONDITION 6.2 (ACTION 1): Repeat PART 17: SIDE PAN- EL TO FRAME ATTACH- MENT AT STA 1640 - LOW FREQUENCY EDDY CUR- RENT (LFEC) INSPECTION for any crack. CONDITION 6.2: NO CRACK IS FOUND DURING PART 17 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 6.2 (ACTION 2): Do PART 20: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION. (a) Accomplishment of PART 9 is terminating action for the inspection requirement at the modified location only. (b) Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. (c) Accomplishment of PART 20 is terminating action for the inspection requirement at the modified location only. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 19 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 20 Group 2: Table 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 24 months after the Revision 1 date of this service bulletin, whichever occurs first. Before 31,000 Total Flight Cy- cles. Do PART 4: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, STA 1380, STA 1440, AND STA 1640 - GENERAL VISUAL INSPECTION to make sure the modifications are complete. All Airplanes. --No further inspection or modi- fication is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1580. CONDITION 7: MODIFI- CATIONS ARE COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENTS FROM STA 1200 TO STA 1580, excluding frames at cargo door locations. -Before Further Flight.Do PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 8: MODIFI- CATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, excluding frames at cargo door locations. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 20 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 21 Group 2: Table 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.CONDITION 8.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 8.1: ANY CRACK IS FOUND DURING PART 7 IN- SPECTION. 3,000 Flight Cy- cles. (a) -CONDITION 8.1 (ACTION 2): Repeat PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack at the unrepaired areas. -Before 52,000 Total Flight Cycles.CONDITION 8.1 (ACTION 3): Do PART 10: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - MODIFICATION for ar- eas with no crack. 3,000 Flight Cy- cles. (a) -CONDITION 8.2 (ACTION 1): Repeat PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 8.2: NO CRACK IS FOUND DURING PART 7 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 8.2 (ACTION 2): Do PART 10: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. CONDITION 9: MODIFI- CATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1380 RIGHT SIDE. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 21 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 22 Group 2: Table 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TION for any crack. CONDITION 10: MODI- FICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. -Before Further Flight.CONDITION 10.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 10.1: ANY CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 10.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. 3,000 Flight Cy- cles. (b) -CONDITION 10.2 (ACTION 1): Repeat PART 12: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1380 RIGHT SIDE - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 10.2: NO CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 10.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1440 right side. CONDITION 11: MODI- FICATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1440 RIGHT SIDE. -Before Further Flight.Do PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TION for any crack. CONDITION 12: MODI- FICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 22 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 23 Group 2: Table 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.CONDITION 12.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 12.1: ANY CRACK IS FOUND DURING PART 14 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 12.1 (ACTION 2): Do PART 15: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - MODIFICATION. 3,000 Flight Cy- cles. (c) -CONDITION 12.2 (ACTION 1): Repeat PART 14: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1440 RIGHT SIDE - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 12.2: NO CRACK IS FOUND DURING PART 14 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 12.2 (ACTION 2): Do PART 15: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1640. CONDITION 13: MODI- FICATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1640. -Before Further Flight.Do PART 18: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 14: MODI- FICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 23 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 24 Group 2: Table 2: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.CONDITION 14.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 14.1: ANY CRACK IS FOUND DURING PART 18 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 14.1 (ACTION 2): Do PART 21: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION. 3,000 Flight Cy- cles. (d) -CONDITION 14.2 (ACTION 1): Repeat PART 18: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1640 - LOW FREQUENCY EDDY CUR- RENT (LFEC) INSPECTION for any crack. CONDITION 14.2: NO CRACK IS FOUND DURING PART 18 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 14.2 (ACTION 2): Do PART 21: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION. (a) Accomplishment of PART 10 is terminating action for the inspection requirement at the modified location only. (b) Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. (c) Accomplishment of PART 15 is terminating action for the inspection requirement at the modified location only. (d) Accomplishment of PART 21 is terminating action for the inspection requirement at the modified location only. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 24 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 25 Group 3: Table 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 24 months after the Revision 1 date of this service bulletin, whichever occurs first. Before 31,000 Total Flight Cy- cles. Do PART 5: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, FROM STA 1440 TO STA 1500, AND STA 1640 - GENERAL VISUAL IN- SPECTION to make sure the modifications are complete. All Airplanes. --No further inspection or modi- fication is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1620. CONDITION 15: MODI- FICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. -Before Further Flight.Do PART 8: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 16: MODI- FICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 25 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 26 Group 3: Table 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.CONDITION 16.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 16.1: ANY CRACK IS FOUND DURING PART 8 IN- SPECTION. 3,000 Flight Cy- cles. (a) -CONDITION 16.1 (ACTION 2): Repeat PART 8: SIDE PANEL TO FRAME ATTACH- MENTS FROM STA 1200 TO STA 1620 - DETAILED IN- SPECTION AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the unrepaired areas. -Before 52,000 Total Flight Cycles.CONDITION 16.1 (ACTION 3): Do PART 11: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION for ar- eas with no crack. 3,000 Flight Cy- cles. (a) -CONDITION 16.2 (ACTION 1): Repeat PART 8: SIDE PANEL TO FRAME ATTACH- MENTS FROM STA 1200 TO STA 1620 - DETAILED IN- SPECTION AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 16.2: NO CRACK IS FOUND DURING PART 8 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 16.2 (ACTION 2): Do PART 11: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. CONDITION 17: MODI- FICATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1380 RIGHT SIDE. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 26 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 27 Group 3: Table 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TION for any crack. CONDITION 18: MODI- FICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. -Before Further Flight.CONDITION 18.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 18.1: ANY CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 18.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. 3,000 Flight Cy- cles. (b) -CONDITION 18.2 (ACTION 1): Repeat PART 12: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1380 RIGHT SIDE - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 18.2: NO CRACK IS FOUND DURING PART 12 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 18.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel, stanchions, and inter- costals from STA 1440 right side, to STA 1500 right side. CONDITION 19: MODI- FICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 27 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 28 Group 3: Table 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TION for any crack. CONDITION 20: MODI- FICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE. -Before Further Flight.CONDITION 20.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 20.1: ANY CRACK IS FOUND DURING PART 14 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 20.1 (ACTION 2): Do PART 16: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE - MODIFICATION. 3,000 Flight Cy- cles. (c) -CONDITION 20.2 (ACTION 1): Repeat PART 14: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1440 RIGHT SIDE - DETAILED INSPEC- TION AND LOW FREQUEN- CY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 20.2: NO CRACK IS FOUND DURING PART 14 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 20.2 (ACTION 2): Do PART 16: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE - MODIFICATION. --No further inspection or modi- fication is necessary at the modified location only for side panel to frame attachment at STA 1640. CONDITION 21: MODI- FICATION IS COM- PLETE ON SIDE PAN- EL TO FRAME AT- TACHMENT AT STA 1640. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 28 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 29 Group 3: Table 3: INSPECTION AND MODIFICATION OF AFT CARGO SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1640 Repeat Interval (Not to Exceed) Compliance Time (Whichever Oc- curs Later) ActionCondition -Before Further Flight.Do PART 19: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. CONDITION 22: MODI- FICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. -Before Further Flight.CONDITION 22.1 (ACTION 1): Contact The Boeing Com- pany for repair instructions and do the repair. CONDITION 22.1: ANY CRACK IS FOUND DURING PART 19 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 22.1 (ACTION 2): Do PART 22: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION. 3,000 Flight Cy- cles. (d) -CONDITION 22.2 (ACTION 1): Repeat PART 19: SIDE PANEL TO FRAME ATTACH- MENT AT STA 1640 - LOW FREQUENCY EDDY CUR- RENT (LFEC) INSPECTION for any crack. CONDITION 22.2: NO CRACK IS FOUND DURING PART 19 IN- SPECTION. -Before 52,000 Total Flight Cycles.CONDITION 22.2 (ACTION 2): Do PART 22: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICA- TION (a) Accomplishment of PART 11 is terminating action for the inspection requirement at the modified location only. (b) Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. (c) Accomplishment of PART 16 is terminating action for the inspection requirement at the modified location only. (d) Accomplishment of PART 22 is terminating action for the inspection requirement at the modified location only. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 29 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 30 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. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection and modification 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 Group 1: Elapsed HoursTask HoursNumber of PersonsTask 3.003.001Open Access 3.703.701FIGURE 1 4.504.501FIGURE 3 3.753.751FIGURE 4 2.302.301FIGURE 5 4.904.901FIGURE 6 3.156.302FIGURE 7 3.156.302FIGURE 8 0.900.901FIGURE 9 0.700.701FIGURE 15 0.650.651FIGURE 17 3.003.001Close Access 33.7040.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 30 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 31 Group 2: Elapsed HoursTask HoursNumber of PersonsTask 3.003.001Open Access 3.753.751FIGURE 4 2.302.301FIGURE 5 3.156.302FIGURE 7 3.156.302FIGURE 8 0.850.851FIGURE 10 3.753.751FIGURE 11 3.153.151FIGURE 12 2.252.251FIGURE 13 3.803.801FIGURE 14 0.700.701FIGURE 15 0.850.851FIGURE 16 0.600.601FIGURE 18 3.003.001Close Access 34.3040.60TOTAL FOR EACH AIRPLANE Group 3: Elapsed HoursTask HoursNumber of PersonsTask 3.003.001Open Access 3.703.701FIGURE 1 4.504.501FIGURE 3 3.753.751FIGURE 4 2.302.301FIGURE 5 4.904.901FIGURE 6 3.156.302FIGURE 7 3.156.302FIGURE 8 0.700.701FIGURE 15 0.850.851FIGURE 16 0.650.651FIGURE 17 1.001.001FIGURE 19 2.002.001FIGURE 20 3.003.001Close Access Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 31 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 32 Group 3: Elapsed HoursTask HoursNumber of PersonsTask 36.6542.95TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR 53068-R b. Boeing Service Related Problem (SRP) 757-SRP-53-0488 c. Service Bulletin Index D624N001 d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-44-01, 20-50-01, 20-50-19, 20-50-20 e. 757 Aircraft Maintenance Manual (AMM) 25-50-02, 25-50-03 f. 757 Fleet Team Digest (FTD) 53-14001 g. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-04, Part 6, 51-00-11, Part 6, 51-00-16, Part 6, 51-00-23 h. 757-200 Structural Repair Manual (SRM) 51-10-01, 51-40-02, 51-40-05, 51-40-06, 51-40-08 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number SUPT INSTL - DECK, STA 1200 TO 1690 AFT CARGO COMP (REWORK DWG) 146N1072 SUPT INSTL - DECK, STA 1200 TO 1640, AFT CARGO COMPT146N5390 SIDE PANEL ASSY - FWD DECK, AFT CARGO COMPT146N5391 SUPT INSTL - DECK, STA 1200 TO 1640, AFT CARGO COMPT REWORK 146N5459 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 32 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 33 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: None. 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 but no new DTIs are necessary. 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: October 05, 1984 757-53A0012Revision 1: January 25, 2017 33 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 34 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 34 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT BLANK PAGE ### Page 35 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) NameKit Number --Kit Instl. - Deck Supt. STA 1200 to 1640 Aft Cargo Comp (Top Kit) (a) 012N8361-1 --Kit Instl. - Deck Supt. STA 1200 to 1640 Aft Cargo Comp (Top Kit) (b) 012N8361-2 --Side Panel Assy (c)146N5391-29 --Stringer Clip (c)140N2005-42 Stringer Clip (c)140N2001-32 (a) Applicable to Group 2 airplanes. (b) Applicable to Group 1 and Group 3 airplanes. (c) Applicable to Group 3 airplanes. Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. B. Industry Support Information This service bulletin was first released before October of 1994. Thus industry support for affected airplanes depends upon whether the operator previously filed a warranty claim with Boeing on this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 35 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 36 NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. Kit 012N8361 NotesExisting Part Number NameQTYNew Part Number -4-3-2-1 --Top Kit - Deck Supt. - STA 1200 to STA 1640 Aft Cargo Comp 012N8361 (a)-Top Kit----012N8361-1 (b)-Top Kit----012N8361-2 (a)-Collector Kit---1012N8361-3 (b)-Collector Kit--1-012N8361-4 --Supt. Instl.-1--146N1072-1 --Supt. Instl.1---146N1072-2 --Splice11--146N5391-13 --Splice11--146N5391-15 --Splice11--146N5391-16 --Splice11--146N5431-11 --Splice11--146N5431-12 --Rivet Package44--65-9220-78 --Rivet Package11--65-9220-79 --Hi-Lok, 1/64 O.S.1010--BACB30MY6K4X --Hi-Lok, 1/32 O.S.55--BACB30MY6K4Y --Hi-Lok, 1/64 O.S.1010--BACB30MY6K5X --Hi-Lok, 1/32 O.S.55--BACB30MY6K5Y --Hi-Lok, 1/64 O.S.1515--BACB30NW6K4X --Hi-Lok, 1/32 O.S.55--BACB30NW6K4Y --Collar, 1/64 O.S.3535--BACC30M6 --Collar, 1/32 O.S.1515--BACC30R6 --Rivet22--BACR15CE6D6 --Rivet22--BACR15CE6D7 --Rivet11--BACR15DS7D6 --Rivet11--BACR15DS7D7 --Rivet6060--BACR15FT6AD4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 36 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 37 Kit 012N8361 NotesExisting Part Number NameQTYNew Part Number -4-3-2-1 --Rivet22--BACR15FT6AD5 --Rivet22--BACR15FT6AD7 --Rivet1212--BACR15FT6D7 --Rivet3030--BACR15FT7AD4 --Rivet11--BACR15FT7AD5 --Rivet11--BACR15FT7AD7 --Rivet66--BACR15FT7D7 --Rivet22--BACR15FT8AD6 --Rivet22--BACR15FT8AD8 --Rivet22--BACR15FT8D10 --Rivet22--BACR15FT8D9 --Rivet11--BACR15FT9AD6 --Rivet11--BACR15FT9AD8 --Rivet11--BACR15FT9D10 --Rivet11--BACR15FT9D9 --Rivet1111--BACR15FT5D6 --Rivet44--BACR15FT5AD6 --Rivet1010--BACR15FT5AD7 --Rivet88--BACR15BA5AD5 (a) Applicable to Group 2 airplanes. (b) Applicable to Group 1 and Group 3 airplanes. Kit 146N1072 NotesExisting Part Number NameQTYNew Part Number -2-1 --SUPPORT INSTAL- LATION 146N1072 --Supt. Instl.--146N1072-1 --Supt. Instl.--146N1072-2 --Angle11146N1072-3 --Angle11146N1072-4 --Seal11146N1072-6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 37 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 38 Kit 146N1072 NotesExisting Part Number NameQTYNew Part Number -2-1 --Angle-1146N1072-21 --Angle-1146N1072-22 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. NotesNameQTYPart Number / Specifica- tion -PrimerAs RequiredBMS 10-11, Type I -EnamelAs RequiredBMS 10-11, Type II -SealantAs RequiredBMS 5-95 -Teflon / Urethane CoatingAs RequiredBMS 10-86 (a)Chemical Conversion Coating As RequiredAlodine or equivalent Type 2, CLASS A (a) Refer to SOPM 20-43-03 for a list of suppliers and alternates. 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: October 05, 1984 757-53A0012Revision 1: January 25, 2017 38 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 39 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 757 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 757 Aircraft Maintenance Manual (AMM). 4. Fastener installation must meet or exceed the minimum edge margin requirements in accordance with 757-200 SRM 51-40-06. 5. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 6. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 7. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 39 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 40 8. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 9. 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. 10. Refer to APPENDIX A, APPENDIX B, and APPENDIX C 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. 11. 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. 12. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 13. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 14. 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. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. Some steps in the Work Instructions are labelled as Required for Compliance (RC). If this service bulletin in mandated by an Airworthiness Directive (AD), then the steps labelled 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. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 40 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 41 and identified figures. Steps not labelled 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 1. Open the aft cargo door to get access to the aft cargo compartment. 2. Do PART 1: AFT CARGO COMPARTMENT SIDEWALL LINING REMOVAL. 3. Do PART 2: AFT CARGO COMPARTMENT AFT BULKHEAD LINING REMOVAL. 4. Group 1: RC - Do PART 3: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, AND STA 1640 - GENERAL VISUAL INSPECTION to make sure the modifications are complete. NOTE: Multiple conditions can apply depending on inspection findings. a. CONDITION 1: MODIFICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. (1) No further inspection or modification is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1620. b. CONDITION 2: MODIFICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. (1) Do PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 2.1: ANY CRACK IS FOUND DURING PART 6 INSPECTION. 1) CONDITION 2.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 2.1 (ACTION 2): Repeat PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the unrepaired areas at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 9 is terminating action for the inspection requirement at the modified location only. 3) CONDITION 2.1 (ACTION 3): Do PART 9: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. (b) CONDITION 2.2: NO CRACK IS FOUND DURING PART 6 INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 41 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 42 1) CONDITION 2.2 (ACTION 1): Repeat PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 9 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 2.2 (ACTION 2): Do PART 9: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. c. CONDITION 3: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. d. CONDITION 4: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 4.1: ANY CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 4.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 4.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. (b) CONDITION 4.2: NO CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 4.2 (ACTION 1): Repeat PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 4.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. e. CONDITION 5: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachments at STA 1640. f. CONDITION 6: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 42 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 43 (1) Do PART 17: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 6.1: ANY CRACK IS FOUND DURING PART 17 INSPECTION. 1) CONDITION 6.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 6.1 (ACTION 2): Do PART 20: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION. (b) CONDITION 6.2: NO CRACK IS FOUND DURING PART 17 INSPECTION. 1) CONDITION 6.2 (ACTION 1): Repeat PART 17: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 20 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 6.2 (ACTION 2): Do PART 20: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION. 5. Group 2: RC - Do PART 4: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, STA 1380, STA 1440, AND STA 1640 - GENERAL VISUAL INSPECTION to make sure the modifications are complete. NOTE: Multiple conditions can apply depending on inspection findings. a. CONDITION 7: MODIFICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, excluding frames at cargo door locations. (1) No further inspection or modification is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1580. b. CONDITION 8: MODIFICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, excluding frames at cargo door locations. (1) Do PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 8.1: ANY CRACK IS FOUND DURING PART 7 INSPECTION. 1) CONDITION 8.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 8.1 (ACTION 2): Repeat PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the 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: October 05, 1984 757-53A0012Revision 1: January 25, 2017 43 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 44 NOTE: Accomplishment of PART 10 is terminating action for the inspection requirement at the modified location only. 3) CONDITION 8.1 (ACTION 3): Do PART 10: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - MODIFICATION. (b) CONDITION 8.2: NO CRACK IS FOUND DURING PART 7 INSPECTION. 1) CONDITION 8.2 (ACTION 1): Repeat PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 10 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 8.2 (ACTION 2): Do PART 10: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - MODIFICATION. c. CONDITION 9: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. d. CONDITION 10: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 10.1: ANY CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 10.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 10.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. (b) CONDITION 10.2: NO CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 10.2 (ACTION 1): Repeat PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 10.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 44 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 45 e. CONDITION 11: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachment at STA 1440 right side. f. CONDITION 12: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE. (1) Do PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 12.1: ANY CRACK IS FOUND DURING PART 14 INSPECTION. 1) CONDITION 12.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 12.1 (ACTION 2): Do PART 15: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - MODIFICATION. (b) CONDITION 12.2: NO CRACK IS FOUND DURING PART 14 INSPECTION. 1) CONDITION 12.2 (ACTION 1): Repeat PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 15 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 12.2 (ACTION 2): Do PART 15: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - MODIFICATION. g. CONDITION 13: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachments at STA 1640. h. CONDITION 14: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. (1) Do PART 18: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 14.1: ANY CRACK IS FOUND DURING PART 18 INSPECTION. 1) CONDITION 14.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 14.1 (ACTION 2): Do PART 21: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 45 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 46 (b) CONDITION 14.2: NO CRACK IS FOUND DURING PART 18 INSPECTION. 1) CONDITION 14.2 (ACTION 1): Repeat PART 18: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 21 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 14.2 (ACTION 2): Do PART 21: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION 6. Group 3: RC - Do PART 5: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, FROM STA 1440 TO STA 1500, AND STA 1640 - GENERAL VISUAL INSPECTION to make sure the modifications are complete. NOTE: Multiple conditions can apply depending on inspection findings. a. CONDITION 15: MODIFICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. (1) No further inspection or modification is necessary at any location found with complete modification for side panel to frame attachments from STA 1200 to STA 1620. b. CONDITION 16: MODIFICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, excluding frames at cargo door locations. (1) Do PART 8: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 16.1: ANY CRACK IS FOUND DURING PART 8 INSPECTION. 1) CONDITION 16.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 16.1 (ACTION 2): Repeat PART 8: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the unrepaired areas at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 11 is terminating action for the inspection requirement at the modified location only. 3) CONDITION 16.1 (ACTION 3): Do PART 11: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. (b) CONDITION 16.2: NO CRACK IS FOUND DURING PART 8 INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 46 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 47 1) CONDITION 16.2 (ACTION 1): Repeat PART 8: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 11 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 16.2 (ACTION 2): Do PART 11: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION. c. CONDITION 17: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachment at STA 1380 right side. d. CONDITION 18: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE. (1) Do PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 18.1: ANY CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 18.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 18.1 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. (b) CONDITION 18.2: NO CRACK IS FOUND DURING PART 12 INSPECTION. 1) CONDITION 18.2 (ACTION 1): Repeat PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 13 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 18.2 (ACTION 2): Do PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION. e. CONDITION 19: MODIFICATIONS ARE COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE. (1) No further inspection or modification is necessary at the modified location only for side panel, stanchions, and intercostals from STA 1440 right side, to STA 1500 right side. f. CONDITION 20: MODIFICATIONS ARE NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE TO STA 1500 RIGHT SIDE. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 47 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 48 (1) Do PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 20.1: ANY CRACK IS FOUND DURING PART 14 INSPECTION. 1) CONDITION 20.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 20.1 (ACTION 2): Do PART 16: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE - MODIFICATION. (b) CONDITION 20.2: NO CRACK IS FOUND DURING PART 14 INSPECTION. 1) CONDITION 20.2 (ACTION 1): Repeat PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack at the times specified in Paragraph 1.E., Compliance. NOTE: Accomplishment of PART 16 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 20.2 (ACTION 2): Do PART 16: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE - MODIFICATION. g. CONDITION 21: MODIFICATION IS COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. (1) No further inspection or modification is necessary at the modified location only for side panel to frame attachments at STA 1640. h. CONDITION 22: MODIFICATION IS NOT COMPLETE ON SIDE PANEL TO FRAME ATTACHMENT AT STA 1640. (1) Do PART 19: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack. (a) CONDITION 22.1: ANY CRACK IS FOUND DURING PART 19 INSPECTION. 1) CONDITION 22.1 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) CONDITION 22.1 (ACTION 2): Do PART 22: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION. (b) CONDITION 22.2: NO CRACK IS FOUND DURING PART 19 INSPECTION. 1) CONDITION 22.2 (ACTION 1): Repeat PART 19: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION for any crack 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: October 05, 1984 757-53A0012Revision 1: January 25, 2017 48 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 49 NOTE: Accomplishment of PART 22 is terminating action for the inspection requirement at the modified location only. 2) CONDITION 22.2 (ACTION 2): Do PART 22: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION 7. Do PART 23: AFT CARGO COMPARTMENT AFT BULKHEAD LINING INSTALLATION. 8. Do PART 24: AFT CARGO COMPARTMENT SIDEWALL LINING INSTALLATION. 9. Put the airplane back to a serviceable condition. PART 1: AFT CARGO COMPARTMENT SIDEWALL LINING REMOVAL 1. Remove and keep the left and right side aft cargo compartment sidewall lining from STA 1200 to STA 1640. Refer to 757 AMM 25-50-02 as an accepted procedure. 2. For additional access to facilitate modification: a. Remove and keep splice in accordance with FIGURE 7. b. Remove and keep fasteners from cargo tiedown fittings in accordance with FIGURE 7. PART 2: AFT CARGO COMPARTMENT AFT BULKHEAD LINING REMOVAL 1. Remove and keep the aft cargo compartment aft bulkhead lining. Refer to 757 AMM 25-50-03 as an accepted procedure. Group 1: PART 3: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, AND STA 1640 - GENERAL VISUAL INSPECTION 1. Do a General Visual Inspection from STA 1200 to STA 1620 on the left and right side, STA 1380 on the right side, and STA 1640 on the left and right side, to make sure that the modifications are complete, in accordance with FIGURE 9. Group 2: PART 4: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580, STA 1380, STA 1440, AND STA 1640 - GENERAL VISUAL INSPECTION 1. Do a General Visual Inspection from STA 1200 to STA 1580 on the left and right side, STA 1380 and STA 1440 on the right side, and STA 1640 on the left side, to make sure that the modifications are complete, in accordance with FIGURE 10. Group 3: PART 5: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620, STA 1380, FROM STA 1440 TO STA 1500, AND STA 1640 - GENERAL VISUAL INSPECTION 1. Do a General Visual Inspection from STA 1200 to STA 1620 on the left and right side, STA 1380 on the right side, from STA 1440 to STA 1500 on the right side, and STA 1640 on the left and right side, to make sure that the modifications are complete, in accordance with FIGURE 19. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 49 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 50 Group 1: PART 6: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do a Detailed Inspection and Low Frequency Eddy Current (LFEC) inspection at each side panel to frame attachment from STA 1200 to STA 1620 on the left and right side of the airplane for any crack in accordance with FIGURE 1. Group 2: PART 7: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do a Detailed Inspection and Low Frequency Eddy Current (LFEC) inspection at each side panel to frame attachment from STA 1200 to STA 1580 on the left and right side of the airplane for any crack in accordance with FIGURE 12. Group 3: PART 8: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do a Detailed Inspection and Low Frequency Eddy Current (LFEC) inspection at each side panel to frame attachment from STA 1200 to STA 1620 on the left and right side of the airplane for any crack in accordance with FIGURE 1. Group 1: PART 9: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION 1. Do side panel to frame attachments modification from STA 1200 to STA 1300 in accordance with FIGURE 5, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. 2. Do side panel to frame attachments modification from STA 1320 to STA 1620 in accordance with FIGURE 6, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. Group 2: PART 10: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1580 - MODIFICATION 1. Do side panel to frame attachments modification from STA 1200 to STA 1300 in accordance with FIGURE 5, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. 2. Do side panel to frame attachments modification from STA 1320 to STA 1580 in accordance with FIGURE 14, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. Group 3: PART 11: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1200 TO STA 1620 - MODIFICATION 1. Do side panel to frame attachments modification from STA 1200 to STA 1300 in accordance with FIGURE 5, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, 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: October 05, 1984 757-53A0012Revision 1: January 25, 2017 50 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 51 2. Do side panel to frame attachments modification from STA 1320 to STA 1620 in accordance with FIGURE 6, including doing an open hole HFEC inspection of the frame for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. PART 12: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do a Detailed Inspection of the side panel attach tabs for any crack, in accordance with FIGURE 15. 2. Do Low Frequency Eddy Current (LFEC) inspection of the frame inner chord at the fastener holes for any crack at STA 1380, in accordance with FIGURE 15. PART 13: SIDE PANEL TO FRAME ATTACHMENT AT STA 1380 RIGHT SIDE - MODIFICATION 1. Do the following steps in accordance with FIGURE 4. a. Trim off existing side panel attach tabs. b. Do open hole High Frequency Eddy Current (HFEC) inspection of the frame inner chord for any crack at STA 1380. (1) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (2) If no crack is found, continue to the side panel, frame, and intercostal modification at STA 1380. Group 2-3: PART 14: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do a Detailed Inspection of the side panel attach tabs for any crack, in accordance with FIGURE 16. 2. Do Low Frequency Eddy Current (LFEC) inspection of the frame inner chord at the fastener holes for any crack, in accordance with FIGURE 16. Group 2: PART 15: SIDE PANEL TO FRAME ATTACHMENT AT STA 1440 RIGHT SIDE - MODIFICATION 1. Do the following steps in accordance with FIGURE 11. a. Trim off existing side panel attach tabs. b. Do open hole High Frequency Eddy Current (HFEC) inspection of the frame inner chord for any crack at STA 1440. (1) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (2) If no crack is found, do the modification at STA 1440. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 51 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 52 Group 3: PART 16: SIDE PANEL TO FRAME ATTACHMENTS FROM STA 1440 RIGHT SIDE, TO STA 1500 RIGHT SIDE - MODIFICATION 1. Do the following steps in accordance with FIGURE 20. a. Remove the existing side panel, stanchions, stringer clips, and intercostals from STA 1440 to STA 1500. b. Install new side panel and replacement stringer clips. Group 1: PART 17: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do Low Frequency Eddy Current (LFEC) inspection through the side panel and support angle of the frame inner chord at STA 1640 for any crack in accordance with FIGURE 17. Group 2: PART 18: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do Low Frequency Eddy Current (LFEC) inspection through the side panel and support angle of the frame inner chord at STA 1640 for any crack in accordance with FIGURE 18. Group 3: PART 19: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION 1. Do Low Frequency Eddy Current (LFEC) inspection through the side panel and support angle of the frame inner chord at STA 1640 for any crack in accordance with FIGURE 17. Group 1: PART 20: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION 1. Do the following steps in accordance with FIGURE 3. a. Do open hole High Frequency Eddy Current (HFEC) inspection of the frame for any crack at STA 1640. (1) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (2) If no crack is found, do the modification at STA 1640. Group 2: PART 21: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION 1. Do the following steps in accordance with FIGURE 13. a. Do open hole High Frequency Eddy Current (HFEC) inspection of the frame for any crack at STA 1640. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 52 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 53 (1) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (2) If no crack is found, do the modification at STA 1640. Group 3: PART 22: SIDE PANEL TO FRAME ATTACHMENT AT STA 1640 - MODIFICATION 1. Do the following steps in accordance with FIGURE 3. a. Do open hole High Frequency Eddy Current (HFEC) inspection of the frame for any crack at STA 1640. (1) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (2) If no crack is found, do the modification at STA 1640. PART 23: AFT CARGO COMPARTMENT AFT BULKHEAD LINING INSTALLATION 1. Install kept aft cargo compartment aft bulkhead lining. Refer to 757 AMM 25-50-03 as an accepted procedure. PART 24: AFT CARGO COMPARTMENT SIDEWALL LINING INSTALLATION 1. If removed, install kept splice in accordance with FIGURE 8. 2. If removed, install kept cargo tiedown fasteners in accordance with FIGURE 8. 3. Install kept left and right side aft cargo compartment sidewall lining if removed to get access for inspection and modification. Refer to 757 AMM 25-50-02 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1: January 25, 2017 53 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 54 (OCR) BOEING SERVICE BULLETIN 757-53A0012 ALERT ALERT This Figure applies only to: Group 1, 3. NO. 2 CARGO DOOR STA 1300 CAP STA 1380 SIDE PANEL INC OR CARGO DOOR AFT CARGO COMPARTMENT 2445380 (RIGHT SIDE SHOWN, LEFT SIDE SIMILAR) FIGURE 1: DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF FRAME INNER CHORD FROM STA 1200 TO STA 1620 (SHEET 1 OF 2) Original Issue: October 05, 1984 Revision 1 January 25, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 757-53A0012 Work - See page 1 for details. 54 of 169 ### Page 55 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More DataQtyIdentificationNameTaskStep (a)40STA 1200 - 1620Side Panel and Fasten- er Head Inspect1 (b)40STA 1200 - 1620FrameInspect2 (a) Do a Detailed Inspection of each fastener head and side panel located at each side panel to frame attach- ment from STA 1200 to STA 1620 on the left and right side of the airplane, excluding frames from STA 1380 through STA 1440 on the right side of the airplane, for any crack. (b) Do Low Frequency Eddy Current (LFEC) inspection through the side panel with fastener in place, of the frame inner chord located at each side panel to frame attachment from STA 1200 to STA 1620 on the left and right side of the airplane, excluding frames from STA 1380 through STA 1440 on the right side of the airplane, for any crack. Do this LFEC inspection, in accordance with 757 NDT Manual Part 6, 51- 00-23. FIGURE 1: DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF FRAME INNER CHORD FROM STA 1200 TO STA 1620 (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1 January 25, 2017 55 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 56 FIGURE 2: THIS FIGURE IS DELETED (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1 January 25, 2017 56 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 57 (OCR) BOEING SERVICE BULLETIN 757-53A0012 ALERT ALERT This Figure applies only to: Group 1, 3. STA STA 1640 1640 000000000000 AFT WALL 4(5 CARGO DECK SUPPORT ANGLE 2 9 _FRAME INED SIDE PANEL AFT WALL NOT SHOWN 2482052 FIGURE 3: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME (SHEET 1 OF 5) Original Issue: October 05, 1984 Revision 1 January 25, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 757-53A0012 Work - See page 1 for details. 57 of 169 ### Page 58 FIGURE 3: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1 January 25, 2017 58 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 59 FIGURE 3: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1 January 25, 2017 59 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT ### Page 60 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More DataQtyIdentificationNameTaskStep (a)22-RivetRemove1 (c)22-FrameInspect ---Support AngleRemove / Keep2 (b)--RivetDrill3 (c)--FrameInspect4 (d) (e)--HoleDrill5 (f)-BACR15FT6AD4RivetInstall (New)6 (g)-TYPE 2, CLASS AChemical Conversion Coating Apply7 (h)-BMS 10-11, TYPE IEpoxy PrimerApply8 (i) (j)--Support AngleInstall (Kept)9 FIGURE 3: SIDE PANEL AND FRAME MODIFICATION AT STA 1640 FRAME (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 1984 757-53A0012Revision 1 January 25, 2017 60 of 169 BOEING SERVICE BULLETIN 757-53A0012 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/757-53a0012/file/1ffbfd140f0f.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. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.