# Boeing Alert Service Bulletin 737-53A1217: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2023-1041; AD 2024-01-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-53A1217](https://openairdocs.org/service-documents/boeing/737-53a1217.md) - Title as filed: 737-53A1217 R1 - Boeing - Pages: 150 - PDF: https://openairdocs.org/files/sha256/18/d2/18d2e165380706c1cc45d8cb1f7ccd3b9cecfe1f6f0f708c494e540b932f35bc - Page: https://openairdocs.org/service-documents/boeing/737-53a1217/file/18d2e1653807 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1217 Original Issue: August 09, 2001 Revision 1: September 08, 2022 ATA System: 5300 SUBJECT: FUSELAGE - Section 43 and Section 47 - Stringer 17 Skin Cracks at STA 360-380 and STA 888-907 EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations (EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per Supp.1 to Part 740 of the EAR. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2001 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 Unpublished Work.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: August 09, 2001 737-53A1217Revision 1: September 08, 2022 1 of 150 5.0 ### Page 2 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 2 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 S u m m a r y ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 1 A . E f f e c t i v i t y ............................................... 1 1 1. Airplanes ............................................ 1 1 2 . S p a r e s A f f e c t e d ........................................ 1 3 B. Concurrent Requirements ...................................... 1 3 C. Reason ................................................ 1 3 D. Description .............................................. 1 4 E. Compliance .............................................. 1 5 F . A p p r o v a l ............................................... 2 1 G. Manpower .............................................. 2 2 H. Weight and Balance Changes .................................... 2 5 I. Electrical Load Data ......................................... 2 6 J . R e f e r e n c e s .............................................. 2 6 1. Existing Data: ......................................... 2 6 2. Data Supplied with this Service Bulletin: ........................... 2 6 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 6 K. Publications Affected ........................................ 2 7 L. Interchangeability and Intermixability of Parts ........................... 2 7 M. Software Accomplishment Summary ................................ 2 7 2. MATERIAL INFORMATION ........................................ 2 9 A. Material - Price and Availability ................................... 2 9 B. Industry Support Information .................................... 2 9 C. Parts Necessary for Each Airplane ................................. 2 9 1 . K i t s / P a r t s ............................................ 2 9 2. Parts and Materials Supplied by the Operator ........................ 2 9 3. Parts Modified and Reidentified ................................ 3 0 4. Parts Removed and Not Replaced .............................. 3 0 D. Parts Necessary to Change Spares ................................. 3 0 E. Special Tooling - Price and Availability ............................... 3 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 0 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1 A. GENERAL INFORMATION ..................................... 3 1 B. WORK INSTRUCTIONS ....................................... 3 3 F I G U R E 1 : D E L E T E D A T R E V I S I O N 1.................................. 4 4 FIGURE 2: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 1 AND ZONE 2 [Group 1, Configuration 1-2; Group 3, Configuration 1-2] ....................... 4 5 FIGURE 3: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 3 AND ZONE 4 [Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2] ....... 4 8 FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 [Group 1, Configuration 1-2; Group 3, Configuration 1-2] ....................................... 5 1 FIGURE 5: TERMINATING ACTION AT ZONE 3 AND ZONE 4 [Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2] ........................ 5 8 FIGURE 6: SKIN REPAIR AT ZONE 1 [Group 1, Configuration 1-2; Group 3, Configuration 1-2] . . . 65 FIGURE 7: SKIN REPAIR AT ZONE 2 [Group 1, Configuration 1-2] ................... 7 4 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 3 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 4 FIGURE 8: SKIN REPAIR AT ZONE 3 [Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2] ....................................... 8 3 FIGURE 9: SKIN REPAIR AT ZONE 4 [Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2] ....................................... 9 2 FIGURE 10: SKIN REPAIR AT ZONE 2 [Group 3, Configuration 1-2] .................. 1 0 1 FIGURE 11: POST REPAIR INSPECTION (EXTERNAL) AT ZONE 1 [Group 1, 3, Configuration 3] . . 110 FIGURE 12: POST REPAIR INSPECTION (INTERNAL) AT ZONE 1 [Group 1, 3, Configuration 3] . . 113 FIGURE 13: POST REPAIR INSPECTION (EXTERNAL) AT ZONE 2 [Group 1, Configuration 3] . . . 115 FIGURE 14: POST REPAIR INSPECTION (EXTERNAL) AT ZONE 2 [Group 3, Configuration 3] . . . 118 FIGURE 15: POST REPAIR INSPECTION (INTERNAL) AT ZONE 2 [Group 1, 3, Configuration 3] . . 121 FIGURE 16: POST REPAIR INSPECTION (EXTERNAL) AT ZONE 3 [Group 1-3, Configuration 3] . . 123 FIGURE 17: POST REPAIR INSPECTION (INTERNAL) AT ZONE 3 [Group 1-3, Configuration 3] . . 126 FIGURE 18: POST REPAIR INSPECTION (EXTERNAL) AT ZONE 4 [Group 1-3, Configuration 3] . . 128 FIGURE 19: POST REPAIR INSPECTION (INTERNAL) AT ZONE 4 [Group 1-3, Configuration 3] . . 131 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 . 133 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION ZONE 3 AND ZONE 4 .............. 1 3 7 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: POST REPAIR INSPECTIONS AT ZONE 1 ................................. 1 3 9 APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4: POST REPAIR INSPECTIONS AT ZONE 2 ................................. 1 4 2 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 5: POST REPAIR INSPECTIONS AT ZONE 3 ................................. 1 4 5 APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 6: POST REPAIR INSPECTIONS AT ZONE 4 ................................. 1 4 8 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 4 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 5 Commercial Airplanes 737 Service Bulletin ALERT Revision Transmittal SheetNumber: 737-53A1217Original Issue: August 09, 2001 Revision 1: September 08, 2022 ATA System: 5300 SUBJECT: FUSELAGE - Section 43 and Section 47 - Stringer 17 Skin Cracks at STA 360-380 and STA 888-907 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 the initial High Frequency Eddy Cur- rent (HFEC) inspections at all locations. Airplanes that have not accomplished this service bulletin. Group 1-3, Configuration 1 Repeat the HFEC inspections at all un- repaired locations. Airplanes that have not done the termi- nating action. Group 1-3, Configuration 2 Do the post repair inspections at each of the repair locations. Airplanes that have installed a repair.Group 1-3, Configuration 3 No further action required at that loca- tion. Airplanes that have done the terminating action. Group 1-3, Configuration 4 Airplane variable numbers YE001-YE010 and YE101-YE104 were moved from Group 1 to new Group 3 of this service bulletin effectivity. REASON FOR REVISION This revision is sent to move airplanes from Group 1 to new Group 3, add new internal and external post repair inspections of the repair doubler, add new inspections for skin repair and add new repair figures for Group 3 airplanes. Post repair inspections are required by Part 26 compliance (Damage Tolerance Evaluation (DTE) and Damage Tolerance Inspections (DTI) ) for the repairs given in this service bulletin. This revision also updates the status of this service bulletin to ALERT. Boeing has determined the unsafe condition identified in this service bulletin to be airplane safety. These sections were changed: Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 5 of 150 ### Page 6 1. In Paragraph 1.A., Effectivity, added service bulletin index information and applicable line number information. Added new Group configuration table information. 2. In Paragraph 1.C., Reason, updated reason statement. Added reason for revision statement. 3. In Paragraph 1.D., Description: Added instructions for new post repair inspections and new affected maintenance zones. 4. In Paragraph 1.J.1., Existing Data, reference to PRR, Boeing SRP, Boeing Service Bulletin, Service Bulletin Index, Standard Overhaul Practices Manual (SOPM), Non-Destructive Testing (NDT) Manual, Aircraft Maintenance Manual (AMM), Structural Repair Manual (SRM) and Fleet Team Digest (FTD) are added. 5. In Paragraph 1.K.2., Publications Affected, Damage Tolerance Based Structural Inspections, new statements added. 6. In Paragraph 1.E., Compliance, updated compliance statement of work. 7. In Paragraph 3.A., General Information, added new general notes. 8. In Paragraph 3.B., Work Instructions, update work instructions format and high level work instructions to add post repair inspections. 9. Revised Figures, Appendix in accordance with procedure. 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 August 09, 2001Original Issue: September 08, 2022Revision 1: Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 6 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 7 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1217Original Issue: August 09, 2001 Revision 1: September 08, 2022 ATA System: 5300 SUBJECT: FUSELAGE - Section 43 and Section 47 - Stringer 17 Skin Cracks at STA 360-380 and STA 888-907 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 Accomplishment of the inspection shown in this service bulletin will make sure that skin cracks at the double row of fasteners centered on Stringers S-17L and S-17R, at station (STA) 360 to STA 380 and at STA 888 to STA 907 are found and repaired. If this service bulletin is not done, continued operation with an undetected crack could result in possible rapid decompression and loss of structural integrity. In production, a structural preload was created in the body skin during the installation of S-17. Analysis by Boeing shows that this preload, combined with pressure cycles, can cause cracks in the skin prior to reaching the Design Service Objective (DSO). Engineering evaluation has shown that airplanes with this condition meet all FAA and JAA static strength requirements and are structurally satisfactory. Analysis indicates that the DSO may not be reached unless the preload condition is repaired. Several airplanes have had inspections and/or repairs accomplished at STA 360 to STA 380. However, some of these airplanes still require an inspection to be accomplished at STA 888 to STA 907. Accomplishment of the terminating action shown in this service bulletin will ensure that cracks do not initiate. Cracks will result in unscheduled time out of service to accomplish repairs. For 737-600, 737-700, and 737-800 airplanes after Line Number 269 the sequence of assembly was changed to eliminate the preload. Service bulletin 737-53A1217 R01 supersedes the damage tolerance inspection data given in service bulletin 737-00-1007 for service bulletin 737-53-1217 R0 Figures 6, 8 and 9. Service bulletin 737-53A1217 R01 also adds post repair inspections for existing Figure 7. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 7 of 150 ### Page 8 Boeing Service Related Problem (SRP) 737NG-SRP-53-0598 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737NG FTD 53-19001 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications 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/PartsNoKits/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 39800-018RS) Do a detailed and High Frequency Eddy Current (HFEC) inspection for cracks in the skin at Stringer S-17, left and right, at STA 360 to STA 380 and at STA 888 to STA 907. The inspection area is a two inch band of skin, centered on the two rows of fasteners of S-17, STA 360 to STA 380 and STA 888 to STA 907, left and right sides. If any crack is found, accomplish the repair and post repair inspections as shown in this service bulletin. If no crack is found, reinspect at intervals shown in the service bulletin or accomplish terminating action as shown in this service bulletin. EFFECTIVITY 737-600/-700/-800 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). 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 Compliance Tables 3 through 6 of this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 8 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 9 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are available for 737 airplanes in warranty as of March 27, 1998. For inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to BCA Contracts - Warranty. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours are required, send a warranty claim to BCA Contracts - Warranty. Boeing warranty remedies are not available for the supplemental Damage Tolerance Inspections associated with Figure 7. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. STA 888 DO DETAILED AND A HFEC INSPECTION FOR ANY CRACK IN THE SKIN AT S-17, STA 360 TO STA 380 DO DETAILED AND A HFEC S-17 STA CRACK IN THE SKIN AT S-17. INSPECTION FOR ANY 360 STA 888 TO STA 907 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE -700 MODEL SHOWN -600/-800 SIMILAR V43633 Original Issue: August 09, 2001 Revision 1: September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 Copyright © Unpublished Work - See page 1 for details. 9 of 150 ### Page 10 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 10 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT BLANK PAGE ### Page 11 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1217 Original Issue: August 09, 2001 Revision 1: September 08, 2022 ATA System: 5300 SUBJECT: FUSELAGE - Section 43 and Section 47 - Stringer 17 Skin Cracks at STA 360-380 and STA 888-907 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 Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This bulletin is applicable to 737-600, 737-700, 737-800 Airplane(s), line number(s) 1-269 in 3 Group(s). Where the effectivity is presented with hyphens between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive. Airplanes might be in more than one configuration and must do the actions for each applicable configuration. DESCRIPTIONCONFIGURATIONGROUP 737-700/-800 airplanes.-1 Airplanes that have not accomplished this service bulletin.1 Airplanes with any inspection zone that have not done the terminating action. 2 Airplanes with any inspection zone that have installed a repair specified in this service bulletin. 3 Airplanes with any inspection zone that have done the terminating action specified in Part 6 of this service bulletin. 4 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 11 of 150 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP 737-600/-700/-800 airplanes.-2 Airplanes that have not accomplished this service bulletin.1 Airplanes with any inspection zone that have not done the terminating action. 2 Airplanes with any inspection zone that have installed a repair specified in this service bulletin. 3 Airplanes with any inspection zone that have done the terminating action specified in Part 8 of this service bulletin. 4 737-600 airplanes.-3 Airplanes that have not accomplished this service bulletin.1 Airplanes with any inspection zone that have not done the terninationg action. 2 Airplanes with any inspection zone that have installed a repair specified in this service bulletin. 3 Airplanes with any inspection zone that have done the terminating action specified in Part 6 of this service bulletin. 4 Airplane Models: 737-600, 737-700, 737-800 GroupVariable Number 1YA001 - YA030 2YA031 1YA201 - YA206 1YA231 - YA242 1YA251 - YA254 1YA271 - YA272 1YA291 1YA301 - YA302 1YA311 - YA313 1YA321 1YA501 - YA521 GroupVariable Number 2YA522 1YA523 1YA541 - YA544 2YA545 - YA546 1YA571 - YA577 1YA601 - YA606 1YA701 - YA704 1YA721 - YA722 1YA731 1YA751 - YA754 2YA755 GroupVariable Number 1YA811 - YA812 2YA831 1YC001 - YC009 2YC010 - YC011 1YC051 - YC058 1YC071 - YC074 1YC101 - YC103 1YC111 - YC112 1YC121 1YC126 1YC301 - YC302 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 12 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 13 GroupVariable Number 1YC321 - YC337 2YC338 1YC381 - YC382 1YC391 1YC401 - YC406 2YC407 1YC471 1YC501 - YC507 2YC508 - YC510 1YC571 - YC578 1YC591 GroupVariable Number 2YC592 1YC601 - YC606 2YC607 1YC701 - YC706 1YC731 - YC732 1YC751 - YC752 2YC761 - YC763 1YC781 2YC782 1YC801 - YC805 2YC806 - YC809 GroupVariable Number 3YE001 - YE010 2YE011 3YE101 - YE104 2YE105 - YE106 2YE151 1YG001 2YG002 1YG003 - YG011 1YG013 - YG018 2YG020 - YG022 -- 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of the inspection shown in this service bulletin will make sure that skin cracks at the double row of fasteners centered on Stringers S-17L and S-17R, at station (STA) 360 to STA 380 and at STA 888 to STA 907 are found and repaired. If this service bulletin is not done, continued operation with an undetected crack could result in possible rapid decompression and loss of structural integrity. In production, a structural preload was created in the body skin during the installation of S-17. Analysis by Boeing shows that this preload, combined with pressure cycles, can cause cracks in the skin prior to reaching the Design Service Objective (DSO). Engineering evaluation has shown that airplanes with this condition meet all FAA and JAA static strength requirements and are structurally satisfactory. Analysis indicates that the DSO may not be reached unless the preload condition is repaired. Several airplanes have had inspections and/or repairs accomplished at STA 360 to STA 380. However, some of these airplanes still require an inspection to be accomplished at STA 888 to STA 907. Accomplishment of the terminating action shown in this service bulletin will ensure that cracks do not initiate. Cracks will result in unscheduled time out of service to accomplish repairs. For 737-600, 737-700, and 737-800 airplanes after Line Number 269 the sequence of assembly was changed to eliminate the preload. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 13 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 14 Service bulletin 737-53A1217 R01 supersedes the damage tolerance inspection data given in service bulletin 737-00-1007 for service bulletin 737-53-1217 R0 Figures 6, 8 and 9. Service bulletin 737-53A1217 R01 also adds post repair inspections for existing Figure 7. This Revision 1 is sent to move airplanes from Group 1 to new Group 3, add new internal and external post repair inspections of the repair doubler, add new inspections for skin repair and add new repair figures for Group 3 airplanes. D. Description Do a Detailed and a High Frequency Eddy Current (HFEC) inspection for cracks in the skin at Stringer S-17, left and right, at STA 360 to STA 380 and at STA 888 to STA 907. The inspection area is a two inch band of skin, centered on the two rows of fasteners of S-17, STA 360 to STA 380 and STA 888 to STA 907, left and right sides. If any crack is found, accomplish the repair and post repair inspections as shown in this service bulletin. If no crack is found, reinspect at intervals shown in the service bulletin or accomplish terminating action as shown in this service bulletin. Effects of this Revision on airplanes on which the original issue was previously done: ActionConditionGroup Do the initial High Frequency Eddy Cur- rent (HFEC) inspections at all locations. Airplanes that have not accomplished this service bulletin. Group 1-3, Configuration 1 Repeat the HFEC inspections at all un- repaired locations. Airplanes that have not done the termi- nating action. Group 1-3, Configuration 2 Do the post repair inspections at each of the repair locations. Airplanes that have installed a repair.Group 1-3, Configuration 3 No further action required at that loca- tion. Airplanes that have done the terminating action. Group 1-3, Configuration 4 Airplane variable numbers YE001-YE010 and YE101-YE104 were moved from Group 1 to new Group 3 of this service bulletin effectivity. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 121, 122, 141, 142, 231, 232, 241, 242737-700, 737-800 Group 2: Affected Maintenance Zones ZoneModel 121, 122, 141, 142, 231, 232, 241, 242737-600, 737-700, 737-800 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 14 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 15 Group 3: Affected Maintenance Zones ZoneModel 121, 122, 141, 142, 231, 232, 241, 242737-600 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 Compliance Tables 3 through 6 of this service bulletin mandatory. For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental Type Certificate (STC) ST01697SE (6500 feet maximum cabin altitude in lieu of 8000 feet) as referenced in Boeing SB 737-21-1149, the flight cycle related compliance times are different from those specified in this service bulletin. All initial compliance times (thresholds) specified in flight cycles must be reduced to half of those specified in this service bulletin. All repeat interval compliance times specified in flight cycles must be reduced to one-quarter of those specified in this service bulletin. Accomplish the required action(s), based on the applicable condition(s) in Table(s) 1 through 7, 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 or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION. Logic diagrams showing compliance tasks and compliance times is included as an aid in APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, and APPENDIX F. Affected Inspection and Repair ZONE Table STA 360-380 Centered on Stringer 17LZONE 1 STA 360-380 Centered on Stringer 17RZONE 2 STA 888-907 Centered on Stringer 17LZONE 3 STA 888-907 Centered on Stringer 17RZONE 4 PART TITLE: TITLEPART HIGH FREQUENCY EDDY CURRENT (HFEC) IN- SPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4. PART 1 SKIN REPAIR AT ZONE 1.PART 2 SKIN REPAIR AT ZONE 2.PART 3 SKIN REPAIR AT ZONE 3.PART 4 SKIN REPAIR AT ZONE 4.PART 5 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 15 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 16 PART TITLE: TITLEPART TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4. PART 6 HIGH FREQUENCY EDDY CURRENT (HFEC) IN- SPECTION OF THE SKIN AT ZONE 3 AND ZONE 4. PART 7 TERMINATING ACTION AT ZONE 3 AND ZONE 4.PART 8 EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1. PART 9 INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1. PART 10 EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2. PART 11 INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2. PART 12 EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3. PART 13 INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3. PART 14 EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4. PART 15 INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4. PART 16 Group 1, Configuration 1-2; Group 3, Configuration 1-2: Table 1: High Frequency Eddy Current (HFEC) Inspection Of The Skin At ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 36,000 total flight cycles.Do PART 1 for any crack. (a)All airplanes. -Before further flight.Do PART 2 skin repair at zone 1.(b) CONDITION 1: ANY CRACK FOUND WITHIN ZONE 1. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 16 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 17 Group 1, Configuration 1-2; Group 3, Configuration 1-2: Table 1: High Frequency Eddy Current (HFEC) Inspection Of The Skin At ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.OPTION 1:CONDITION 2: Do PART 3 skin repair at zone 2. (c)(e) ANY CRACK FOUND WITHIN ZONE 2. -Before further flight.OPTION 2: Contact The Boeing Compa- ny for repair instructions and do the repair. (d) -Before further flight.Do PART 4 skin repair at zone 3. (f) CONDITION 3: ANY CRACK FOUND WITHIN ZONE 3. -Before further flight.Do PART 5 skin repair at zone 4.(g) CONDITION 4: ANY CRACK FOUND WITHIN ZONE 4. 6,000 flight cy- cles. (h) -OPTION 1: Repeat PART 1 for any crack at any unrepaired zone. (c) CONDITION 5: NO CRACK FOUND on airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing draw- ing 800A0003 specified in the Type Certificate Data Sheet A16WE. -Before further flight.OPTION 2: Do PART 6 at any unre- paired zone. (c)(h) 6,000 flight cy- cles. (h) -OPTION 1: Repeat PART 1 for any crack at any unre- paired zone. (a)(d) CONDITION 6: NO CRACK FOUND on air- planes that have converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certifi- cate Data Sheet A16WE. 6,000 flight cy- cles. (h) -OPTION 2: (Action 1) Repeat PART 1 for any crack at unrepaired zone 2. (d) -Before further flightOPTION 2: (Action 2) Do PART 6 at unrepaired zone 3 and unrepaired zone 4. (d)(h) (a) It is not required to do the High Frequency Eddy Current Skin Inspections for Zone 1 for airplanes converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. (b) Refer to Compliance Table 3 for post repair inspections. (c) Only applicable to airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 17 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 18 Group 1, Configuration 1-2; Group 3, Configuration 1-2: Table 1: High Frequency Eddy Current (HFEC) Inspection Of The Skin At ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Repeat Interval (Not to Exceed) Compliance TimeActionCondition (d) Only applicable to airplanes that have converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. (e) Refer to Compliance Table 4 for post repair inspections. (f) Refer to Compliance Table 5 for post repair inspections. (g) Refer to Compliance Table 6 for post repair inspections. (h) Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. Group 2, Configuration 1-2: Table 2: High Frequency Eddy Current (HFEC) Inspection Of The Skin At ZONE 3 AND ZONE 4 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 36,000 total flight cycles.Do PART 7 for any crack.All airplanes. -Before further flight.Do PART 4 skin repair at zone 3. (a) CONDITION 7: ANY CRACK FOUND WITHIN ZONE 3. -Before further flight.Do PART 5 skin repair at zone 4.(b) CONDITION 8: ANY CRACK FOUND WITHIN ZONE 4. 6,000 flight cy- cles. (c) -OPTION 1: Repeat PART 7 for any crack at any unrepaired zone. CONDITION 9: NO CRACK FOUND -Before further flight.OPTION 2: Do PART 8 at any unrepaired zone. (c) (a) Refer to Compliance Table 5 for post repair instructions. (b) Refer to Compliance Table 6 for post repair instructions. (c) Accomplishment of PART 8: TERMINATING ACTION AT ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 18 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 19 Group 1, 3, Configuration 3: Table 3: Post Repair Inspections At ZONE 1 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspec- tions and applicable corrective actions. Airplanes that have ac- complished a repair in accordance with SB 737-53-1217 Original Issue. -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 1: Do PART 9 for any crack. Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. -Within 36,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 2: Do PART 10 for any crack. -Before further flight.Contact The Boeing Company for repair instructions and do the repair. CONDITION 10: ANY CRACK FOUND. 4,000 flight cy- cles. -CONDITION 11 (ACTION 1): Repeat PART 9 for any crack. CONDITION 11: NO CRACK FOUND. 36,000 flight cy- cles. -CONDITION 11 (ACTION 2): Repeat PART 10 for any crack. Group 1, 3, Configuration 3: Table 4: Post Repair Inspections At ZONE 2 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspec- tions and applicable corrective actions. Airplanes that have ac- complished a repair in accordance with SB 737-53-1217 Original Issue. -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 1: Do PART 11 for any crack. Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. -Within 36,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 2: Do PART 12 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 19 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 20 Group 1, 3, Configuration 3: Table 4: Post Repair Inspections At ZONE 2 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair instructions and do the repair. CONDITION 12: ANY CRACK FOUND. 4,000 flight cy- cles. -CONDITION 13 (ACTION 1): Repeat PART 11 for any crack. CONDITION 13: NO CRACK FOUND. 36,000 flight cy- cles. -CONDITION 13 (ACTION 2): Repeat PART 12 for any crack. Group 1-3, Configuration 3: Table 5: Post Repair Inspections At ZONE 3 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspec- tions and applicable corrective actions. Airplanes that have ac- complished a repair in accordance with SB 737-53-1217 Original Issue. -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 1: Do PART 13 for any crack. Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. -Within 36,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 2: Do PART 14 for any crack. -Before further flight.Contact The Boeing Company for repair instructions and do the repair. CONDITION 14: ANY CRACK FOUND. 4,000 flight cy- cles. -CONDITION 15 (ACTION 1): Repeat PART 13 for any crack. CONDITION 15: NO CRACK FOUND. 36,000 flight cy- cles. -CONDITION 15 (ACTION 2): Repeat PART 14 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 20 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 21 Group 1-3, Configuration 3: Table 6: Post Repair Inspections At ZONE 4 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspec- tions and applicable corrective actions. Airplanes that have ac- complished a repair in accordance with SB 737-53-1217 Original Issue. -Within 4,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 1: Do PART 15 for any crack. Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. -Within 36,000 flight cycles af- ter repair instal- lation. Before 50,000 total flight cy- cles. ACTION 2: Do PART 16 for any crack. -Before further flight.Contact The Boeing Company for repair instructions and do the repair. CONDITION 16: ANY CRACK FOUND. 4,000 flight cy- cles. -CONDITION 17 (ACTION 1): Repeat PART 15 for any crack. CONDITION 17: NO CRACK FOUND. 36,000 flight cy- cles. -CONDITION 17 (ACTION 2): Repeat PART 16 for any crack. 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 Union 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. This service bulletin is also approved for airplanes having FAA Aviation Partners Boeing (APB) Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas affected by the split scimitar winglet configuration). This service bulletin is also approved for airplanes converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 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. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 21 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 22 G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin 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, Configuration 1-2; Group 3, Configuration 1-2: High Frequency Eddy Current (HFEC) Inspection of ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 2.004.002FIGURE 2 2.004.002FIGURE 3 4.008.00TOTAL FOR EACH AIRPLANE Group 1, Configuration 1-2; Group 3, Configuration 1-2: Terminating Action for ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 5.5011.002FIGURE 4 5.5011.002FIGURE 5 12.0024.002Close Access 33.0066.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1-2: High Frequency Eddy Current (HFEC) Inspection of ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 2.004.002FIGURE 3 2.004.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1-2: Terminating Action for ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 22 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 23 Group 2, Configuration 1-2: Terminating Action for ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 5.5011.002FIGURE 5 12.0024.002Close Access 27.5055.00TOTAL FOR EACH AIRPLANE Group 1, Configuration 1-2: Skin Repair for ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 15.5031.002FIGURE 6 16.0032.002FIGURE 7 15.0030.002FIGURE 8 16.0032.002FIGURE 9 12.0024.002Close Access 84.50169.00TOTAL FOR EACH AIRPLANE Group 3, Configuration 1-2: Skin Repair for ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 15.5031.002FIGURE 6 15.0030.002FIGURE 8 16.0032.002FIGURE 9 16.0032.002FIGURE 10 12.0024.002Close Access 84.50169.00TOTAL FOR EACH AIRPLANE Group 2, Configuration 1-2: Skin Repair for ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 15.0030.002FIGURE 8 16.0032.002FIGURE 9 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 23 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 24 Group 2, Configuration 1-2: Skin Repair for ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 12.0024.002Close Access 53.00106.00TOTAL FOR EACH AIRPLANE Group 1, Configuration 3: External Post Repair Inspections At ZONE 1 AND ZONE 2 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 3.006.002FIGURE 11 3.006.002FIGURE 13 12.0024.002Close Access 28.0056.00TOTAL FOR EACH AIRPLANE Group 3, Configuration 3: External Post Repair Inspections At ZONE 1 AND ZONE 2 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 3.006.002FIGURE 11 3.006.002FIGURE 14 12.0024.002Close Access 28.0056.00TOTAL FOR EACH AIRPLANE Group 1, 3, Configuration 3: Internal Post Repair Inspections At ZONE 1 AND ZONE 2 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 2.004.002FIGURE 12 2.004.002FIGURE 15 12.0024.002Close Access 26.0052.00TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 24 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 25 Group 1-3, Configuration 3: External Post Repair Inspections At ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 3.006.002FIGURE 16 3.006.002FIGURE 18 12.0024.002Close Access 28.0056.00TOTAL FOR EACH AIRPLANE Group 1-3, Configuration 3: Internal Post Repair Inspections At ZONE 3 AND ZONE 4 Elapsed HoursTask HoursNumber of PersonsTask 10.0020.002Open Access 2.004.002FIGURE 17 2.004.002FIGURE 19 12.0024.002Close Access 26.0052.00TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes The addition of tapered fillers to Stringer S-17 is not large enough to impact the weight and balance of the airplane. The information in the table below is for the addition of the doublers during the repair of cracked skin. Group 1, 3: Skin Repair at ZONE 1 and ZONE 2 Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane +920+2.7737-600 +770+2.7737-700 +460+2.7737-800 Skin Repair at ZONE 3 and ZONE 4 Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane +2100+2.2737-600 +2200+2.2737-700 +2400+2.2737-800 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 25 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 26 I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR 39800-018RS b. Boeing Service Bulletin 737-21-1149 c. Boeing Service Related Problem (SRP) 737NG-SRP-53-0598 d. Service Bulletin Index D6-19567 e. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01, 20-50-19 f. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-30-00, Part 6, Subject 51-00-00 g. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 25-21-46, 25-22-00, 25-27-15, 25-80-00, 53-21-00 h. 737-600 Structural Repair Manual (SRM) 51-10-01, 51-10-02, 51-20-05, 51-20-13, 51-40-02, 51-40-08 i. 737-700 Structural Repair Manual (SRM) 51-10-01, 51-10-02, 51-20-05, 51-20-13, 51-40-02, 51-40-08 j. 737-800 Structural Repair Manual (SRM) 51-10-01, 51-10-02, 51-20-05, 51-20-13, 51-40-02, 51-40-08 k. 737-800BCF Structural Repair Manual (SRM) 51-10-01, 51-10-02, 51-20-05, 51-20-13, 51-40-02, 51-40-08 l. 737NG Fleet Team Digest (FTD) 53-19001 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Skin Panel Instl. STA 360 to STA 540 Stringer 14L to Stringer 24L143A3210 Panel Instl - Entry. Section 47147A0010 CHORD141A8240 ANGLE SPLICE140A9101 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 26 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 27 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 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. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. 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: August 09, 2001 737-53A1217Revision 1: September 08, 2022 27 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 28 Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 28 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT BLANK PAGE ### Page 29 2. MATERIAL INFORMATION A. Material - Price and Availability None. B. Industry Support Information Boeing warranty remedies are available for 737 airplanes in warranty as of March 27, 1998. For inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to BCA Contracts - Warranty. If the condition described in this service bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours are required, send a warranty claim to BCA Contracts - Warranty. Boeing warranty remedies are not available for the supplemental Damage Tolerance Inspections associated with Figure 7. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 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 / Specification (a)(e)BOLT246BACB30NW6K( )Y (a)(e)BOLT24BACB30NX6K()Y (a)(e)COLLAR272BACC30R6 (a)(e)RIVET66BACR15ET7D (a)(e)RIVET356BACR15GF6D (e)CLAD SHEET-2024-T3 (b)(e)SEALANT5 OuncesBMS 5-95 (b)(c)(e)PRIMER5 OuncesBMS 10-11, TYPE I (b)(d)(e)CHEMICAL CON- VERSION COAT- ING 5 OuncesTYPE II, CLASS A (b)(e)CORROSION IN- HIBITING COM- POUND 5 OuncesBMS 3-23, TYPE II, CLASS 2 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. (b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 29 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 30 NotesNameQTYPart Number / Specification (c) Some primers contain Strontium Chromate and will not be available in the European Union after January 2019 without an authorization. EU operators are encouraged to ensure their suppliers are authorized to provide the material after the sunset date and that downstream users comply with the risk mitigation measures and operational con- ditions. (d) Some conversion coatings contain Chromium trioxide/Chromic acid and will not be available in the European Union after September 2017 without an authorization. EU operators are encouraged to ensure their suppliers are authorized to provide the mate- rial after the sunset date and that downstream users comply with the risk mitigation measures and operational conditions. (e) Boeing Distribution Services Inc (cage code: 2N935) 3760 W. 108th Street, Miami, FL 33018 USA Website: https://www.boeingdistribution.com Telephone: +1.305.925.2600 Fax: +1.305.507.7191 AOG: +1.305.471.8888 Email: Your BDSI customer representative or AOGdesk@Boeingdistribution.com. 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: August 09, 2001 737-53A1217Revision 1: September 08, 2022 30 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 31 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION 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. CAUTION NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 737 Structural Repair Manual, Chapter 51. — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. 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. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. This could include tactile assessment in which a component or assembly can be checked for tightness/security. 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: August 09, 2001 737-53A1217Revision 1: September 08, 2022 31 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 32 7. 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. 8. Refer to APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D, APPENDIX E, and APPENDIX F for logic diagram(s). Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 9. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 11. 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. 12. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 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 or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION. 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 labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled "RC Exempt," then the RC requirement is removed from that step or sub-step. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 32 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 33 B. WORK INSTRUCTIONS 1. Group 1, Configuration 1-2; Group 3, Configuration 1-2: High Frequency Eddy Current (HFEC) Inspection of the skin at ZONE 1, ZONE 2, ZONE 3 AND ZONE 4. a. Do PART 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 for any crack. NOTE: It is not required to do the HFEC Skin Inspections for Zone 1 for airplanes converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. (1) CONDITION 1: ANY CRACK FOUND WITHIN ZONE 1. (a) Do PART 17: GET ACCESS. (b) Do PART 2: SKIN REPAIR AT ZONE 1. NOTE: Refer to PART 9 and PART 10 for post repair inspections. (c) Do PART 18: CLOSE ACCESS. (2) CONDITION 2: ANY CRACK FOUND WITHIN ZONE 2. (a) OPTION 1: NOTE: OPTION 1 is only applicable to airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) Do PART 17: GET ACCESS. 2) Do PART 3: SKIN REPAIR AT ZONE 2. NOTE: Refer to PART 11 and PART 12 for post repair inspections. 3) Do PART 18: CLOSE ACCESS. (b) OPTION 2: NOTE: OPTION 2 is only applicable to airplanes that have converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) Contact The Boeing Company for repair instructions and do the repair. (3) CONDITION 3: ANY CRACK FOUND WITHIN ZONE 3. (a) Do PART 17: GET ACCESS. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 33 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 34 (b) Do PART 4: SKIN REPAIR AT ZONE 3. NOTE: Refer to PART 13 and PART 14 for post repair inspections. (c) Do PART 18: CLOSE ACCESS. (4) CONDITION 4: ANY CRACK FOUND WITHIN ZONE 4. (a) Do PART 17: GET ACCESS. (b) Do PART 5: SKIN REPAIR AT ZONE 4. NOTE: Refer to PART 15 and PART 16 for post repair inspections. (c) Do PART 18: CLOSE ACCESS. (5) CONDITION 5: NO CRACK FOUND on airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. (a) OPTION 1: NOTE: OPTION 1 is only applicable to airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) Repeat PART 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 for any crack at any unrepaired zone. NOTE: Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. (b) OPTION 2: NOTE: OPTION 2 is only applicable to airplanes that have not converted into 737-800BCF under project number TS14-0042 and have not incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) Do PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 at any unrepaired zone. NOTE: Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. (6) CONDITION 6: NO CRACK FOUND on airplanes that have converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 34 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 35 (a) OPTION 1: NOTE: OPTION 1 is only applicable to airplanes that have converted into 737-800BCF under project number TS14-0042 and have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) Repeat PART 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 for any crack at any unrepaired zone. NOTE: It is not required to do the High Frequency Eddy Current Skin Inspections for Zone 1 for airplanes converted into 737-800BCF under project number TS14-0042 that have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. NOTE: Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. (b) OPTION 2: NOTE: OPTION 2 is only applicable to airplanes that have converted into 737-800BCF under project number TS14-0042 and have incorporated Boeing drawing 800A0003 specified in the Type Certificate Data Sheet A16WE. 1) OPTION 2 (ACTION 1): Repeat PART1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 for any crack at unrepaired zone 2. NOTE: Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. 2) OPTION 2 (ACTION 2): Do PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 at any of ZONE 3 and ZONE 4 at unrepaired ZONE 3 and unrepaired ZONE 4. NOTE: Accomplishment of PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. 2. Group 2, Configuration 1-2: High Frequency Eddy Current (HFEC) Inspection of the skin at ZONE 3 and ZONE 4. a. Do PART 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 3 AND ZONE 4 for any crack. (1) CONDITION 7: ANY CRACK FOUND WITHIN ZONE 3. (a) Do PART 17: GET ACCESS. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 35 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 36 (b) Do PART 4: SKIN REPAIR AT ZONE 3. NOTE: Refer to PART 13 and PART 14 for post repair inspections. (c) Do PART 18: CLOSE ACCESS. (2) CONDITION 8: ANY CRACK FOUND WITHIN ZONE 4. (a) Do PART 17: GET ACCESS. (b) Do PART 5: SKIN REPAIR AT ZONE 4. NOTE: Refer to PART 15 and PART 16 for post repair inspections. (c) Do PART 18: CLOSE ACCESS. (3) CONDITION 9: NO CRACK FOUND. (a) OPTION 1: Repeat PART 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 3 AND ZONE 4 for any crack at any unrepaired zone. (b) OPTION 2: Do PART 8: TERMINATING ACTION AT ZONE 3 AND ZONE 4 at any unrepaired zone. NOTE: Accomplishment of PART 8: TERMINATING ACTION AT ZONE 3 AND ZONE 4 is terminating action to the repeat inspections at that zone location. 3. Group 1, 3, Configuration 3: Post Repair Inspections At ZONE 1. a. RC - Airplanes that have accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspections and applicable corrective actions. b. RC - Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) ACTION 1: Do PART 9: EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. (a) CONDITION 10: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 11: NO CRACK FOUND. 1) CONDITION 11 (ACTION 1): Repeat PART 9: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 36 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 37 2) CONDITION 11 (ACTION 2): Repeat PART 10: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. (2) RC Exempt- Do PART 17: GET ACCESS. (3) RC - ACTION 2: Do PART 10: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. (a) CONDITION 10: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 11: NO CRACK FOUND. 1) CONDITION 11 (ACTION 1): Repeat PART 9: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. 2) CONDITION 11 (ACTION 2): Repeat PART 10: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1 for any crack. (4) RC Exempt - Do PART 18: CLOSE ACCESS. 4. Group 1, 3, Configuration 3: Post Repair Inspections At ZONE 2. a. RC - Airplanes that have accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspections and applicable corrective actions. b. RC - Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) ACTION 1: Do PART 11: EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. (a) CONDITION 12: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 13: NO CRACK FOUND. 1) CONDITION 13 (ACTION 1): Repeat PART 11: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 37 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 38 2) CONDITION 13 (ACTION 2): Repeat PART 12: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. (2) RC Exempt- Do PART 17: GET ACCESS. (3) RC - ACTION 2: Do PART 12: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. (a) CONDITION 12: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 13: NO CRACK FOUND. 1) CONDITION 13 (ACTION 1): Repeat PART 11: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. 2) CONDITION 13 (ACTION 2): Repeat PART 12: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2 for any crack. (4) RC Exempt - Do PART 18: CLOSE ACCESS. 5. Group 1-3, Configuration 3: Post Repair Inspections At ZONE 3. a. RC - Airplanes that have accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspections and applicable corrective actions. b. RC - Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) ACTION 1: Do PART 13: EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. (a) CONDITION 14: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 15: NO CRACK FOUND. 1) CONDITION 15 (ACTION 1): Repeat PART 13: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 38 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 39 2) CONDITION 15 (ACTION 2): Repeat PART 14: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. (2) RC Exempt- Do PART 17: GET ACCESS. (3) RC - ACTION 2: Do PART 14: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. (a) CONDITION 14: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 15: NO CRACK FOUND. 1) CONDITION 15 (ACTION 1): Repeat PART 13: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. 2) CONDITION 15 (ACTION 2): Repeat PART 14: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3 for any crack. (4) RC Exempt - Do PART 18: CLOSE ACCESS. 6. Group 1-3, Configuration 3: Post Repair Inspections At ZONE 4. a. RC - Airplanes that have accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) Contact The Boeing Company for alternative inspection and corrective action instructions and do the alternative inspections and applicable corrective actions. b. RC - Airplanes that have not accomplished a repair in accordance with SB 737-53-1217 Original Issue. (1) ACTION 1: Do PART 15: EXTERNAL DETAILED INSPECTION AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. (a) CONDITION 16: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 17: NO CRACK FOUND. 1) CONDITION 17 (ACTION 1): Repeat PART 15: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 39 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 40 2) CONDITION 17 (ACTION 2): Repeat PART 16: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. (2) RC Exempt- Do PART 17: GET ACCESS. (3) RC - ACTION 2: Do PART 16: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. (a) CONDITION 16: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 17: NO CRACK FOUND. 1) CONDITION 17 (ACTION 1): Repeat PART 15: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. 2) CONDITION 17 (ACTION 2): Repeat PART 16: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4 for any crack. (4) RC Exempt - Do PART 18: CLOSE ACCESS. 7. Put the airplane back to a serviceable condition. Group 1, Configuration 1-2; Group 3, Configuration 1-2: PART 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4. 1. Do a HFEC inspection of the skin at ZONE 1 AND ZONE 2 for any crack, in accordance with FIGURE 2. 2. Do a HFEC inspection of the skin at ZONE 3 AND ZONE 4 any crack, in accordance with FIGURE 3. Group 1, Configuration 1-2; Group 3, Configuration 1-2: PART 2: SKIN REPAIR AT ZONE 1. 1. Do a skin repair in accordance with FIGURE 6. Group 1, Configuration 1-2; Group 3, Configuration 1-2: PART 3: SKIN REPAIR AT ZONE 2. 1. Group 1, Configuration 1-2: Do a skin repair in accordance with FIGURE 7. 2. Group 3, Configuration 1-2: Do a skin repair in accordance with FIGURE 10. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 40 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 41 Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2: PART 4: SKIN REPAIR AT ZONE 3. 1. Do a skin repair in accordance with FIGURE 8. Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2: PART 5: SKIN REPAIR AT ZONE 4. 1. Do a skin repair in accordance with FIGURE 9. Group 1, Configuration 1-2; Group 3, Configuration 1-2: PART 6: TERMINATING ACTION AT ZONE 1, ZONE 2, ZONE 3 AND ZONE 4. 1. Do the terminating action ZONE 1 AND ZONE 2 in accordance with FIGURE 4. 2. Do the terminating action ZONE 3 AND ZONE 4 in accordance with FIGURE 5. Group 2, Configuration 1-2: PART 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE SKIN AT ZONE 3 AND ZONE 4. 1. Do a HFEC inspection of the skin, for any crack, in accordance with FIGURE 3. Group 2, Configuration 1-2: PART 8: TERMINATING ACTION AT ZONE 3 AND ZONE 4. 1. Do the terminating action in accordance with FIGURE 5. Group 1, 3, Configuration 3: PART 9: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1. 1. Do an external detailed inspection of the skin around the repair doubler edge, and an LFEC inspection of the skin for any crack, in accordance with FIGURE 11. Group 1, 3, Configuration 3: PART 10: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 1. 1. Do a detailed and MFEC inspection of the internal skin for any crack, in accordance with FIGURE 12. Group 1, 3, Configuration 3: PART 11: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2. 1. Group 1, Configuration 3: Do an external detailed inspection of the skin around the repair doubler edge, and an LFEC inspection of the skin for any crack, in accordance with FIGURE 13. 2. Group 3, Configuration 3: Do a detailed inspection of the skin around the repair doubler edge and LFEC inspection of the skin for any crack, in accordance with FIGURE 14. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 41 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 42 Group 1, 3, Configuration 3: PART 12: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 2. 1. Do a detailed and MFEC inspection of the internal skin for any crack, in accordance with FIGURE 15. Group 1-3, Configuration 3: PART 13: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3. 1. Do an external detailed inspection of the skin around the repair doubler edge, and an LFEC inspection of the skin for any crack, in accordance with FIGURE 16. Group 1-3, Configuration 3: PART 14: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 3. 1. Do a detailed and MFEC inspection of the internal skin for any crack, in accordance with FIGURE 17. Group 1-3, Configuration 3: PART 15: EXTERNAL DETAILED AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4. 1. Do an external detailed inspection of the skin around the repair doubler edge, and an LFEC inspection of the skin for any crack, in accordance with FIGURE 18. Group 1-3, Configuration 3: PART 16: INTERNAL DETAILED AND MEDIUM FREQUENCY EDDY CURRENT (MFEC) INSPECTION OF THE SKIN REPAIR AT ZONE 4. 1. Do a detailed and MFEC inspection of the internal skin for any crack, in accordance with FIGURE 19. PART 17: GET ACCESS 1. Remove and keep passenger seats as necessary. Refer to 737-600/700/800/900 AMM 25-22-00 as an accepted procedure. 2. Remove and keep sidewall panels as necessary. Refer to 737-600/700/800/900 AMM 25-21-46 as an accepted procedure. 3. Remove and keep wall insulation blankets as necessary. Refer to 737-600/700/800/900 AMM 25-80-00 as an accepted procedure. 4. Remove and keep carpet as necessary. Refer to 737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 5. Remove and keep floor panels as necessary. Refer to 737-600/700/800/900 AMM 53-21-00 as an accepted procedure. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 42 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 43 PART 18: CLOSE ACCESS 1. Install kept floor panels. Refer to 737-600/700/800/900 AMM 53-21-00 as an accepted procedure. 2. Install kept carpet. Refer to 737-600/700/800/900 AMM 25-27-15 as an accepted procedure. 3. Install kept wall insulation blankets. Refer to 737-600/700/800/900 AMM 25-80-00 as an accepted procedure. 4. Install kept sidewall panels. Refer to 737-600/700/800/900 AMM 25-21-46 as an accepted procedure. 5. Install kept passenger seats. Refer to 737-600/700/800/900 AMM 25-22-00 as an accepted procedure. Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1: September 08, 2022 43 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 44 FIGURE 1: DELETED AT REVISION 1 (SHEET 1 OF 1) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 44 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 45 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT | This Figure applies only to: Group 1, Configuration 1-2; Group 3, Configuration 1-2. STA 360 - S-17L STA 360 RIGHT SIDE OPPOSITE LEFT SIDE SHOWN S-15. S-16. S- S-18. S-19 S-20 S-2 V43836 FIGURE 2: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 1 AND ZONE 2 (SHEET 1 OF 3) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 737-53A1217 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. 45 of 150 ### Page 46 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT STA 360 STA 364 S-17- STA 371 0000 C C C C SKIN .... VENO SPLICE ANGLE STA 364 SKIN STA 371 S-17 2.00 MIN SKIN FWD VIEW LOOKING INBOARD HFEC INSPECTION A-A NOTE: STATION NUMBERS ARE FOR REFERENCE ONLY. LOCATE INSPECTION ZONE BASED ON FASTENER COUNT AS SHOWN IN SECTION A-A. V43637 FIGURE 2: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 1 AND ZONE 2 (SHEET 2 OF 3) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 Copyright © Unpublished Work - See page 1 for details. 46 of 150 ### Page 47 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 this figure. More DataQtyIdentificationNameTaskStep (a)(b)-ZONE 1SKINInspect1 (a)(b)-ZONE 2SKINInspect (a) Do a surface High Frequency Eddy Current (HFEC) inspection of the skin at S-17L and S-17R, for any crack. Inspect the skin in accordance with 737 NDT Manual Part 6, Subject 51-00-00, Procedure 4 or Procedure 23. (b) Make sure inspection area extends a minimum of 1 inch above and below S-17L and S-17R around each fastener. FIGURE 2: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 1 AND ZONE 2 (SHEET 3 OF 3) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 47 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2. STA 888 STA 1016 S-15. LEFT SIDE SHOWN RIGHT SIDE OPPOSITE S-16 S-17 S-18 S-19. S-20 S-21 V43638 FIGURE 3: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 3 AND ZONE 4 (SHEET 1 OF 3) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY LIZIVES LEL Copyright © Unpublished Work - See page 1 for details. ### Page 49 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT STA 888 STA 891 S-17~ STA 899 0000 C C C CIC OCCC SKIN SPLICE STA STA ANGLE 891 SKIN 899 S-17 2.00 MIN SKIN -WD HFEC INSPECTION VIEW LOOKING INBOARD A-A NOTE: STATION NUMBERS ARE FOR REFERENCE ONLY. LOCATE INSPECTION ZONE BASED ON FASTENER COUNT AS SHOWN IN SECTION A-A. V43630 FIGURE 3: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 3 AND ZONE 4 (SHEET 2 OF 3) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 737-53A1217 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. 49 of 150 ### Page 50 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 this figure. More DataQtyIdentificationNameTaskStep (a)(b)-ZONE 3SKINInspect1 (a)(b)-ZONE 4SKINInspect (a) Do a surface High Frequency Eddy Current (HFEC) inspection of the skin at S-17L and S-17R, for any crack. Inspect the skin in accordance with 737 NDT Manual Part 6, Subject 51-00-00, Procedure 4 or Procedure 23. (b) Make sure inspection area extends a minimum of 1 inch above and below S-17L and S-17R around each fastener. FIGURE 3: DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION- ZONE 3 AND ZONE 4 (SHEET 3 OF 3) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 50 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 51 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT | This Figure applies only to: Group 1, Configuration 1-2; Group 3, Configuration 1-2. STA 360 - S-17L LEFT SIDE SHOWN STA RIGHT SIDE OPPOSITE 360 EXCEPT AS NOTED S-15. S-17 B AND E V43840 FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 1 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 Copyright © Unpublished Work - See page 1 for details. 51 of 150 ### Page 52 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT STA 360 SKIN STA 380 S-17 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE V43641 FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 2 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 737-53A1217 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. 52 of 150 ### Page 53 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT STA 360 SKIN STA 8 LOCATIONS 380 ® 1 7 AS NEEDED LEFT SIDE SHOWN RIGHT SIDE OPPOSITE STA 360 8 14 18 4 LOCATIONS (EXCEPT AS NOTED) S-17_ ® 1 4 8 2 LOCATIONS ® 1 4 8 16 LOCATIONS FOR LHS ONLY Đ1 € 4 AS NEEDED 2 LOCATIONS 4|8 ® V43642 FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 3 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Copyright © Unpublished Work - See page 1 for details. Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 53 of 150 ### Page 54 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 this figure. More DataQtyIdentificationNameTaskStep (a)--FASTENERSRemove1 (m)(n)--EXISTING FASTENER HOLES Inspect2 (b)-STRINGER FLANGESEALANTRemove3 (c)(d)--GAPMeasure4 (e)(l)--SHIM/TAPERED FILLER Make5 (f)-TYPE II, CLASS ACHEMICAL CONVER- SION COATING Apply6 (g)-BMS 10-11, TYPE IPRIMERApply --SHIM/TAPERED FILLER Align7 FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 4 OF 7) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 54 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 55 More DataQtyIdentificationNameTaskStep (h)(q)--SHIM/TAPERED FILLER Drill8 --SHIM/TAPERED FILLER Remove9 (l)--SHIM/TAPERED FILLER Clean/Deburr10 (p)--SKIN, STRINGER, SPLICE ANGLE, IN- TERCOSTAL Clean11 (i)-BMS 5-95SEALANTApply12 (o)--SHIM/TAPERED FILLER Align13 (j)(r)--FASTENERSInstall (New)14 (k)-BMS 5-95SEALANTApply15 (s)-BMS 3-23, TYPE II, CLASS 2 CORROSION INHIBIT- ING COMPOUND Apply16 (a) Remove fasteners as shown. Refer to 737-600 SRM 51-40-02, 737-700 SRM 51-40-02, or 737-800 SRM 51-40-02 as an accepted procedure. (b) Remove sealant and make sure to take caution not to scratch or create any tool marks on the faying surface of mating parts. Refer to SOPM 20-50-19 as an accepted procedure. (c) Measure the gap between the stringer flange and the fuselage skin. Measure gap between splice angle and stringer flange. If any gap is more than 0.050 inches, contact The Boeing Company for repair instruc- tions and do the repair. (d) Measure the gap between the stringer flange and the intercostal. Measure gap between splice angle and intercostal. If any gap is more than 0.050 inches, contact The Boeing Company for repair instructions and do the repair. (e) Make shim/tapered filler from 2024-T3 Clad sheet per QQ-A-250/5. Size the shim/tapered filler to match the gap so that pull up after fastener installation does not exceed 0.010 inches. (f) Apply chemical conversion coating to all bare surfaces of the repair parts and existing structure. Omit coating in fastener holes. Refer to SOPM 20-43-03 as an accepted procedure. (g) Apply two layers of BMS 10-11 Type I primer to all unprimed surfaces of the repair parts and existing structure. Omit coating in fastener holes. Refer to SOPM 20-41-02 as an accepted procedure. (h) Temporarily position shim/tapered filler firmly against the adjacent structure, then backdrill existing fastener holes through the shim/tapered filler. Refer to fastener code table for final hole size. Refer to 737-600 SRM 51-10-02, 737-700 SRM 51-10-02, or 737-800 SRM 51-10-02 as an accepted procedure. (i) Apply BMS 5-95 sealant to all mating surfaces during installation. Refer to SOPM 20-50-19 as an accepted procedure. FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 5 OF 7) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 55 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 56 More DataQtyIdentificationNameTaskStep (j) Refer to fastener code table for installation of fasteners. Refer to 737-600 SRM 51-40-02, 737-700 SRM 51-40-02 or 737-800 SRM 51-40-02 as an accepted procedure. (k) Edge fillet seal around entire periphery of internal structure affected by this modification. Refer to SOPM 20-50-19 as an accepted procedure. (l) Break all sharp edges. (m) Do a High Frequency Eddy Current (HFEC) inspection of the countersunk surface at fastener holes for any crack. Inspect in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 1 (Meter Display), or 737 NDT Manual Part 6, 53-30-00, Procedure 3 (Rotary Probe), or 737 NDT Manual Part 6, 53-30-00, Procedure 4 (Impedance Plane Display). (n) Do an open hole HFEC inspection of the fastener holes for any crack. Inspect all fastener holes in accor- dance with 737 NDT Manual Part 6, 51-00-00, Procedure 16. (o) Install temporary hardware to clamp repair part with structure for sealant squeeze out. Make sure fastener holes are aligned. Allow sealant to cure before removing temporary hardware. Refer to SOPM 20-50-19 as an accepted procedure. (p) Remove all debris from faying surfaces. Deburr accessible hole edges. Take caution not to scratch or create any tool marks on the surface of mating parts. (q) Install temporary fasteners to tightly clamp the structure as drilling progresses to prevent debris from getting into voids between part surfaces. Use newly sharpened drills and reamers. Deburr accessible hole edges. Refer to 737-600 SRM 51-10-02, 737-700 SRM 51-10-02, or 737-800 SRM 51-10-02 as an accepted procedure. (r) Install all rivets dry. Ensure fastener holes are free of sealant and/or contamination before rivet installation. (s) Apply Corrosion Inhibiting Compound (CIC) to the internal area of work. Refer to SOPM 20-41-05 as an accepted procedure. The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 6 OF 7) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 56 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 57 More DataHole DiaQtyIdentificationNameCode (a)(b)(c)0.216 - 0.21928BACB30NW6K( )YBoltA --28BACC30R6Collar (a)(c)0.225 - 0.2317BACR15ET7D( )RivetB (a)(b)0.216 - 0.2198BACB30NX6K( )YBoltC --8BACC30R6Collar (a) Install fasteners. Refer to 737-600 SRM 51-40-02, 737-700 SRM 51-40-02, or 737-800 SRM 51-40-02 as an accepted procedure. (b) Install fasteners wet with BMS 5-95. Refer to 737-600 SRM 51-20-05, 737-700 SRM 51-20-05, or 737- 800 SRM 51-20-05 as an accepted procedure. (c) If more fasteners were required for removal, install this fastener type at the location required. FIGURE 4: TERMINATING ACTION AT ZONE 1 AND ZONE 2 (SHEET 7 OF 7) Export Controlled ECCN: 9E991 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. Original Issue: August 09, 2001 737-53A1217Revision 1 September 08, 2022 57 of 150 BOEING SERVICE BULLETIN 737-53A1217 ALERTALERT ### Page 58 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT This Figure applies only to: Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 3, Configuration 1-2. STA 888 STA 1016 - S-17L S-15 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE S-16 S-17. S-18 S-19. S-20. S-21 V43643 FIGURE 5: TERMINATING ACTION AT ZONE 3 AND ZONE 4 (SHEET 1 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 Copyright © Unpublished Work - See page 1 for details. 58 of 150 ### Page 59 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT STA 888 S-17. D STA 888 SKIN STA 907 TEND S-17 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE V43644 FIGURE 5: TERMINATING ACTION AT ZONE 3 AND ZONE 4 (SHEET 2 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 737-53A1217 BOEING PROPRIETARY Copyright © Unpublished Work - See page 1 for details. 59 of 150 ### Page 60 (OCR) BOEING SERVICE BULLETIN 737-53A1217 ALERT ALERT ® 1 |2 3 LOCATIONS SKIN 8 LOCATIONS STA 907 ® 1% AS NEEDED S-17 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE STA 888 AS 2 LOCATIONS ® 14 S-17 ® A /$ 10 LOCATIONS 8X14 - I AS NEEDED 14 4/8 8 LOCATIONS V43645 FIGURE 5: TERMINATING ACTION AT ZONE 3 AND ZONE 4 (SHEET 3 OF 7) Original Issue: August 09, 2001 Revision 1 September 08, 2022 Export Controlled ECCN: 9E991 BOEING PROPRIETARY 737-53A1217 Copyright © Unpublished Work - See page 1 for details. 60 of 150 The text continues at https://openairdocs.org/service-documents/boeing/737-53a1217/file/18d2e1653807.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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