# Boeing Alert Service Bulletin 737-53A1347: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-5597; AD 2016-23-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-53A1347](https://openairdocs.org/service-documents/boeing/737-53a1347.md) - Title as filed: U.S. DOT/FAA - SB-737-53A1347-00 - Pages: 110 - PDF: https://openairdocs.org/files/sha256/04/80/048023faf2fd17760f877f4861333e72f489eea577486724a1424a343e2c9d83 - Page: https://openairdocs.org/service-documents/boeing/737-53a1347/file/048023faf2fd ## 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: 737-53A1347 Original Issue: December 09, 2015 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Body Stations 559, 578 and 601 - Body Frame and Overwing Stub Beam Inspection and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2015 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 Unpublished Work.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: December 09, 2015 737-53A1347 1 of 110 4.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 2 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT BLANK PAGE ### Page 3 Table of Contents S u m m a r y ...................................................... 5 1. PLANNING INFORMATION ........................................ 1 1 A . E f f e c t i v i t y ............................................... 1 1 1. Airplanes ............................................ 1 1 2 . S p a r e s A f f e c t e d ........................................ 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 1 H. Weight and Balance Changes .................................... 2 4 I. Electrical Load Data ......................................... 2 4 J . R e f e r e n c e s .............................................. 2 4 1. Existing Data: ......................................... 2 4 2. Data Supplied with this Service Bulletin: ........................... 2 4 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 5 K. Publications Affected ........................................ 2 5 L. Interchangeability and Intermixability of Parts ........................... 2 5 M. Software Accomplishment Summary ................................ 2 5 2. MATERIAL INFORMATION ........................................ 2 7 A. Material - Price and Availability ................................... 2 7 B. Industry Support Information .................................... 2 7 C. Parts Necessary for Each Airplane ................................. 2 7 1 . K i t s / P a r t s : ........................................... 2 7 2. Parts and Materials Supplied by the Operator: ........................ 2 8 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 FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION .................................................. 3 8 FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION .................................................. 4 3 FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION .......................................... 4 8 FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION .......................................... 5 3 FIGURE 5: LEFT OVERWING STUB BEAM AT STA 578 - INSTALLATION .............. 5 8 FIGURE 6: RIGHT OVERWING STUB BEAM AT STA 578 - INSTALLATION .............. 6 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 3 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 4 FIGURE 7: LEFT FRAME AT STA 559, STA 578 AND STA 601 FROM STRINGER S-16L AND OVERWING STUB BEAMS AT STA 559 AND 601 FROM S-17L DOWN TO THE WING CENTER FUEL TANK UPPER PANEL - DETAILED INSPECTION ...................... 8 0 FIGURE 8: RIGHT FRAME AT STA 559, STA 578 AND STA 601 FROM STRINGER S-16R AND OVERWING STUB BEAMS AT STA 559 AND 601 FROM S-17R DOWN TO THE WING CENTER FUEL TANK UPPER PANEL - DETAILED INSPECTION ...................... 8 5 FIGURE 9: LEFT FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - DETAILED INSPECTION OPTION 1 ..... 9 0 FIGURE 10: RIGHT FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - DETAILED INSPECTION OPTION 1 . 92 FIGURE 11: LEFT FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - HFEC INSPECTION OPTION 2 ........ 9 4 FIGURE 12: RIGHT FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - HFEC INSPECTION OPTION 2 . . 96 FIGURE 13: POST-REPLACEMENT HFEC INSPECTION - LEFT OVERWING STUB BEAM AT STA 578 .................................................. 9 8 FIGURE 14: POST-REPLACEMENT HFEC INSPECTION - RIGHT OVERWING STUB BEAM AT STA 578 ................................................. 1 0 1 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: INSPECTION OF THE FRAMES AND OVERWING STUB BEAMS AT STA 559, STA 578 AND STA 601 AND REPLACEMENT OF THE OVERWING STUB BEAM AT STA 578, LEFT AND RIGHT SIDES ( R E Q U I R E D M I N I M U M F O R S A F E T Y ) . .......................... 1 0 4 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: INSPECTION OF THE OVERWING STUB BEAM UPPER CHORD AT STA 578 - POST REPAIR OVERWING STUB BEAM REPLACEMENT HFEC INSPECTION, LEFT AND RIGHT SIDES (REQUIRED MINIMUM F O R S A F E T Y )........................................ 1 0 7 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: DETAILED OR HFEC INSPECTION OF THE FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578, LEFT AND RIGHT SIDES (RECOMMENDED ECONOMIC INSPECTION) ....................... 1 0 8 APPENDIX D: PART DEMAND INTENT .................................. 1 1 0 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 4 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 5 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1347Original Issue: December 09, 2015 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Body Stations 559, 578 and 601 - Body Frame and Overwing Stub Beam Inspection and Repair THIS BULLETIN 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 SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin gives instructions to inspect the left and right side overwing stub beam upper chords for any crack emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chords at Body Stations (STA) 559, 578 and 601. High flight cycle fatigue stresses from both pressurization and maneuver loads can cause cracks in the upper chord of the overwing stub beam at STA 578 which could adversely affect the structural integrity and result in possible decompression of the airplane. Periodic repeat inspections and the replacement of any cracked overwing stub beam at STA 578 will reduce the possibility of undetected fatigue cracks occurring in the adjacent frame and overwing stub beam structure at Body Stations (STA) 559, 578 and 601. Boeing has received ten reports from four operators of cracks in the upper chord of the overwing stub beams at STA 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord on 737-400 airplanes. At the time of release of this service bulletin there have been no reports of any crack in the upper chords of the overwing stub beams at STA 559 or STA 601. The earliest reported crack in an overwing stub beam upper chord occurred on an airplane with 31,843 flight cycles. Seven airplanes had a severed overwing stub beam upper chord on either the left or right side and two airplanes had severed overwing stub beam upper chords on the left and right side. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 5 of 110 ### Page 6 In addition, this service bulletin gives instructions for a recommended economic inspection for any crack in the inboard frame chord between the crease beam web and the wing center fuel tank upper panel at STA 578 which could prevent costly repairs in the future should any cracks occur. The cause of the cracks in the inboard chord of the frame between the crease beam web and the wing center fuel tank upper panel at STA 578 is due to pull-up stresses and is similar to the frame cracks at STA 601 addressed by an economic inspection and repair in Boeing Service Bulletin 737-53A1254, Revision 2. Boeing has received eight reports of cracks in the inboard chord of the frame between the crease beam web and the wing center fuel tank upper panel at STA 578 on 737-400 airplanes. Three airplanes had cracks on either the left or right side and one airplane had cracks on both the left and right side. Boeing Service Related Problem (SRP) 737-SRP-53-0411 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 53-14006 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 ChangesNoWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 35005-305RS) 1. Do a surface High Frequency Eddy Current (HFEC) inspection of the overwing stub beam upper chord on the left and right sides for any crack at Body Stations (STA) 559, 578 and 601. a. If no crack is found, repeat the surface HFEC inspection in accordance with Paragraph 1.E., Compliance. b. If any crack is found at STA 559 or STA 601, contact The Boeing Company for repair instructions and do the repair. c. If any crack is found at STA 578: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 6 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 7 (1) Do a detailed inspection for any crack in the frames and adjacent structure at STA 559, STA 578 and STA 601 from stringer S-16 down to the wing center fuel tank upper panel. (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, replace the cracked overwing stub beam at STA 578. (2) Do the post-replacement inspection of the overwing stub beam replacement at STA 578 in accordance with Paragraph 1.E., Compliance. (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, repeat the post-replacement inspection for any crack in accordance with Paragraph 1.E., Compliance. Operators have the option to do a detailed inspection or a surface HFEC inspection of the frame inner chord between the crease beam web and wing center fuel tank upper panel at STA 578 for any crack. The permitted number of flight cycles between inspections is increased if a surface HFEC inspection is done. If any crack is found, contact The Boeing Company for repair instructions and do the repair. This inspection is not mandatory for safety. It is an optional economic inspection to find any crack in the inner frame chord which could prevent costly repairs in the future should any cracks occur. EFFECTIVITY All 737-400 airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection, repair and modification procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 7 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 8 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT STA 559 STA 639 FRAME ∞ D (TYPICAL) STA HATCH ESCAPE 639 S-16L CREASE BEAM INNER CHORD LONGITUDINAL FLOOR BEAM STUB BEAM AT STA 601 WING CENTER FUEL TANK UPPER PANEL STUB BEAM AT STA 578 STUB BEAM AT STA 559 $ LBL 45.5 2331075 LEFT SIDE SHOWN, RIGHT SIDE SIMILAR Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright @ Unpublished Work - See page 1 for details. 8 of 110 ### Page 9 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME DO A HFEC INSPECTION OF THE STUB BEAM UPPER CHORD AT THE CREASE BEAM INNER CHORD FASTENER ATTACHMENT AT STA 559, STA 578 AND STA S-16L- 601 FOR ANY CRACK S-17L STUB BEAM STA 559 FRAME A-A S-16L CRACK (TYPICAL) S-17L STUB BEAM FRAME S-16l CREASE BEAM LONGITUDINAL INNER CHORD FLOOR BEAM (TYPICAL) (TYPICAL) S-17L - WING CENTER FUEL 000 0 o TANK UPPER PANEL (TYPICAL) STUB BEAM STA 601 LEFT SIDE SHOWN, RIGHT SIDE SIMILAR C-C INBD 2367924 Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1347 Work - See page 1 for details. 9 of 110 ### Page 10 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 10 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT BLANK PAGE ### Page 11 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1347 Original Issue: December 09, 2015 ATA System: 5311 SUBJECT: FUSELAGE - Frames and Bulkheads - Body Stations 559, 578 and 601 - Body Frame and Overwing Stub Beam Inspection and Repair THIS BULLETIN 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 SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN 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 service bulletin is for the airplanes shown below. DESCRIPTIONCONFIGURATIONGROUP All 737-400 airplanes.-1 Airplane Models: 737-400 GroupVariable Number 1PJ301 - PJ302 1PJ551 - PJ561 1PJ601 - PJ615 1PJ811 1PJ816 - PJ817 1PM551 - PM564 1PV001 - PV055 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 11 of 110 ### Page 12 GroupVariable Number 1PV201 - PV209 1PV226 - PV229 1PV231 - PV237 1PV271 - PV272 1PV281 - PV287 1PV296 1PV301 - PV302 1PV351 1PV356 - PV357 1PW001 - PW054 1PW061 - PW068 1PW072 1PW086 - PW088 1PW091 - PW094 1PW101 - PW102 1PW106 1PW111 - PW120 1PW156 - PW157 1PW161 - PW171 1PW201 - PW252 1PW261 - PW268 1PW271 - PW276 1PW278 1PW281 - PW293 1PW296 1PW301 - PW327 1PW401 - PW408 1PW411 - PW418 1PW421 - PW424 1PW431 - PW435 1PW441 - PW450 1PW461 - PW467 1PW501 - PW504 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 12 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 13 GroupVariable Number 1PW511 - PW522 1PW524 - PW550 1PW556 - PW557 1PW561 - PW564 1PW571 - PW576 1PW591 - PW596 1PW611 - PW622 1PW631 - PW637 1PW661 - PW662 1PW681 - PW683 1PW701 - PW702 1PW711 - PW717 1PW741 - PW742 1PW761 1PW771 1PW831 1PW851 - PW856 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to inspect the left and right side overwing stub beam upper chords for any crack emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chords at Body Stations (STA) 559, 578 and 601. High flight cycle fatigue stresses from both pressurization and maneuver loads can cause cracks in the upper chord of the overwing stub beam at STA 578 which could adversely affect the structural integrity and result in possible decompression of the airplane. Periodic repeat inspections and the replacement of any cracked overwing stub beam at STA 578 will reduce the possibility of undetected fatigue cracks occurring in the adjacent frame and overwing stub beam structure at Body Stations (STA) 559, 578 and 601. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 13 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 14 Boeing has received ten reports from four operators of cracks in the upper chord of the overwing stub beams at STA 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord on 737-400 airplanes. At the time of release of this service bulletin there have been no reports of any crack in the upper chords of the overwing stub beams at STA 559 or STA 601. The earliest reported crack in an overwing stub beam upper chord occurred on an airplane with 31,843 flight cycles. Seven airplanes had a severed overwing stub beam upper chord on either the left or right side and two airplanes had severed overwing stub beam upper chords on the left and right side. In addition, this service bulletin gives instructions for a recommended economic inspection for any crack in the inboard frame chord between the crease beam web and the wing center fuel tank upper panel at STA 578 which could prevent costly repairs in the future should any cracks occur. The cause of the cracks in the inboard chord of the frame at STA 578 between the crease beam web and the wing center fuel tank upper panel is due to pull-up stresses and is similar to the frame cracks at STA 601 addressed by an economic inspection and repair in Boeing Service Bulletin 737-53A1254, Revision 2. Boeing has received eight reports of cracks in the inboard chord of the frame between the crease beam web and the wing center fuel tank upper panel at STA 578 on 737-400 airplanes. Three airplanes had cracks on either the left or right side and one airplane had cracks on both the left and right side. Boeing Service Related Problem (SRP) 737-SRP-53-0411 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737 FTD 53-14006 is related to this service bulletin. D. Description 1. Do a surface High Frequency Eddy Current (HFEC) inspection of the overwing stub beam upper chord on the left and right sides for any crack at Body Stations (STA) 559, 578 and 601. a. If no crack is found, repeat the surface HFEC inspection in accordance with Paragraph 1.E., Compliance. b. If any crack is found at STA 559 or STA 601, contact The Boeing Company for repair instructions and do the repair. c. If any crack is found at STA 578: (1) Do a detailed inspection for any crack in the frames and adjacent structure at STA 559, STA 578 and STA 601 from stringer S-16 down to the wing center fuel tank upper panel. (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, replace the cracked overwing stub beam at STA 578. (2) Do the post-replacement inspections of the overwing stub beam replacement at STA 578 in accordance with Paragraph 1.E., Compliance. (a) If any crack is found, contact The Boeing Company for repair instructions and do the repair. (b) If no crack is found, repeat the post-replacement inspection for any crack in accordance with Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 14 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 15 Operators have the option to do a detailed inspection or a surface HFEC inspection of the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578 for any crack. The permitted number of flight cycles between inspections is increased if a surface HFEC inspection is done. If any crack is found, contact The Boeing Company for repair instructions and do the repair. This inspection is not mandatory for safety. It is an optional economic inspection to find any crack in the inner frame chord which could prevent costly repairs in the future should any cracks occur. The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones ZoneModel 221737-400 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. NOTE: The damage tolerance inspections specified in Table 2 below may be used in support of compliance with 14 Code of Federal Regulations, Section 121.1109 or 129.109. Tables 1 and 2 below provide the required inspections to maintain safety of flight. Table 3 below provides economic inspections to find any crack in the inner frame chord which could prevent costly repairs in the future should any cracks occur (not mandatory for safety). Do the required actions in accordance with Paragraph 3, Accomplishment Instructions. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B and APPENDIX C. Table 1: Inspection of the overwing stub beams at STA 559, STA 578 and STA 601, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Before 30,000 total flight cycles.Do PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack. Airplanes with less than 25,500 total flight cycles at the original issue date of this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 15 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 16 Table 1: Inspection of the overwing stub beams at STA 559, STA 578 and STA 601, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Within 4,500 flight cycles af- ter the original issue date of this service bul- letin. Before 51,500 total flight cy- cles. Do PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack. Airplanes with 25,500 to 50,000 total flight cycles at the original issue date of this service bulletin. -Within 1,500 flight cycles after the original issue date of this service bulletin. Do PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack. Airplanes with more than 50,000 total flight cycles at the original issue date of this service bulletin. 9,000 flight cycles. (b) -Repeat PART 2: OVER- WING STUB BEAM UP- PER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPEC- TION for any crack. CONDITION 1: NO CRACK FOUND AT STA 559, STA 578, AND STA 601 DURING PART 2 IN- SPECTION. -Before further flight.CONDITION 2 (ACTION 1): CONDITION 2: ANY CRACK FOUND AT STA 559 OR STA 601 DURING PART 2 INSPECTION. Contact The Boeing Company for repair in- structions and do the re- pair. 9,000 flight cycles. (b) -CONDITION 2 (ACTION 2): Repeat PART 2: OVER- WING STUB BEAM UP- PER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPEC- TION for any crack at the unrepaired STA 559, STA 578 and STA 601 stub beam locations. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 16 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 17 Table 1: Inspection of the overwing stub beams at STA 559, STA 578 and STA 601, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Before further flight.Do PART 3: FRAME AND ADJACENT STRUC- TURE AT STA 559, STA 578 AND STA 601 FROM STRINGER S-16 DOWN TO THE WING CENTER FUEL TANK UPPER PANEL - DETAILED IN- SPECTION for any crack. (a) CONDITION 3: ANY CRACK FOUND AT STA 578 DURING PART 2 IN- SPECTION. -Before further flight.CONDITION 3.1 (AC- TION 1): CONDITION 3.1: ANY CRACK FOUND AT STA 578 STUB BEAM DURING PART 2 INSPECTION Contact The Boeing Company for repair in- structions and STA 578 stub beam replacement instructions and do the repair and STA 578 stub beam replacement. AND ANY CRACK FOUND DURING PART 3 INSPEC- TION. 9,000 flight cycles. (b) -CONDITION 3.1 (AC- TION 2): Repeat PART 2: OVER- WING STUB BEAM UP- PER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPEC- TION for any crack at the unrepaired STA 559, STA 578 and STA 601 stub beam locations. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 17 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 18 Table 1: Inspection of the overwing stub beams at STA 559, STA 578 and STA 601, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs First) ActionCondition -Before further flight.CONDITION 3.2 (AC- TION 1) Do PART 4: OVERWING STUB BEAM AT STA 578 - RE- PLACEMENT. (a) (b) (c) CONDITION 3.2: ANY CRACK FOUND AT STA 578 STUB BEAM DURING PART 2 INSPECTION AND NO CRACK FOUND DUR- ING PART 3 INSPECTION. 9,000 flight cycles.(b)-CONDITION 3.2 (AC-TION 2): Repeat PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578, AND STA 601 - HFEC INSPECTION for any crack at the unrepaired STA 559, STA 578 and STA 601 stub beam loca- tions. (a) Accomplishment of PART 3 and PART 4 are required only on the side of the airplane where any crack was found at STA 578 only during PART 2 inspection. (b) Accomplishment of the overwing stub beam replacement in accordance with PART 4 is terminating action for the repeat of the PART 2 inspection at the STA 578 replacement location only. (c) Post-Replacement Inspection requirements are in Table 2. Table 2: Post-Replacement Inspection of the overwing stub beam upper chord at STA 578, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 37,500 flight cycles after the overwing stub beam replace- ment has been accomplished. Do PART 5: POST-RE- PLACEMENT INSPEC- TION OF THE OVER- WING STUB BEAM UP- PER CHORD AT STA 578 for any crack. Airplanes that have accom- plished PART 4: OVER- WING STUB BEAM AT STA 578 - REPLACE- MENT. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 4: ANY CRACK FOUND DURING PART 5: POST-REPLACE- MENT INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 18 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 19 Table 2: Post-Replacement Inspection of the overwing stub beam upper chord at STA 578, left and right side (required minimum for safety) Repeat Interval (Not to Exceed) Compliance TimeActionCondition 9,000 flight cycles.-Repeat PART 5: POST- REPLACEMENT INSPEC- TION OF THE OVER- WING STUB BEAM UP- PER CHORD AT STA 578 for any crack. CONDITION 5: NO CRACK FOUND DURING PART 5: POST- REPLACE- MENT INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 19 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 20 Table 3: Inspection of the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578, left and right side (recommended economic inspection) Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs First) ActionCondition -Before 56,500 total flight cy- cles. Within 3,000 flight cycles af- ter the original issue date of this service bul- letin. OPTION 1: Do PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - DETAILED INSPECTION for any crack. OR OPTION 2: Do PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - HFEC INSPECTION for any crack. Airplanes with 15,000 to 55,000 total flight cycles at the original issue date of this service bulletin. -Within 1,500 flight cycles after the original issue date of this service bulletin. OPTION 1: Do PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - DETAILED INSPECTION for any crack. OR OPTION 2: Do PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - HFEC INSPECTION for any crack. Airplanes with more than 55,000 total flight cycles at the original issue date of this service bulletin. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: ANY CRACK FOUND DURING PART 6 INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 20 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 21 Table 3: Inspection of the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578, left and right side (recommended economic inspection) Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichever Occurs First) ActionCondition 4,500 flight cy- cles. -OPTION 1: Repeat PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - DETAILED INSPECTION for any crack. CONDITION 7: NO CRACK FOUND DURING PART 6 INSPECTION. 9,000 flight cy- cles. -OPTION 2: Repeat PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CEN- TER FUEL TANK UPPER PANEL AT STA 578 - HFEC INSPECTION 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 Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. These data have been reviewed by the Boeing Organization Designation Authorization (ODA) for fuel tank ignition prevention requirements, and no further approval from the FAA Oversight Office is required to satisfy the requirements of Critical Design Configuration Control Limitation (CDCCL) 28-AWL-11 of Document D6-38278-CMR, provided the repair or alteration is accomplished in accordance with this service bulletin. 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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 21 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 22 — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Table 1: Left and right overwing stub beam at STA 559, STA 578 and STA 601 - HFEC In- spection Elapsed HoursTask-HoursNumber of Per- sons Task 5.0010.002Open Access 1.701.701FIGURE 1 1.701.701FIGURE 2 5.0010.002Close Access 13.4023.40Total for each airplane. Table 2: Left overwing stub beam at STA 578 - Replacement Elapsed HoursTask HoursNumber of PersonsTask 4.0016.004Open Access 3.757.502FIGURE 3 6.0012.002FIGURE 5 2.755.502Close Access 16.5041.00Total for each airplane. Table 3: Right overwing stub beam at STA 578 - Replacement Elapsed HoursTask HoursNumber of PersonsTask 4.0016.004Open Access 3.757.502FIGURE 4 6.0012.002FIGURE 6 2.755.502Close Access 16.5041.00Total for each airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 22 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 23 Table 4: Left frame and adjacent structure from S-16 down to the wing center fuel tank upper panel at STA 559, STA 578 and STA 601 - Detailed Inspection Elapsed HoursTask-HoursNumber of Per- sons Task 3.757.502FIGURE 7 3.757.50Total for each airplane. Table 5: Right frame and adjacent structure from S-16 down to the wing center fuel tank upper panel at STA 559, STA 578 and STA 601 - Detailed Inspection Elapsed HoursTask-HoursNumber of Per- sons Task 3.757.502FIGURE 8 3.757.50Total for each airplane. Table 6: Left and right frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578 - Detailed inspection Elapsed HoursTask-HoursNumber of Per- sons Task 0.750.751FIGURE 9 0.750.751FIGURE 10 1.501.50Total for each airplane Table 7: Left and right frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578 - HFEC inspection Elapsed HoursTask-HoursNumber of Per- sons Task 0.750.751FIGURE 11 0.750.751FIGURE 12 1.501.50Total for each airplane Table 8: Post-Replacement HFEC Inspection of the left overwing stub beam at STA 578 Elapsed HoursTask-HoursNumber of Per- sons Task 0.750.751FIGURE 13 0.750.75Total for each airplane Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 23 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 24 Table 9: Post-Replacement HFEC Inspection of the right overwing stub beam at STA 578 Elapsed HoursTask-HoursNumber of Per- sons Task 0.750.751FIGURE 14 0.750.75Total for each airplane H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR 35005-305RS b. Boeing Service Bulletin 737-53A1254 c. Boeing Service Letter 737-SL-51-042 d. Boeing Service Related Problem (SRP) 737-SRP-53-0411 e. Service Bulletin Index D6-19567 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-30-93, 20-41-02, 20-41-05, 20-43-03, 20-50-01, 20-50-19, 20-50-20 g. 737 Fleet Team Digest (FTD) 53-14006 h. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-30-00 i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-31-31, 20-10-41, 20-10-91, 25-21-01, 25-22-00, 25-27-15, 27-09-14, 27-11-00, 27-31-00, 27-51-00, 28-10-00, 28-11-00, 28-11-31, 51-31-00, 53-21-00 j. 737-400 Structural Repair Manual (SRM) 51-20-01, 51-40-02 2. Data Supplied with this Service Bulletin: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 24 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 25 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Frame Installation - Emergency Escape Hatch, Body Station 60165C32394 Frame Installation - Body Station 55965-46536 Frame Installation - Emergency Escape Hatch, Body Station 57865C32755 Crease Beam Installation - Floor STA 540 - 663.7565-47973 Floor Beam Installation - Wing Center Section65-45410 Upper Panel Installation - Wing Center Section65-45404 Skin Panel Installation - S-10 to S-18A, STA 540 to STA 72765-45771 Seal Application, Center Section - Wing65-47810 Sealing Index and Requirements - Wing65-47801 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS and new 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: December 09, 2015 737-53A1347 25 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 26 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 26 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT BLANK PAGE ### Page 27 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) NamePart Number 41,500.00(a)Stub Beam - Wing Center Section, STA 57865C32772-11 41,500.00(a)Stub Beam - Wing Center Section, STA 57865C32772-12 (a) ROLT is not available at this time. Contact The Boeing Company prior to ordering the ROLT for this service bulletin. Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. B. Industry Support Information Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One overwing stub beam and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary to replace one STA 578 overwing stub beam for each airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 27 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 28 End Item Parts NotesExisting Part Number NameQTYNew Part Number (a)65C32772-7 or 65C32772-9 Stub Beam - Wing Center Section, STA 578 165C32772-11 (b)65C32772-8 or 65C32772-10 Stub Beam - Wing Center Section, STA 578 165C32772-12 (a) The 65C32772-11 overwing stub beam replaces the 65C32772-7 or 65C32772-9 overwing stub beam. (b) The 65C32772-12 overwing stub beam replaces the 65C32772-8 or 65C32772-10 overwing stub beam. 2. Parts and Materials Supplied by the Operator: NOTE: The fasteners shown below are necessary to replace one STA 578 overwing stub beam for each airplane. NotesNameQTYPart Number / Specification -Bolt1BACB30MB8A8 -Bolt7BACB30MY8K5 -Bolt1BACB30NX10K7 -Bolt2BACB30NX12K12 -Bolt2BACB30NX12K14 -Bolt11BACB30VT6K6 -Bolt1BACB30VT6K7 -Bolt2BACB30VT6K9 -Bolt1BACB30VT6K11 -Bolt1BACB30VT6K12 -Bolt2BACB30VT8K5 -Bolt4BACB30VT8K7 -Bolt3BACB30VT8K8 -Bolt1BACB30VT8K9 -Bolt2BACB30VT8K10 -Bolt2BACB30VT8K12 -Bolt3BACB30VT10K6 -Bolt1BACB30VT10K7 -Bolt1BACB30YP8K6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 28 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 29 NotesNameQTYPart Number / Specification -Collar1BACC30BH8 -Collar1BACC30BH10 -Collar4BACC30BH12 -Collar11BACC30BL6 -Collar13BACC30BL8 -Collar4BACC30BL10 -Collar5BACC30BQ6 -Collar2BACC30BQ8 -Collar7BACC30M8 -Grommet2BACG20H204N -Rivet1BACR15FT5D8C -Rivet1BACR15FT5D9C -Rivet1BACR15FT5D10C -Rivet1BACR15FT5D11C -Rivet1BACR15FT6D9C -Rivet10BACR15FT8D7C -Rivet4BACR15GF6D5 -Rivet1BACR15GF7D11 -Shim1BACS40R007B011F -Shim1BACS40R010C069F -Shim1BACS40R010Y012F -Shim1BACS40R010Y018F -Shim1BACS40R010Y033F -Shim1BACS40R024C035F (a)Corrosion Inhibiting Compound 100 ozBMS 3-29 (a)Sealant8 ozBMS 5-81 Type II (a)Sealant10 ozBMS 5-45, Class B-2 (a)Sealant8 ozBMS 5-95, Class B-1/2, -2 (a)Primer4 ozBMS 10-11, Type I (a)Adhesive4 ozBMS 5-126, Type II, Class 1 (a)White Enamel4 ozGloss Enamel, BMS 10-11, Type II, BAC 702 GLOSS WHITE (a)Primer4 ozBMS 10-20, Type II Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 29 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 30 NotesNameQTYPart Number / Specification (b)Chemical Conversion Coating 4 ozTYPE 2, CLASS A (a)Solvent Cleaner4 ozBMS 11-7 (b)Chemical Conversion Coating 4 ozAlodine 600 (c)0.63 inch x 6.0 inches x 9.0 inches 17075-T6 Clad Aluminum Sheet (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Refer to SOPM 20-43-03 for supplier data. (c) Used to make tapered filler if needed between overwing stub beam and frame web. 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: December 09, 2015 737-53A1347 30 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 31 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 737 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 737 Airplane Maintenance Manual (AMM). — Values for engine maintenance tasks are included in Chapter 70 of 737 Airplane Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. 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. 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: December 09, 2015 737-53A1347 31 of 110 BOEING SERVICE BULLETIN 737-53A1347 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. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 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 part with the same part number can be installed as an alternative to the kept part. 12. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 13. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. 14. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 15. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 17. 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. 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: December 09, 2015 737-53A1347 32 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 33 18. Use caution not to damage the holes when removing fasteners from the structure. 19. Every effort has been made to account for all possible unique production configurations. However if the fastener patterns, types and sizes, or the structure does not agree with the modification instructions, contact The Boeing Company with the details before proceeding. B. WORK INSTRUCTIONS 1. Do PART 1: ACCESS. 2. Do PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack. a. CONDITION 1: NO CRACK FOUND AT STA 559, STA 578 AND STA 601 DURING PART 2 INSPECTION. (1) Repeat PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack at the repeat interval in accordance with Paragraph 1.E., Compliance. NOTE: Accomplishment of the overwing stub beam replacement in accordance with PART 4 is terminating action for the repeat of the PART 2 inspection at the STA 578 replacement location only. b. CONDITION 2: ANY CRACK FOUND AT STA 559 OR STA 601 DURING PART 2 INSPECTION. (1) CONDITION 2 (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. (2) CONDITION 2 (ACTION 2): Repeat PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack at the unrepaired STA 559, STA 578 and STA 601 stub beam locations at the repeat interval in accordance with Paragraph 1.E., Compliance. c. CONDITION 3: ANY CRACK FOUND AT STA 578 DURING PART 2 INSPECTION. (1) Do PART 3: FRAME AND ADJACENT STRUCTURE AT STA 559, STA 578 AND STA 601 FROM STRINGER S-16 DOWN TO THE WING CENTER FUEL TANK UPPER PANEL - DETAILED INSPECTION for any crack. NOTE: Accomplishment of PART 3 is required only on the side of the airplane where any crack was found at STA 578 only during PART 2 inspection. (a) CONDITION 3.1: ANY CRACK FOUND AT STA 578 STUB BEAM DURING PART 2 INSPECTION AND ANY CRACK FOUND DURING PART 3 INSPECTION. 1) CONDITION 3.1 (ACTION 1): Contact The Boeing Company for repair instructions and STA 578 stub beam replacement instructions and do the repair and STA 578 stub beam replacement. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 33 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 34 2) CONDITION 3.1 (ACTION 2): Repeat PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION for any crack at the unrepaired STA 559, STA 578 and STA 601 stub beam locations at the repeat interval in accordance with Paragraph 1.E., Compliance. (b) CONDITION 3.2: ANY CRACK FOUND AT STA 578 STUB BEAM DURING PART 2 INSPECTION AND NO CRACK FOUND DURING PART 3 INSPECTION. 1) CONDITION 3.2 (ACTION 1): Do PART 4: OVERWING STUB BEAM AT STA 578 - REPLACEMENT. NOTE: Accomplishment of PART 4 is required only on the side of the airplane where any crack was found at STA 578 only during PART 2 inspection. NOTE: Accomplishment of the overwing stub beam replacement in accordance with PART 4 is terminating action for the repeat of the PART 2 inspection at the STA 578 replacement location only. NOTE: Post-Replacement Inspection requirements are in PART 5. 2) CONDITION 3.2 (ACTION 2): Repeat PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 and STA 601 - HFEC INSPECTION for any crack at the unrepaired STA 559, 578, and STA 601 stub beam locations at the repeat interval in accordance with Paragraph 1.E., Compliance. 3. (RECOMMENDED ECONOMIC INSPECTION) DO PART 6: FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - DETAILED OR HFEC INSPECTION for any crack. NOTE: This inspection is not mandatory for safety. It is optional to do OPTION 1 or OPTION 2 as follows: a. OPTION 1: DETAILED INSPECTION (1) Do a detailed inspection for any crack in the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578. (a) CONDITION 6: ANY CRACK FOUND DURING PART 6 INSPECTION. 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 7: NO CRACK FOUND DURING PART 6 INSPECTION. 1) Repeat PART 6, OPTION 1 for any crack at the repeat interval in accordance with Paragraph 1.E., Compliance. b. OPTION 2: HFEC INSPECTION (1) Do a surface HFEC inspection for any crack in the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578. (a) CONDITION 6: ANY CRACK FOUND DURING PART 6 INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 34 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 35 1) Contact The Boeing Company for repair instructions and do the repair. (b) CONDITION 7: NO CRACK FOUND DURING PART 6 INSPECTION. 1) Repeat PART 6, OPTION 2 for any crack at the repeat interval in accordance with Paragraph 1.E., Compliance. 4. Do PART 7: CLOSE ACCESS. 5. Put the airplane back to a serviceable condition. PART 1: ACCESS 1. Get access to the overwing body frame to overwing stub beam joints at STA 559, STA 578 and STA 601 on the left and right side. Remove/keep seats, sidewall linings, insulation, carpets and floor panels. Refer to 737-300/400/500 AMM 25-22-00, 737-300/400/500 AMM 25-21-01, 737-300/400/500 AMM 25-27-15, 737-300/400/500 AMM 53-21-00 as accepted procedures. PART 2: OVERWING STUB BEAM UPPER CHORD AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION 1. RC - Do a surface High Frequency Eddy Current (HFEC) inspection for any crack in the overwing stub beam upper chord at STA 559, STA 578 and STA 601 in accordance with FIGURE 1 (left side) and FIGURE 2 (right side). PART 3: FRAME AND ADJACENT STRUCTURE AT STA 559, STA 578 AND STA 601 FROM STRINGER S-16 DOWN TO THE WING CENTER FUEL TANK UPPER PANEL - DETAILED INSPECTION 1. RC - Do a detailed inspection of the frames and adjacent structure at STA 559, STA 578 and STA 601 from stringer S-16 down to the wing center fuel tank upper panel for any crack in accordance with FIGURE 7 (left side) or FIGURE 8 (right side). PART 4: OVERWING STUB BEAM AT STA 578 - REPLACEMENT 1. Get access to the wing center fuel tank: a. Remove and retain the access panel. Refer to 737-300/400/500 AMM 28-11-31 as an accepted procedure. b. Purge the center fuel tank. Refer to 737-300/400/500 AMM 28-10-00 as an accepted procedure. WARNING: OBEY THE PRECAUTIONS FOR PURGING, AND FUEL TANK ENTRY. IF YOU DO NOT OBEY THE PRECAUTIONS, INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN OCCUR. 2. Remove the wing-to-body fairing to get access to fasteners common to the fuselage skin. Refer to 737-300/400/500 AMM 12-31-31 as an accepted procedure. 3. Disconnect flight control cables. Refer to 737-300/400/500 AMM 20-10-91 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 35 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 36 4. RC - Remove cracked overwing stub beam and do open hole HFEC inspections in accordance with FIGURE 3 (left side) or FIGURE 4 (right side). a. If any crack is found: (1) Contact The Boeing Company for repair instructions and do the repair. b. If no crack found: (1) Install new overwing stub beam in accordance with FIGURE 5 (left side) or FIGURE 6 (right side). 5. Rig and test the flight control cables. Refer to 737-300/400/500 AMM 27-09-14, 737-300/400/500 AMM 27-11-00, 737-300/400/500 AMM 27-31-00 and 737-300/400/500 AMM 27-51-00 as accepted procedures. 6. Close access to the center fuel tank. Install the retained center fuel tank access door. Refer to 737-300/400/500 AMM 28-10-00 and 737-300/400/500 AMM 28-11-31 as accepted procedures. CAUTION: MAKE SURE ALL UNWANTED PARTICLES AND MATERIALS ARE REMOVED FROM THE FUEL TANK. UNWANTED MATERIALS CAN COLLECT IN THE FUEL TANK, WHICH COULD CAUSE BLOCKAGE OR INCORRECT SYSTEM OPERATION. 7. Make sure that the removed and installed center fuel tank access door does not leak. Refer to 737-300/400/500 AMM 28-11-00 as an accepted procedure. 8. Install wing-to-body fairing. Refer to 737-300/400/500 AMM 12-31-31 as an accepted procedure. 9. Do PART 5: POST-REPLACEMENT INSPECTION OF THE OVERWING STUB BEAM UPPER CHORD AT STA 578 for any crack at the compliance time in accordance with Paragraph 1.E., Compliance. PART 5: POST-REPLACEMENT INSPECTION OF THE OVERWING STUB BEAM UPPER CHORD AT STA 578 1. Get access to the overwing body frame to overwing stub beam joints at STA 578 on the left and right side. Remove/keep seats, sidewall linings, insulation, carpets and floor panels. Refer to 737-300/400/500 AMM 25-22-00, 737-300/400/500 AMM 25-21-01, 737-300/400/500 AMM 25-27-15, 737-300/400/500 AMM 53-21-00 as accepted procedures. 2. RC - Do a surface High Frequency Eddy Current (HFEC) inspection for any crack in the overwing stub beam upper chord at STA 578 in accordance with FIGURE 13 (left side) or FIGURE 14 (right side). a. CONDITION 4: ANY CRACK FOUND DURING PART 5: POST-REPLACEMENT INSPECTION. (1) Contact The Boeing Company for repair instructions and do the repair. b. CONDITION 5: NO CRACK FOUND DURING PART 5: POST-REPLACEMENT INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 36 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 37 (1) Repeat PART 5: POST-REPLACEMENT INSPECTION OF THE OVERWING STUB BEAM UPPER CHORD AT STA 578 for any crack at the repeat interval in accordance with Paragraph 1.E., Compliance. PART 6: (RECOMMENDED ECONOMIC INSPECTION) FRAME INNER CHORD BETWEEN THE CREASE BEAM WEB AND THE WING CENTER FUEL TANK UPPER PANEL AT STA 578 - DETAILED OR HFEC INSPECTION 1. Get access to the overwing body frame to overwing stub beam joints at STA 578 on the left and right side. Remove/keep seats, sidewall linings, insulation, carpets and floor panels. Refer to 737-300/400/500 AMM 25-22-00, 737-300/400/500 AMM 25-21-01, 737-300/400/500 AMM 25-27-15, 737-300/400/500 AMM 53-21-00 as accepted procedures. 2. Do the OPTION 1 OR OPTION 2 inspections that follow. a. OPTION 1: DETAILED INSPECTION. Do a detailed inspection for any crack in the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578 in accordance with FIGURE 9 (left side) or FIGURE 10 (right side). b. OPTION 2: HFEC INSPECTION. Do a surface HFEC inspection for any crack in the frame inner chord between the crease beam web and the wing center fuel tank upper panel at STA 578 in accordance with FIGURE 11 (left side) or FIGURE 12 (right side). PART 7: CLOSE ACCESS 1. Install the floor panels, carpets, carpet risers and seats. Refer to 737-300/400/500 AMM 25-22-00, 737-300/400/500 AMM 25-21-01, 737-300/400/500 AMM 25-27-15, 737-300/400/500 AMM 53-21-00 as accepted procedures. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 37 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 38 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT STA 559 STA 639 FRAME (TYPICAL) STA ESCAPE HATCH 639 S-16L CREASE BEAM INNER CHORD STA 578 STA 559 LONGITUDINAL FLOOR BEAM STUB BEAM AT STA 601 WING CENTER FUEL TANK UPPER PANEL STUB BEAM AT STA 578 STUB BEAM → LBL 45.5 2331337 AT STA 559 FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 1 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1347 Work - See page 1 for details. 38 of 110 ### Page 39 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME CREASE BEAM OUTER CHORD S-16L- CREASE BEAM WEB CREASE BEAM INNER CHORD LONGITUDINAL FLOOR BEAM RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD STUB BEAM S-17L- INBD SIDE OF BODY PLUS CHORD STA 559 (VIEW LOOKING FORWARD) A-A RIVET COMMON TO THE STUB TYPICAL BEAM UPPER CHORD AND THE CRACK CREASE BEAM INNER CHORD CREASE BEAM INNER CHORD 1.0 INCH CENTERED ON FASTENER CREASE BEAM WEB STUB BEAM UPPER CHORL *HFEC UPPER CHORD STUB BEAM PROBE VIEW LOOKING UP PWD TYPICAL VIEW LOOKING OUTBOARD HFEC INSPECTION ZONE D-D FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 2 OF 5) Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1347 Work - See page 1 for details. 39 of 110 ### Page 40 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME CREASE BEAM OUTER CHORD S-16L- CREASE BEAM WEB CREASE BEAM INNER CHORD LONGITUDINAL FLOOR BEAM RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD STUB BEAM S-17L- SIDE OF BODY INBD PLUS CHORD STA 578 (VIEW LOOKING FORWARD) B-B RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD CREASE BEAM INNER CHORD 1.0 INCH CENTERED ON FASTENER CREASE BEAM WEB HFEC PROBE * STUB BEAM STUB BEAM UPPER UPPER CHORD CHORD VIEW LOOKING UP TYPICAL VIEW LOOKING OUTBOARD FWD 2331877 HFEC INSPECTION ZONE E-E FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 3 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1347 Work - See page 1 for details. 40 of 110 ### Page 41 (OCR) BOEING SERVICE BULLETIN 737-53A1347C ALERT ALERT • FRAME S-16L- CREASE BEAM OUTER CHORD CREASE BEAM WEB CREASE BEAM INNER LONGITUDINAL CHORD FLOOR BEAM RIVET COMMON TO THE STUB STUB BEAM UPPER CHORD AND THE BEAM CREASE BEAM INNER CHORD S-17L NBD SIDE OF BODY PLUS CHORD STA 601 (VIEW LOOKING FORWARD) C-C RIVET COMMON TO THE STUB TYPICAL BEAM UPPER CHORD AND THE CRACK CREASE BEAM INNER CHORD CREASE BEAM INNER CHORD 1.0 INCH CENTERED ON CREASE BEAM WEB FASTENER STUB BEAM *HFEC UPPER CHORD PROBE STUB BEAM UPPER CHORD VIEW LOOKING UP TYPICAL VIEW LOOKING OUTBOARD F-F WD HFEC INSPECTION ZONE FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 4 OF 5) Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 737-53A1347 41 of 110 ### Page 42 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 one side of the airplane. More DataQtyIdentificationNameTaskStep (a)1-Overwing Stub Beam Upper Chord at STA 559 Inspect1 (a)1-Overwing Stub Beam Upper Chord at STA 578 Inspect2 (a)1-Overwing Stub Beam Upper Chord at STA 601 Inspect3 (a) Do a surface High Frequency Eddy Current (HFEC) inspection for any crack in the overwing stub beam upper chord at the inspection zone locations (as shown) around the fastener and along the edge of the horizontal flange (1.0 inch centered on fastener) in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23. Use a HFEC pencil probe with a 90 degree, 0.5 inch long maximum drop. FIGURE 1: LEFT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 42 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 43 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT STA 559 STA 639 FRAME (TYPICAL) HATCH ESCAPE STA 639 S-16R CREASE 601 BEAM INNER CHORD STA 578 STA 559 LONGITUDINAI FLOOR BEAN STUB BEAM AT STA 601 WING CENTER FUEL TANK UPPER PANEL STUB BEAM RBL 45.5 STUB BEAM AT STA 578 2331907 AT STA 559 FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 1 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 110 ### Page 44 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME CREASE BEAM OUTER CHORD - S-16R CREASE BEAM WEB CREASE BEAM INNER CHORD LONGITUDINAL RIVET COMMON TO THE STUB FLOOR BEAM BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD STUB BEAM -S-17R INBD SIDE OF BODY PLUS CHORD STA 559 (VIEW LOOKING FORWARD) A-A 1) TYPICAL CRACK RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD 1.0 INCH CENTERED ON FASTENER CREASE BEAM INNER CHORD CREASE BEAM WEB STUB BEAM STUB BEAM UPPER CHORD HFEC* UPPER CHORD PROBE VIEW LOOKING UP FWD TYPICAL VIEW LOOKING OUTBOARD HFEC INSPECTION ZONE 2331951 D-D FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 2 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING LELVES-LEL PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 110 ### Page 45 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME CREASE BEAM OUTER CHORD CREASE BEAM WEB -S-16R CREASE BEAM INNEI CHORI LONGITUDINAL FLOOR BEAM RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD STUB BEAM -S-17R INBD SIDE OF BODY STA 578 PLUS CHORD (VIEW LOOKING FORWARD) B-B TYPICAL CRACK RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD 1.0 INCH CENTERED ON CREASE BEAM INNER FASTENER CHORD CREASE BEAM WEB STUB BEAM UPPER CHORD HFEC STUB BEAM PROBE VIEW LOOKING UP UPPER CHORD TYPICAL VIEW LOOKING OUTBOARD E-E FEC INSPECTION ZONE 2331966 FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 3 OF 5) Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1347 Work - See page 1 for details. 45 of 110 ### Page 46 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FRAME CREASE BEAM -S-16R OUTER CHORD CREASE BEAM WEB LONGITUDINAL CREASE BEAM INNEF FLOOR BEAM CHORL RIVET COMMON TO THE STUB BEAM UPPER CHORD AND THE STUB BEAM CREASE BEAM INNER CHORD -S-17R INBD SIDE OF BODY PLUS CHORD STA 601 (VIEW LOOKING FORWARD) C-C TYPICAL RIVET COMMON TO THE STUB CRACK BEAM UPPER CHORD AND THE CREASE BEAM INNER CHORD 1.0 INCH CREASE BEAM INNER CENTERED ON CHORD FASTENER • CREASE BEAM WEB STUB BEAM HFEC STUB BEAM UPPER CHORD PROBE UPPER CHORD VIEW LOOKING UP TYPICAL VIEW LOOKING OUTBOARD FWD F-F HFEC INSPECTION ZONE 2331992 FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 4 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 110 ### 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 one side of the airplane. More DataQtyIdentificationNameTaskStep (a)1-Overwing Stub Beam Upper Chord Inspect1 (a)1-Overwing Stub Beam Upper Chord at STA 578 Inspect2 (a)1-Overwing Stub Beam Upper Chord at STA 601 Inspect3 (a) Do a surface High Frequency Eddy Current (HFEC) inspection for any crack in the overwing stub beam upper chord at the inspection zone locations (as shown) around the fastener and along the edge of the horizontal flange (1.0 inch centered on fastener) in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23. Use a HFEC pencil probe with a 90 degree, 0.5 inch long maximum drop. FIGURE 2: RIGHT OVERWING STUB BEAM AT STA 559, STA 578 AND STA 601 - HFEC INSPECTION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 47 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FUSELAGE SKIN STA STA 578 578 FRAME INNER CHORD CREASE BEAM WEB S-16L CREASE BEAM INNER B CHORL CHORD STUB BEAM LONGITUDINAL FLOOR BEAM S-17L SIDE OF BODY PLUS CHORD LBL 70.85 WING CENTER FUEL TANK UPPER PANEL LBL 45.5 2332249 FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 1 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. OLL10 80 ### Page 49 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FILLER STUB SHIM BEAM 6 LOCATIONS SHIM (g SHIM 3 TEE CLIP 17 LOCATIONS SHIM INBD VIEW LOOKING FORWARD A-A 21 LOCATIONS 1 SHIM 9 LOCATIONS FILLER FILLER VIEW LOOKING AFT NBD B-B FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 2 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 110 ### Page 50 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT WING CENTER FUEL TANK UPPER PANEL / CREASE BEAM INNER CHORD LONGITUDINAL FILLER FLOOR BEAM STUB BEAM D FILLER BEAM WEB SIDE OF BODY INED PLUS CHORD VIEW LOOKING DOWN C-C 2384518 FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 3 OF 5) Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1347 Work - See page 1 for details. 50 of 110 ### Page 51 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FUSELAGE SKIN CREASE BEAM OUTER CHORD LONGITUDINAL _ 5 LOCATIONS FLOOR BEAM CREASE BEAM INNER CHORD •CREASE BEAM WEB WING CENTER FUEL TANK UPPER PANEL PLUS CHORD SIDE OF BODY 17 PLACES INBD VIEW LOOKING FORWARD D-D FRAME OUTER CHORD FRAME INNER, 12) 5 LOCATIONS CHORD FUSELAGE SKIN CREASE BEAM CREASE BEAM • SUPPORT BRACKET WEB 3 LOCATIONS (12 12) 3 LOCATIONS SIDE OF BODY FUEL TANK UPPERY PANEL WING CENTER PLUS CHORD UPPER 12 10 LOCATIONS PANEL FRAME WEB STRINGER INBD (ROTATED 180 DEG CW) VIEW LOOKING AFT 2332259 E-E FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 4 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 110 ### Page 52 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 one side of the airplane. More DataQtyIdentificationNameTaskStep (a)50-FastenersRemove1 (b)5-FastenersRemove2 -169-77282-5Tee ClipRemove / Keep3 -165-47973-43FillerRemove / Keep4 -165-47973-11FillerRemove / Keep5 (c)--FastenersRemove6 -1-Overwing Stub BeamRemove7 (d)1-FillerRemove8 -5-ShimRemove9 (e)---Clean10 (f) (g)9-Fastener HolesInspect11 (f)53-Fastener HolesInspect12 (c) (f)--Fastener HolesInspect13 (h)2-Fastener HoleInspect14 (h)--Fastener HolesInspect15 (a) Remove fasteners common to the cracked overwing stub beam in accordance with 737-400 SRM 51-40- 02. Make sure not to damage the holes when removing fasteners from the structure. (b) Remove fasteners common to the tee clip and fuselage skin in accordance with 737-400 SRM 51-40-02. Make sure not to damage the holes when removing fasteners from the structure. (c) Remove only the number of fasteners necessary to obtain clearance for the removal of the cracked overwing stub beam and installation of the new overwing stub beam. (d) Remove any tapered solid filler that may have been installed between the frame web and overwing stub beam. (e) The inspection area must be clean of dirt, grease, corrosion inhibiting compound, sealant, or other com- pounds that prevent a detailed inspection of the structure. Refer to SOPM 20-30-03 as an accepted pro- cedure for solvent cleaning. Make sure you only use approved sealant removal tools to remove sealant or other compounds. Refer to 737-300/400/500 AMM 51-31-00 as an accepted procedure. (f) Do an open hole HFEC inspection for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 11 or Procedure 16, 0.030 inch notch calibration. (g) Inspect the holes in the tee clip after it has been removed and cleaned. (h) Do a countersink inspection for any crack in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 1 or Procedure 3 or Procedure 4 and do an open hole inspection for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 11 or Procedure 16, 0.030 inch notch calibration. FIGURE 3: LEFT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 52 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 53 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FUSELAGE SKIN STA 578 FRAME INNER CHORD CREASE BEAM WEB S-16R CREASE BEAM INNEF CHORD CREASE BEAM OUTER CHORD STUB BEAM LONGITUDINAL FLOOR BEAM ~ S-17R RBL 70.85 SIDE OF BODY PLUS CHORD WING CENTER FUEL TANK UPPER PANEL 'RBL 45.5 2332789 FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 1 OF 5) Original Issue: December 09, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1347 Work - See page 1 for details. 53 of 110 ### Page 54 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT SHIM STUB FILLER BEAM 6 LOCATIONS 100 SHIM SHIM SHIM 17 LOCATIONS TEE CLIP 3 INBD VIEW LOOKING FORWARD A-A 1 21 LOCATIONS SHIM 11) 9 LOCATIONS FILLER FILLER VIEW LOOKING AFT B-B 2332791 FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 2 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 110 ### Page 55 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT VING CENTEF FUEL TANK UPPEF PANEL CREASE BEAM INNER CHORD FILLER LONGITUDINAL FLOOR BEAM 1 STUB BEAM D ED FILLER CREASE BEAM WEB SIDE OF BODY INBD PLUS CHORD VIEW LOOKING DOWN C-C 2332802 FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 3 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 110 ### Page 56 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FUSELAGE SKIN CREASE BEAM LONGITUDINAL OUTER CHORD FLOOR BEAM 5 LOCATIONS CREASE BEAM INNER CHORD 12 CREASE BEAM WEB WING CENTER FUEL TANK UPPER PANEL (12 SIDE OF BODY INBD 17 LOCATIONS PLUS CHORD VEW LOOKING FORWARD D-D FRAME OUTER CHORD 12) 5 LOCATIONS FRAME INNER FUSELAGE CHORD SKIN CREASE BEAM SUPPORT BRACKET WEASE BEAM 3 LOCATIONS ( 12) 3 LOCATIONS WING CENTER SIDE OF BODY FUEL TANK UPPER PLUS CHORD PANEL 10 LOCATIONS (12 UPPER FRAME WEB PANEL STRINGER VIEW LOOKING AFT (ROTATED 180 DEG CW) E-E • INBD 2385121 FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 4 OF 5) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 737-53A1347 Work - See page 1 for details. 56 of 110 ### Page 57 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 one side of the airplane. More DataQtyIdentificationNameTaskStep (a)50-FastenersRemove1 (b)5-FastenersRemove2 -169-77282-6Tee ClipRemove / Keep3 -165-47973-43FillerRemove / Keep4 -165-47973-11FillerRemove / Keep5 (c)--FastenersRemove6 -1-Overwing Stub BeamRemove7 (d)1-FillerRemove8 -5-ShimRemove9 (e)---Clean10 (f) (g)9-Fastener HolesInspect11 (f)53-Fastener HolesInspect12 (c) (f)--Fastener HolesInspect13 (h)2-Fastener HoleInspect14 (h)--Fastener HolesInspect15 (a) Remove fasteners common to the cracked overwing stub beam in accordance with 737-400 SRM 51-40- 02. Make sure not to damage the holes when removing fasteners from the structure. (b) Remove fasteners common to the tee clip and fuselage skin in accordance with 737-400 SRM 51-40-02. Make sure not to damage the holes when removing fasteners from the structure. (c) Remove only the number of fasteners necessary to obtain clearance for the removal of the cracked overwing stub beam and installation of the new overwing stub beam. (d) Remove any tapered solid filler that may have been installed between the frame web and overwing stub beam. (e) The inspection area must be clean of dirt, grease, corrosion inhibiting compound, sealant, or other com- pounds that prevent a detailed inspection of the structure. Refer to SOPM 20-30-03 as an accepted pro- cedure for solvent cleaning. Make sure you only use approved sealant removal tools to remove sealant or other compounds. Refer to 737-300/400/500 AMM 51-31-00 as an accepted procedure. (f) Do an open hole HFEC inspection for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 11 or Procedure 16, 0.030 inch calibration. (g) Inspect the holes in the tee clip after it has been removed and cleaned. (h) Do a countersink inspection for any crack in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 1 or Procedure 3 or Procedure 4 and do an open hole inspection for any crack in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 11 or Procedure 16, 0.03 inch notch calibration. FIGURE 4: RIGHT OVERWING STUB BEAM AT STA 578 - REMOVAL AND HFEC OPEN HOLE INSPECTION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: December 09, 2015 737-53A1347 57 of 110 BOEING SERVICE BULLETIN 737-53A1347 ALERTALERT ### Page 58 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT FUSELAGE SKIN STA STA 578 578 FRAME INNER CHORD CREASE BEAM WEB S-16L CREASE BEAM INNER B CHORD CREASE BEAM OUTER CHORD STUB BEAM S-17L LONGITUDINAL FLOOR BEAM SIDE OF BODY PLUS CHORD LBL 70.85 WING CENTER FUEL TANK UPPER PANEL LBL 2333239 45.5 FIGURE 5: LEFT OVERWING STUB BEAM AT STA 578 - INSTALLATION (SHEET 1 OF 11) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 110 ### Page 59 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT CREASE BEAM WEB 6 LOCATIONS FILLER (19) TEE CLIP AND SHIM CIEN O WIHS * 17 11) KIEN LIEN KIEN HİSN SHIM 18 22 23 17 LOCATIONS INBD A SEAT STA 578 (VIEW LOOKING FORWARD) A-A FIGURE 5: LEFT OVERWING STUB BEAM AT STA 578 - INSTALLATION (SHEET 2 OF 11) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 110 ### Page 60 (OCR) BOEING SERVICE BULLETIN 737-53A1347 ALERT ALERT (17) 5 LOCATIONS FILLER 28) 3 LOCATIONS 17 1 3 LOCATIONS ® SHIM 9% € STUB BEAM _SIDE OF BODY PLUS CHORD 16) 10 LOCATIONS FRAME TAPERED WEB 18 22 23 ·112N • SHIM FILLER STA 578 FILLET INBD (VIEW LOOKING AFT) SEAL B-B FIGURE 5: LEFT OVERWING STUB BEAM AT STA 578 - INSTALLATION (SHEET 3 OF 11) Original Issue: December 09, 2015 Export Controlled ECCN: 9E991 - BOEING 737-53A1347 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 110 The text continues at https://openairdocs.org/service-documents/boeing/737-53a1347/file/048023faf2fd.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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