# Boeing Alert Service Bulletin 737-53A1322: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0538; AD 2014-01-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 737-53A1322](https://openairdocs.org/service-documents/boeing/737-53a1322.md) - Title as filed: Boeing - Service Bulletin - Pages: 229 - PDF: https://openairdocs.org/files/sha256/b4/fc/b4fc052392898ee4d8a54a7bf73d95ebe263524ad3489e5a3050f3a7b70ca4a6 - Page: https://openairdocs.org/service-documents/boeing/737-53a1322/file/b4fc05239289 ## 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: 737-53A1322 Original Issue: November 05, 2012 ATA System: 5312 5311 SUBJECT: FUSELAGE - Stringers and Other Longitudinal Members - Stringer Splices and Butt Straps at Body Station 360 and Body Station 908, Stringer S-10L to S-10R - Inspection and Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2012 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 Unpublished Work.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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, 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. BOEING is a trademark of Boeing Management Company. Original Issue: November 05, 2012 737-53A1322 1 of 229 7.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 2 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary ...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity ................................................ 9 1. Airplanes ............................................. 9 2. Spares Affected ........................................ 2 5 B. Concurrent Requirements ...................................... 2 5 C. Reason ................................................ 2 5 D. Description .............................................. 2 6 E. Compliance .............................................. 2 7 F. Approval ............................................... 4 2 G. Manpower .............................................. 4 3 H. Weight and Balance Changes .................................... 4 8 I. Electrical Load Data ......................................... 4 8 J. References .............................................. 4 8 1. Existing Data: ......................................... 4 8 2. Data Supplied with this Service Bulletin: ........................... 4 9 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 9 K. Publications Affected ........................................ 5 0 L. Interchangeability and Intermixability of Parts ........................... 5 0 M. Software Accomplishment Summary ................................ 5 0 2. MATERIAL INFORMATION ........................................ 5 1 A. Material - Price and Availability ................................... 5 1 B. Industry Support Information .................................... 5 1 C. Parts Necessary for Each Airplane ................................. 5 1 1. Kits/Parts ............................................ 5 1 2. Parts and Materials Supplied by the Operator ........................ 5 3 3. Parts Modified and Reidentified ................................ 5 4 4. Parts Removed and Not Replaced .............................. 5 4 D. Parts Necessary to Change Spares ................................. 5 5 E. Special Tooling - Price and Availability ............................... 5 5 F. Special Tooling Necessary to do this Service Bulletin ....................... 5 5 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 7 A. GENERAL INFORMATION ..................................... 5 7 B. WORK INSTRUCTIONS ....................................... 5 8 FIGURE 1: STA 360 AND STA 908, ZONE A AND B (S-10L TO S-10R) - STRINGER SPLICE AND BUTT STRAP - INTERNAL DETAILED INSPECTION [Group 2-4] ................. 7 0 FIGURE 2: STA 360 AND STA 908, ZONE A (S-5L TO S-3L, S-3R TO S-5R) OPTION 1 - BUTT STRAP - EDDY CURRENT INSPECTION [Group 2-4] ......................... 7 4 FIGURE 3: STA 360 AND STA 908, ZONE A (S-5L TO S-3L, S-3R TO S-5R) OPTION 2 - BUTT STRAP - EDDY CURRENT INSPECTION [Group 2-4] ......................... 7 9 FIGURE 4: STA 360 AND STA 908, ZONE B (S-10L TO S-5L, S-3L TO S-3R, S-5R TO S-10R) - BUTT STRAP - INTERNAL EDDY CURRENT INSPECTION [Group 2-4] ............. 8 4 FIGURE 5: STA 908, ZONE A AND B (S-10L TO S-10R) - STRINGER SPLICE AND BUTT STRAP - INTERNAL DETAILED INSPECTION [Group 5-6] ...................... 9 0 FIGURE 6: STA 908, ZONE A (S-5L TO S-3L, S-3R TO S-5R) OPTION 1 - BUTT STRAP - INTERNAL EDDY CURRENT INSPECTION [Group 5-6] ......................... 9 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 3 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 4 FIGURE 7: STA 908, ZONE A (S-5L TO S-3L, S-3R TO S-5R) OPTION 2 - BUTT STRAP - EDDY CURRENT INSPECTION [Group 5-6] ................................... 9 7 FIGURE 8: STA 908, ZONE B (S-10L TO S-5L, S-3L TO S-3R, S-5R TO S-10R) - BUTT STRAP - INTERNAL EDDY CURRENT INSPECTION [Group 5-6] ........................ 1 0 0 FIGURE 9: STA 360 AND STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 2, Configuration 1-4] ................... 1 0 5 FIGURE 10: STA 360 AND STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 2, Configuration 5-8] ................... 1 1 2 FIGURE 11: STA 360 AND STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 3, Configuration 1] .................... 1 1 5 FIGURE 12: STA 360 AND STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 3, Configuration 2; Group 4] ............... 1 2 1 FIGURE 13: STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 5, Configuration 1-4] ...................... 1 2 4 FIGURE 14: STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 5, Configuration 5-8] ...................... 1 2 9 FIGURE 15: STA 908(S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 6, Configuration 1] ....................... 1 3 2 FIGURE 16: STA 908 (S-5L TO S-3L, S-3R TO S-5R) - BUTT STRAP - FASTENER REMOVAL AND REINSTALLATION [Group 6, Configuration 2] ....................... 1 3 6 FIGURE 17: STA 360 (S-5L TO S-6R, S-8R TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 2, Configuration 1-4] ....................................... 1 3 9 FIGURE 18: STA 908 (S-10L TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 2, Configuration 1-4; Group 5, Configuration 1-4] ............................... 1 5 0 FIGURE 19: STA 360 (S-5L TO S-6R, S-8R TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 2, Configuration 5-8] ....................................... 1 5 9 FIGURE 20: STA 908 (S-10L TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 2, Configuration 5-8; Group 5, Configuration 5-8] ............................... 1 6 8 FIGURE 21: STA 360 (S-5L TO S-6R, S-8R TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 3, Configuration 1] ........................................ 1 7 6 FIGURE 22: STA 908 (S-10L TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 3, 6, Configuration 1 ] ................................................ 1 8 6 FIGURE 23: STA 360 (S-5L TO S-6R, S-8R TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 3, Configuration 2; Group 4] ................................... 1 9 5 FIGURE 24: STA 908 (S-10L TO S-10R) - STRINGER SPLICE - REPLACEMENT [Group 3, Configuration 2; Group 4; Group 6, Configuration 2] ............................ 2 0 4 APPENDIX A: STRINGER SPLICE DATA .................................. 2 1 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 4 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 5 Commercial Airplanes 737 Service Bulletin ALERT SummaryNumber: 737-53A1322Original Issue: November 05, 2012 ATA System: 5312 5311 SUBJECT: FUSELAGE - Stringers and Other Longitudinal Members - Stringer Splices and Butt Straps at Body Station 360 and Body Station 908, Stringer S-10L to S-10R - Inspection and Replacement 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 Accomplishment of the inspections and replacement given in this Service Bulletin (SB) will make sure that stringer splice and butt strap cracks are found and repaired. Fuselage skin vertical chem-mill step cracks can interact with stringer splice cracks and butt strap cracks. The interaction of cracking with the three structural elements may result in the airplane not being able to sustain limit load requirements and potential uncontrolled decompression. Boeing received fleet reports of 197 stringer splice cracks at Body Station STA 360 and STA 908, between Stringer S-10L and S-10R, 16 butt strap cracks between S-5L and S-3L, S-3R and S-5R and 12 vertical chem-mill fuselage skin cracks at butt joints as addressed in SB 737-53A1210 and SB 737-53A1234. Additionally, Boeing received one report of all three structural elements cracking on the same airplane during a maintenance inspection. Analysis by Boeing indicates that cracking of the stringer splices is attributed to airplane fatigue loads. Cracking of the butt strap at STA 360 and STA 908 is attributed to fatigue loading from S-4 lap joint. Boeing Service Related Problem (SRP) 737-SRP-53-0362 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., ComplianceYesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 5 of 229 ### Page 6 ReferenceAffectedPlanning Data 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 Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Group 1: On Group 1 airplanes, contact Boeing to get instructions for the inspection, and/or repair for this SB 737-53A1322 Original Issue, and do the work instructed by Boeing. Group 2-6: Do internal detailed inspections of the stringer splices and the butt straps for cracks. If any crack is found in the stringer splice, remove and replace with a new splice. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. Do internal High Frequency Eddy Current (HFEC) surface inspections, internal Low Frequency Eddy Current (LFEC) inspections and HFEC open hole rotary probe inspections of the butt straps for cracks. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. If no crack is found, close access and put the airplane back to a serviceable condition. Group 2, Configuration 5-8; Group 3, Configuration 2; Group 5, Configuration 5-8; Group 6, Configuration 2: Economic Consideration: For airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177, Boeing recommends accomplishing the inspections in accordance with SB 737-53A1322 Original Issue while SB 737-53A1177 lap modification is being accomplished. EFFECTIVITY 737-100/-200/-200C/-300/-400/-500 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 6 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 7 INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operator Supplied Parts/Materials. 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: November 05, 2012 737-53A1322 7 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 8 (OCR) BOEING SERVICE BULLETIN 737-53A1322 ALERT ALERT DO INTERNAL DETAILED INSPECTIONS OF THE STRINGER SPLICES AND THE BUTT STRAPS FOR CRACKS AT BODY STATION 360 AND BODY STATION 908, S-10L TO S-10R. DO EDDY CURRENT INSPECTIONS OF THE BUTT STRAPS FOR CRACKS AT BODY STATION 360 AND BODY STATION 908, S-10L TO S-10R. FOR ZONE A (S-5L TO S-3L, S-3R TO S-5R): OPTION 1 - DO INTERNAL HIGH FREQUENCY EDDY CURRENT SURFACE INSPECTIONS, INTERNAL LOW FREQUENCY EDDY CURRENT INSPECTIONS OF THE BUTT STRAPS FOR CRACKS, AND DO A HIGH FREQUENCY EDDY CURRENT OPEN HOLE ROTARY PROBE INSPECTION AT ONE (1) LOCATION OF THE BUTT STRAP FOR CRACKS. OPTION 2 - DO INTERNAL HIGH FREQUENCY EDDY CURRENT SURFACE INSPECTIONS, INTERNAL LOW FREQUENCY EDDY CURRENT INSPECTIONS AND HIGH FREQUENCY EDDY CURRENT OPEN HOLE ROTARY PROBE INSPECTIONS OF THE BUTT STRAPS FOR CRACKS. FOR ZONE B (S-10L TO S-5L, S-3L TO S-3R, S-5R TO S-10R): DO INTERNAL HIGH FREQUENCY EDDY CURRENT SURFACE INSPECTIONS AND INTERNAL LOW FREQUENCY EDDY CURRENT INSPECTIONS OF THE BUTT STRAPS FOR CRACKS STA 908 STA 360 S-10R 000000000000 S-10L 2118578 Original Issue: November 05, 2012 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 737-53A1322 Work - See page 1 for details. 8 of 229 ### Page 9 Commercial Airplanes 737 Service Bulletin ALERT Number: 737-53A1322 Original Issue: November 05, 2012 ATA System: 5312 5311 SUBJECT: FUSELAGE - Stringers and Other Longitudinal Members - Stringer Splices and Butt Straps at Body Station 360 and Body Station 908, Stringer S-10L to S-10R - Inspection and Replacement 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 This service bulletin is for the airplanes shown below. Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 737-100/-200/-200C Airplane line numbers 1-291.-1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 9 of 229 ### Page 10 DESCRIPTIONCONFIGURATIONGROUP 737-200 Airplane line numbers 292-519.-2 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 1 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modification in accordance with SB 737-53-1076 but have not accomplished SB 737-53A1039. 2 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modification in accordance with SB 737-53A1039 but have not accomplished SB 737-53-1076. 3 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and have not accomplished preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 4 Airplanes that have accomplished the preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039 and have not accomplished lap modification in accordance with SB 737-53A1177. 5 Airplanes that have accomplished the preventive modification in accordance with SB 737-53-1076 and have not accomplished modifications in accordance with SB 737-53A1177 and SB 737-53A1039. 6 Airplanes that have accomplished the preventive modification in accordance with SB 737-53A1039 and have not accomplished modifications in accordance with SB 737-53A1177 or SB 737-53-1076. 7 Airplanes that have not accomplished the lap modification in accordance with SB 737-53A1177 and have not accomplished preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 8 737-200/-300/-400/-500 Airplane line numbers 520-2552.-3 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. 1 Airplanes that have not accomplished the lap modification in accordance with SB 737-53A1177. 2 737-300/-400/-500 Airplane line numbers 2553-3132.-4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 10 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 11 DESCRIPTIONCONFIGURATIONGROUP 737-200C Airplane line numbers 292-519.-5 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 1 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modification in accordance with SB 737-53-1076 but have not accomplished SB 737-53A1039. 2 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and preventive modification in accordance with SB 737-53A1039 but have not accomplished SB 737-53-1076. 3 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177 and have not accomplished preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 4 Airplanes that have accomplished the preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039 and have not accomplished lap modification in accordance with SB 737-53A1177. 5 Airplanes that have accomplished the preventive modification in accordance with SB 737-53-1076 and have not accomplished modifications in accordance with SB 737-53A1177 and SB 737-53A1039. 6 Airplanes that have accomplished the preventive modification in accordance with SB 737-53A1039 and have not accomplished modifications in accordance with SB 737-53A1177 or SB 737-53-1076. 7 Airplanes that have not accomplished the lap modification in accordance with SB 737-53A1177 and have not accomplished preventive modifications in accordance with SB 737-53-1076 and SB 737-53A1039. 8 737-200C Airplane line numbers 520-1113.-6 Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. 1 Airplanes that have not accomplished the lap modification in accordance with SB 737-53A1177. 2 Airplane Models: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 11 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 12 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 GroupVariable Number 1PA001 - PA022 1PA099 1PA231 - PA232 1PC001 - PC005 1PG001 - PG075 1PG199 1PG201 - PG230 1PG251 - PG255 1PG271 - PG279 1PG301 - PG314 1PG331 - PG332 1PG351 - PG356 1PG375 1PG401 - PG403 1PG431 - PG442 1PG471 - PG475 1PG501 - PG505 1PG571 - PG583 2PG584 - PG586 1PG621 - PG630 1PG651 - PG652 1PG701 - PG705 2PH001 2PH011 - PH013 2PH021 - PH024 1PH701 - PH715 1PH731 - PH732 1PH741 - PH742 2PH743 1PJ001 - PJ002 2PJ003 - PJ006 3PJ007 - PJ009 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 12 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 13 GroupVariable Number 1PJ031 - PJ032 1PJ071 - PJ072 1PJ101 - PJ104 2PJ105 - PJ111 3PJ112 - PJ119 2PJ201 - PJ219 3PJ301 - PJ302 3PJ551 4PJ552 - PJ561 4PJ601 - PJ615 4PJ811 4PJ816 - PJ817 2PK026 - PK029 2PK041 - PK053 2PK061 - PK070 2PK081 3PK082 2PK091 - PK099 2PK101 - PK103 2PK111 - PK120 2PK141 - PK146 2PK201 - PK203 3PK204 2PK211 - PK212 3PK213 - PK220 2PK221 3PK222 - PK223 2PK231 - PK235 3PK236 - PK240 2PK241 2PK251 - PK258 2PK271 - PK273 3PK274 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 13 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 14 GroupVariable Number 2PK281 3PK282 - PK289 2PK291 2PK301 - PK306 3PK307 - PK310 2PK311 - PK315 3PK316 - PK318 2PK341 2PK351 - PK353 3PK354 - PK361 2PK391 3PK431 - PK433 2PK451 - PK452 2PK461 - PK465 3PK466 - PK469 3PK495 2PK501 3PK502 - PK504 2PK511 3PK512 - PK515 3PK519 2PK521 3PK522 - PK528 3PK541 - PK565 3PK581 3PK591 - PK599 3PK601 - PK617 3PK621 - PK637 3PK641 - PK642 3PK661 - PK666 3PK671 - PK681 3PK691 - PK697 3PK711 - PK716 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 14 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 15 GroupVariable Number 3PK731 - PK765 3PK771 - PK779 3PK801 - PK804 3PK819 - PK827 3PK830 3PK861 - PK863 3PK871 - PK874 3PK881 - PK884 3PK901 - PK938 3PK971 - PK974 2PL001 - PL002 3PL003 - PL028 3PL061 3PL081 3PL101 - PL113 3PL151 3PL171 - PL172 3PL201 - PL203 3PL221 3PL401 - PL417 3PL421 3PL441 3PL451 - PL456 3PL471 3PL491 3PL501 - PL506 3PL551 - PL562 3PL581 3PL601 - PL603 3PL611 3PL621 - PL626 3PL631 - PL632 1PL711 - PL712 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 15 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 16 GroupVariable Number 1PL716 2PL717 - PL743 3PL744 - PL747 2PL756 2PL758 2PL761 - PL767 3PL768 - PL770 2PL781 - PL782 3PL783 - PL788 2PL793 1PL801 - PL803 3PM001 - PM006 3PM016 - PM017 3PM021 - PM023 3PM051 - PM066 3PM101 - PM119 3PM141 - PM142 3PM171 3PM181 3PM251 - PM255 3PM281 - PM283 3PM381 - PM399 3PM401 - PM417 3PM541 - PM542 4PM543 - PM550 3PM551 - PM564 3PN001 - PN002 3PN021 - PN043 3PN081 - PN086 3PN101 - PN117 3PN131 - PN163 3PN401 - PN420 3PN431 - PN433 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 16 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 17 GroupVariable Number 3PN451 - PN456 3PN471 - PN474 3PN481 3PN491 - PN493 3PN501 - PN502 3PN511 - PN512 3PN521 3PP001 - PP054 3PP101 - PP169 3PP181 - PP199 3PP201 - PP205 3PP221 3PP231 - PP243 3PP281 - PP286 3PP301 - PP305 3PP351 - PP353 3PP376 - PP384 3PP391 - PP393 3PP401 - PP440 3PP471 - PP475 3PP501 - PP517 4PP518 - PP520 3PP521 - PP522 3PP631 - PP634 3PP651 - PP652 3PP671 - PP699 3PP701 - PP733 3PP771 - PP779 3PP801 - PP808 3PP821 - PP827 3PP831 - PP848 3PP851 - PP852 3PP861 - PP875 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 17 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 18 GroupVariable Number 4PP876 - PP877 3PP891 - PP899 3PP901 - PP936 3PP946 - PP948 3PP951 - PP952 3PP961 - PP967 3PP981 - PP991 3PP993 3PQ001 - PQ016 3PQ026 - PQ041 3PQ051 - PQ092 3PQ101 - PQ199 3PQ201 - PQ202 3PQ221 - PQ237 3PQ241 - PQ243 3PQ251 - PQ267 3PQ281 - PQ296 4PQ297 - PQ299 3PQ301 - PQ307 3PQ331 - PQ332 3PQ341 - PQ344 4PQ345 - PQ348 3PQ361 - PQ369 4PQ370 - PQ373 4PQ391 - PQ395 3PQ401 - PQ407 4PQ408 - PQ410 3PQ411 - PQ413 4PQ414 - PQ418 3PQ421 4PQ431 - PQ438 4PQ447 - PQ448 4PQ451 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 18 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 19 GroupVariable Number 4PQ454 3PQ471 - PQ472 4PQ473 - PQ475 3PQ479 - PQ481 3PQ486 - PQ487 3PQ491 - PQ493 3PQ771 4PQ772 3PQ791 - PQ793 3PQ801 - PQ805 3PQ931 - PQ932 4PQ933 - PQ935 4PQ951 4PQ971 - PQ997 4PR001 - PR017 4PR021 - PR034 4PR041 - PR045 4PR061 - PR072 4PR077 - PR082 4PR091 - PR092 4PR096 4PR101 4PR121 - PR122 4PR131 - PR132 4PR141 - PR143 4PR161 - PR172 4PR181 3PS601 - PS616 4PS617 - PS630 3PS631 3PS636 - PS638 3PS641 - PS644 3PS651 - PS657 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 19 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 20 GroupVariable Number 3PS666 - PS669 3PS691 - PS692 3PS701 - PS703 4PS704 - PS706 3PS751 - PS762 4PS763 - PS799 4PS811 4PS836 - PS837 4PS841 - PS846 4PS851 - PS852 4PS856 4PS861 - PS863 4PS866 - PS868 4PS871 - PS874 4PS896 - PS897 4PS901 - PS941 4PS956 - PS957 4PS961 - PS963 4PS971 - PS978 3PT001 - PT011 4PT012 - PT015 3PT021 - PT028 4PT029 - PT031 3PT041 - PT063 4PT064 3PT101 - PT105 3PT121 - PT125 4PT126 - PT138 3PT146 - PT148 3PT161 - PT170 3PT181 - PT187 4PT188 3PT211 - PT220 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 20 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 21 GroupVariable Number 3PT295 3PT301 - PT306 4PT307 - PT309 3PT331 - PT360 3PT381 - PT399 3PT401 - PT438 3PT501 - PT512 4PT513 - PT517 3PT561 - PT565 3PT581 - PT584 4PT585 - PT586 3PT611 - PT621 3PT641 - PT642 4PT643 - PT644 3PT651 - PT655 4PT656 3PT671 - PT672 4PT681 - PT685 3PT701 - PT703 4PT716 - PT717 4PT721 - PT725 4PT801 - PT834 4PT851 - PT854 4PT871 - PT886 4PT901 - PT930 4PT971 - PT973 4PT981 - PT985 4PT996 3PU001 - PU025 4PU301 4PU311 - PU313 3PV001 - PV055 3PV201 - PV203 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 21 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 22 GroupVariable Number 4PV204 - PV209 4PV226 - PV229 3PV231 - PV237 3PV271 - PV272 3PV281 - PV283 4PV284 - PV287 4PV296 4PV301 - PV302 4PV351 4PV356 - PV357 3PW001 - PW054 3PW061 - PW068 3PW072 4PW086 - PW088 3PW091 - PW094 3PW101 - PW102 3PW106 3PW111 - PW120 3PW156 - PW157 3PW161 - PW167 4PW168 - PW171 3PW201 - PW244 4PW245 - PW252 3PW261 4PW262 - PW264 3PW265 - PW268 4PW271 - PW276 3PW278 3PW281 4PW282 - PW292 3PW293 3PW296 3PW301 - PW327 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 22 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 23 GroupVariable Number 4PW401 - PW408 4PW411 - PW418 4PW421 - PW424 4PW431 - PW435 4PW441 - PW450 3PW461 - PW467 3PW501 - PW504 3PW511 - PW520 4PW521 - PW522 4PW524 - PW525 3PW526 4PW527 - PW530 3PW531 - PW546 4PW547 - PW550 3PW556 - PW557 3PW561 - PW564 3PW571 - PW576 3PW591 - PW596 3PW611 - PW620 4PW621 - PW622 3PW631 - PW634 4PW635 - PW637 3PW661 - PW662 3PW681 - PW683 3PW701 - PW702 3PW711 - PW717 3PW741 - PW742 3PW761 3PW771 4PW831 4PW851 - PW856 1PX071 1PX701 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 23 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 24 GroupVariable Number 1PY001 - PY008 1PY021 5PY022 1PY031 5PY036 - PY037 5PY046 - PY048 5PY051 - PY053 6PY056 - PY057 5PY101 - PY103 5PY111 - PY113 5PY131 - PY133 6PY134 - PY135 5PY141 - PY143 5PY151 - PY152 6PY153 - PY154 5PY156 - PY157 5PY161 - PY162 5PY166 5PY191 5PY201 5PY221 - PY222 6PY231 6PY241 - PY244 6PY270 5PY271 - PY274 6PY275 5PY281 5PY286 1PY301 - PY304 1PY321 - PY323 1PY341 - PY346 1PY361 - PY362 1PY381 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 24 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 25 GroupVariable Number 6PY401 6PY409 - PY411 6PY421 - PY422 6PY441 6PY451 6PY461 - PY463 6PY591 - PY595 6PY611 - PY612 6PY621 6PY631 6PY651 6PY671 - PY672 6PY721 6PY741 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of the inspections and replacement given in this Service Bulletin (SB) will make sure that stringer splice and butt strap cracks are found and repaired. Fuselage skin vertical chem-mill step cracks can interact with stringer splice cracks and butt strap cracks. The interaction of cracking with the three structural elements may result in the airplane not being able to sustain limit load requirements and potential uncontrolled decompression. Boeing received fleet reports of 197 stringer splice cracks at Body Station STA 360 and STA 908, between Stringer S-10L and S-10R, 16 butt strap cracks between S-5L and S-3L, S-3R and S-5R and 12 vertical chem-mill fuselage skin cracks at butt joints as addressed in SB 737-53A1210 and SB 737-53A1234. Additionally, Boeing received one report of all three structural elements cracking on the same airplane during a maintenance inspection. Analysis by Boeing indicates that cracking of the stringer splices is attributed to airplane fatigue loads. Cracking of the butt strap at STA 360 and STA 908 is attributed to fatigue loading from S-4 lap joint. Boeing Service Related Problem (SRP) 737-SRP-53-0362 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 25 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 26 D. Description Group 1: On Group 1 airplanes, contact Boeing to get instructions for the inspection, and/or repair for this SB 737-53A1322 Original Issue, and do the work instructed by Boeing. Group 2-6: Do internal detailed inspections of the stringer splices and the butt straps for cracks. If any crack is found in the stringer splice, remove and replace with a new splice. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. Do internal High Frequency Eddy Current (HFEC) surface inspections, internal Low Frequency Eddy Current (LFEC) inspections and HFEC open hole rotary probe inspections of the butt straps for cracks. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. If no crack is found, close access and put the airplane back to a serviceable condition. Group 2, Configuration 5-8; Group 3, Configuration 2; Group 5, Configuration 5-8; Group 6, Configuration 2: ECONOMIC CONSIDERATION: For airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177, Boeing recommends accomplishing the inspections in accordance with SB 737-53A1322 Original Issue while SB 737-53A1177 lap modification is being accomplished. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 1-7, 1-8737-100, 737-200, 737-200C Group 2-3: Affected Maintenance Zones ZoneModel 1-7, 1-8737-200 Group 3-4: Affected Maintenance Zones ZoneModel 107, 108737-300, 737-400, 737-500 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 26 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 27 Group 5-6: Affected Maintenance Zones ZoneModel 1-7, 1-8737-200C 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. 1. Compliance Time Exceptions: If an existing fuselage skin repair is common to the inspection area of the butt joint and meets the criteria shown below, then the initial compliance time for the area that was previously repaired and inspected is from the applicable compliance time specified in the tables since the time of the repair accomplishment or within 5,000 flight cycles after the original issue date of this service bulletin, whichever occurs later. The inspections of the non-repaired area do not change. a. The installed repair was approved by the FAA or by a Boeing company authorized representative who was authorized by the FAA to make such findings. b. The repair installs a 0.032 inch thick, 2024-T3 clad doubler and 0.050 inch thick 2024-T3 clad tripler or only a 0.050 inch thick 2024-T3 clad doubler similar to 737-100/200 SRM 53-30-3, Figure 48, or 737-300/400/500 SRM 53-00-01, Repair 31. c. The repair installs solid rivets common to the inspection area. d. At the time of the skin repair an open hole rotary inspection in accordance with 737 NDT Part 6, 51-00-00, Figure 16 was accomplished for all fastener holes common to the skin repair and the butt joint inspection area. Group 1: Table 1: STA 360 and STA 908 (S-10L to S-10R) Inspection. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 5,000 flight cycles af- ter the original issue date of this service bul- letin. Before 50,000 total flight cy- cles. Contact Boeing to get in- structions for the inspec- tion, and/or repair for this service bulletin and do the work instructed by Boeing. All Airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 27 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 28 Group 2, Configuration 1-4; Group 3, Configuration 1: Table 2: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection – Airplanes that have ac- complished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 55,000 total flight cy- cles. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. 5,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 28 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 29 Group 2, Configuration 1-4; Group 3, Configuration 1: Table 2: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection – Airplanes that have ac- complished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 55,000 flight cycles af- ter butt strap replacement. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) 5,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 29 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 30 Group 2, Configuration 5-8; Group 3, Configuration 2: Table 3: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 50,000 total flight cy- cles. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. 5,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 30 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 31 Group 2, Configuration 5-8; Group 3, Configuration 2: Table 3: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 50,000 flight cycles af- ter butt strap replacement. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) 5,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 31 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 32 Group 4: Table 4: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 50,000 total flight cy- cles. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. 11,500 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 32 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 33 Group 4: Table 4: STA 360 and STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 50,000 flight cycles af- ter butt strap replacement. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) 11,500 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 1:STA 908- Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks, and do an HFEC open hole ro- tary probe inspection at one (1) location of the butt strap for cracks in accordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. Option 2: 20,000 flight cy- cles. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections, internal LFEC inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 33 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 34 Group 2, Configuration 1-4; Group 3, Configuration 1: Table 5: STA 360 and STA 908 Zone B (S-10L to S-5L, S-3L to S-3R, S-5R to S-10R) Inspection - Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 20,000 flight cy- cles. STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 55,000 total flight cy- cles. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. (b) 20,000 flight cy- cles. (b) STA 908 - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 55,000 flight cycles af- ter butt strap replacement. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) (b) 20,000 flight cy- cles. (b) STA 908 - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. (b) Stringer splices S-3L, S-5L, S-3R and S-5R are inspected at times defined in Paragraph 1.E., Compliance, Table 2. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 34 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 35 Group 2, Configuration 5-8; Group 3, Configuration 2; Group 4: Table 6: STA 360 and STA 908 Zone B (S-10L to S-5L, S-3L to S-3R, S-5R to S-10R) Inspection - Airplanes that have not accomplished the lap modification or are not effective for the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 20,000 flight cy- cles. STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 50,000 total flight cy- cles. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. (b) 20,000 flight cy- cles. (b) STA 908 - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. STA 360Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 50,000 flight cycles af- ter butt strap replacement. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) (b) 20,000 flight cy- cles. (b) STA 908 - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. (b) Stringer splices S-3L, S-5L, S-3R and S-5R are inspected at times defined in Paragraph 1.E., Compliance, Table 3 or Table 4 as applicable. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 35 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 36 Group 5, Configuration 1-4; Group 6, Configuration 1: Table 7: STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 55,000 total flight cy- cles. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 36 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 37 Group 5, Configuration 1-4; Group 6, Configuration 1: Table 7: STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 55,000 flight cycles af- ter butt strap replacement. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 37 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 38 Group 5, Configuration 5-8; Group 6, Configuration 2: Table 8: STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 50,000 total flight cy- cles. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections and HFEC open hole rotary probe inspec- tions the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 38 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 39 Group 5, Configuration 5-8; Group 6, Configuration 2: Table 8: STA 908 Zone A (S-5L to S-3L, S-3R to S-5R) Inspection - Airplanes that do not have the lap modification accomplished in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition Option 1:STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 50,000 flight cycles af- ter butt strap replacement. Option 1: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) 13,000 flight cy- cles. Option 2: 20,000 flight cy- cles. - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. Option 2: - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. - Do internal HFEC surface inspections and HFEC open hole rotary probe inspec- tions of the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 39 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 40 Group 5, Configuration 1-4; Group 6, Configuration 1: Table 9: STA 908 Zone B (S-10L to S-5L, S-3L to S-3R, S-5R to S-10R) Inspection - Airplanes that have accomplished the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 20,000 flight cy- cles. STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 55,000 total flight cy- cles. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. (b) - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 55,000 flight cycles af- ter butt strap replacement. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) (b) - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. (b) Stringer splices S-3L, S-5L, S-3R and S-5R are inspected at times defined in Paragraph 1.E., Compliance, Table 7. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 40 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 41 Group 5, Configuration 5-8; Group 6, Configuration 2: Table 10: STA 908 Zone B (S-10L to S-5L, S-3L to S-3R, S-5R to S-10R) Inspection - Airplanes that have not accomplished the lap modification or are not effective for the lap modification in accordance with SB 737-53A1177. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 20,000 flight cy- cles. STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Before 50,000 total flight cy- cles. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. All Airplanes, ex- cept those on which a butt strap was previ- ously replaced. (b) - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. 20,000 flight cy- cles. STA 908Within 5,000 flight cycles after the original issue date of this ser- vice bulletin. Within 50,000 flight cycles af- ter butt strap replacement. - Do internal detailed inspec- tions of the stringer splices and the butt straps for cracks in accordance with Paragraph 3.B., Work In- structions - PART II. Airplanes on which a butt strap was previ- ously replaced. (a) (b) - Do internal HFEC surface inspections and internal LFEC inspections of the butt straps for cracks in ac- cordance with Paragraph 3.B., Work Instructions - PART III. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. -Before further flight.Contact Boeing for skin in- spections and repair instruc- tions and do the work in- structed by Boeing. Any crack found in the butt strap. (a) The inspections of the non-repaired butt strap do not change. (b) Stringer splices S-3L, S-5L, S-3R and S-5R are inspected at times defined in Paragraph 1.E., Compliance, Table 8. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 41 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 42 Group 2-6: Table 11: Stringer Splice Post Repair Inspection - Airplanes that have accomplished the removal and replacement of stringer splice in accordance with SB 737-53A1322 Original Issue. Repeat Interval (not to exceed) Compliance TimeActionCondition 30,000 flight cycles.Within 30,000 flight cycles after stringer splice replace- ment. Do internal detailed inspec- tions of the stringer splice in accordance with Para- graph 3.B., Work Instruc- tions - PART II. Stringer splice was re- moved and replaced. -Before further flight.Remove and replace stringer splice in accor- dance with Paragraph 3.B., Work Instructions - PART V. Any crack found in the stringer splice. 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. The Manager of the FAA Seattle Aircraft Certification Office approves the butt strap and stringer splice channel inspection methods, compliance time and repeat intervals defined in this service bulletin Paragraph 1.E., Compliance for Group 2 and Group 3 (737-200 only) aircraft as an alternative method of compliance (AMOC) to the inspections of 737-100/200/200C SSID D6-37089 F-38B and 737-100/200/200C SSID D6-37089 F-38E between stringer S-10L and S-10R, as applicable, requirements of paragraph (b) and (c) of AD 98-11-04 R1. This approval applies only to these SSIs and only for the areas covered by the inspections of the butt strap and stringer splice channel in this service bulletin. If operators choose this AMOC, then they must revise their FAA approved maintenance or inspection program to incorporate these alternative inspections. All requirements of the AD 98-11-04 R1 that are not specifically addressed by this AMOC remain fully applicable and must be complied with accordingly. The Manager of the FAA Seattle Aircraft Certification Office approves the butt strap and stringer splice channel inspection methods, compliance time and repeat intervals defined in this service bulletin Paragraph 1.E., Compliance for Group 5 and Group 6 aircraft as an alternative method of compliance (AMOC) to the inspection of 737-100/200/200C SSID D6-37089 F-38E between stringer S-10L and S-10R, as applicable, requirements of paragraph (g) and (h) of AD 2008-08-23. This approval applies Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 42 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 43 only to these SSIs and only for the areas covered by the inspections of the butt strap and stringer splice channel in this service bulletin. If operators choose this AMOC, then they must revise their FAA approved maintenance or inspection program to incorporate these alternative inspections. All requirements of the AD 2008-08-23 that are not specifically addressed by this AMOC remain fully applicable and must be complied with accordingly. The Manager of the FAA Seattle Aircraft Certification Office approves the butt strap and stringer splice channel inspection methods, compliance time and repeat intervals defined in this service bulletin Paragraph 1.E., Compliance for Group 3 (737-300/400/500) and Group 4 as an alternative method of compliance (AMOC) to the inspections of 737-300/400/500 SSID D6-82669 F-38A and 737-300/400/500 SSID D6-82669 F-38D between stringer S-10L and S-10R, as applicable, requirements of paragraph (g) and (h) of AD 2008-09-13. This approval applies only to these SSIs and only for the areas covered by the inspections of the butt strap and stringer splice channel in this service bulletin. If operators choose this AMOC, then they must revise their FAA approved maintenance or inspection program to incorporate these alternative inspections. All requirements of the AD 2008-09-13 that are not specifically addressed by this AMOC remain fully applicable and must be complied with accordingly. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection and replacement 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 2, Configuration 1-4: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 14.7529.502FIGURE 1 8.9017.802FIGURE 4 6.5513.102FIGURE 2 8.9017.802FIGURE 3 (a) 1.751.751FIGURE 9 (b) 1.201.201FIGURE 17 (c) (d) 1.251.251FIGURE 18 (c) (d) 17.75142.008CLOSE ACCESS 76.35363.95TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 43 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 44 Group 2, Configuration 1-4: Elapsed HoursTask HoursNumber of PersonsTask (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 2, Configuration 5-8: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 14.7529.502FIGURE 1 8.9017.802FIGURE 4 6.5513.102FIGURE 2 8.9017.802FIGURE 3 (a) 1.751.751FIGURE 10 (b) 1.201.201FIGURE 19 (c) (d) 1.251.251FIGURE 20 (c) (d) 17.75142.008CLOSE ACCESS 76.35363.95TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 3, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 14.7529.502FIGURE 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 44 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 45 Group 3, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 8.9017.802FIGURE 4 6.5513.102FIGURE 2 8.9017.802FIGURE 3 (a) 1.751.751FIGURE 11 (b) 1.201.201FIGURE 21 (c) (d) 1.251.251FIGURE 22 (c) (d) 17.75142.008CLOSE ACCESS 76.35363.95TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 3, Configuration 2; Group 4: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 14.7529.502FIGURE 1 8.9017.802FIGURE 4 6.5513.102FIGURE 2 8.9017.802FIGURE 3 (a) 1.751.751FIGURE 12 (b) 1.201.201FIGURE 23 (c) (d) 1.251.251FIGURE 24 (c) (d) 17.75142.008CLOSE ACCESS 76.35363.95TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 45 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 46 Group 3, Configuration 2; Group 4: Elapsed HoursTask HoursNumber of PersonsTask (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 5, Configuration 1-4: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 7.3814.752FIGURE 5 4.458.902FIGURE 8 2.885.752FIGURE 6 2.254.502FIGURE 7 (a) 1.751.751FIGURE 13 (b) 1.251.251FIGURE 18 (c) (d) 17.75142.008CLOSE ACCESS 54.20319.65TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 5, Configuration 5-8: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 7.3814.752FIGURE 5 4.458.902FIGURE 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 46 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 47 Group 5, Configuration 5-8: Elapsed HoursTask HoursNumber of PersonsTask 2.885.752FIGURE 6 2.254.502FIGURE 7 (a) 1.751.751FIGURE 14 (b) 1.251.251FIGURE 20 (c) (d) 17.75142.008CLOSE ACCESS 54.20319.65TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 6, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 7.3814.752FIGURE 5 4.458.902FIGURE 8 2.885.752FIGURE 6 2.254.502FIGURE 7 (a) 1.751.751FIGURE 15 (b) 1.251.251FIGURE 22 (c) (d) 17.75142.008CLOSE ACCESS 54.20319.65TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 47 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 48 Group 6, Configuration 1: Elapsed HoursTask HoursNumber of PersonsTask (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. Group 6, Configuration 2: Elapsed HoursTask HoursNumber of PersonsTask 17.75142.008OPEN ACCESS 7.3814.752FIGURE 5 4.458.902FIGURE 8 2.885.752FIGURE 6 2.254.502FIGURE 7 (a) 1.751.751FIGURE 16 (b) 1.251.251FIGURE 24 (c) (d) 17.75142.008CLOSE ACCESS 54.20319.65TOTAL FOR EACH AIRPLANE (a) More time may be required if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. (b) Remove and reinstall fasteners is required if an HFEC open hole rotary probe inspection is accomplished in accordance with Paragraph 3.B., Work Instruc- tions - PART III. (c) Time estimated is to remove and replace one (1) stringer splice. More time may be required for remove and replace additional stringer splices in accor- dance with Paragraph 3.B., Work Instructions - PART V. (d) Add labor estimates to total as required if stringer splice is removed and re- placed in accordance with Paragraph 3.B., Work Instructions - PART V. H. Weight and Balance Changes None. I. Electrical Load Data Not applicable. J. References 1. Existing Data: a. Boeing Service Bulletin 737-53-1076, 737-53-1268, 737-53A1039, 737-53A1177, 737-53A1210, 737-53A1234 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 48 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 49 b. Boeing Service Letter 737-SL-51-042 c. Boeing Service Related Problem (SRP) 737-SRP-53-0362 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2008-08-23, 2008-09-13, 98-11-04 R1 e. Service Bulletin Index D6-19567 f. Standard Overhaul Practices Manual (SOPM) 20-43-03, 20-50-19 g. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 51-00-26 h. 737-100/200/200C Supplemental Structural Inspection Document (SSID) D6-37089F-38B, D6-37089F-38E i. 737-100/200 Aircraft Maintenance Manual (AMM) 21-23-11, 25-21-300, 25-21-341, 25-21-345, 25-21-346, 25-21-371, 25-22-0, 25-23-511, 25-23-611, 25-24-111, 25-24-112, 25-24-131, 25-24-133, 25-24-143, 25-24-144, 25-24-311, 25-24-313, 25-24-511, 25-31-01, 25-31-21, 25-31-31, 25-31-61 j. 737-100/200 Structural Repair Manual (SRM) 51-30-02, 53-30-3 k. 737-300/400/500 Aircraft Maintenance Manual (AMM) 21-23-25, 25-21-39, 25-21-45, 25-21-46, 25-21-71, 25-22-00, 25-23-61, 25-24-15, 25-24-31, 25-31-21, 25-31-31, 25-31-61, 25-40-01 l. 737-300/400/500 Structural Repair Manual (SRM) 51-40-02, 53-00-01 m. 737-300/400/500 Supplemental Structural Inspection Document (SSID) D6-82669F-38A, D6-82669F-38D 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number SKIN PANEL INSTALLATION - S-10L TO S-10R STA 360 - STA 540 65-45765 SKIN PANEL INSTL - S-10L TO S-10R STA 727 TO STA 101665-45772 SKIN PANEL INSTL - S-4 TO S-25, LEFT SIDE, STA 908 TO STA 1016 65-45777 SKIN PANEL INSTL - AFT. GALLEY DOOR, STA 908 - STA 1016, S-4R TO S-25R 65-45778 SKIN & STRINGER INSTALLATION - SECTION 4165-45800 SKIN PANEL INSTL - S-4L TO S-25L, STA 908 TO STA 101665-52988 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 49 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 50 TitleDrawing Number SKIN INSTL - AFT ENTRY DOOR, STA 908 TO STA 1016, S-4L TO S-25L 65C27755 SKIN INSTL - AFT GALLEY DOOR STA 908 TO STA 1016, S-4R TO S-25R 65C27756 SKIN INSTL - STA 259-50 TO STA 360.00, S-4L TO S-4R65C27758 SKIN AND STRINGER INSTL - FORWARD ENTRY AND GALLEY DOORS 65C34778 SKIN INSTL - S-10L TO S-10R, STA 360 TO STA 54065C35765 SKIN INSTL - STA 727 TO STA 908, S-10L TO S-10R65C35772 AFT ENTRY DOOR, STA 908 - STA 1016, S-4L TO S-25L65C35777 SKIN PANEL INSTL - AFT GALLEY DOOR, STA 908 STA 1016, S-4R TO S-25R 65C35778 SKIN INSTL - STA 908 TO STA 1016, S-4L TO S-4R65C45772 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. 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: November 05, 2012 737-53A1322 50 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 51 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. 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 parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: The items shown below are necessary for each airplane if any crack is found in the stringer splice. Refer to APPENDIX A for stringer splice part number airplane applicability. NotesNameQTYNew Part Number STA 908STA 360 S-10LStringer Splice-165-61777-4 1-65-51698-8 S-9LStringer Splice-165-61777-3 or 65-61777-504 1-65-51698-7 or 65-51698-19 S-8LStringer Splice-165-61777-2 1-65-51698-1 or 65-51698-7 or 65-51698-19 S-7LStringer Splice-165-61777-1 1-65-51698-6 or 65-51698-13 S-6LStringer Splice1-65-51698-1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 51 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 52 NotesNameQTYNew Part Number STA 908STA 360 S-5LStringer Splice-169-47528-1 1-65-51698-1 S-4LStringer Splice-165-59664-4 or 65-59664-25 1-65-51698-9 S-3LStringer Splice-165-59664-1 1-65-51698-1 S-2LStringer Splice-165-59664-1 or 65-59664-503 1-65-51698-1 S-1Stringer Splice-165-59664-1 or 65-59664-504 1-65-51698-1 S-2RStringer Splice-165-59664-1 1-65-51698-1 S-3RStringer Splice-165-59664-1 1-65-51698-1 S-4RStringer Splice-165-59664-2 or 65-59664-26 1-65-51698-2 or 65-51698-47 S-5RStringer Splice-165-59664-1 1-65-51698-1 S-6RStringer Splice-165-59664-1 1-65-51698-1 S-7RStringer Splice1-65-51698-1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 52 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 53 NotesNameQTYNew Part Number STA 908STA 360 S-8RStringer Splice-165-59664-502 1-65-51698-12 S-9RStringer Splice-165-59664-21 1-65-51698-7 or 65-51698-19 S-10RStringer Splice-165-59664-16 or 65-59664-28 1-65-51698-8 2. Parts and Materials Supplied by the Operator NOTE: The items shown below are necessary for each airplane if optional inspection is accomplished in accordance with Paragraph 3.B., Work Instructions - PART III. Group 1: On Group 1 airplanes, contact Boeing to get instructions for the inspection, and/or repair for this Service Bulletin (SB) 737-53A1322 Original Issue, and do the work instructed by Boeing. Group 2, Configuration 1-4: NotesNameQTYPart Number / Specification (a)Rivet28BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 2, Configuration 5-8: NotesNameQTYPart Number / Specification (a)Rivet32BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 3, Configuration 1: NotesNameQTYPart Number / Specification (a)Rivet44BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 53 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 54 Group 3, Configuration 2; Group 4: NotesNameQTYPart Number / Specification (a)Rivet56BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 5, Configuration 1-4: NotesNameQTYPart Number / Specification (a)Rivet14BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 5, Configuration 5-8: NotesNameQTYPart Number / Specification (a)Rivet16BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 6, Configuration 1: NotesNameQTYPart Number / Specification (a)Rivet22BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. Group 6, Configuration 2: NotesNameQTYPart Number / Specification (a)Rivet28BACR15GF6D6 (a) Refer to 737 Structural Repair Manual Chapter 51 for alternate fasteners. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 54 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 55 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: November 05, 2012 737-53A1322 55 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 56 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 56 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT BLANK PAGE ### Page 57 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 limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process 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. 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. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 57 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 58 9. Refer to APPENDIX A for stringer splice replacement data. APPENDIX A is given as an aid only when stringer splice replacement is accomplished. 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 corrosion is found, contact Boeing for repair instructions and do the work instructed by Boeing. 13. When the fasteners are removed, take care to not increase the diameter of the hole beyond the starting hole size tolerance. 14. At production configuration fastener locations, fasteners can be oversized by a maximum of 1/32" over the original diameter. Maintain a minimum 1.7D edge margin. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 15. A lap joint modification as identified in this service bulletin is also referred to as lap joint cut-out repair in SB 737-53A1177. The modification removes the entire production lap joint from butt joint to butt joint and installs a doubler and tripler. 16. 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 production drawing requirements or applicable modification drawing requirements, contact Boeing with the details before proceeding. 17. Shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. B. WORK INSTRUCTIONS Group 1: On Group 1 airplanes, contact Boeing to get instructions for the inspection, and/or repair for this Service Bulletin (SB) 737-53A1322 Original Issue, and do the work instructed by Boeing. Group 2-6: 1. PART I - OPEN ACCESS 1. Remove the following equipment as necessary to get internal access at Body Station STA 360 and STA 908, Stringer S-10L to S-10R. Refer to the applicable AMM reference below as an accepted procedure. a. 737-200/-200C 737-100/-200/-200C AMM SubjectEquipment 737-100/200 AMM 25-31-21Galley No. 2 737-100/200 AMM 25-31-31Galley No. 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 58 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 59 737-100/-200/-200C AMM SubjectEquipment 737-100/200 AMM 25-31-01Galleys 737-100/200 AMM 25-31-61Aft Galley 737-100/200 AMM 25-24-111, 25-24-112Forward Left Windscreen 737-100/200 AMM 25-24-131, 25-24-133Aft Left Windscreen 737-100/200 AMM 25-24-143, 25-24-144Aft Right Windscreen 737-100/200 AMM 25-22-0Passenger Seats 737-100/200 AMM 25-21-346Sidewall Panels 737-100/200 AMM 25-21-300Passenger Cabin Lining and Insulation 737-100/200 AMM 25-21-345Sculptured Ceiling Panels 737-100/200 AMM 25-21-371Lowered Ceiling Panels 737-100/200 AMM 25-21-341Curved Ceiling Panels 737-100/200 AMM 25-24-311, 25-24-313, 25-24-511Overhead Stowage Bin 737-100/200 AMM 25-23-511, 25-23-611Passenger Service Unit 737-100/200 AMM 21-23-11Overhead Distribution Duct b. 737-300/-400/-500 737-300/-400/-500 AMM SubjectEquipment 737-300/400/500 AMM 25-31-21Galley No. 2 737-300/400/500 AMM 25-31-31Galley No. 3 737-300/400/500 AMM 25-31-61Galley No. 6 737-300/400/500 AMM 25-40-01Lavatory 737-300/400/500 AMM 25-24-15Windscreen 737-300/400/500 AMM 25-22-00Passenger Seats 737-300/400/500 AMM 25-21-46Sidewall Panels 737-300/400/500 AMM 25-21-45Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-71Lowered Ceiling Panels 737-300/400/500 AMM 25-21-39Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-24-31Overhead Stowage Bins 737-300/400/500 AMM 25-23-61Passenger Service Units 737-300/400/500 AMM 21-23-25Overhead Air Distribution Duct Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 59 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT ### Page 60 Group 2-6: 2. PART II - DETAILED INSPECTION (ZONE A AND B) 1. Group 2-4: Zone A and B: Do internal detailed inspections of the stringer splices and the butt straps at STA 360 and STA 908, from S-10L to S-10R for cracks in accordance with FIGURE 1. a. If any crack is found in the stringer splice, remove and replace the splice in accordance with Paragraph 3.B., Work Instructions - PART V. b. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. c. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. 2. Group 5-6: Zone A and B: Do internal detailed inspections of the stringer splices and the butt straps at STA 908, from S-10L to S-10R for cracks in accordance with FIGURE 5. a. If any crack is found in the stringer splice, remove and replace the splice in accordance with Paragraph 3.B., Work Instructions - PART V. b. If any crack is found in the butt strap, contact Boeing for skin inspections and repair instructions and do the work instructed by Boeing. c. If no crack is found, continue repeat inspections in accordance with Paragraph 1.E., Compliance. Group 2-6: 3. PART III - EDDY CURRENT INSPECTION (ZONE A AND B) 1. Group 2-4: Zone A: Do eddy current inspections of the butt straps at STA 360 and STA 908, from S-5L to S-3L and from S-3R to S-5R. a. Option 1: Do internal High Frequency Eddy Current (HFEC) surface inspections and internal Low Frequency Eddy Current (LFEC) inspections of the butt straps for cracks, and do an HFEC open hole rotary inspection at one (1) location of the butt strap for cracks in accordance with FIGURE 2. (1) Do an internal HFEC surface inspection of the butt straps for cracks common to the edges of the stringer splices. (2) Do an internal HFEC surface inspection of the butt straps for cracks around the fastener formed tails common to the two (2) fastener rows forward and aft of the skin gap common to the butt joint. (3) Do an internal LFEC inspection of the upper butt strap for cracks around the fastener formed tails common to the last fastener row in the lower butt strap. (4) Do an internal HFEC surface inspection of the lower butt strap for cracks around the fastener formed tails common to the last fastener row in the upper butt strap. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 05, 2012 737-53A1322 60 of 229 BOEING SERVICE BULLETIN 737-53A1322 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/737-53a1322/file/b4fc05239289.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.