# Boeing Special Attention Service Bulletin 737-53-1287: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0036; AD 2013-04-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Special Attention Service Bulletin 737-53-1287](https://openairdocs.org/service-documents/boeing/sb-737-53-1287.md) - Title as filed: U.S. DOT/FAA - Boeing - SB-737-53-1287-01 - Pages: 250 - PDF: https://openairdocs.org/files/sha256/0b/65/0b65ee8be6faa123599a9bf6c2184733e864fa024288b7af27397ede0064b50e - Page: https://openairdocs.org/service-documents/boeing/sb-737-53-1287/file/0b65ee8be6fa ## 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 SPECIAL ATTENTION Number: 737-53-1287 Original Issue: March 11, 2009 Revision 1: November 15, 2010 ATA System: 5331 2321 SUBJECT: FUSELAGE - Skin - Skin Cracking Under the Number 3 VHF Antenna - Inspection, Repair and Preventive Modification Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. 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 the Boeing livery 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 1 of 250 7.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 2 of 250 BOEING SERVICE BULLETIN 737-53-1287 BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 7 Summary ...................................................... 9 1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3 1. Airplanes ............................................ 1 3 2. Spares Affected ........................................ 2 3 B. Concurrent Requirements ...................................... 2 3 C. Reason ................................................ 2 4 D. Description .............................................. 2 5 E. Compliance .............................................. 2 6 F. Approval ............................................... 3 9 G. Manpower .............................................. 3 9 H. Weight and Balance Changes .................................... 4 7 I. Electrical Load Data ......................................... 4 7 J. References .............................................. 4 8 1. Existing Data .......................................... 4 8 2. Data supplied with this Service Bulletin ............................ 4 8 3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 4 9 K. Publications Affected ........................................ 4 9 L. Interchangeability and Intermixability of Parts ........................... 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 1 3. Parts Modified and Reidentified ................................ 6 1 4. Parts Removed and Not Replaced .............................. 6 1 D. Parts Necessary to Change Spares ................................. 6 2 E. Special Tooling - Price and Availability ............................... 6 2 F. Special Tooling Necessary to do this Service Bulletin ....................... 6 2 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 3 A. GENERAL INFORMATION ..................................... 6 3 B. WORK INSTRUCTIONS ....................................... 6 3 FIGURE 1: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR COVER PLATE NOT REMOVED [Group 1, Configuration 1-2; Group 2, Configuration 1-2; Group 5] . 74 FIGURE 2: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR COVER PLATE NOT REMOVED [Group 3, 6] ............................. 7 6 FIGURE 3: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR COVER PLATE NOT REMOVED [Group 4] .............................. 7 8 FIGURE 4: NUMBER 3 VHF ANTENNA LOCATION - COVER PLATE REMOVAL [Group 1-4, 6, Configuration 2 ] ................................................ 8 0 FIGURE 5: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR THE COVER PLATE REMOVED [Group 1, Configuration 1-2; Group 2, Configuration 1-2] ....... 8 2 FIGURE 6: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR THE COVER PLATE REMOVED [Group 3, 6] ................................ 8 4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 3 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 4 FIGURE 7: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA OR THE COVER PLATE REMOVED [Group 4] ................................. 8 6 FIGURE 8: NUMBER 3 VHF ANTENNA - EXTERNAL INSPECTION WITH THE ANTENNA REMOVED [Group 5] ............................................ 8 8 FIGURE 9: NUMBER 3 VHF ANTENNA - INTERNAL INSPECTION [Group 1-2, Configuration 1; Group 5] .................................................. 9 0 FIGURE 10: NUMBER 3 VHF ANTENNA - INTERNAL INSPECTION [Group 3, 6, Configuration 1] . . 93 FIGURE 11: NUMBER 3 VHF ANTENNA - INTERNAL INSPECTION [Group 4, Configuration 1] .... 9 6 FIGURE 12: NUMBER 3 VHF ANTENNA LOCATION - COVER PLATE INSTALLATION [Group 1-4, 6, Configuration 2] ......................................... 9 9 FIGURE 13: NUMBER 3 VHF ANTENNA LOCATION - REPAIR PREPARATION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] ............................... 1 0 1 FIGURE 14: NUMBER 3 VHF ANTENNA LOCATION - REPAIR INSTALLATION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] ............................... 1 0 8 FIGURE 15: NUMBER 3 VHF ANTENNA LOCATION - REPAIR PREPARATION [Group 3] ...... 1 1 2 FIGURE 16: NUMBER 3 VHF ANTENNA LOCATION - REPAIR INSTALLATION [Group 3] ...... 1 1 9 FIGURE 17: NUMBER 3 VHF ANTENNA LOCATION - REPAIR PREPARATION [Group 4] ...... 1 2 3 FIGURE 18: NUMBER 3 VHF ANTENNA LOCATION - REPAIR INSTALLATION [Group 4] ...... 1 3 0 FIGURE 19: NUMBER 3 VHF ANTENNA LOCATION - REPAIR PREPARATION [Group 6] ...... 1 3 4 FIGURE 20: NUMBER 3 VHF ANTENNA LOCATION - REPAIR INSTALLATION [Group 6] ...... 1 4 1 FIGURE 21: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - PREPARATION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] .................. 1 4 5 FIGURE 22: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSPECTION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] ...................... 1 5 2 FIGURE 23: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - ANTENNA SUPPORT STRUCTURE INSTALLATION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] . 156 FIGURE 24: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSTALLATION [Group 1, Configuration 1-2; Group 2, Configuration 1-2] .................. 1 6 3 FIGURE 25: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - PREPARATION [Group 3] ............................................ 1 6 5 FIGURE 26: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSPECTION [Group 3 ] ................................................ 1 7 2 FIGURE 27: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - ANTENNA SUPPORT STRUCTURE INSTALLATION [Group 3] .......................... 1 7 6 FIGURE 28: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSTALLATION [Group 3] ............................................ 1 8 3 FIGURE 29: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - PREPARATION [Group 4] ............................................ 1 8 5 FIGURE 30: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSPECTION [Group 4 ] ................................................ 1 9 2 FIGURE 31: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - ANTENNA SUPPORT STRUCTURE INSTALLATION [Group 4] .......................... 1 9 6 FIGURE 32: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSTALLATION [Group 4] ............................................ 2 0 3 FIGURE 33: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - PREPARATION [Group 6] ............................................ 2 0 5 FIGURE 34: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSPECTION [Group 6 ] ................................................ 2 1 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 4 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 5 FIGURE 35: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - ANTENNA SUPPORT STRUCTURE INSTALLATION [Group 6] .......................... 2 1 6 FIGURE 36: NUMBER 3 VHF ANTENNA LOCATION - PREVENTIVE MODIFICATION - INSTALLATION [Group 6] ............................................ 2 2 3 FIGURE 37: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITH AN ANTENNA INSTALLED [Group 1-2, Configuration 1] .............. 2 2 5 FIGURE 38: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITHOUT AN ANTENNA INSTALLED [Group 1-2, Configuration 2] ........... 2 2 8 FIGURE 39: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITH AN ANTENNA INSTALLED [Group 3, Configuration 1] ............... 2 3 0 FIGURE 40: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITHOUT AN ANTENNA INSTALLED [Group 3, Configuration 2] ............. 2 3 3 FIGURE 41: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITH AN ANTENNA INSTALLED [Group 4, Configuration 1] ............... 2 3 5 FIGURE 42: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITHOUT AN ANTENNA INSTALLED [Group 4, Configuration 2] ............. 2 3 8 FIGURE 43: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITH AN ANTENNA INSTALLED [Group 6, Configuration 1] ............... 2 4 0 FIGURE 44: NUMBER 3 VHF ANTENNA LOCATION - SUPPLEMENTAL INSPECTION ON AIRPLANES WITHOUT AN ANTENNA INSTALLED [Group 6, Configuration 2] ............. 2 4 3 APPENDIX A: SEALANT REMOVAL PROCEDURE FOR EXTERIOR PRESSURIZED FUSELAGE SKIN. 245 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 5 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 6 of 250 BOEING SERVICE BULLETIN 737-53-1287 BLANK PAGE ### Page 7 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION Revision Transmittal SheetNumber: 737-53-1287Original Issue: March 11, 2009 Revision 1: November 15, 2010 ATA System: 5331 2321 SUBJECT: FUSELAGE - Skin - Skin Cracking Under the Number 3 VHF Antenna - Inspection, Repair and Preventive Modification This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. NOTE: The method for accomplishing internal frame inspections is changed in this revision. New and repeat inspections must be accomplished in accordance with Revision 1 of this Service Bulletin. REASON FOR REVISION This revision is sent to give instructions for the repair and preventive modification of the skin at the number 3 VHF antenna location. The following sections are changed: 1. The Summary Action section is updated. 2. The summary illustration is updated. 3. Paragraph 1.A., Effectivity - 737-400 airplanes are moved from Group 3 to new Group 6. A new Group 7 is added. Group 2 airplanes before line number 292 are moved to Group 7. 4. Paragraph 1.C., Reason is updated. 5. Paragraph 1.D., Description is updated. 6. Paragraph 1.E., Compliance - A compliance table for Group 4 is added. A table for supplemental inspection information is also added. 7. Paragraph 1.G., Manpower - The manpower information is updated. 8. Paragraph 1.J.1., Existing Data - Non-Destructive Testing (NDT) and Structural Repair Manual (SRM) references are added. 9. Paragraph 1.J.2., Data supplied with this Service Bulletin - Installation drawings are added. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 7 of 250 ### Page 8 10. Paragraph 1.K., Publications Affected - A Damage Tolerance Based Structural Inspection statement is added. 11. Paragraph 2.C.2., Parts and Materials Supplied by the Operator - Parts are added. 12. Paragraph 3.A., General Information - A note about fastener specification is added. 13. Paragraph 3.B., Work Instructions - Repair, preventive modification and supplemental inspection instructions are added. 14. Figures 13 to 44 are added. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. REVISION HISTORY March 11, 2009Original Issue: November 15, 2010Revision 1: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 8 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 9 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION SummaryNumber: 737-53-1287Original Issue: March 11, 2009 Revision 1: November 15, 2010 ATA System: 5331 2321 SUBJECT: FUSELAGE - Skin - Skin Cracking Under the Number 3 VHF Antenna - Inspection, Repair and Preventive Modification BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements. BACKGROUND This service bulletin is sent to inspect the skin and surrounding structure for cracking under the number 3 VHF antenna. If the work given in this service bulletin is not done, then cracking in the skin or surrounding structure could remain undetected. Continued operation with undetected cracks could result in crack growth, possibly leading to separation of the antenna from the airplane, and rapid depressurization. The number 3 VHF antenna is located on the lower external surface of the airplane at Buttock Line (BL) 0.0, aft of the main landing gear wheel well. In May 2006 one operator reported a 15 inch longitudinal crack in the skin near BL 0.0 just forward of the number 3 VHF antenna cutout, running forward. The first 14 inches of the crack was hidden beneath the number 3 VHF antenna. Boeing has received five other reports of skin cracks between 1.5 and 3 inches in length in the same area. The reports also indicated that the main antenna support channel and other support structure were cracked. The earliest reported cracking occurred at 18,289 total flight cycles. The reported cracks were caused by dynamic loading of the number 3 VHF antenna due to extended main landing gear turbulence. Accomplishment of this service bulletin will make sure that any crack under the number 3 VHF antenna is detected and repaired before it reaches a critical length. A support fitting to stop cracks developing in the skin at the number 3 VHF antenna location is installed in production on airplanes from line 2791. Boeing Service Related Problem (SRP) 737-SRP-53-0313 is related to this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 9 of 250 ### Page 10 ACTION (PRR 35005-293RS) Group 1-4, Configuration 1; Group 5; Group 6, Configuration 1: Get internal access to the number 3 VHF antenna support structure. Do an internal detailed inspection of the antenna support structure, surrounding frames, stringers and skin for cracking or corrosion. Do an external detailed inspection and High Frequency Eddy Current (HFEC) inspection of the skin for cracking. If any crack is found in the skin, install a repair. If no cracking is found, repeat the inspections or install a preventive modification. If any crack is found in the antenna support structure, surrounding frames or stringers, contact Boeing for repair instructions and do the repair. If corrosion is found install a repair or contact Boeing for repair instructions and do the repair. Group 1-4, 6, Configuration 2: If a number 3 VHF antenna was previously installed, or it is unknown if the antenna was previously installed, accomplish detailed inspections of the skin until the cover plate is removed from the number 3 VHF antenna location. With the cover plate removed, do a one time external detailed inspection and a HFEC inspection of the skin for cracking. If any crack is found, install a repair. If no cracking is found install the cover plate at the number 3 VHF antenna location. If records show that a number 3 VHF antenna has never been installed then no work is necessary. If a repair or preventive modification is installed as given in this service bulletin, do supplemental Low Frequency Eddy Current (LFEC) inspections in the skin at fastener locations common to the doubler; do external detailed inspections of the doubler, tripler and skin and internal detailed inspections of the antenna support structure and skin for cracking. Do HFEC inspections for cracking in the frames. If any crack is found, contact Boeing for repair instructions and do the repair. Group 1-2, Configuration 3: No work is necessary. Group 7: Contact Boeing for the inspection, repair and preventive modification instructions. EFFECTIVITY 737-200/-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. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and repair given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower . BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 10 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 11 MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 11 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 12 (OCR) BOEING SERVICE BULLETIN 737-53-1287 1 INSPECTION AREA TYPICAL SKIN CRACK ANTENNA TWO INCHES FOOTPRINT ALL AROUND SEE SKIN AND TYPICAL SKIN CRACK AREA OF REMOVED SEALANT (TYPICAL) WITH THE NUMBER 3 VHF ANTENNA OR COVER PLATE REMOVED, DO AN EXTERNAL INSPECTION OF THE SKIN FWD < FOR CRACKING. IF ANY CRACK IS FOUND, INSTALL A REPAIR. DO AN INTERNAL INSPECTION FOR CRACKING OR CORROSION IN THE SKIN, ANTENNA SUPPORT STRUCTURE, SURROUNDING FRAMES AND STRINGERS. IF ANY CRACK IS FOUND IN THE SKIN, INSTALL A REPAIR. IF ANY CRACK OR CORROSION IS FOUND IN THE ANTENNA SUPPORT STRUCTURE, SURROUND FRAMES AND STRINGERS, CONTACT BOEING FOR REPAIR INSTRUCTIONS AND DO THE REPAIR. DO A DETAILED INSPECTION AND A HFEC SURFACE INSPECTION OF THE SKIN FOR CRACKING AROUND THE ANTENNA BASE AND SEALANT. NUMBER 3 IF ANY CRACK IS FOUND, INSTALL FWD < VHF ANTENNA 1496973 A REPAIR. B Original Issue: March 11, 2009 Revision 1: November 15, 2010 737-53-1287 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 250 ### Page 13 Commercial Airplanes 737 Service Bulletin SPECIAL ATTENTION Number: 737-53-1287 Original Issue: March 11, 2009 Revision 1: November 15, 2010 ATA System: 5331 2321 SUBJECT: FUSELAGE - Skin - Skin Cracking Under the Number 3 VHF Antenna - Inspection, Repair and Preventive Modification BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. DESCRIPTIONCONFIGURATIONGROUP 737-200/200C airplanes after line number 291 delivered with solid skin and have antenna support structure at the number 3 VHF antenna location. -1 Airplanes that have a number 3 VHF antenna installed.1 Airplanes that have a cover plate installed at the number 3 VHF antenna location. 2 Airplanes that have neither an antenna nor a cover plate installed at the number 3 VHF antenna location. 3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 13 of 250 ### Page 14 DESCRIPTIONCONFIGURATIONGROUP 737-200/200C airplanes after line number 291 delivered with bonded skin and have antenna support structure at the number 3 VHF antenna location. -2 Airplanes that have a number 3 VHF antenna installed.1 Airplanes that have a cover plate installed at the number 3 VHF antenna location. 2 Airplanes that have neither an antenna nor a cover plate installed at the number 3 VHF antenna location. 3 737-300 airplanes line numbers 292-2790 with antenna support structure at the number 3 VHF antenna location. -3 Airplanes that have a number 3 VHF antenna installed.1 Airplanes that have a cover plate installed at the number 3 VHF antenna location. 2 737-500 airplanes line numbers 292-2790 with antenna support structure at the number 3 VHF antenna location. -4 Airplanes that have a number 3 VHF antenna installed.1 Airplanes that have a cover plate installed at the number 3 VHF antenna location. 2 737-200 airplanes line numbers 868, 947 and 985 with six mounting bolts at the number 3 VHF antenna. -5 737-400 airplanes line numbers 292-2790 with antenna support structure at the number 3 VHF antenna location. -6 Airplanes that have a number 3 VHF antenna installed.1 Airplanes that have a cover plate installed at the number 3 VHF antenna location. 2 737-200/200C airplanes line numbers 1-291.-7 Airplane Models: 737-200, 737-200C, 737-300, 737-400, 737-500 GroupVariable Number 7PG001 - PG075 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 14 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 15 GroupVariable Number 7PG199 7PG201 - PG230 7PG251 - PG255 7PG271 - PG279 7PG301 - PG314 7PG331 - PG332 7PG351 - PG356 7PG375 7PG401 - PG403 7PG431 - PG442 7PG471 - PG475 7PG501 - PG505 7PG571 - PG583 2PG584 - PG586 7PG621 - PG630 7PG651 - PG652 7PG701 - PG705 2PH001 2PH011 - PH013 2PH021 - PH024 7PH701 - PH715 7PH731 - PH732 7PH741 - PH742 2PH743 7PJ001 - PJ002 2PJ003 1PJ004 - PJ009 7PJ031 - PJ032 7PJ071 - PJ072 7PJ101 - PJ104 2PJ105 - PJ109 1PJ110 - PJ119 2PJ201 - PJ219 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 15 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 16 GroupVariable Number 6PJ301 - PJ302 6PJ551 - PJ559 2PK026 - PK028 1PK029 2PK041 - PK048 1PK049 - PK053 2PK061 - PK067 1PK068 - PK070 2PK081 1PK082 2PK091 1PK092 - PK099 2PK101 - PK103 2PK111 - PK120 2PK141 - PK146 1PK201 - PK204 1PK211 - PK223 1PK231 - PK241 1PK251 - PK258 1PK271 - PK274 1PK281 - PK289 1PK291 1PK301 - PK318 1PK341 1PK351 - PK361 1PK391 1PK431 - PK433 1PK451 - PK452 1PK461 - PK469 1PK495 1PK501 - PK504 1PK511 - PK515 1PK519 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 16 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 17 GroupVariable Number 1PK521 - PK528 1PK541 - PK565 1PK581 1PK591 - PK599 1PK601 - PK617 1PK621 - PK637 1PK641 - PK642 1PK661 - PK666 1PK671 - PK681 1PK691 - PK697 1PK711 - PK716 1PK731 - PK765 1PK771 - PK779 1PK801 - PK804 1PK819 - PK827 1PK830 1PK861 - PK863 1PK871 - PK874 1PK881 - PK884 1PK901 - PK938 1PK971 - PK974 2PL001 1PL002 - PL028 1PL061 1PL081 1PL101 - PL113 1PL151 1PL171 - PL172 1PL201 - PL203 1PL221 1PL401 - PL417 1PL421 1PL441 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 17 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 18 GroupVariable Number 1PL451 - PL456 1PL471 1PL491 1PL501 - PL506 1PL551 - PL562 1PL581 5PL601 - PL603 1PL611 1PL621 - PL626 1PL631 - PL632 7PL711 - PL712 7PL716 2PL717 - PL721 1PL722 - PL725 2PL726 - PL730 1PL731 - PL735 2PL736 - PL743 1PL744 - PL747 2PL756 2PL758 2PL761 - PL766 1PL767 - PL770 2PL781 - PL782 1PL783 - PL788 2PL793 7PL801 - PL803 1PM001 - PM006 1PM016 - PM017 1PM021 - PM023 1PM051 - PM066 1PM101 - PM119 1PM141 - PM142 1PM171 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 18 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 19 GroupVariable Number 1PM181 1PM251 - PM255 1PM281 - PM283 3PM546 1PN001 - PN002 1PN021 - PN043 1PN081 - PN086 1PN101 - PN117 1PN131 - PN163 1PN401 - PN420 1PN431 - PN433 1PN451 - PN456 1PN471 - PN474 1PN481 1PN491 - PN493 1PN501 - PN502 1PN511 - PN512 1PN521 3PP001 - PP054 3PP101 - PP169 3PP231 - PP243 3PP301 - PP305 3PP401 - PP440 3PP471 - PP475 3PP671 - PP699 3PP701 - PP733 3PP771 - PP779 3PP861 - PP875 3PP961 - PP967 3PP991 3PQ001 - PQ016 3PQ026 - PQ041 3PQ069 - PQ085 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 19 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 20 GroupVariable Number 3PQ101 - PQ199 3PQ201 - PQ202 3PQ251 - PQ267 3PQ331 - PQ332 3PQ373 3PQ407 3PQ432 - PQ438 3PQ771 - PQ772 3PQ801 - PQ805 3PS701 - PS706 3PS751 - PS799 3PS836 - PS837 3PS856 3PS896 - PS897 3PS901 - PS912 4PT001 - PT012 4PT021 - PT029 4PT101 - PT105 4PT121 - PT127 4PT146 - PT148 4PT181 - PT188 4PT211 4PT295 4PT301 - PT309 4PT331 - PT360 4PT381 - PT399 4PT401 - PT438 4PT501 - PT517 4PT561 - PT565 4PT581 - PT585 4PT611 - PT621 4PT641 - PT644 4PT651 - PT656 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 20 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 21 GroupVariable Number 4PT671 - PT672 4PT701 - PT703 4PT801 - PT834 4PT851 - PT853 4PT871 - PT874 4PT971 - PT973 4PU001 - PU025 6PV001 - PV055 6PV201 - PV203 6PV231 - PV237 6PV271 - PV272 6PV281 - PV284 6PW049 - PW050 6PW161 - PW167 6PW201 - PW250 6PW267 - PW268 6PW278 6PW281 - PW293 6PW301 - PW327 6PW401 - PW403 6PW411 - PW412 6PW461 - PW467 6PW501 - PW504 6PW511 - PW522 6PW525 - PW528 6PW531 - PW549 6PW556 - PW557 6PW561 - PW564 6PW571 - PW576 6PW611 - PW622 6PW631 - PW637 6PW681 - PW683 6PW701 - PW702 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 21 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 22 GroupVariable Number 6PW711 - PW717 6PW741 - PW742 6PW761 7PX071 7PX701 7PY001 - PY008 7PY021 2PY022 7PY031 2PY036 - PY037 2PY046 - PY047 1PY048 2PY051 - PY052 1PY053 1PY056 - PY057 2PY101 - PY103 2PY111 - PY113 2PY131 - PY133 1PY134 - PY135 2PY141 - PY142 1PY143 1PY151 - PY154 1PY156 - PY157 1PY161 - PY162 1PY166 1PY191 1PY201 1PY221 - PY222 1PY231 1PY241 - PY244 1PY270 2PY271 - PY273 1PY274 - PY275 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 22 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 23 GroupVariable Number 1PY281 1PY286 7PY301 - PY304 7PY321 - PY323 7PY341 - PY346 7PY361 - PY362 7PY381 1PY401 1PY409 - PY411 1PY421 - PY422 1PY441 1PY451 1PY461 - PY463 1PY591 - PY595 1PY611 - PY612 1PY621 1PY631 1PY651 1PY671 - PY672 1PY721 1PY741 2. Spares Affected None. B. Concurrent Requirements Group 2, 7: The service bulletin listed below must be done in accordance with FAA Airworthiness Directive AD 90-06-02 . If the service bulletin below has not previously been accomplished as required by AD 90-06-02 , then it must be accomplished before further flight: DescriptionService BulletinCompany Replaces bonded skin panels with solid skin panels. 737-53A1042 Revision 5, 6, 7, 8 or 9, Part V - Skin Panel Replacement. (a) Boeing (a) The Modification given in Boeing Service Bulletin 737-53A1042 Revision 5, 6, 7, 8 or 9 is necessary to comply with FAA Airworthiness Directive FAA AD 90-06-02. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 23 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 24 Group 1, 3-6: None C. Reason This service bulletin is sent to inspect the skin and surrounding structure for cracking under the number 3 VHF antenna. If the work given in this service bulletin is not done, then cracking in the skin or surrounding structure could remain undetected. Continued operation with undetected cracks could result in crack growth, possibly leading to separation of the antenna from the airplane, and rapid depressurization. The number 3 VHF antenna is located on the lower external surface of the airplane at Buttock Line (BL) 0.0, aft of the main landing gear wheel well. In May 2006 one operator reported a 15 inch longitudinal crack in the skin near BL 0.0 just forward of the number 3 VHF antenna cutout, running forward. The first 14 inches of the crack was hidden beneath the number 3 VHF antenna. Boeing has received five other reports of skin cracks between 1.5 and 3 inches in length in the same area. The reports also indicated that the main antenna support channel and other support structure were cracked. The earliest reported cracking occurred at 18,289 total flight cycles. The reported cracks were caused by dynamic loading of the number 3 VHF antenna due to extended main landing gear turbulence. Accomplishment of this service bulletin will make sure that any crack under the number 3 VHF antenna is detected and repaired before it reaches a critical length. Boeing Service Related Problem (SRP) 737-SRP-53-0313 is related to this service bulletin. Revision 1 is sent to give instructions for the repair and preventive modification of the skin at the number 3 VHF antenna location. The following sections are changed: 1. The Summary Action section is updated. 2. The summary illustration is updated. 3. Paragraph 1.A., Effectivity - 737-400 airplanes are moved from Group 3 to new Group 6. A new Group 7 is added. Group 2 airplanes before line number 292 are moved to Group 7. 4. Paragraph 1.C., Reason is updated. 5. Paragraph 1.D., Description is updated. 6. Paragraph 1.E., Compliance - A compliance table for Group 6 is added. A table for supplemental inspection information is also added. 7. Paragraph 1.G., Manpower - The manpower information is updated. 8. Paragraph 1.J.1., Existing Data - Non-Destructive Testing (NDT) and Structural Repair Manual (SRM) references are added. 9. Paragraph 1.J.2., Data supplied with this Service Bulletin - Installation drawings are added. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 24 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 25 10. Paragraph 1.K., Publications Affected - A Damage Tolerance Based Structural Inspection statement is added. 11. Paragraph 2.C.2., Parts and Materials Supplied by the Operator - Parts are added. 12. Paragraph 3.A., General Information - A note about fastener specification is added. 13. Paragraph 3.B., Work Instructions - Repair, preventive modification and supplemental inspection instructions are added. 14. Figures 13 to 44 are added. D. Description Group 1-4, Configuration 1; Group 5; Group 6, Configuration 1: Get internal access to the number 3 VHF antenna support structure. Do an internal detailed inspection of the antenna support structure, surrounding frames, stringers and skin for cracking or corrosion. Do an external detailed inspection and High Frequency Eddy Current (HFEC) inspection of the skin for cracking. If any crack is found in the skin, install a repair. If no cracking is found, repeat the inspections or install a preventive modification. If any crack is found in the antenna support structure, surrounding frames or stringers, contact Boeing for repair instructions and do the repair. If corrosion is found install a repair or contact Boeing for repair instructions and do the repair. Group 1-4, 6, Configuration 2: If a number 3 VHF antenna was previously installed, or it is unknown if the antenna was previously installed, accomplish detailed inspections of the skin until the cover plate is removed from the number 3 VHF antenna location. With the cover plate removed, do a one time external detailed inspection and a HFEC inspection of the skin for cracking. If any crack is found, install a repair. If no cracking is found install the cover plate at the number 3 VHF antenna location. If records show that a number 3 VHF antenna has never been installed then no work is necessary. If a repair or preventive modification is installed as given in this service bulletin, do supplemental Low Frequency Eddy Current (LFEC) inspections in the skin at fastener locations common to the doubler; do external detailed inspections of the doubler, tripler and skin and internal detailed inspections of the antenna support structure and skin for cracking. If any crack is found, contact Boeing for repair instructions and do the repair. Group 1-2, Configuration 3: No work is necessary. Group 7: Contact Boeing for the inspection, repair and preventive modification instructions. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. NOTE: The method for accomplishing internal frame inspections is changed in Revision 1 of this Service Bulletin. New and repeat inspections must be accomplished in accordance with Revision 1 of this Service Bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 25 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 26 Group 1-2, 7: Affected Maintenance Zones ZoneModel 2-18737-200, 737-200C Group 3: Affected Maintenance Zones ZoneModel 218737-300 Group 4: Affected Maintenance Zones ZoneModel 218737-500 Group 5: Affected Maintenance Zones ZoneModel 2-18737-200 Group 6: Affected Maintenance Zones ZoneModel 218737-400 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Group 7: Before further flight contact Boeing for the inspection, repair and preventive modification instructions and do the instructions. Group 1-2, Configuration 3: No work is necessary. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 26 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 27 Group 1-2, Configuration 1: Table 1: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,100 flight cycles. (b) Within 1,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.a. (a) (b) All Airplanes. 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external High Fre- quency Eddy Current (HFEC) inspection for any crack in the skin in accor- dance with Work Instruc- tions paragraph 3.B.3.a. (a) (b) 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an internal detailed and HFEC inspection for any crack or corrosion in the skin, antenna support structure, surrounding frames and stringers in accordance with Work In- structions paragraph 3.B.5.a. (b) 18,000 flight cy- cles. (b) Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the antenna and do an external detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.4.a. and do an internal detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.5.a. All Airplanes. (a) (b) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.a. Any crack or corrosion found in the skin or support channel. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 27 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 28 Group 1-2, Configuration 1: Table 1: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact Boeing for repair instructions and do the repair. Any crack or corrosion found in the surrounding frames or stringers or an- tenna support structure other than the support channel. (a) If an external doubler exists under the antenna that extends a minimum of 3 rows of fasteners all around the antenna base plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the antenna that does not extend a minimum of 3 rows of fasteners all around the antenna base plate, contact Boeing for inspection requirements or new repair instructions. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.a., or the repair in accordance with Work Instructions paragraph 3.B.6.a. terminates these inspection require- ments. Group 1-2, Configuration 2: Table 2: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition --No work is necessary.Airplanes that have never had a number 3 VHF anten- na installed. 2,100 flight cycles. (a) (b) Within 2,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.a. (a) (b) (c) Airplanes that have previ- ously had a number 3 VHF antenna installed or it is unknown if the airplane previously had a number 3 VHF antenna installed. -Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the cover plate and do an external de- tailed and High Frequen- cy Eddy Current (HFEC) inspection for any crack or corrosion in the skin in accordance with Work In- structions paragraph 3.B.4.a. (b) (c) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.a. Any crack or corrosion found in the skin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 28 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 29 Group 1-2, Configuration 2: Table 2: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) To terminate repeat external detailed inspections, accomplish the HFEC inspection with the cover plate removed or install a preventive modification in accordance with Work Instructions paragraph 3.B.7.a. (b) The Installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.a., or the repair in accordance with Work Instructions paragraph 3.B.6.a. terminates these inspection require- ments. (c) If an external doubler exists under the cover plate that extends a minimum of 3 rows of fasteners all around the cover plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the cover plate that does not extend a minimum of 3 rows of fasteners all around the cover plate, contact Boeing for inspection requirements or new repair instructions. Group 3, Configuration 1: Table 3: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,100 flight cycles. (b) Within 1,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.b. (a) (b) All Airplanes. 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external High Fre- quency Eddy Current (HFEC) inspection for any crack in the skin in accor- dance with Work Instruc- tions paragraph 3.B.3.b. (a) (b) 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an internal detailed and HFEC inspection for any crack or corrosion in the skin, antenna support structure, surrounding frames and stringers in accordance with Work In- structions paragraph 3.B.5.b. (b) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 29 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 30 Group 3, Configuration 1: Table 3: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 18,000 flight cy- cles. (b) Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the antenna and do an external detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.4.b. and do an internal detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.5.b. All Airplanes. (a) (b) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.b. Any crack or corrosion found in the skin or support channel. -Before further flight.Contact Boeing for repair instructions and do the repair. Any crack or corrosion found in the surrounding frames or stringers or an- tenna support structure other than the support channel. (a) If an external doubler exists under the antenna that extends a minimum of 3 rows of fasteners all around the antenna base plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the antenna that does not extend a minimum of 3 rows of fasteners all around the antenna base plate, contact Boeing for inspection requirements or new repair instructions. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.b., or the repair in accordance with Work Instructions paragraph 3.B.6.b. terminates these inspection require- ments. Group 3, Configuration 2: Table 4: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition --No work is necessary.Airplanes that have never had a number 3 VHF anten- na installed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 30 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 31 Group 3, Configuration 2: Table 4: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 2,100 flight cycles. (a) (b) Within 2,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.b. (a) (b) (c) Airplanes that have previ- ously had a number 3 VHF antenna installed or it is unknown if the airplane previously had a number 3 VHF antenna installed. -Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the cover plate and do an external de- tailed and High Frequen- cy Eddy Current (HFEC) inspection for any crack or corrosion in the skin in accordance with Work In- structions paragraph 3.B.4.b. (b) (c) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.b. Any crack or corrosion found in the skin. (a) To terminate repeat external detailed inspections, accomplish the HFEC inspection with the cover plate removed or install a preventive modification in accordance with Work Instructions paragraph 3.B.7.b. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.b., or the repair in accordance with Work Instructions paragraph 3.B.6.b. terminates these inspection require- ments. (c) If an external doubler exists under the cover plate that extends a minimum of 3 rows of fasteners all around the cover plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the cover plate that does not extend a minimum of 3 rows of fasteners all around the cover plate, contact Boeing for inspection requirements or new repair instructions. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 31 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 32 Group 4, Configuration 1: Table 5: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,100 flight cycles. (b) Within 1,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.c. (a) (b) All Airplanes. 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external High Fre- quency Eddy Current (HFEC) inspection for any crack in the skin in accor- dance with Work Instruc- tions paragraph 3.B.3.c. (a) (b) 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an internal detailed and HFEC inspection for any crack or corrosion in the skin, antenna support structure, surrounding frames and stringers in accordance with Work In- structions paragraph 3.B.5.c. (b) 18,000 flight cy- cles. (b) Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the antenna and do an external detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.4.c. and do an internal detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.5.c. All Airplanes. (a) (b) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.c. Any crack or corrosion found in the skin or support channel. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 32 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 33 Group 4, Configuration 1: Table 5: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact Boeing for repair instructions and do the repair. Any crack or corrosion found in the surrounding frames or stringers or an- tenna support structure other than the support channel. (a) If an external doubler exists under the antenna that extends a minimum of 3 rows of fasteners all around the antenna base plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the antenna that does not extend a minimum of 3 rows of fasteners all around the antenna base plate, contact Boeing for inspection requirements or new repair instructions. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.c., or the repair in accordance with Work Instructions paragraph 3.B.6.c. terminates these inspection require- ments. Group 4, Configuration 2: Table 6: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition --No work is necessary.Airplanes that have never had a number 3 VHF anten- na installed. 2,100 flight cycles. (a) (b) Within 2,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.c. (a) (b) (c) Airplanes that have previ- ously had a number 3 VHF antenna installed or it is unknown if the airplane previously had a number 3 VHF antenna installed. -Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the cover plate and do an external de- tailed and High Frequen- cy Eddy Current (HFEC) inspection for any crack or corrosion in the skin in accordance with Work In- structions paragraph 3.B.4.c. (b) (c) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.c. Any crack or corrosion found in the skin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 33 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 34 Group 4, Configuration 2: Table 6: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) To terminate repeat external detailed inspections, accomplish the HFEC inspection with the cover plate removed or do the preventive modification in accordance with Work Instructions paragraph 3.B.7.c. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.c., or the repair in accordance with Work Instructions paragraph 3.B.6.c. terminates these inspection require- ments. (c) If an external doubler exists under the cover plate that extends a minimum of 3 rows of fasteners all around the cover plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the cover plate that does not extend a minimum of 3 rows of fasteners all around the cover plate, contact Boeing for inspection requirements or new repair instructions. Group 5: Table 7: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,100 flight cycles.Within 1,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.d. (a) All Airplanes. 6,000 flight cycles.Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external High Fre- quency Eddy Current (HFEC) inspection for any crack in the skin in accor- dance with Work Instruc- tions paragraph 3.B.3.d. (a) 6,000 flight cycles.Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an internal detailed and HFEC inspection for any crack or corrosion in the skin, antenna support structure, surrounding frames and stringers in accordance with Work In- structions paragraph 3.B.5.d. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 34 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 35 Group 5: Table 7: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 18,000 flight cy- cles. Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the antenna and do an external detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.4.d. and do an internal detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.5.d. All Airplanes. (a) -Before further flight.Contact Boeing for repair instructions and do the repair. Any crack or corrosion found in the skin, antenna support structure, surround- ing frames or stringers. (a) If an external doubler exists under the antenna that extends a minimum of 3 rows of fasteners all around the antenna base plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the antenna that does not extend a minimum of 3 rows of fasteners all around the antenna base plate, contact Boeing for inspection requirements or new repair instructions. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 35 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 36 Group 6, Configuration 1: Table 8: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,100 flight cycles. (b) Within 1,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.b. (a) (b) All Airplanes. 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external High Fre- quency Eddy Current (HFEC) inspection for any crack in the skin in accor- dance with Work Instruc- tions paragraph 3.B.3.b. (a) (b) 6,000 flight cycles. (b) Within 6,000 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an internal detailed and HFEC inspection for any crack or corrosion in the skin, antenna support structure, surrounding frames and stringers in accordance with Work In- structions paragraph 3.B.5.b. (b) 18,000 flight cy- cles. (b) Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the antenna and do an external detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.4.b. and do an internal detailed and HFEC inspection for any crack or corrosion in the skin in accordance with Work Instructions paragraph 3.B.5.b. All Airplanes. (a) (b) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.d. Any crack or corrosion found in the skin or support channel. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 36 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 37 Group 6, Configuration 1: Table 8: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight. Contact Boeing for repair instructions and do the repair. Any crack or corrosion found in the surrounding frames or stringers or an- tenna support structure other than the support channel. (a) If an external doubler exists under the antenna that extends a minimum of 3 rows of fasteners all around the antenna base plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the antenna that does not extend a minimum of 3 rows of fasteners all around the antenna base plate, contact Boeing for inspection requirements or new repair instructions. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.d., or the repair in accordance with Work Instructions paragraph 3.B.6.d. terminates these inspection require- ments. Group 6, Configuration 2: Table 9: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition --No work is necessary.Airplanes that have never had a number 3 VHF anten- na installed. 2,100 flight cycles. (a) (b) Within 2,100 flight cycles af- ter the original issue date of this service bul- letin. Before 15,000 total airplane flight cycles. Do an external detailed inspection for any crack in the skin in accordance with Work Instructions paragraph 3.B.3.b. (a) (b) (c) Airplanes that have previ- ously had a number 3 VHF antenna installed or it is unknown if the airplane previously had a number 3 VHF antenna installed. -Within 18,000 flight cycles after the original issue date of this ser- vice bulletin. Remove the cover plate and do an external de- tailed and High Frequen- cy Eddy Current (HFEC) inspection for any crack or corrosion in the skin in accordance with Work In- structions paragraph 3.B.4.b. (b) (c) -Before further flight.Install a repair in accor- dance with Work Instruc- tions paragraph 3.B.6.d. Any crack or corrosion found in the skin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 37 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 38 Group 6, Configuration 2: Table 9: Inspection for Cracking at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) To terminate repeat external detailed inspections, accomplish the HFEC inspection with the cover plate removed or install a preventive modification in accordance with Work Instructions paragraph 3.B.7.d. (b) The installation of the preventive modification in accordance with Work Instructions paragraph 3.B.7.d., or the repair in accordance with Work Instructions paragraph 3.B.6.d. terminates these inspection require- ments. (c) If an external doubler exists under the cover plate that extends a minimum of 3 rows of fasteners all around the cover plate, accomplish these inspections on the doubler instead of the skin. If an external repair doubler exists under the cover plate that does not extend a minimum of 3 rows of fasteners all around the cover plate, contact Boeing for inspection requirements or new repair instructions. Table 10: Supplemental Inspections for Part 26 for Repairs and Modifications at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance TimeActionCondition 15,000 flight cy- cles. Within 60,000 flight cycles after the repair or preventive modifica- tion is installed. Do a Low Frequency Eddy Current (LFEC) inspection for any crack in the skin at the outer row of fasteners common to the doubler in accordance with Work In- structions paragraph 3.B.8. Repaired or Modified Air- planes with the Antenna Installed. 1,100 flight cycles.Within 75,000 flight cycles after the repair or preventive modifica- tion is installed. Do an external detailed in- spection for any crack in the doubler, tripler and skin in accordance with Work In- structions paragraph 3.B.8. 6,000 flight cycles.Within 75,000 flight cycles after the repair or preventive modifica- tion is installed. Do an internal detailed in- spection for any crack in the antenna support structure, skin, stringers and structural fillers (if installed) between frame bays and between stringers 26L and 26R in ac- cordance with Work Instruc- tions paragraph 3.B.8. 6,000 flight cycles.Within 75,000 flight cycles after the repair or preventive modifica- tion is installed. Do High Frequency Eddy Current (HFEC) inspections for cracking in the frames in accordance with Work In- structions paragraph 3.B.8. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 38 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 39 Table 10: Supplemental Inspections for Part 26 for Repairs and Modifications at the number 3 VHF Antenna Location. Repeat Interval (Not to Exceed) Compliance TimeActionCondition 15,000 flight cy- cles. Within 60,000 flight cycles after the repair or preventive modifica- tion is installed. Do an LFEC inspection for any crack in the skin at the outer row of fasteners com- mon to the doubler in accor- dance with Work Instructions paragraph 3.B.8. Repaired or Modified Air- planes without the Anten- na Installed. 6,000 flight cycles.Within 75,000 flight cycles after the repair or preventive modifica- tion is installed. Do HFEC inspections for cracking in the frames in ac- cordance with Work Instruc- tions paragraph 3.B.8. Before further flight.Contact Boeing for repair in- structions and do the repair. Any crack found. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:  Time to adjust to the workplace  Time to schedule the work  Time to inspect the work  Time to cure the materials  Time to make the parts  Time to find the tools. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 39 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 40 Group 1-2, Configuration 1: Table 1 - Inspection, Repair and preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501Open Access 2.102.101FIGURE 1External Inspection (With antenna not removed) 2.502.501FIGURE 5External Inspection (With antenna removed) 2.104.202FIGURE 9Internal Inspection 8.0016.002FIGURE 13Repair Preparation 7.0014.002FIGURE 14 (a)Repair Installation 3.256.502FIGURE 21Preventive Modification Prepara- tion 5.0010.002FIGURE 22Preventive Modification Inspection 2.502.501FIGURE 23 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 24 (a)Preventive Modification Installation 1.251.251Close Access 10.4512.55TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 25.4542.55TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 27.9545.05TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 1-2, Configuration 1: Table 2 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 5.2510.502FIGURE 37Supplemental Inspection Group 1-2, Configuration 2: Table 3 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.102.101FIGURE 1External Inspection (With cover plate not removed) 1.601.601FIGURE 4Cover Plate Removal BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 40 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 41 Group 1-2, Configuration 2: Table 3 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501FIGURE 5External Inspection (With cover plate removed) 1.601.601FIGURE 12Cover Plate Installation 8.0016.002FIGURE 13Repair Preparation 7.0014.002FIGURE 14 (a)Repair Installation 3.256.502FIGURE 21Preventive Modification Prepara- tion 5.0010.002FIGURE 22Preventive Modification Inspection 2.502.501FIGURE 23 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 24 (a)Preventive Modification Installation 1.251.251Close Access 7.807.80TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 22.4537.45TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 24.9539.95TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 1-2, Configuration 2: Table 4 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 1.002.002FIGURE 38Supplemental Inspection Group 3, Configuration 1: Table 5 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501Open Access 2.102.101FIGURE 2External Inspection (With antenna not removed) 2.502.501FIGURE 6External Inspection (With antenna removed) 2.104.202FIGURE 10Internal Inspection BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 41 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 42 Group 3, Configuration 1: Table 5 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 8.0016.002FIGURE 15Repair Preparation 7.0014.002FIGURE 16 (a)Repair Installation 3.507.002FIGURE 25Preventive Modification Prepara- tion 5.2510.502FIGURE 26Preventive Modification Inspection 2.502.501FIGURE 27 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 28 (a)Preventive Modification Installation 1.251.251Close Access 10.4512.55TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 25.4542.55TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 28.4546.05TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 3, Configuration 1: Table 6 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 5.2510.502FIGURE 39Supplemental Inspection Group 3, Configuration 2: Table 7 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.102.101FIGURE 2External Inspection (With cover plate not removed) 1.601.601FIGURE 4Cover Plate Removal 2.502.501FIGURE 6External Inspection (With cover plate removed) 1.601.601FIGURE 12Cover Plate Installation 8.0016.002FIGURE 15Repair Preparation 7.0014.002FIGURE 16 (a)Repair Installation BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 42 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 43 Group 3, Configuration 2: Table 7 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 3.256.502FIGURE 25Preventive Modification Prepara- tion 5.0010.002FIGURE 26Preventive Modification Inspection 2.502.501FIGURE 27 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 28 (a)Preventive Modification Installation 1.251.251Close Access 7.807.80TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 22.4537.45TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 24.9539.95TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 3, Configuration 2: Table 8 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 1.002.002FIGURE 40Supplemental Inspection Group 4, Configuration 1: Table 9 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501Open Access 2.102.101FIGURE 3External Inspection (With antenna not removed) 2.502.501FIGURE 7External Inspection (With antenna removed) 2.104.202FIGURE 11Internal Inspection 8.0016.002FIGURE 17Repair Preparation 7.0014.002FIGURE 18 (a)Repair Installation 3.507.002FIGURE 29Preventive Modification Prepara- tion 5.2510.502FIGURE 30Preventive Modification Inspection BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 43 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 44 Group 4, Configuration 1: Table 9 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501FIGURE 31 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 32 (a)Preventive Modification Installation 1.251.251Close Access 10.4512.55TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 25.4543.80TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 28.4546.05TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 4, Configuration 1: Table 10 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 5.2510.502FIGURE 41Supplemental Inspection Group 4, Configuration 2: Table 11 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.102.101FIGURE 3External Inspection (With cover plate not removed) 1.601.601FIGURE 4Cover Plate Removal 2.502.501FIGURE 7External Inspection (With cover plate removed) 1.601.601FIGURE 12Cover Plate Installation 8.0016.002FIGURE 17Repair Preparation 7.0014.002FIGURE 18 (a)Repair Installation 3.507.002FIGURE 29Preventive Modification Prepara- tion 5.2510.502FIGURE 30Preventive Modification Inspection 2.502.501FIGURE 31 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 32 (a)Preventive Modification Installation BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 44 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 45 Group 4, Configuration 2: Table 11 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 1.251.251Close Access 7.807.80TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 22.4537.45TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 25.4540.95TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 4, Configuration 2: Table 12 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 1.002.002FIGURE 42Supplemental Inspection Group 5: Table 13 - Inspection Elapsed HoursTask HoursNumber of Persons Task 2.502.501Open Access 2.102.101FIGURE 1External Inspection (With antenna not removed) 2.402.401FIGURE 8External Inspection (With antenna removed) 2.104.202FIGURE 9Internal Inspection 1.251.251Close Access 10.3512.45TOTAL FOR EACH AIRPLANE Group 6, Configuration 1: Table 14 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501Open Access 2.102.101FIGURE 2External Inspection (With antenna not removed) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 45 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 46 Group 6, Configuration 1: Table 14 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.502.501FIGURE 6External Inspection (With antenna removed) 2.104.202FIGURE 10Internal Inspection 8.0016.002FIGURE 19Repair Preparation 7.0014.002FIGURE 20 (a)Repair Installation 3.507.002FIGURE 33Preventive Modification Prepara- tion 5.2510.502FIGURE 34Preventive Modification Inspection 2.502.501FIGURE 35 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 36 (a)Preventive Modification Installation 1.251.251Close Access 10.4512.55TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 25.4542.55TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 28.4546.05TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 6, Configuration 1: Table 15 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 5.2510.502FIGURE 43Supplemental Inspection Group 6, Configuration 2: Table 16 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 2.102.101FIGURE 2External Inspection (With cover plate not removed) 1.601.601FIGURE 4Cover Plate Removal 2.502.501FIGURE 6External Inspection (With cover plate removed) 1.601.601FIGURE 12Cover Plate Installation BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 46 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 47 Group 6, Configuration 2: Table 16 - Inspection, Repair and Preventive Modification Elapsed HoursTask HoursNumber of Persons Task 8.0016.002FIGURE 19Repair Preparation 7.0014.002FIGURE 20 (a)Repair Installation 3.507.002FIGURE 33Preventive Modification Prepara- tion 5.2510.502FIGURE 34Preventive Modification Inspection 2.502.501FIGURE 35 (a)Preventive Modification - Antenna Support Structure Installation 6.7513.502FIGURE 36 (a)Preventive Modification Installation 1.251.251Close Access 7.807.80TOTAL FOR EACH AIRPLANE (INSPECTION ONLY) 22.4537.45TOTAL FOR EACH AIRPLANE IF A REPAIR IS INSTALLED 25.4540.95TOTAL FOR EACH AIRPLANE IF A PREVENTIVE MODIFICATION IS INSTALLED (a) Estimates do not include time to make parts. More time will be required to make parts. Group 6, Configuration 2: Table 17 - Supplemental Inspection Elapsed HoursTask HoursNumber of Persons Task 1.002.002FIGURE 44Supplemental Inspection H. Weight and Balance Changes Change in Moment (Pound-inches)Change in Weight (Pounds)Airplane Preventive Modifi- cation RepairPreventive Modification Repair + 6,300+ 7,000+ 7.7+ 8.6737-200 + 6,300+ 7,000+ 7.7+ 8.6737-200C + 6,300+ 7,000+ 7.7+ 8.6737-300 + 6,300+ 7,000+ 7.7+ 8.6737-400 + 6,300+ 7,000+ 7.7+ 8.6737-500 I. Electrical Load Data Not changed. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 47 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 48 J. References 1. Existing Data a. Boeing Service Bulletin 737-53A1042. b. Boeing Service Related Problem (SRP) 737-SRP-53-0313. c. Federal Aviation Administration (FAA) Airworthiness Directive 90-06-02. d. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-11, 20-50-19, 20-60-01. e. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 51-00-00, Part 6, 53-30-00 . f. 737-100/200 Aircraft Maintenance Manual (AMM) 23-21-11, 25-52-141, 25-52-51. g. 737-300/400/500 Aircraft Maintenance Manual (AMM) 23-21-11, 25-52-51, 25-52-91. h. 737-100/200 Structural Repair Manual (SRM) 51-20-1, 51-70. i. 737-300 Structural Repair Manual (SRM) 51-10-01, 51-30-01. j. 737-400 Structural Repair Manual (SRM) 51-10-01, 51-30-01. k. 737-500 Structural Repair Manual (SRM) 51-10-01, 51-30-01. l. Engineering Change Memo PRR 35005-293RS. m. Boeing Parts Standard Documents D-590. n. Boeing Drawing 65-88700. 2. Data supplied with this Service Bulletin a. Drawings: ADCNDCN/REVSheetTitleDrawing No --1TOP KIT - PREVENTIVE MOD INSTAL, AFT #3 VHF ANTENNA 65C37048 --2 --3 --4 --PSDLTOP KIT - PREVENTIVE MOD INSTAL, AFT #3 VHF ANTENNA 65C37048 DL -AKPLTOP KIT - PREVENTIVE MOD INSTAL, AFT #3 VHF ANTENNA 65C37048-1 -AKPLTOP KIT - PREVENTIVE MOD INSTL, AFT #3 VHF ANTENNA 65C37048-2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 48 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 49 ADCNDCN/REVSheetTitleDrawing No -AKPLTOP KIT - PREVENTIVE MOD INSTL, AFT #3 VHF ANTENNA 65C37048-3 -AKPLTOP KIT - PREVENTIVE MOD INSTL, AFT #3 VHF ANTENNA 65C37048-4 --1TOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049 --2 --3 --4 --PSDLTOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049 DL -AKPLTOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049-1 -AKPLTOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049-2 -AKPLTOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049-3 -AKPLTOP KIT - REPAIR INSTL, AFT #3 VHF ANTENNA 65C37049-4 3. Installation Drawings Used in the Preparation of this Service Bulletin TitleDrawing Number Skin Panel Instl - S-25L to S-25R, STA 727 to STA 101665-45776 Support Installation - VHF No. 3 Antenna, Lower Body65-65710 Antenna Installation - VHF No. 369-41653 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 49 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 50 L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 50 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### 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, repair and modification given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator Group 1, Configuration 1-2; Group 2, Configuration 1-2: Table 1: Repair NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET17 x 8 x 0.063 inches2023-T3 Clad (c)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (d)ALUMINUM SHEET22 x 13 x 0.071 inches2023-T3 Clad (e)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (g)BOLT8BACB30LR4-12 (g)BOLT8BACB30LR4-13 (g)BOLT2BACB30LR4-14 (g)BOLT8BACB30NW6K4Y (f) (g)BOLT77BACB30NW6K5Y (f) (g)BOLT53BACB30NW6K6Y (g)BOLT2BACB30NW6K7Y (g)BOLT2BACB30VT6K2 (g)BOLT8BACB30VT8K2 (f) (g)BOLT70BACB30YP6K3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 51 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 52 Group 1, Configuration 1-2; Group 2, Configuration 1-2: Table 1: Repair NotesNameQTYPart Number / Specification (f) (g)BOLT186BACB30YP6K4 (g)BOLT21BACB30YP6K5 (f)COLLAR279BACC30BL6 -COLLAR8BACC30BL8 (f)COLLAR140BACC30R6 -NUTPLATE2BACN10JZ4B2 (g)RIVET4BACR15GF4D8 (g)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37049-13 filler in accordance with this service bulletin. (c) This material is necessary to make the 65C37049-5 doubler in accordance with this service bulletin. (d) This material is necessary to make the 65C37049-6 tripler in accordance with this service bulletin. (e) This material is necessary to make the 65C37049-17 nutplate assembly in accordance with this service bulletin. (f) The quantity shown is in excess of requirements. (g) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. Group 1, Configuration 1-2; Group 2, Configuration 1-2: Table 2: Preventive Modification NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (c)ALUMINUM SHEET22 x 13 x 0.071 inches2023-T3 Clad (d)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (f)BOLT8BACB30LR4-12 (f)BOLT8BACB30LR4-13 (f)BOLT2BACB30LR4-14 (f)BOLT8BACB30MY8K2Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 52 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 53 Group 1, Configuration 1-2; Group 2, Configuration 1-2: Table 2: Preventive Modification NotesNameQTYPart Number / Specification (f)BOLT4BACB30MY8K3Y (f)BOLT8BACB30NW6K4Y (e) (f)BOLT77BACB30NW6K5Y (e) (f)BOLT53BACB30NW6K6Y (f)BOLT2BACB30NW6K7Y (f)BOLT10BACB30NX6K2Y (f)BOLT4BACB30NX6K3Y (f)BOLT2BACB30VT6K2 (f)BOLT8BACB30VT8K2 (e) (f)BOLT70BACB30YP6K3 (e) (f)BOLT180BACB30YP6K4 (f)BOLT26BACB30YP6K5 (f)BOLT1BACB30YP6K8 (e)COLLAR278BACC30BL6 (f)COLLAR8BACC30BL8 (e)COLLAR154BACC30R6 -COLLAR12BACC30R8 -NUTPLATE2BACN10JZ4B2 (f)RIVET4BACR15GF4D8 (f)RIVET5BACR15BA5AD3C (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37048-5 doubler in accordance with this service bulletin. (c) This material is necessary to make the 65C37048-6 tripler in accordance with this service bulletin. (d) This material is necessary to make the 65C37048-13 nutplate assembly in accordance with this service bulletin. (e) The quantity shown is in excess of requirements. (f) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 53 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 54 Group 3: Table 3: Repair NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET17 x 8 x 0.063 inches2023-T3 Clad (c)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (d)ALUMINUM SHEET22 x 13 x 0.071 inches2023-T3 Clad (e)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (g)BOLT8BACB30LR4-12 (g)BOLT8BACB30LR4-13 (g)BOLT2BACB30LR4-14 (g)BOLT8BACB30NW6K4Y (f) (g)BOLT80BACB30NW6K5Y (f) (g)BOLT51BACB30NW6K6Y (g)BOLT2BACB30NW6K7Y (g)BOLT2BACB30NX6K2Y (g)BOLT8BACB30VT8K2 (f) (g)BOLT70BACB30YP6K3 (f) (g)BOLT182BACB30YP6K4 (g)BOLT19BACB30YP6K5 (f)COLLAR271BACC30BL6 -COLLAR8BACC30BL8 (f)COLLAR143BACC30R6 -NUTPLATE2BACN10JZ4B2 (g)RIVET2BACR15GF6D9 (g)RIVET4BACR15GF4D8 (g)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37049-14 filler in accordance with this service bulletin. (c) This material is necessary to make the 65C37049-7 doubler in accordance with this service bulletin. (d) This material is necessary to make the 65C37049-8 tripler in accordance with this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 54 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 55 Group 3: Table 3: Repair NotesNameQTYPart Number / Specification (e) This material is necessary to make the 65C37049-17 nutplate assembly in accordance with this service bulletin. (f) The quantity shown is in excess of requirements. (g) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. Group 3: Table 4: Preventive Modification NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (c)ALUMINUM SHEET22 x 13 x 0.071 inches2023-T3 Clad (d)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (f)BOLT8BACB30LR4-12 (f)BOLT8BACB30LR4-13 (f)BOLT2BACB30LR4-14 (f)BOLT8BACB30NW6K4Y (e) (f)BOLT80BACB30NW6K5Y (e) (f)BOLT51BACB30NW6K6Y (f)BOLT2BACB30NW6K7Y (f)BOLT16BACB30NX6K2Y (f)BOLT8BACB30NX6K3Y (f)BOLT8BACB30VT6K3 (f)BOLT8BACB30VT8K2 (e) (f)BOLT70BACB30YP6K3 (e) (f)BOLT182BACB30YP6K4 (f)BOLT19BACB30YP6K5 (f)BOLT1BACB30YP6K8 (e)COLLAR279BACC30BL6 -COLLAR8BACC30BL8 (e)COLLAR165BACC30R6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 55 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 56 Group 3: Table 4: Preventive Modification NotesNameQTYPart Number / Specification -NUTPLATE2BACN10JZ4B2 (f)RIVET2BACR15GF6D9 (f)RIVET4BACR15GF4D8 (f)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37048-7 doubler in accordance with this service bulletin. (c) This material is necessary to make the 65C37048-8 tripler in accordance with this service bulletin. (d) This material is necessary to make the 65C37048-13 nutplate assembly in accordance with this service bulletin. (e) The quantity shown is in excess of requirements. (f) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. Group 4: Table 5: Repair NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET17 x 8 x 0.063 inches2023-T3 Clad (c)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (d)ALUMINUM SHEET22 x 14 x 0.071 inches2023-T3 Clad (e)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (g)BOLT8BACB30LR4-12 (g)BOLT8BACB30LR4-13 (g)BOLT2BACB30LR4-14 (g)BOLT8BACB30NW6K4Y (f) (g)BOLT80BACB30NW6K5Y (f) (g)BOLT50BACB30NW6K6Y (g)BOLT2BACB30NW6K7Y (g)BOLT2BACB30NX6K2Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 56 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 57 Group 4: Table 5: Repair NotesNameQTYPart Number / Specification (g)BOLT8BACB30VT8K2 (f) (g)BOLT70BACB30YP6K3 (f) (g)BOLT181BACB30YP6K4 (g)BOLT21BACB30YP6K5 (f)COLLAR274BACC30BL6 -COLLAR8BACC30BL8 (f)COLLAR143BACC30R6 -NUTPLATE2BACN10JZ4B2 (g)RIVET2BACR15GF6D9 (g)RIVET4BACR15GF4D8 (g)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37049-16 filler in accordance with this service bulletin. (c) This material is necessary to make the 65C37049-11 doubler in accordance with this service bulletin. (d) This material is necessary to make the 65C37049-12 tripler in accordance with this service bulletin. (e) This material is necessary to make the 65C37049-17 nutplate assembly in accordance with this service bulletin. (f) The quantity shown is in excess of requirements. (g) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. Group 4: Table 6: Preventive Modification NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET25 x 19 x 0.071 inches2023-T3 Clad (c)ALUMINUM SHEET22 x 14 x 0.071 inches2023-T3 Clad (d)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (f)BOLT8BACB30LR4-12 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 57 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 58 Group 4: Table 6: Preventive Modification NotesNameQTYPart Number / Specification (f)BOLT8BACB30LR4-13 (f)BOLT2BACB30LR4-14 (f)BOLT8BACB30NW6K4Y (e) (f)BOLT81BACB30NW6K5Y (e) (f)BOLT51BACB30NW6K6Y (f)BOLT2BACB30NW6K7Y (f)BOLT16BACB30NX6K2Y (f)BOLT8BACB30NX6K3Y (f)BOLT8BACB30VT6K3 (f)BOLT8BACB30VT8K2 (e) (f)BOLT70BACB30YP6K3 (e) (f)BOLT182BACB30YP6K4 (f)BOLT21BACB30YP6K5 (f)BOLT1BACB30YP6K8 (e)COLLAR281BACC30BL6 -COLLAR8BACC30BL8 (e)COLLAR166BACC30R6 -NUTPLATE2BACN10JZ4B2 (f)RIVET2BACR15GF6D9 (f)RIVET4BACR15GF4D8 (f)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37048-11 doubler in accordance with this service bulletin. (c) This material is necessary to make the 65C37048-12 tripler in accordance with this service bulletin. (d) This material is necessary to make the 65C37048-13 nutplate assembly in accordance with this service bulletin. (e) The quantity shown is in excess of requirements. (f) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 58 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 59 Group 6: Table 7: Repair NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET17 x 8 x 0.063 inches2023-T3 Clad (c)ALUMINUM SHEET24 x 19 x 0.071 inches2023-T3 Clad (d)ALUMINUM SHEET22 x 14 x 0.071 inches2023-T3 Clad (e)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (g)BOLT8BACB30LR4-12 (g)BOLT8BACB30LR4-13 (g)BOLT2BACB30LR4-14 (g)BOLT3BACB30NW6K3Y (g)BOLT3BACB30NW6K4Y (f) (g)BOLT56BACB30NW6K5Y (f) (g)BOLT48BACB30NW6K6Y (g)BOLT4BACB30NW6K7Y (g)BOLT4BACB30NW6K8Y (g)BOLT2BACB30NX6K2Y (g)BOLT8BACB30VT8K2 (f) (g)BOLT66BACB30YP6K3 (f) (g)BOLT175BACB30YP6K4 (g)BOLT30BACB30YP6K5 (f)COLLAR271BACC30BL6 -COLLAR8BACC30BL8 (f)COLLAR120BACC30R6 -NUTPLATE2BACN10JZ4B2 (g)RIVET2BACR15GF6D9 (g)RIVET4BACR15GF4D8 (g)RIVET4BACR15GF5D7 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup- plier data. (b) This material is necessary to make the 65C37049-15 filler in accordance with this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 59 of 250 BOEING SERVICE BULLETIN 737-53-1287 ### Page 60 Group 6: Table 7: Repair NotesNameQTYPart Number / Specification (c) This material is necessary to make the 65C37049-9 doubler in accordance with this service bulletin. (d) This material is necessary to make the 65C37049-10 tripler in accordance with this service bulletin. (e) This material is necessary to make the 65C37049-17 nutplate assembly in accordance with this service bulletin. (f) The quantity shown is in excess of requirements. (g) Alternate fasteners are listed in Structural Repair Manual, Chapter 51. Group 6: Table 8: Preventive Modification NotesNameQTYPart Number / Specification (a)PRESSURE AND ENVIRON- MENTAL SEALANT 10 OzBMS 5-95, CLASS B-1/2 (a)CORROSION INHIBITING COMPOUND 15 OzBMS 3-35 or BMS 3-29 (b)ALUMINUM SHEET24 x 19 x 0.071 inches2023-T3 Clad (c)ALUMINUM SHEET22 x 14 x 0.071 inches2023-T3 Clad (d)ALUMINUM PLATE4 x 3 x 0.25 inches7075-T651 (f)BOLT8BACB30LR4-12 (f)BOLT8BACB30LR4-13 (f)BOLT2BACB30LR4-14 (f)BOLT3BACB30NW6K3Y (f)BOLT3BACB30NW6K4Y (e) (f)BOLT56BACB30NW6K5Y (e) (f)BOLT48BACB30NW6K6Y (f)BOLT4BACB30NW6K7Y (f)BOLT4BACB30NW6K8Y (f)BOLT16BACB30NX6K2Y (f)BOLT8BACB30NX6K3Y (f)BOLT8BACB30VT6K3 (f)BOLT8BACB30VT8K2 (e) (f)BOLT66BACB30YP6K3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 11, 2009 737-53-1287Revision 1: November 15, 2010 60 of 250 BOEING SERVICE BULLETIN 737-53-1287 The text continues at https://openairdocs.org/service-documents/boeing/sb-737-53-1287/file/0b65ee8be6fa.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.