# Boeing Alert Service Bulletin 747-53A2088: Revision 4 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-1023; AD 2014-05-24 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-53A2088](https://openairdocs.org/service-documents/boeing/747-53a2088.md) - Title as filed: U.S. DOT/FAA - SB-747-53A2088-04- - Pages: 62 - PDF: https://openairdocs.org/files/sha256/86/d9/86d9a976942a820cd18a1ae7d3982bd0d3c35a01d7dd599abb2fdf85745066a4 - Page: https://openairdocs.org/service-documents/boeing/747-53a2088/file/86d9a976942a ## 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 747 Service Bulletin ALERT Number: 747-53A2088 Original Issue: March 08, 1974 Revision 4: January 11, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Body Station 760 or 780 - Frame to Tension Tie Joint - Inspection / Modification Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 1989 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management Company. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 1 of 62 5.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 2 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 3 A. Effectivity ............................................... 1 3 1. Airplanes ............................................ 1 3 2. Spares Affected ........................................ 1 5 B. Concurrent Requirements ...................................... 1 5 C. Reason ................................................ 1 5 D. Description .............................................. 1 7 E. Compliance .............................................. 1 8 F. Approval ............................................... 2 1 G. Manpower .............................................. 2 1 H. Weight and Balance Changes .................................... 2 2 I. Electrical Load Data ......................................... 2 2 J. References .............................................. 2 2 1. Existing Data: ......................................... 2 2 2. Data Supplied with this Service Bulletin: ........................... 2 3 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 3 K. Publications Affected ........................................ 2 3 L. Interchangeability and Intermixability of Parts ........................... 2 3 M. Software Accomplishment Summary ................................ 2 3 2. MATERIAL INFORMATION ........................................ 2 5 A. Material - Price and Availability ................................... 2 5 B. Industry Support Information .................................... 2 5 C. Parts Necessary for Each Airplane ................................. 2 5 1. Kits/Parts ............................................ 2 5 2. Parts and Materials Supplied by the Operator ........................ 2 6 3. Parts Modified and Reidentified ................................ 2 7 4. Parts Removed and Not Replaced .............................. 2 7 D. Parts Necessary to Change Spares ................................. 2 7 E. Special Tooling - Price and Availability ............................... 2 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9 A. GENERAL INFORMATION ..................................... 2 9 B. WORK INSTRUCTIONS ....................................... 3 0 FIGURE 1: UNMODIFIED TENSION TIE INSPECTION ......................... 3 3 FIGURE 2: MODIFIED TENSION TIE INSPECTION ........................... 3 6 FIGURE 3: FRAME TENSION TIE MODIFICATION ........................... 3 8 FIGURE 4: THIS FIGURE IS DELETED (REVISION 4) ......................... 4 3 FIGURE 5: THIS FIGURE IS DELETED (REVISION 4) ......................... 4 4 FIGURE 6: THIS FIGURE IS DELETED (REVISION 4) ......................... 4 5 FIGURE 7: ALTERNATIVE MODIFICATION [Group 1] .......................... 4 6 FIGURE 8: ALTERNATIVE MODIFICATION [Group 2] .......................... 5 1 FIGURE 9: ALTERNATIVE MODIFICATION [Group 3] .......................... 5 6 APPENDIX A: ADDENDUM - FLIGHT SAFETY SECTION .......................... 6 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 3 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 4 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT BLANK PAGE ### Page 5 Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-53A2088Original Issue: March 08, 1974 Revision 4: January 11, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Body Station 760 or 780 - Frame to Tension Tie Joint - Inspection / Modification This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on all airplanes that have not been modified in accordance with the original issue, Revision 1, Revision 2 or Revision 3 of this service bulletin. Do a surface High Frequency Eddy Current (HFEC) inspection of the radius common to the aft channel of the tension tie at the next inspection that is scheduled to be done in accordance with Paragraph 1.E., Compliance and accomplish the tension tie modification at the time given in Paragraph 1.E., Compliance. Federal Aviation Administration (FAA) Airworthiness Directive AD 84-19-01 is related to this service bulletin. REASON FOR REVISION This revision is sent to add a surface High Frequency Eddy Current (HFEC) inspection of the upper and lower radius common to the aft channel of the tension tie and to add a compliance time for the accomplishment of the tension tie modification. These sections were changed: 1. Summary Section: Added new Background information related to the revision. Updated Action section to reflect new requirements. Added Federal Aviation Administration (FAA) Airworthiness Directive information to the compliance section. Added new industry support information. Revised Summary illustration text to reflect changed actions. 2. In Paragraph 1.C., Reason: Added new background information related to the revision. 3. In Paragraph 1.D., Description: Updated the action descriptions to reflect new requirements, added "More work" statement and added maintenance zone tables. 4. In Paragraph 1.E., Compliance: Updated compliance times and added new compliance tables. 5. In Paragraph 1.F., Approval: Is updated and a new approval statement added. 6. In Paragraph 1.G., Manpower: Updated manpower estimate. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 5 of 62 ### Page 6 7. In Paragraph 1.H., Weight and Balance Changes: Updated weight and balance and added new weight and balance tables. 8. In Paragraph 1.J., References: Added new references related to this revision. 9. In Paragraph 1.K., Publications Affected: Added statement for damage tolerance inspections. 10. In Paragraph 2.B., Industry Support Information: Added new industry support information. 11. In Paragraph 3.A., General Information: Updated general notes to current requirements. 12. In Paragraph 3.B., Work Instructions, PART I - Flight Safety Inspection Program: Added a new surface High Frequency Eddy Current (HFEC) inspection of tension ties. Removed compliance times and removed the reference to report any discrepancies in the Flight Safety Addendum. 13. Figure 1: Added a new detailed inspection and surface High Frequency Eddy Current (HFEC) inspection of tension ties. 14. Figure 2: Updated the AMM reference for ceiling panel removal. Removed the word optional from the view A-A illustration. Changed close visual inspection to a detailed inspection. 15. Figure 3: Added a new section view to the illustration. 16. Figure 4, Figure 5 and Figure 6 logic diagrams have been deleted. The flight safety and economic based inspection program information can be found in Paragraph 1.E., Compliance. 17. Figure 7, Figure 8 and Figure 9: Added and removed typical measurements from the illustrations. 18. APPENDIX A: In table 1 the inspection method and repeat inspection threshold times have been updated. 19. ADDENDUM: Removed the evaluation form from the addendum section. 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 08, 1974Original Issue: May 01, 1974Revision 1: August 26, 1983Revision 2: September 08, 1994Revision 3: January 11, 2013Revision 4: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 6 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 7 Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-53A2088Original Issue: March 08, 1974 Revision 4: January 11, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Body Station 760 or 780 - Frame to Tension Tie Joint - Inspection / Modification THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND Accomplishment of the inspection program detailed in this bulletin will make sure the structural integrity of the Body Station 760 or 780 (as applicable) tension tie throughout the operational life of the airplane. Undetected tension tie cracking could eventually result in in-flight depressurization of the airplane and the inability to withstand current regulatory failsafe loads. Inspection of the fatigue test airplane after the equivalent of 12,000 flight-cycles revealed a crack in the BS 760 tension tie as a result of bending due to cabin pressurization. Structural reassessment of the 747 airplane has been conducted under the requirements of Federal Aviation Administration (FAA) Advisory Circular 91-56, in accordance with Federal Aviation Regulation (FAR) 25.571 as amended in 1978, to ensure the safe operation of 747 airplanes throughout their operational life. As a result of this reassessment, the BS 760 or 780 (as applicable) tension tie has been determined to be structurally significant in that it is critical to the structural integrity of the airplane. Tension tie cracking not detected prior to it reaching critical crack length may result in in-flight depressurization of the airplane and the inability to withstand current regulatory failsafe loads. Therefore, a flight-safety inspection program which will continue throughout the operational life of the airplane is defined in this service bulletin. The upper deck tension ties have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD, refer to Boeing Service Letter 747-SL-53-088. Boeing Fleet Team Digest (FTD) 747 FTD 53-03005 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 7 of 62 ### Page 8 Boeing Service Related Problem (SRP) 747-SRP-53-0403 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., ComplianceYesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 85901-120RS) This bulletin contains a flight safety inspection, an economics based inspection, and a modification. The flight safety inspection is the minimum inspection program to maintain the structural integrity of the affected area of the airplane. The economics based inspection, applicable to airplanes on which the modification described herein has not been incorporated, may be used in lieu of the flight safety inspection, at operator's option, until the modification is incorporated. The modification described herein will improve the resistance to cracking of the tension tie but does not alter the structural environment of the tension tie such that a flight safety inspection is not required. It does enable the initiation of the flight safety inspection to be deferred and increases the reinspection interval. Flight Safety Inspection Program - Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection for cracking in the outboard ends of each affected tension tie. If any cracking is found within specified limits, do the modification. If any cracking is found out of specified limits, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections until the tension tie is repaired or modified. Do the tension tie modification at the time in accordance with Paragraph 1.E., Compliance. The modification consists of replacing the existing tension tie doubler with a longer doubler. At tension tie locations that have been repaired or modified, do a detailed inspection for any cracking. If any cracking is found in a repaired or modified tension tie, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections at the times in accordance with Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 8 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 9 Economic Inspection Program - The economics based inspections (detailed and surface HFEC inspections at operator's option) are used to detect cracking at an earlier stage. If any cracking is found within specified limits do the modification. If cracking is found out of specified limits, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections until the tension tie is repaired or modified. EFFECTIVITY 747-100, 747-200B, 747-200F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE Refer to Paragraph 1.E., Compliance. Federal Aviation Administration (FAA) Airworthiness Directive AD 84-19-01 is related to this service bulletin. INDUSTRY SUPPORT INFORMATION This service bulletin was first released before October of 1994. Thus industry support for affected airplanes depends upon whether the operator previously filed a warranty claim with Boeing on this service bulletin. MANPOWER Elapsed HoursTotal Task HoursAirplanes 2.505.00Inspection 16.0032.00Modification MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 9 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 10 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 10 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 11 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT DO A DETAILED INSPECTION AND A HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE TENSION TIE FOR ANY CRACKING. IF ANY CRACKING IS FOUND WITHIN SPECIFIED LIMITS, DO THE MODIFICATION. IF CRACKING IS FOUND OUT OF SPECIFIED LIMITS, CONTACT BOEING FOR REPAIR INSTRUCTIONS AND DO THE WORK STA 760 (GROUP 1 AND 2) INSTRUCTED BY BOEING. IF NO CRACKING IS STA 780 (GROUP 3) FOUND, DO THE TENSION TIE MODIFICATION IN FRAME ACCORDANCE WITH PARAGRAPH 1.E.,COMPLIANCE FATIGUE TEST CRACK \ +++++++ + T SUP INSPECTION AREA INBD < VIEW A-A EXISTING CONFIGURATION DO A POST MODIFICATION DETAILED INSPECTION OF THE TENSION TIE FOR ANY CRACKING. IF ANY CRACKING IS FOUND CONTACT BOEING FOR REPAIR INSTRUCTIONS AND DO THE WORK INSTRUCTED BY BOEING. IF NO CRACKING IS FOUND, REPEAT THE INSPECTIONS IN ACCORDANCE WITH PARAGRAPH 1.E., COMPLIANCE. INSPECTION AREA ADD NEW. VIEW A-A DOUBLER MODIFIED CONFIGURATION R09726 Original Issue: March 08, 1974 Revision 4: January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 11 of 62 ### Page 12 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 12 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT BLANK PAGE ### Page 13 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2088 Original Issue: March 08, 1974 Revision 4: January 11, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Body Station 760 or 780 - Frame to Tension Tie Joint - Inspection / Modification THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplane(s) shown below. Refer to PRR85901-120RS for data about this change. Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. NOTE: Airplanes that follow that have been modified by Boeing to the Special Freighter configuration are not affected by this service bulletin. 1. 2. Airplanes that follow that have been modified by Boeing to the Extended Upper Deck configuration are not affected by this service bulletin. 3. Airplanes that follow that have been modified as shown in Boeing Service Bulletin 747-25-2692, "Equipment/Furnishings - Upper Deck Passenger Compartment Conversion - Upper Deck Extension Station 710 - Station 780 Modification," are not affected by this service bulletin. DESCRIPTIONCONFIGURATIONGROUP 747-100 and 747-200B Passenger airplanes with a different Tension tie lay out to Group 2 and Group 3 airplanes. -1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 13 of 62 ### Page 14 DESCRIPTIONCONFIGURATIONGROUP 747-100 and 747-200B Passenger airplanes with a different Tension tie lay out to Group 1 and Group 3 airplanes. -2 747-200F airplanes with a different Tension tie lay out to Group 1 and Group 2 airplanes. -3 Airplane Models: 747-100, 747-200B, 747-200F GroupVariable Number 1RA001 - RA025 1RA027 - RA028 1RA030 - RA032 1RA034 1RA104 - RA110 1RA113 - RA115 2RA164 1RA201 - RA203 1RA216 2RA217 1RA251 - RA255 2RA256 - RA261 2RA309 2RA311 1RA351 - RA360 1RA369 - RA371 2RA372 - RA373 1RA404 2RA413 1RA501 - RA502 1RA521 - RA523 2RA525 - RA527 1RA532 - RA534 2RA535 - RA540 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 14 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 15 GroupVariable Number 1RA551 - RA552 1RA559 - RA560 2RA561 1RA581 - RA582 2RA585 1RA601 - RA602 1RA631 1RA633 1RA651 - RA652 2RA676 1RA701 2RA702 1RA721 1RA741 1RA761 1RA781 1RA903 - RA909 1RA914 2RB071 - RB075 1RB101 - RB102 3RR201 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of the inspection program detailed in this bulletin will make sure the structural integrity of the Body Station 760 or 780 (as applicable) tension tie throughout the operational life of the airplane. Undetected tension tie cracking could eventually result in in-flight depressurization of the airplane and the inability to withstand current regulatory failsafe loads. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 15 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 16 Body tension ties are located in the upper body just aft of the upper deck floor structure to reduce body flexure caused by pressurization cycles. On the fatigue test airplane, the tension tie at BS 760 was found cracked after the equivalent of 12,000 flights. Cracking occurred near the inboard end of the splice doubler at the juncture of the tension tie and the BS 760 frame. Cracking is attributed to bending loads induced by frame flexure during cabin pressurization. Structural reassessment of the 747 airplane has been conducted under the requirements of Federal Aviation Administration (FAA) Advisory Circular 91-56, in accordance with Federal Aviation Regulation (FAR) 25.571 as amended in 1978, to ensure the safe operation of 747 airplanes throughout their operational life. As a result of this reassessment, the affected tension tie has been determined to be structurally significant in that it is critical to the structural integrity of the airplane. Tension tie cracking not detected prior to it reaching critical crack length may result in in-flight depressurization of the airplane. Therefore, a flight-safety inspection program which will continue throughout the operational life of the airplane is defined in this service bulletin. Revision 1 added previously omitted airplanes to Group 1 of the effectivity and incorporated Notice of Status Change dated 5 April, 1974 which corrected a typographical error in the note under Paragraph I .A.1. Revision 2 added the flight safety and economics based inspection program definitions, where applicable, throughout the service bulletin. In addition, a flight safety addendum is added to the bulletin as a summary of the inspections required to ensure the structural integrity of the applicable area and to provide the format for reporting inspection results to Boeing. Notices of Status Change dated 16 October, 1975 and 4 April, 1980 are incorporated to revise subkit nomenclature and to note that airplanes converted to the Special Freighter configuration are not affected by this bulletin. Also, the effectivity is updated to reflect current airplane ownership. Revision 3 is sent to add an alternative tension tie modification. This is shown in new Figures 7, 8, and 9. Revision 3 is also sent to add reference to Boeing Service Bulletin 747-25-2692, "Equipment/Furnishings - Upper Deck Passenger Compartment Conversion - Upper Deck Extension Station 710 - Station 780 Modification." As part of the change in Service Bulletin 747-25-2692, the tension tie at STA 760 is removed and replaced with a floor beam. The work shown in this service bulletin is not necessary after the change in Service Bulletin 747-25-2692 has been installed. The airplanes that follow have been removed from Paragraph I.A.1, Effectivity. These airplanes were changed by Boeing to the Special Freighter or Extended Upper Deck configuration: RA029, RA033, RA101-RA103, RA111-RA112, RA161-RA163, RA245-RA246, RA301-RA306, RA307-RA308, RA310, RA312, RA524, RA632, RA634-RA635, RA671-RA675, RA677, RA722-RA724, RA742-RA743, RA901-RA902, RA910-RA913, RA915-RA916, RB041, RB043. As part of the change to the Special Freighter or Extended Upper Deck configuration, the tension tie at STA 760 was removed and replaced with a floor beam. Airplane RB013 has also been removed from Paragraph I.A.1, Effectivity. On this airplane, a floor beam was installed at BS 760 in production. All affected airplanes, unmodified or modified per previous issues of this bulletin require flight safety inspection as noted herein. The upper deck tension ties have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD, refer to Boeing Service Letter 747-SL-53-088. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 16 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 17 Boeing Fleet Team Digest (FTD) 747 FTD 53-03005 is related to this service bulletin. Boeing Service Related Problem (SRP) 747-SRP-53-0403 is related to this service bulletin. Revision 4 is sent to add a surface High Frequency Eddy Current (HFEC) inspection of the upper and lower radius common to the aft channel of the tension tie and to add a compliance time for the accomplishment of the tension tie modification. D. Description This bulletin contains a flight safety inspection, an economics based inspection, and a modification. The flight safety inspection is the minimum inspection program to maintain the structural integrity of the affected area of the airplane. The economics based inspection, applicable to airplanes on which the modification described herein has not been incorporated, may be used in lieu of the flight safety inspection, at operator's option, until the modification is incorporated. The modification described herein will improve the resistance to cracking of the tension tie but does not alter the structural environment of the tension tie such that a flight safety inspection is not required. It does enable the initiation of the flight safety inspection to be deferred and increases the reinspection interval. Flight Safety Inspection Program - Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection for cracking in the outboard ends of each affected tension tie. If any cracking is found within specified limits, do the modification. If any cracking is found out of specified limits, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections until the tension tie is repaired or modified. Do the tension tie modification at the time in accordance with Paragraph 1.E., Compliance. The modification consists of replacing the existing tension tie doubler with a longer doubler. At tension tie locations that have been repaired or modified, do a detailed inspection for any cracking. If any cracking is found in a repaired or modified tension tie, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections at the times in accordance with Paragraph 1.E., Compliance. Economic Inspection Program - The economics based inspections (detailed and surface HFEC inspections at operator's option) are used to detect cracking at an earlier stage. If any cracking is found within specified limits do the modification. If cracking is found out of specified limits, contact Boeing for repair instructions and do the work instructed by Boeing. If no cracking is found, repeat the inspections until the tension tie is repaired or modified. Revision 3 - No more work is necessary on airplanes changed by the initial release, Revision 1, or Revision 2 of this service bulletin as a result of Revision 3. The effectivity is divided into three groups because of differences in inspection and modification area. PLEASE REPORT ADVERSE INSPECTION RESULTS TO BOEING USING THE REPORT SYSTEM DESCRIBED IN APPENDIX A OF THIS SERVICE BULLETIN. NOTE: Contact Boeing for instructions if any damaged areas exceed the specified limits. To expedite Boeing response, be specific when defining and locating the damage. Circumstances leading up to the damage and any secondary effects, when known, should be included in the communication and followed up by sketches and photographs when appropriate. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 17 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 18 SEND TO: BOEING COMMERCIAL AIRPLANE GROUP ATTENTION: MANAGER, AIRLINE SUPPORT Revision 4 - More work is necessary on all airplanes that have not been modified in accordance with the original issue, Revision 1, Revision 2 or Revision 3 of this service bulletin. Do a surface High Frequency Eddy Current (HFEC) inspection of the radius common to the aft channel of the tension tie at the next inspection that is scheduled to be done in accordance with Paragraph 1.E., Compliance and accomplish the tension tie modification at the time given in Paragraph 1.E., Compliance. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1-2: Affected Maintenance Zones ZoneModel 233, 234747-100, 747-200B Group 3: Affected Maintenance Zones ZoneModel 233, 234747-200F E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 84-19-01 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 18 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 19 Table 1: Tension Tie Inspection and Modification (Flight Safety Inspection Program) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 3,700 flight cy- cles.(a) Within 500 flight cycles after the effective date of AD 84-19-01. Before 8,000 to- tal flight cycles. Do a detailed inspection of the tension tie at BS 760 (Group 1 and 2 air- planes) or BS 780 (Group 3 airplanes) for any cracking in accordance with Paragraph 3.B., Work Instructions Part I. Airplanes that have not ac- complished the modifica- tion to the tension tie at BS 760 (Group 1 and 2) or BS 780 (Group 3) in accor- dance with this service bul- letin. Within 3,700 flight cycles af- ter the Revision 4 date of this service bulletin. Before 8,000 to- tal flight cycles. Do a detailed inspection and a surface High Fre- quency Eddy Current (HFEC) inspection of the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 air- planes) for any cracking in accordance with Para- graph 3.B., Work Instruc- tions Part I. -Before further flight.Do the modification in ac- cordance with Paragraph 3.B., Work Instructions Part III. If cracking is found within limits. (a) -Before further flight.Contact Boeing for repair instructions and do the work instructed by Boe- ing. If cracking is found in the tension tie out of limits. -Within 2,000 flight cycles af- ter the Revision 4 date of this service bulletin. Before 16,000 total flight cy- cles. Do the modification in ac- cordance with Paragraph 3.B., Work Instructions Part III. (a) If no cracking is found. (a) Accomplishment of the modification terminates the repeat inspection requirement. Refer to Table 2 for post modification inspections. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 19 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 20 Table 2: Post Modification Inspection (Flight Safety Inspection Program) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 8,000 flight cycles. (a) Within 1,000 flight cycles af- ter the effective date of AD 84- 19-01. (a) Within 10,000 flight cycles af- ter the accom- plishment of the modification. (a) Do a detailed inspection of the tension tie at BS 760 (Group 1 and 2 air- planes) or BS 780 (Group 3 airplanes) for any cracking in accordance with Paragraph 3.B., Work Instructions Part I. Airplanes that have accom- plished the Modification to the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 air- planes) in accordance with this service bulletin. -Before further flight.Contact Boeing for repair instructions and do the work instructed by Boe- ing. If any crack is found in a modified tension tie. (a) Additional post modification inspections are given in Boeing service bulletin 747-53A2502. Table 3: Tension Tie Inspection and Modification (Economic Based Inspection Program) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition 1,000 flight cy- cles.(a) Before 7,000 total flight cycles.Do a detailed inspection and a surface High Fre- quency Eddy Current (HFEC) inspection of the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 air- planes) for any cracking in accordance with Para- graph 3.B., Work Instruc- tions Part II. Airplanes that have not ac- complished the modifica- tion to the tension tie at BS 760 (Group 1 and 2) or BS 780 (Group 3) in accor- dance with this service bul- letin. -Before further flight.Do the modification in ac- cordance with Paragraph 3.B., Work Instructions Part III. If cracking is found within limits. (a) -Before further flight.Contact Boeing for repair instructions and do the work instructed by Boe- ing. If cracking is found in the tension tie out of limits. -Within 2,000 flight cycles af- ter the Revision 4 date of this service bulletin. Before 16,000 total flight cy- cles. Do the modification in ac- cordance with Paragraph 3.B., Work Instructions Part III. (a) If no cracking is found. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 20 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 21 Table 3: Tension Tie Inspection and Modification (Economic Based Inspection Program) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (a) Accomplishment of the modification terminates the repeat inspection requirement. Refer to Table 2 for post modification inspections. 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. In addition, the Manager of the FAA Seattle Aircraft Certification Office (ACO) approves the accomplishment of the inspection, modification and post modification inspections with the corresponding compliance times given in Service Bulletin 747-53A2088, Revision 4, as an alternative method of compliance to the inspection, optional modification, and post modification inspection requirements with corresponding compliance times required by paragraphs (A) and (B) of AD 84-19-01. Where this SB states to contact Boeing for repair instructions, these instructions must be approved as an AMOC per the instructions in paragraph (C) of AD 84-19-01. All provisions of AD 84-19-01 that are not specifically referenced in this paragraph remain fully applicable and must be complied with accordingly. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection and modification for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:  Time to adjust to the workplace  Time to schedule the work  Time to inspect the work  Time to cure the materials  Time to make the parts  Time to find the tools. Elapsed HoursTask HoursNumber of PersonsTask 0.501.002Open Access 1.503.002Inspection (a)(a)(a)Repair 15.0030.002Modification Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 21 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 22 Elapsed HoursTask HoursNumber of PersonsTask 0.501.002Restoration TOTAL FOR EACH AIRPLANE 1.503.00Inspection (a)(a)Repair 1632Modification (a) For some tension tie cracks, the modification can be used as a repair. For unmodified airplanes with cracks other than as described in Paragraph 3.B., Work Instructions, repair time will depend on extent of cracking. H. Weight and Balance Changes Group 1-2: Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane + 585.2+ 0.8Tension Tie Modification + 390.7+ 0.5Alternative Modification Group 3: Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane + 627.8+ 0.8Tension Tie Modification + 401.0+ 0.5Alternative Modification I. Electrical Load Data Not applicable. J. References 1. Existing Data: a. Engineering Change Memo PRR 85901-120RS b. Boeing Service Bulletin 747-25-2692, 747-53A2502 c. Boeing Service Letter 747-SL-51-048, 747-SL-53-088 d. Boeing Service Related Problem (SRP) 747-SRP-53-0403 e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 84-19-01 f. Service Bulletin Index D6-30300 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 22 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 23 g. 747 Fleet Team Digest (FTD) 53-03005 h. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 Procedure 1, Procedure 4, Procedure 11, Procedure 16, Procedure 23 i. 747-100/200/300 Aircraft Maintenance Manual (AMM) 25-22-01 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Tension Tie Installation - STA 760 to STA 94065B09631 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-SectionPublication 53-10747 Structural Repair Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 23 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 24 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 24 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT BLANK PAGE ### Page 25 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 03 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) NameKit Number $672.00280KIT, FRAME TO TENSION TIE JOINT MODIFICATION - BODY STATION 760 63B12132-1 B. Industry Support Information This service bulletin was first released before October of 1994. Thus industry support for affected airplanes depends upon whether the operator previously filed a warranty claim with Boeing on this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: Top kit assembly is divided into subkits for convenience of installation. One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. 63B12132 - FRAME TO TENSION TIE JOINT MODIFICATION - BODY STATION 760 Kit 63B12132-1 NameQTYNew Part Number -1-2-3 Top Kit Assembly-..63B12132-1 Kit Assembly, Left Side1-.63B12132-2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 25 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 26 63B12132 - FRAME TO TENSION TIE JOINT MODIFICATION - BODY STATION 760 Kit 63B12132-1 NameQTYNew Part Number -1-2-3 Kit Assembly, Right Side1.-63B12132-3 Doubler.1.65B42544-1 Doubler..165B42544-2 Bolt.66BACB30KK6-3 Bolt.1212BACB30KK6-4 Bolt.1515BACB30KK6-5 Bolt.33BACB30KK8-6 Bolt.55BACB30KK8-7 Bolt.55BACB30KK8-8 Collar.3333BACC30R6 Collar.1313BACC30R8 Rivet.22BACR15BA6D10 2. Parts and Materials Supplied by the Operator NOTE: The parts and materials shown in the table that follows are necessary to install the alternative modification shown in Figures 7, 8, or 9. NotesNameGroup 1 QTY Group 2 QTY Group 3 QTY Part Number / Specification (a)Strap2..A (b)Strap.2.B (c)Strap..2C (e)Bolt114BACB30MY6K4X (e)Bolt663BACB30MY6K5X (e)Bolt11.BACB30MY6K6X (e)Bolt32.BACB30MY6K7X (e)Bolt..5BACB30MY6K8X (e)Bolt..5BACB30MY6K9X (e)Bolt668BACB30MY6K4Y (e)Bolt222BACB30MY8K4 (e)Bolt1..BACB30MY8K7X Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 26 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 27 NotesNameGroup 1 QTY Group 2 QTY Group 3 QTY Part Number / Specification (e)Bolt53.BACB30MY8K8X (e)Bolt.3.BACB30MY8K9X -Collar10915BACC30M6 -Collar882BACC30M8 -Collar668BACC30R6 (d)Sealant4 Ounces4 Ounces4 OuncesBMS 5-95 -Paint4 Ounces4 Ounces4 OuncesBMS 10-11, Type I (a) Make as shown in FIGURE 7. (b) Make as shown in FIGURE 8. (c) Make as shown in FIGURE 9. (d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (e) Refer to 747 Structural Repair Manual Chapter 51 for alternate fasteners. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 27 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 28 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 28 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT BLANK PAGE ### Page 29 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References , for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 7. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 8. Boeing Service Letter 747-SL-51-048 Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 9. Refer to Appendix A for Addendum on flight safety. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 29 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 30 10. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 11. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 12. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. B. WORK INSTRUCTIONS PART I - FLIGHT SAFETY INSPECTION PROGRAM 1. On airplanes on which Part III - Modification has not been incorporated accomplish the following: a. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) for any cracking in accordance with FIGURE 1. b. If no cracking is found, repeat the tension tie inspections in accordance with FIGURE 1 at the time given in Paragraph 1.E., Compliance or alternatively, accomplish Part III - Modification and do the tension tie inspection in accordance with Part I, Step 2. c. If any cracking is found in one channel of the tension tie at the most inboard row of fasteners common to the tension tie channels and the existing steel joint doubler or in the aft channel in the area of the channel trim out, do the Part III - Modification as a repair and do the inspections in accordance with Part I, Step 2. If any cracking is found other than as described above, contact Boeing for repair instructions and do the work instructed by Boeing. d. Restore access and return the airplane to a serviceable condition. 2. On airplanes on which Part III - Modification has been incorporated accomplish the following: a. Do a detailed inspection of the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) for any cracking in accordance with FIGURE 2 at the time given in Paragraph 1.E., Compliance. b. If no cracking is found, repeat the inspections in accordance with FIGURE 2 at the time given in Paragraph 1.E., Compliance. c. If any cracking is found, contact Boeing for repair instructions and do the work instructed by Boeing. d. Restore access and return the airplane to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 30 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 31 PART II - ECONOMICS BASED INSPECTION PROGRAM - OPERATOR'S OPTION 1. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the tension tie at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) for any cracking in accordance with FIGURE 1. NOTE: 1. This inspection may be used in lieu of Part I - Flight Safety Inspection Program, at operator's option, until Part III - Modification is accomplished. 2. This inspection applies only to airplanes on which Part III - Modification has not been accomplished. 2. If no cracking is found, repeat the tension tie inspection in accordance with FIGURE 1 at the time given in Paragraph 1.E., Compliance or alternatively, do the modification in accordance with Part III - Modification and do tension tie modification inspections in accordance with Part I, Step 2. 3. If any cracking is found in one channel of the tension tie at the most inboard row of fasteners common to the tension tie channels and the existing steel joint doubler or in the aft channel in the area of the channel trim out, do the Part III - Modification as a repair and initiate re-inspections in accordance with Part I, Step 2. If any cracking is found other than as described above, contact Boeing for repair instructions and do the work instructed by Boeing. 4. Restore access and return the airplane to a serviceable condition. PART III - MODIFICATION 1. Get access to the tension tie ends at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) by removing ceiling panels 231HL and 231HR (if installed). Refer to 747-100/200/300 AMM 25-22-01 or operator's comparable procedure. NOTE: This modification may be used as an alternative to repeat inspections in accordance with Part II, as a means of deferring initial or repeat inspections in accordance with Part I, or as a repair for cracks as shown in the notes that follow. The modification does not terminate Part I inspection requirements. 2. Replace existing tension tie end doublers with longer doublers in accordance with FIGURE 3. As an alternative, modify the tension tie in accordance with FIGURE 7, FIGURE 8 or FIGURE 9. NOTE: 1. The modification in accordance with FIGURE 3 may be used as a repair for a crack in one channel of the tension tie at the most inboard row of fasteners common to the tension tie channels and the existing steel joint doubler on unmodified airplanes. 2. The modification in accordance with FIGURE 7, FIGURE 8 or FIGURE 9 can also be used as a repair for cracks in the aft channel of the tension tie. This repair can only be used if the trim in accordance with FIGURE 7, FIGURE 8 or FIGURE 9 completely removes all cracks in the aft channel. If the trim does not completely remove all cracks from the aft channel, or if other cracks are found, contact Boeing for repair instructions and do the work instructed by Boeing. 3. Reinstall access panels and return the airplane to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 31 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 32 4. Do inspections of the modified tension ties in accordance with Part I. Step 2, at the times given in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4: January 11, 2013 32 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 33 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT STA 780 STA TENSION 760 TIE STA 780 TENSION TIE CHANNEL • DOUBLER UP INBD 2 FWD LEFT SIDE SHOWN → FWD RIGHT SIDE OPPOSITE FRAME VIEW B-B STA 760 (GROUP 1 AND 2) STA 780 (GROUP 3) FRAME FATIGUE TEST CRACK ++++++ ++++ UP > B DOUBLER INSPECTION AREA INBD < VIEW A-A R09575 FIGURE 1: UNMODIFIED TENSION TIE INSPECTION (SHEET 1 OF 3) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 33 of 62 ### Page 34 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT S-12 STA 760 (GROUP 1 AND 2) STA 780 (GROUP 3) FRAME AFT CHANNEL FORWARD CHANNEL TYPICAL CRACKS VIEW C-C LEFT SIDE SHOWN RIGHT SIDE OPPOSITE UP > INBD 2169045 FIGURE 1: UNMODIFIED TENSION TIE INSPECTION (SHEET 2 OF 3) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 34 of 62 ### Page 35 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQtyIdentificationNameTaskStep (a)--Ceiling PanelsRemove / Keep1 (b)--Tension TieInspect2 (c) (d)--Tension TieInspect3 (c) (d)--Tension TieInspect4 (a) Get access to the tension tie ends at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) by removing ceiling panels 231HL and 231HR (if installed). Refer to 747-100/200/300 AMM 25-22-01 or operator's comparable procedure. (b) Do a detailed inspection of the indicated tension tie area on the left and right side for any cracking. (c) Do a detailed inspection of the edge of the radius of the tension tie aft channel on the left and right side for any cracking. (d) Do a surface High Frequency Eddy Current (HFEC) inspection on the edge of the radius of the tension tie aft channel on the left and right side for any cracking. Do the inspection in accordance with 747 NDT Part 6, 51-00-00, Procedure 4 or Procedure 23. FIGURE 1: UNMODIFIED TENSION TIE INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 35 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 36 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT STA TENSION 760 TIE STA 780 TENSION TIE CHANNEL DOUBLER UP INBD < →FWD → FWD LEFT SIDE SHOWN RIGHT SIDE OPPOSITE FRAME VIEW B-B STA 760 (GROUP 1 AND 2) STA 780 (GROUP 3) FRAME DOUBLER TENSION TIE • B ++++ = + + 30.00 > B UP INSPECTION AREA INBD R09580 VIEW A-A FIGURE 2: MODIFIED TENSION TIE INSPECTION (SHEET 1 OF 2) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 62 ### Page 37 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQtyIdentificationNameTaskStep (a)--Ceiling PanelsRemove / Keep1 (b)--Tension TieInspect2 (a) Get access to the tension tie ends at BS 760 (Group 1 and 2 airplanes) or BS 780 (Group 3 airplanes) by removing ceiling panels 231HL and 231HR (if installed). Refer to 747-100/200/300 AMM 25-22-01 or operator's comparable procedure. (b) Do a detailed inspection of the indicated tension tie area on the left and right side for any cracking. FIGURE 2: MODIFIED TENSION TIE INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 37 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 38 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT ~ STA 780 GROUP 3 GRO STA AND 2 760 AFT UPPER DECK STA FRAME FLOOR BEAM (REF) 780 FRAME DOOR #2 LIFE RAFT SUPPORT (REF) UP PSU DUCT LEFT SIDE SHOWN RIGHT SIDE OPPOSITE INBD AFWD R09594 FIGURE 3: FRAME TENSION TIE MODIFICATION (SHEET 1 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 38 of 62 ### Page 39 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT (GROUP 1 AND 2) 3) (GROUP STA 760 FRAME STA 760 780 STA GROUP 1 ONLY SEE DETAIL I FOR GROUP 1 SEE DETAIL II FOR GROUP 3 INBD C • GROUP 2 SHOWN VIEW A-A EXISTING CONFIGURATION VIEW A-A NEW CONFIGURATION R09600 FIGURE 3: FRAME TENSION TIE MODIFICATION (SHEET 2 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 39 of 62 ### Page 40 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT TENSION TIE TENSION TIE CHANNEL CHANNEL EXISTING NEW - DOUBLER - DOUBLER UP UP FRAME FRAME → FWD → FWD SECTION B-B SECTION C-C RETAIN RETAIN FILLER FILLER DETAIL I DETAIL II (GROUP 1) (GROUP 3) R09601 FIGURE 3: FRAME TENSION TIE MODIFICATION (SHEET 3 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 40 of 62 ### Page 41 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this Figure. More DataQtyIdentificationNameTaskStep Group 1.40-FastenersRemove1 Group 2 and 3.39-FastenersRemove --65B09614-27 (65B09614-19 or 65B09614-21 optional) DoublerRemove2 Group 2 only.2-HoleCountersink3 Left side.165B42544-1DoublerInstall (New)4 Right side.165B42544-2DoublerInstall (New) The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More DataHole DiaQtyIdentificationNameCode Install with BMS 5-95 sealant. 0.216 - 0.219-BACB30KK6-( )BoltA ---BACC30R6Collar Install with BMS 5-95 sealant 0.278 - 0.281-BACB30KK8-( )BoltB ---BACC30R8Collar FIGURE 3: FRAME TENSION TIE MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 41 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 42 More DataHole DiaQtyIdentificationNameCode 100 degree countersink 0.33 inch diameter for- ward side only. --BACR15BA6D10RivetC FIGURE 3: FRAME TENSION TIE MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 42 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 43 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT THIS FIGURE IS DELETED. D38438 FIGURE 4: THIS FIGURE IS DELETED (REVISION 4) (SHEET 1 OF 1) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 43 of 62 ### Page 44 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT THIS FIGURE IS DELETED. D38438 FIGURE 5: THIS FIGURE IS DELETED (REVISION 4) (SHEET 1 OF 1) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 44 of 62 ### Page 45 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT THIS FIGURE IS DELETED. D38438 FIGURE 6: THIS FIGURE IS DELETED (REVISION 4) (SHEET 1 OF 1) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 45 of 62 ### Page 46 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT This Figure applies only to: Group 1. STA 760 STA TENSION 760 TIE STA 780 UP S-12 • INBD‹ →FWD LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 22 LOCATIONS AFT CHANNEL 0.50R (TYPICAL) +8 +s 95 5 E†s 5 6 75 45 FORWARD -0.38 (TYPICAL) CHANNEL VIEW A-A LEFT SIDE SHOWN RIGHT SIDE OPPOSITE UP FOR OPTIONAL TRIM SEE DETAIL I → INBD R09648 FIGURE 7: ALTERNATIVE MODIFICATION (SHEET 1 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 46 of 62 ### Page 47 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT S-12 FORWARD TYPICAL (1 7) CHANNEL 0.50R AFT CHANNEL (TYPICAL) 5 ‡¾ + + B 0.38 (TYPICAL) UF DETAIL I OPTIONAL TRIM • INBD AFT CHANNEL FUSELAGE FRAME VIEW B-B LEFT SIDE SHOWN FORWARD CHANNEL RIGHT SIDE OPPOSITE FIGURE 7: ALTERNATIVE MODIFICATION (SHEET 2 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 747-53A2088 47 of 62 ### Page 48 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT _ AFT CHANNEL 0.19 _ FORWARD CHANNEL AFT 0.43 MIN (TYPICAL) →uP 2.06 SECTION C-C 0.19R (TYPICAL) • 11.20 2.06 12.25. REPAIR STRAP A LEFT SIDE SHOWN RIGHT SIDE OPPOSITE FIGURE 7: ALTERNATIVE MODIFICATION (SHEET 3 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 48 of 62 ### Page 49 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. NOTE: The figure shows two alternate aft channel trims. Any trim line that is between those shown in the figure is acceptable. At least five fasteners in each row are necessary common to the aft channel, forward channel and repair strap inboard of the trim line. 1. 2. Install all parts with BMS 5-95 sealant. 3. All trimmed edges and repair parts should be finished to 125 microinches or better. More DataQtyIdentificationNameTaskStep ---FastenersRemove1 -1-PlateRemove / Keep2 -1-Aft ChannelCut3 -1-Trimmed SectionRemove4 To aft channel to match adjacent structure. --PaintApply5 0.071 thick 2024-T3.1ARepair StrapMake6 One coat BMS 10- 11, Type I. --PaintApply Trim as necessary.1ARepair StrapInstall (New) -1-PlateInstall (Kept)7 FIGURE 7: ALTERNATIVE MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 49 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 50 The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More DataHole DiaQtyIdentificationNameCode Install with BMS 5-95 sealant. 0.2026 - 0.2036 -BACB30MY6K( )XBoltD ---BACC30M6Collar Install with BMS 5-95 sealant. 0.2651 - 0.2661 -BACB30MY8K( )XBoltE ---BACC30M8Collar Install with BMS 5-95 sealant. 0.216 - 0.219-BACB30MY6K4YBoltF ---BACC30R6Collar Install with BMS 5-95 sealant. 0.2495 - 0.2505 (a) -BACB30MY8K4BoltG ---BACC30M8Collar (a) Before the hole is made larger, do an open hole HFEC inspection at these locations in accordance with 747 NDT Part 6, 51-00-00, Procedure 1 or Procedure 11 or Procedure 16. If no cracking is found, make the fastener holes the size shown. FIGURE 7: ALTERNATIVE MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 50 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 51 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT This Figure applies only to: Group 2. SIA 760 STA TENSION 760 TIE STA 780 UP INBD FWD S-11 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 5) FORWARD TYPICAL (1 0.50R 20 CHANNEL (TYPICAL) AFT CHANNEL P5 + 4 S-12 48 F8 767557144 0.38 (TYPICAL) VIEW A-A LEFT SIDE SHOWN UP RIGHT SIDE OPPOSITE —INBD FOR OPTIONAL TRIM SEE DETAIL I R09702 FIGURE 8: ALTERNATIVE MODIFICATION (SHEET 1 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2088 Work - See page 1 for details. 51 of 62 ### Page 52 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT S-11 0.50R (TYPICAL) S-12 78 48 49 B 0.38 (TYPICAL) UP DETAIL I OPTIONAL TRIM > INBD AFT CHANNEL FUSELAGE FRAME VIEW B-B LEFT SIDE SHOWN FORWARD CHANNEL RIGHT SIDE OPPOSITE FIGURE 8: ALTERNATIVE MODIFICATION (SHEET 2 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 52 of 62 ### Page 53 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT AFT CHANNEL 0.19 FORWARD CHANNEL AFT 0.43 MIN (TYPICAL) - 2.06 SECTION C-C 12.30 • 0.19R (TYPICAL) 11.50 1.30 2.06 11.25 REPAIR STRAP B LEFT SIDE SHOWN RIGHT SIDE OPPOSITE R09708 FIGURE 8: ALTERNATIVE MODIFICATION (SHEET 3 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 747-53A2088 53 of 62 ### Page 54 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. NOTE: The figure shows two alternate aft channel trims. Any trim line that is between those shown in the figure is acceptable. At least five fasteners in each row are necessary common to the aft channel, forward channel and repair strap inboard of the trim line. 1. 2. Install all parts with BMS 5-95 sealant. 3. All trimmed edges and repair parts should be finished to 125 microinches or better. More DataQtyIdentificationNameTaskStep ---FastenersRemove1 -1-PlateRemove / Keep2 -1-Aft ChannelCut3 -1-Trimmed SectionRemove4 To aft channel to match adjacent structure. 1-PaintApply5 0.071 thick 2024-T3.1BRepair StrapMake6 One coat BMS 10- 11, Type I. --PaintApply Trim as necessary-BRepair StrapInstall (New) -1-PlateInstall (Kept)7 FIGURE 8: ALTERNATIVE MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 54 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 55 The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More DataHole DiaQtyIdentificationNameCode Install with BMS 5-95 sealant. 0.2026 - 0.2036 -BACB30MY6K( )XBoltD ---BACC30M6Collar Install with BMS 5-95 sealant. 0.2651 - 0.2661 -BACB30MY8K( )XBoltE ---BACC30M8Collar Install with BMS 5-95 sealant. 0.216 - 0.219-BACB30MY6K4YBoltF ---BACC30R6Collar Install with BMS 5-95 sealant. 0.2495 - 0.2505 (a) -BACB30MY8K4BoltG ---BACC30M8Collar (a) Before the hole is made larger, do an open hole HFEC inspection at these locations in accordance with 747 NDT Part 6, 51-00-00, Procedure 1 or Procedure 11 or Procedure 16. If no cracking is found, make the fastener holes the size shown. FIGURE 8: ALTERNATIVE MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 55 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 56 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT This Figure applies only to: Group 3. STA 780 STA TENSION 780 TIE UP INBD < →FWD S-11 LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 3)5 FORWARD TYPICAL Q 0.50R 20 CHANNEL (TYPICAL) AFT CHANNEL S-12 + 44 0.38 (TYPICAL) VIEW A-A LEFT SIDE SHOWN RIGHT SIDE OPPOSITE UP SEE DETAIL I FOR OPTIONAL TRIM —→ INBD R09714 FIGURE 9: ALTERNATIVE MODIFICATION (SHEET 1 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 56 of 62 ### Page 57 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT S-11 0.50R X7 (TYPICAL) 48 78 9 99 44 47 S-12 7898 to o to 744: 4444 - 0.38 (TYPICAL) DETAIL I UP OPTIONAL TRIM —→ INBD AFT CHANNEL FUSELAGE FRAME VIEW B-B FORWARD CHANNEL LEFT SIDE SHOWN 2X7 RIGHT SIDE OPPOSITE R09716 FIGURE 9: ALTERNATIVE MODIFICATION (SHEET 2 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. 747-53A2088 57 of 62 ### Page 58 (OCR) BOEING SERVICE BULLETIN 747-53A2088 ALERT ALERT AFT CHANNEL 0.19 FORWARD CHANNEL 27 AFT 0.43 MIN (TYPICAL) 2.06 SECTION C-C - 12.70 - 0.19R (TYPICAL) - 11.75 1.40 2.06 - 11.75 REPAIR STRAP C LEFT SIDE SHOWN RIGHT SIDE OPPOSITE FIGURE 9: ALTERNATIVE MODIFICATION (SHEET 3 OF 5) Original Issue: March 08, 1974 Revision 4 January 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2088 Work - See page 1 for details. 58 of 62 ### Page 59 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. More DataQtyIdentificationNameTaskStep ---FastenersRemove1 -1-PlateRemove / Keep2 -1-Aft ChannelCut3 -1-Trimmed SectionRemove4 To aft channel to match adjacent structure. 1-PaintApply5 0.071 thick 2024-T3.1CRepair StrapMake6 One coat BMS 10- 11, Type I. 1-PaintApply Trim as necessary.-CRepair StrapInstall (New) -1-PlateInstall (Kept)7 FIGURE 9: ALTERNATIVE MODIFICATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 59 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT ### Page 60 The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More DataHole DiaQtyIdentificationNameCode Install with BMS 5-95 sealant. 0.2026 - 0.2036 -BACB30MY6K( )XBoltD ---BACC30M6Collar Install with BMS 5-95 sealant. 0.2651 - 0.2661 -BACB30MY8K( )XBoltE ---BACC30M8Collar Install with BMS 5-95 sealant. 0.216 - 0.219-BACB30MY6K4YBoltF ---BACC30R6Collar Install with BMS 5-95 sealant. 0.2495 - 0.2505 (a) -BACB30MY8K4BoltG ---BACC30M8Collar (a) Before the hole is made larger, do an open hole HFEC inspection at these locations in accordance with 747 NDT Part 6, 51-00-00, Procedure 1 or Procedure 11 or Procedure 16. If no cracking is found, make the fastener holes the size shown. FIGURE 9: ALTERNATIVE MODIFICATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 08, 1974 747-53A2088Revision 4 January 11, 2013 60 of 62 BOEING SERVICE BULLETIN 747-53A2088 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/747-53a2088/file/86d9a976942a.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.