# Boeing Alert Service Bulletin 767-54A0074: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2008-1363; AD 2009-20-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 767-54A0074](https://openairdocs.org/service-documents/boeing/767-54a0074.md) - Title as filed: U.S. DOT/FAA - Boeing Service Bulletin SB 767-54A0074 Revision 1 dated April 24, 2008 - Pages: 33 - PDF: https://openairdocs.org/files/sha256/00/ca/00ca24977e7f16cd1b5320ae45687ed33d5db93a5358eac16fb122525e8ede3a - Page: https://openairdocs.org/service-documents/boeing/767-54a0074/file/00ca24977e7f ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 33 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-54A0074 Date: March 27, 1997 Revision 1: April 24, 2008 ATA System: 5451 SUBJECT: NACELLE/PYLON - Strut Attach Fuse Pins - Upper Link Fuse Pin Inspection/ Replacement BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 1997 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise. ### Page 2 BLANK PAGE March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT BLANK PAGE ### Page 3 Table of Contents March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 24 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 24 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 24 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 25 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 26 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 FIGURE 1: INSPECTION INTERVALS AND MAINTENANCE ALTERNATIVES . . . . . . . . . . . . 30 FIGURE 2: DETAILED INSPECTION OF THE UPPER LINK FUSE PIN . . . . . . . . . . . . . . . 32 ### Page 4 Table of Contents March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT BLANK PAGE ### Page 5 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 33 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-54A0074 Revision Transmittal Sheet Date: March 27, 1997 Revision 1: April 24, 2008 ATA System: 5451 SUBJECT: NACELLE/PYLON - Strut Attach Fuse Pins - Upper Link Fuse Pin Inspection/ Replacement This Revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes inspected as shown in the original issue of this service bulletin. However, continued repeat inspections are necessary at an increased frequency. Additionally, initial inspections on JT9D airplanes are required at a reduced threshold. REASON FOR REVISION This revision is sent to update the initial and repeat inspection intervals for early detection of cracks in the upper link fuse pin. The Boeing analysis of in-service fractured pins from two operators has found that the previous inspection intervals given in the original issue of this service bulletin are not sufficient to find fatigue cracks in the fuse pin. A change to the inspection intervals is necessary to ensure that cracks are detected before the failure of the fuse pin. These sections were changed: 1. Summary Background and Paragraph 1.C., Reason, were changed to add new information on the fatigue damage found by two operators. 2. Summary Action, clarified the inspection procedure, and moved the terminating action information to Summary Compliance. 3. Summary Illustration, revised the text to match the work instructions. 4. Paragraph 1.D., Description, clarified the inspection procedure, deleted the request for inspection results, and moved the terminating action information to Paragraph 1.E., Compliance. 5. Paragraph 1.J., References, was updated to show the correct references. 6. Paragraph 2.C., Parts and Materials Supplied by the Operator, item 2, corrected the cotter pin part number. 7. Paragraph 3.A., General Information, added caution information and clarified the inspection definition. ### Page 6 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 8. Paragraph 3.B., Work Instructions, item 4, clarified the inspection procedure. 9. Figure 1, changed the initial and repeat inspection intervals for the upper link fuse pin, and added terminating action information. 10. Figure 2, clarified the cleaning procedure. Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes. 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 Original Issue: March 27, 1997 Revision 1: April 24, 2008 ### Page 7 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 33 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-54A0074 Summary Date: March 27, 1997 Revision 1: April 24, 2008 ATA System: 5451 SUBJECT: NACELLE/PYLON - Strut Attach Fuse Pins - Upper Link Fuse Pin Inspection/ Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This fuse pin inspection will permit early detection of cracks in the upper link fuse pin. Cracks in the fuse pin could result in a fractured fuse pin. A fractured fuse pin can result in reduced structural capability of the nacelle strut, and possible separation of the strut and engine from the airplane during flight. No operators have reported cracks in the upper link fuse pins. Cracks were found in an upper link fuse pin at Boeing during testing of a RB211 Strut. As part of the service bulletin validation program, this inspection was completed on airplane VB051 by Service Bulletin Validation Copy 1 before the initial release of this service bulletin. The inspection completed on VB051 by Service Bulletin Validation Copy 1 is equivalent to the initial release of this service bulletin. After the original issue of this service bulletin, two operators reported cracked upper link fuse pins. The two airplanes had PW4000 engines with 11,573 flight cycles and 14,780 flight cycles. Boeing analysis found cracks in the longitudinal direction of the fuse pins. The longitudinal cracks were the result of fatigue loads. No material anomalies were found. Further Boeing analysis has found that the previous inspection intervals given in the original issue of this service bulletin are not sufficient to find fatigue cracks in the fuse pin. As a result, a change to the inspection intervals is necessary to ensure that cracks are detected before the failure of the fuse pin. ### Page 8 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT ACTION Remove the strut underwing fairings. Remove the end caps and corrosion preventive compound from the upper link fuse pin and clean the inside surface of the upper link fuse pin. Do a detailed inspection of the inside surface of the upper link fuse pin in place, without engine removal and strut removal, for corrosion. If corrosion is found in the base metal of the fuse pin, or if any crack is found, replace the fuse pin with a new fuse pin with the same part number. If no corrosion is found, do a High Frequency Eddy Current (HFEC) inspection. If crack is detected, remove the upper link fuse pin and do a Magnetic Particle inspection on the inside surface of the upper link fuse pin. If crack is found in the upper link fuse pin, replace the fuse pin with a new fuse pin with the same part number. Apply the corrosion preventive compound on the upper link fuse pin and install the end caps. Install the strut underwing fairings. EFFECTIVITY 767-200/-300/-300F 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. See Figure 1 for compliance recommendations and maintenance alternatives. Terminating action for this service bulletin is the accomplishment of the modification of the nacelle strut and wing structure for Pratt and Whitney, General Electric and Rolls Royce powered airplanes, in accordance with Service Bulletin 767-54-0080, Original Issue or Revision 1; or 767-54-0081, Original Issue or Revision 1; or 767-54-0082, Original Issue, Revision 1 or Revision 3, as applicable. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. MANPOWER Total Man-hours - 6 for each strut Elapsed Time - 4 Hours MATERIAL INFORMATION Operator Supplied PartsRefer to Paragraph 2.A., Material - Price and Availability. ### Page 9 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT FUSE PIN END CAP END CAP COMPOUND FROM THE FUSE PIN. DO A DETAILED INSPECTION OF THE INNER SURFACE OF THE FUSE PIN. CORROSION PREVENTIVE REMOVE THE END CAPS AND UPPER LINK STRUT TYPICAL LEFT STRUT SHOWN RIGHT STRUT OPPOSITE FWD UP R85906 ### Page 10 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT BLANK PAGE ### Page 11 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 33 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-54A0074 Date: March 27, 1997 Revision 1: April 24, 2008 ATA System: 5451 SUBJECT: NACELLE/PYLON - Strut Attach Fuse Pins - Upper Link Fuse Pin Inspection/ Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document D6-D624T001, Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Airplane models: 767-200 767-300 767-300F IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AA 767 LLC (SVX) 1V E 0 6 7 ABX AIR (ABX) 1 VA301 VA303–VA306 VA309–VA315 VA508 VA803 VA807–VA809 VB101–VB123 VB125 VB302 GROUP CONFIGURATION DESCRIPTION 1 - 767 airplanes, line numbers 1 through 663, that have not accomplished service bulletins 767-54- 0080, 767-54-0081 or 767-54-0082. ### Page 12 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT AEROFLOT (ARO) 1 VL896–VL897 VN471–VN472 AEROMEXICO (AMX) 1 VF071 VF093 VF162 AEROSVIT (UKA) 1 VN154–VN155 VN157 AEROTURBINE (AUB) 1 VB051 VB054–VB055 VB321 AIR ALGERIE (ALG) 1 VK131–VK133 AIR ASTANA (AKZ) 1 VL899–VL900 AIR CANADA (ACN) 1 VA701–VA709 VA711–VA719 VB001–VB002 VB201–VB202 VN051–VN054 VN056–VN062 VN531 VN541 VN546–VN547 VN751–VN752 VN811–VN812 VN931–VN936 AIR CHINA (BEJ) 1 VE064 VE083 VE085–VE086 VK161–VK164 AIR EUROPA (ARE) 1V N 6 3 8 AIR ITALY (RIT) 1 VL913 AIR MADAGASCAR (MAD) 1V N 1 6 7 V N 7 3 1 AIR NEW ZEALAND (ANZ) 1 VN653 VN655–VN657 AIR PACIFIC (APC) 1V N 6 7 6 AIR SEYCHELLES (ASY) 1 VL941 AIR TRANSPORT INTERNATIONAL (TIN) 1 VA509–VA513 AIR ZIMBABWE (ZMB) 1 VF061–VF062 ALITALIA (ALI) 1 VL701–VL702 VN422–VN427 VN732 VN813 ### Page 13 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT ALL NIPPON AIRWAYS (ANA) 1 VK081–VK112 VN191–VN198 AMERICAN AIRLINES (AAL) 1 VA501–VA505 VA514–VA523 VA525 VA527–VA530 VN001–VN041 ARKEFLY (HXL) 1 VN156 VN164–VN165 VN225 ASIANA AIRLINES (AAR) 1 VK143–VK147 VW851 AUSTRIAN AIRLINES AG (AUL) 1 VN242–VN243 VN671 AVIANCA (AVI) 1 VE171–VE172 VF072 VF092 VF161 VN152 VN532 AWAS (AWW) 1V B 3 2 5 BELAIR AIRLINES (BLB) 1 VL932 BELLVIEW AIRLINES (BEB) 1 VE125–VE126 BLUE CITY HOLDING (BCY) 1V E 0 6 9 BLUE PANORAMA AIRLINES (BPA) 1 VN174 VN681 BOEING (TBC) 1V A 0 0 1 BRA TRANSPORTES AEREOS (BRW) 1 VA806 VN376 BRAVO AIRLINES (BVA) 1V E 1 0 4 BRISTOL AIR LIMITED (BMD) 1V A 8 0 4 BRITISH AIRWAYS (BAB) 1 VN111–VN114 VN118–VN122 VN124–VN127 VN133–VN137 CAMEROON AIRLINES (CAM) 1V A 8 0 1 ### Page 14 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT CHINA EASTERN AIRLINES (CEA) 1 VL871–VL873 CONDOR (CDF) 1 VN683–VN691 CSDS AVIATION (CSO) 1 VA506–VA507 DELTA AIR LINES (DAL) 1 VA302 VK036 VK038–VK056 VL753 VN251–VN271 VN301–VN306 EL AL ISRAEL AIRLINES (ELA) 1 VB281–VB284 VF101–VF102 VN537 VN682 VN972 ERITREAN AIR LINES (ERJ) 1 VE066 ETHIOPIAN AIRLINES (ETH) 1 VE002 VL898 EUROATLANTIC AIRWAYS (MAE) 1 VN151 VN551 VN561–VN562 EVERGREEN MAINTENANCE CENTER (EAC) 1 VE061 FIRST CHOICE AIRWAYS (ATZ) 1 VL751–VL752 VL754 VN791–VN792 VN921 FLYGLOBESPAN.COM (FGS) 1V N 6 5 4 GABON AIRLINES (GBO) 1 VA017–VA018 GECAS (GEF) 1 VE123 GULF AIR (GUL) 1 VL004–VL006 VN307–VN310 VN313–VN314 HAWAIIAN AIRLINES (HWI) 1 VK031–VK034 VN171–VN173 VN381 HEWA BORA AIRWAYS (EXD) 1 VE021 ICELANDAIR (ICE) 1 VN158 VN163 VN211 ### Page 15 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT ITOCHU CORPORATION (CIT) 1 VF181–VF184 JAL INTERNATIONAL (JAL) 1 VB371–VB373 VK001–VK015 VK021–VK022 JETAIRFLY (TLB) 1 VN234 KALAIR (BERMUDA) (KLB) 1 VN311 KAM AIR (KMC) 1V A 0 1 9 KENYA AIRWAYS (KEN) 1 VK141 VL003 VN421 KRASAIR (ZXD) 1 VE001 VE022–VE023 VF051 LAN AIRLINES (LAN) 1 VL703 VN063–VN064 VN166 VN168 VN966–VN969 VN971 LATCHARTER (LCH) 1 VN536 VN542 LOT POLISH AIRLINES (LOT) 1 VF041–VF042 VN233 VN291–VN293 VN652 MALEV HUNGARIAN AIRLINES (HGA) 1 VF171–VF172 MARTINAIR HOLLAND (MTH) 1 VN221–VN224 VN385 VN672 MAXJET AIRWAYS (SLQ) 1 VB301 VE041 VE063 VF001–VF002 MEXICANA (CMA) 1 VL001–VL002 MID EAST JET (SKL) 1V F 2 5 1 MYTRAVEL AIRWAYS (GUE) 1 VN951–VN953 NATIONWIDE AIRLINES (NWR) 1 VN556 ### Page 16 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT NEOS (NEO) 1 VL892 VL894 NORTH AMERICAN AIRLINES (NNA) 1 VL755 VL895 VL911 VN922 OCEANAIR AIRLINES (OAL) 1V N 4 9 5 V N 5 0 0 PACE AIRLINES (PIE) 1 VB053 PHOENIX AIRCRAFT LEASING, INC. (PLB) 1 VA810 PLUNA (PLU) 1V N 4 3 6 V N 6 5 1 QANTAS (QAN) 1 VN081–VN098 VN115–VN117 VN123 VN130–VN132 ROYAL AIR MAROC (RAM) 1V N 6 3 6 ROYAL BRUNEI AIRLINES (RBA) 1 VN372 VN382–VN384 VN386–VN387 RYAN INTERNATIONAL AIRLINES (RYN) 1 VK035 SAFI AIRWAYS (FFI) 1 VE084 SALAMIS AVIATION (LMV) 1 VE068 SHANGHAI AIRLINES (SHA) 1 VK171 SILVERJET (SVJ) 1 VB329–VB330 VE117 SKYSTAR (SYW) 1 VA011–VA012 STAR AIR (SBJ) 1 VA307–VA308 VB323 VB328 VB441–VB444 VE101–VE103 TAA (TNL) 1 VA002–VA003 VA009 VA014–VA015 VA020 ### Page 17 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT TAMPA CARGO (TMP) 1 VE121–VE122 VE124 TEEBAH AIRLINES (EBH) 1V A 7 1 0 THE SULTAN'S FLIGHT (BWN) 1V F 1 8 0 THOMSONFLY (BRI) 1 VB331–VB332 VL912 VL914 TRANS-AUSTRALIA AIRLINES (TAA) 1 VA007–VA008 TRANSAERO AIRLINES (TRX) 1 VE116 VE118 VE143 VN371 VN631–VN633 TRANSATLANTIC INTL AIRLINES (TIB) 1V A 0 1 6 UK INTERNATIONAL AIRLINES (UKI) 1 VA004–VA005 UNITED AIR LINES (UAL) 1 VN491–VN494 VN496–VN499 VN501–VN513 UPS (UPS) 1 VW701–VW716 US AIRWAYS (USA) 1 VE141–VE142 VE144–VE149 VE151–VE152 UZBEKISTAN AIRWAYS (UZB) 1 VL806–VL807 VARIG AIRLINES (VAR) 1 VN231–VN232 VISION AIR (VEG) 1V A 0 0 6 V A 0 1 0 VIVA MACAU (VMC) 1 VF091 VK142 VOLARE S.P.A (VLR) 1 VL931 VRG LINHAS AEREAS S.A. (VGG) 1 VN055 VN388 VN637 VN753 ### Page 18 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT WEST DOVER LLC (WDR) 1 VK037 XL AIRWAYS (SBE) 1 VB326–VB327 VL011 VN153 VN557 YONA (IOP) 1V N 3 1 2 ZOOM AIRLINES (YFM) 1 VL891 VL893 VN634–VN635 IDENTIFICATION BY VARIABLE NUMBER Variable Group VA001–VA020 1 VA301–VA315 1 VA501–VA530 1 VA701–VA719 1 VA801–VA810 1 VB001–VB002 1 VB051–VB055 1 VB101–VB125 1 VB201–VB202 1 VB251–VB253 1 VB281–VB284 1 VB301–VB302 1 VB321–VB332 1 VB371–VB373 1 VB401 1 VB441–VB444 1 VE001–VE003 1 VE021–VE023 1 VE041–VE043 1 VE061–VE069 1 VE083–VE086 1 VE101–VE104 1 VE116–VE118 1 VE121–VE126 1 VE141–VE152 1 VE171–VE172 1 VF001–VF002 1 VF041–VF042 1 ### Page 19 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT VF051 1 VF061–VF062 1 VF071–VF072 1 VF091–VF093 1 VF101–VF102 1 VF161–VF162 1 VF171–VF172 1 VF180–VF184 1 VF251 1 VK001–VK015 1 VK021–VK022 1 VK031–VK056 1 VK081–VK112 1 VK131–VK133 1 VK141–VK147 1 VK161–VK164 1 VK171 1 VL001–VL006 1 VL011 1 VL701–VL703 1 VL751–VL755 1 VL806–VL807 1 VL871–VL873 1 VL891–VL900 1 VL911–VL914 1 VL931–VL932 1 VL941 1 VN001–VN041 1 VN051–VN064 1 VN081–VN098 1 VN111–VN127 1 VN130–VN137 1 VN151–VN158 1 VN163–VN168 1 VN171–VN174 1 VN191–VN198 1 VN211–VN212 1 VN221–VN225 1 VN231–VN234 1 Variable Group ### Page 20 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 2. Spares Affected None VN241–VN243 1 VN251–VN271 1 VN291–VN293 1 VN301–VN314 1 VN371–VN372 1 VN376 1 VN381–VN388 1 VN421–VN427 1 VN436 1 VN471–VN472 1 VN491–VN513 1 VN531–VN532 1 VN536–VN537 1 VN541–VN542 1 VN546–VN547 1 VN551 1 VN556–VN557 1 VN561–VN562 1 VN631–VN638 1 VN651–VN657 1 VN671–VN672 1 VN676 1 VN681–VN691 1 VN731–VN732 1 VN751–VN753 1 VN791–VN792 1 VN811–VN813 1 VN921–VN922 1 VN931–VN936 1 VN951–VN953 1 VN966–VN969 1 VN971–VN972 1 VW701–VW716 1 VW851 1 Variable Group ### Page 21 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT B. Concurrent Requirements None. C. Reason This fuse pin inspection will permit early detection of cracks in the upper link fuse pin. Cracks in the fuse pin could result in a fractured fuse pin. A fractured fuse pin can result in reduced structural capability of the nacelle strut, and possible separation of the strut and engine from the airplane during flight. No operators have reported cracks in the upper link fuse pins. Cracks were found in an upper link fuse pin at Boeing during testing of a RB211 Strut. As part of the service bulletin validation program, this inspection was completed on airplane VB051 by Service Bulletin Validation Copy 1 before the initial release of this service bulletin. The inspection completed on VB051 by Service Bulletin Validation Copy 1 is equivalent to the initial release of this service bulletin. After the original issue of this service bulletin, two operators reported cracked upper link fuse pins. The two airplanes had PW4000 engines with 11,573 flight cycles and 14,780 flight cycles. Boeing analysis found cracks in the longitudinal direction of the fuse pins. The longitudinal cracks were the result of fatigue loads. No material anomalies were found. Further Boeing analysis has found that the previous inspection intervals given in the original issue of this service bulletin are not sufficient to find fatigue cracks in the fuse pin. As a result, a change to the inspection intervals is necessary to ensure that cracks are detected before the failure of the fuse pin. Revision 1 is sent to update the initial and repeat inspection intervals for early detection of cracks in the upper link fuse pin. The Boeing analysis of in-service fractured pins from two operators has found that the previous inspection intervals given in the original issue of this service bulletin are not sufficient to find fatigue cracks in the fuse pin. A change to the inspection intervals is necessary to ensure that cracks are detected before the failure of the fuse pin. These sections were changed in Revision 1: 1. Summary Background and Paragraph 1.C., Reason, were changed to add new information on the fatigue damage found by two operators. 2. Summary Action, clarified the inspection procedure, and moved the terminating action information to Summary Compliance. 3. Summary Illustration, revised the text to match the work instructions. 4. Paragraph 1.D., Description, clarified the inspection procedure, deleted the request for inspection results, and moved the terminating action information to Paragraph 1.E., Compliance. 5. Paragraph 1.J., References, was updated to show the correct references. 6. Paragraph 2.C., Parts and Materials Supplied by the Operator, item 2, corrected the cotter pin part number. 7. Paragraph 3.A., General Information, added caution information and clarified the inspection definition. ### Page 22 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 8. Paragraph 3.B., Work Instructions, item 4, clarified the inspection procedure. 9. Figure 1, changed the initial and repeat inspection intervals for the upper link fuse pin, and added terminating action information. 10. Figure 2, clarified the cleaning procedure. D. Description Remove the strut underwing fairings. Remove the end caps and corrosion preventive compound from the upper link fuse pin and clean the inside surface of the upper link fuse pin. Do a detailed inspection of the inside surface of the upper link fuse pin in place, without engine removal and strut removal, for corrosion. If corrosion is found in the base metal of the fuse pin, or if any crack is found, replace the fuse pin with a new fuse pin with the same part number. If no corrosion is found, do a High Frequency Eddy Current (HFEC) inspection. If crack is detected, remove the upper link fuse pin and do a Magnetic Particle inspection on the inside surface of the upper link fuse pin. If crack is found in the upper link fuse pin, replace the fuse pin with a new fuse pin with the same part number. Apply the corrosion preventive compound on the upper link fuse pin and install the end caps. Install the strut underwing fairings. The service bulletins listed below have similar access requirements and are provided for your information and planning purposes. Revision 1 - No more work is necessary on airplanes inspected as shown in the original issue of this service bulletin. However, continued repeat inspections are necessary at an increased frequency. Additionally, initial inspections on JT9D airplanes are required at a reduced threshold. 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. See Figure 1 for compliance recommendations and maintenance alternatives. Terminating action for this service bulletin is the accomplishment of the modification of the nacelle strut and wing structure for Pratt and Whitney, General Electric and Rolls Royce powered airplanes, in accordance with Service Bulletin 767-54-0080, Original Issue or Revision 1; or 767-54-0081, Original Issue or Revision 1; or 767-54-0082, Original Issue, Revision 1 or Revision 3, as applicable. Common Access Service Bulletins Number Title 767-57-0053 Wings - Outer Wing Attachment Fittings - Wing Front Spar Pitch Load Fittings Inspection and Rework 767-54-0072 Nacelles/Pylons - Strut Attach Upper Link - Upper Link Inspection, Rework or Replacement ### Page 23 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 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 man-hours necessary to do this inspection for each engine position. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator man-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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. H. Weight and Balance Changes None I. Electrical Load Data Not changed J. References 1. Existing Data: a. 767 Aircraft Maintenance Manual (AMM) 06-43-00, 27-81-00, 54-51-03, 78-31-00 b. 767 Non-Destructive Testing (NDT) Manual, Part 6, 54-51-02 c. Boeing Service Bulletin 767-54-0080, 767-54-0081, 767-54-0082 TASK NUMBER OF PERSONS MAN-HOURS ELAPSED TIME ( HOURS ) Open Access 2 2 1 Inspect 1 2 2 Close Access 2 2 1 TOTAL FOR EACH ENGINE POSITION 6 4 TOTAL FOR EACH AIRPLANE 12 8 ### Page 24 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT d. Standard Overhaul Practices Manual (SOPM) 20-20-01, 20-30-03 2. Data supplied with this Service Bulletin: None 3. Installation Drawings Used in the Preparation of this Service Bulletin: 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 None L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. DRAWING NUMBER TITLE 310T1030 ENGINE STRUT TO WING INSTL - CF6-80A ENGINE 310T2030 ENGINE STRUT TO WING INSTL - CF6-80C2 ENGINE 310T3030 ENGINE STRUT TO WING INSTL - JT9D-7R4 ENGINE 310T4040 ENGINE STRUT TO WING INSTL - PW4000 ENGINE 311T5700 ENGINE STRUT TO WING INSTL - RB211 ENGINE ### Page 25 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 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 given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts: None. 2. Parts and Materials Supplied by the Operator: 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 Quantity Part Number ( Specification ) Name 4 oz MIL-C-11796, class I (b) Corrosion preventive compound 1 oz MIL-G-23827 or MIL-G-21164 (b) Grease 2 MS24665-374 (a) Cotter pin 1 oz BMS 5-79 or BMS 5-95 (a) Sealant As required 311T2090-1 Fuse pin (PW4000 or CF6-80C) As required 311T3090-3 (311T3090-4 assy optional) Fuse pin (JT9D or CF6-80A) As required 311T5090-1 Fuse pin (RB211) (a) See the Qualified Products List (QPL) at the end of the Boeing Material Specifications (BMS) for supplier data. (b) See the Qualified Products List (QPL) at the end of the MIL SPEC for supplier data. ### Page 26 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the inspection 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. ### Page 27 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 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. The paragraphs identified with a letter give the general work instructions. The instructions identified with numbers on the figures give the recommended sequence of steps. 2. Unless shown differently, these dimensions and tolerances are used: — Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual Chapter 51. 3. Alternative fasteners are given in 767 Structural Repair Manual Chapter 51. 4. Obey all of the warnings and cautions given in the specified manual sections. 5. See Figure 1 for compliance recommendations and maintenance alternatives. 6. A new fuse pin of the same part number may be installed at any point in the Accomplishment Instructions to gain the longer reinspection interval as shown in Figure 1. 7. The Figures and instructions are for the left strut (unless otherwise noted), repeat for the right strut. 8. 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. 9. These work instructions refer to procedures included on 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 "as given in" are included in the instruction, the procedure in the Boeing document must be used. B. WORK INSTRUCTIONS 1. Do the deactivation procedure for the leading edge slats in the retracted position. Refer to 767 AMM 27-81-00/201 as an accepted procedure. 2. Do the deactivation procedure for the thrust reverser for ground maintenance. Refer to 767 AMM 78-31-00/201 as an accepted procedure. ### Page 28 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT 3. Remove and keep the following access panels. Refer to 767 AMM 06-43-00 as an accepted procedure. 4. Do a detailed inspection of the inside surface of the fuse pin for corrosion as given in Figure 2. a. If corrosion is found in the base metal, and the corrosion can not be removed as given in Figure 2, (1) Replace the fuse pin with a new fuse pin of the same part number. Refer to 767 AMM 54-51-03 as an accepted procedure. (2) Do a detailed inspection of the fuse pin at the time given in Figure 1, Table 1.1. b. If NO CORROSION is found, or small corrosion is found that could be removed as given in Figure 2, do a High Frequency Eddy Current (HFEC) inspection of the inside surface of the fuse pin, as given in 767 NDT, Part 6, 54-51-02. NOTE: Electrical wire bundles may have to be removed to provide additional access for the HFEC probe. (1) If NO CRACK INDICATION is found, (a) Apply two layers of BMS 10-11 primer to the inside surface of the fuse pin. (b) Reinstall the adapter rings (if applicable), the end caps, the washers, the bolt, the castellated nut, and a new cotter pin. Refer to 767 AMM 54-51-03 as an accepted procedure. (c) Do a repeat detailed inspection of the fuse pin at the interval given in Figure 1, Table 1.2. (2) If any CRACK INDICATION is found, (a) Remove the fuse pin. Refer to 767 AMM 54-51-03 as an accepted procedure. (b) Do a magnetic particle inspection of the inside surface of the fuse pin as given in SOPM 20-20-01. 1) If any CRACK is found, ENGINE TYPE ACCESS PANEL IDENTIFICATION NUMBER Left Strut Right Strut JT9D, CF6-80A, PW4000, CF6- 80C 431ET 441ET 432FL 442FR 437AL 447AR RB211 432CL 442DR 432DL 442ER 433DL 443LR ### Page 29 March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT {a} Replace the fuse pin with a new fuse pin of the same part number and reinstall the adapter rings (if applicable), the end caps, the washers, the bolt, the castellated nut, and a new cotter pin. Refer to 767 AMM 54-51-03 as an accepted procedure. {b} Do a detailed inspection of the fuse pin at the time given in Figure 1, Table 1.1. 2) If NO CRACK is found, {a} Apply two layers of BMS 10-11 primer to the inside surface of the fuse pin. {b} Reinstall the fuse pin and the adapter rings (if applicable), the end caps, the washers, the bolt, the castellated nut, and a new cotter pin. Refer to 767 AMM 54-51-03 as an accepted procedure. {c} Do a repeat detailed inspection of the fuse pin at the interval given in Figure 1, Table 1.2. 5. Reinstall the following access panels. Refer to 767 AMM 06-43-00 as an accepted procedure. 6. Do the thrust reverser activation procedure. Refer to 767 AMM 78-31-00/201 as an accepted procedure. 7. Do the activation procedure for the leading edge slats. Refer to 767 AMM 27-81-00/201 as an accepted procedure. 8. Put the airplane back in serviceable condition. ENGINE TYPE ACCESS PANEL IDENTIFICATION NUMBER Left Strut Right Strut JT9D, CF6-80A, PW4000, CF6- 80C 431ET 441ET 432FL 442FR 437AL 447AR RB211 432CL 442DR 432DL 442ER 433DL 443LR ### Page 30 FIGURE 1: INSPECTION INTERVALS AND MAINTENANCE ALTERNATIVES March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT FIGURE 1: INSPECTION INTERVALS AND MAINTENANCE ALTERNATIVES 1 DO A DETAILED INSPECTION OF THE FUSE PIN AT THE INTERVAL SHOWN IN TABLE 1.1 REPEAT DETAILED NSPECTION OF THE FUSE PIN AT THE INETERVAL GIVEN IN TABLE 1.2 NO CRACK INDICATION FOUND. REMOVE FUSE PIN. INSTALL NEW FUSE PIN. CORROSION FOUND. REMOVE FUSE PIN. INSTALL NEW FUSE PIN. NO CORROSION FOUND. HFEC INSPECT THE FUSE PIN FOR CRACK INDICATION. REMOVE FUSE PIN. MAGNETICALLY PARTICLE INSPECT FUSE PIN. CRACK FOUND.NO CRACK FOUND. INSTALL NEW FUSE PIN.REINSTALL FUSE PIN. CRACK INDICATION FOUND. DO A DETAILED INSPECTION OF THE UPPER LINK FUSE PIN IN PLACE FOR CORROSION. WHEN THE AIRPLANE REACHES THE INITIAL INSPECTION THRESHOLD, AS SHOWN IN TABLE 1.1 OR IF THE AIRPLANE HAS PASSED THE INITIAL INSPECTION THRESHOLD, THEN WITHIN 3,000 FLIGHT-CYCLES OR 18 MONTHS WHICHEVER COMES FIRST, AFTER THE DATE OF REVISION 1 OF THIS SERVICE BULLETIN, DO EITHER OF THE FOLLOWING DO A DETAILED INSPECTION OF THE FUSE PIN AT THE INTERVAL SHOWN IN TABLE 1.1 DO A DETAILED INSPECTION OF THE FUSE PIN AT THE INTERVAL SHOWN IN TABLE 1.1 R85489 (SHEET 1 OF 2) ### Page 31 FIGURE 1: INSPECTION INTERVALS AND MAINTENANCE ALTERNATIVES March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. Table 1.1: Initial Inspection Threshold For Upper Link Fuse Pin Engine Type Initial Inspection Threshold (flight - cycles) JT9D 14,000 CF6-80A 24,000 PW4000 8,000 CF6-80C2 10,000 RB211 24,000 Table 1.2: Reinspection Interval For Upper Link Fuse Pin Replacement Engine Type Reinspection Interval JT9D 3,000 flight-cycles or 24 months, whichever comes first CF6-80A PW4000 CF6-80C2 RB211 FLAG NOTE MORE DATA 1 Terminating action for this service bulletin is the accomplishment of the modification of the nacelle strut and wing structure for Pratt and Whitney, General Electric and Rolls Royce powered airplanes, in accordance with Service Bulletin 767-54-0080, Original Issue or Revision 1; or 767-54-0081, Original Issue or Revision 1; or 767-54-0082, Original Issue, Revision 1 or Revision 3, as applicable. (SHEET 2 OF 2) ### Page 32 FIGURE 2: DETAILED INSPECTION OF THE UPPER LINK FUSE PIN March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT FIGURE 2: DETAILED INSPECTION OF THE UPPER LINK FUSE PIN RING ADAPTER RING ADAPTER WASHER BOLT END CAP END CAP WASHER COTTER PIN RIGHT STRUT OPPOSITE STRUT UPPER LINK TYPICAL LEFT STRUT SHOWN A A UP FWD 2 2 2 2 2 2 2 1 2 NUT R85731 (SHEET 1 OF 2) ### Page 33 FIGURE 2: DETAILED INSPECTION OF THE UPPER LINK FUSE PIN March 27, 1997 Revision 1: April 24, 2008 767-54A0074 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 33 BOEING SERVICE BULLETIN 767-54A0074 ALERT ALERT The step numbers shown below agree with the numbers shown in the circle symbols in the figure. STEP TASK NAME PROCEDURE REFERENCES NOTES 1 Remove/ Discard Cotter Pin - 767 AMM 54-51-03 - 2 Remove/ Keep Castellated Nut - 767 AMM 54-51-03 See Table 2.1 for part numbers associated with engine types. Bolt - Washers - End Caps - Collars - Adapter Ring - - (a) 3 Clean Fuse Pin - SOPM 20-30-03 (b) 4 Inspect Fuse Pin Detailed Inspection - for corrosion. (a) Part number 311T3090-6 is only applicable to JT9D and CF6-80A engines equipped with 311T3090-4 fuse pin assembly. (b) Small surface corrosion on the inside surface of the upper link fuse pin can be removed with a nylon scuff pad. Table 2.1: Part Numbers and Associated Engine Types PART NAME ENGINE TYPE JT9D CF6-80A PW4000 CF6-80C RB211 Cotter Pin MS24665-374 MS24665-374 MS24665-374 MS24665-374 MS24665-374 Castellated Nut BACN10JD9CD BACN10JD9 BACN10JD9CD BACN10JD9 BACN10JD9 Washer BACW10BN9SP AN960C916L BACW10BN9SP AN960C916L (a) End Cap 311T3101-3 311T3101-3 311T3101-3 311T3101-3 311T5098-1 (a) BACW10BP9ACU on the bolt side and AN960C916L on the nut side. A-A UPPER LINK STRUT 43 R85820 (SHEET 2 OF 2) --- 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.