# Boeing Alert Service Bulletin 747-54A2230: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0865; AD 2010-01-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-54A2230](https://openairdocs.org/service-documents/boeing/747-54a2230.md) - Title as filed: U.S. DOT/FAA - Service Information - Pages: 300 - PDF: https://openairdocs.org/files/sha256/5e/ba/5ebac956f66d45d33ab152114c408309ff19e58ba8aa0aa9af0230716dfe3e82 - Page: https://openairdocs.org/service-documents/boeing/747-54a2230/file/5ebac956f66d ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 300 ALERT ALERT Commercial Airplane Group 747 ALERTALERT Service Bulletin Number: 747-54A2230 Date: October 30, 2008 ATA System: 5400 5430 SUBJECT: NACELLES / PYLONS - Front Spar Chord Inspection and Strut Cap Skin Installation BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 ### Page 2 BLANK PAGE October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT BLANK PAGE ### Page 3 Table of Contents October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Table of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 35 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 36 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 36 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 63 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 63 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 FIGURE 1: STRUT NO. 1 - VARIABLE CAMBER FLAP SEAL FAIRING REMOVAL. . . . . . . . . . 80 FIGURE 2: STRUT NO. 1 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . 82 FIGURE 3: STRUT NO. 1 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . 89 FIGURE 4: STRUT NO. 1 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . 94 FIGURE 5: STRUT NO. 1 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . 100 FIGURE 6: STRUT NO. 1 - VARIABLE CAMBER FLAP SEAL FAIRING INSTALLATION . . . . . . . 104 FIGURE 7: STRUT NO. 2 - SKIRT SEAL REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . 106 FIGURE 8: STRUT NO. 2 - SKIRT SEAL REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . 109 ### Page 4 Table of Contents October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT FIGURE 9: STRUT NO. 2 - SKIRT SEAL REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . 113 FIGURE 10: STRUT NO. 2 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 116 FIGURE 11: STRUT NO. 2 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 119 FIGURE 12: STRUT NO. 2 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 122 FIGURE 13: STRUT NO. 2 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 125 FIGURE 14: STRUT NO. 2 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 131 FIGURE 15: STRUT NO. 2 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 137 FIGURE 16: STRUT NO. 2 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 144 FIGURE 17: STRUT NO. 2 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 148 FIGURE 18: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 152 FIGURE 19: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 162 FIGURE 20: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 172 FIGURE 21: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 176 FIGURE 22: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 180 FIGURE 23: STRUT NO. 2 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 184 FIGURE 24: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 188 FIGURE 25: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 191 FIGURE 26: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 195 FIGURE 27: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 198 FIGURE 28: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 201 FIGURE 29: STRUT NO. 3 - SKIRT SEAL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . . 204 FIGURE 30: STRUT NO. 3 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 207 FIGURE 31: STRUT NO. 3 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 213 FIGURE 32: STRUT NO. 3 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 219 FIGURE 33: STRUT NO. 3 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 226 FIGURE 34: STRUT NO. 3 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 230 FIGURE 35: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 234 FIGURE 36: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 244 FIGURE 37: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 254 FIGURE 38: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 258 FIGURE 39: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 262 FIGURE 40: STRUT NO. 3 - SKIRT SEAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 266 FIGURE 41: STRUT NO. 4 - VARIABLE CAMBER FLAP SEAL FAIRING REMOVAL . . . . . . . . 270 FIGURE 42: STRUT NO. 4 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . 272 FIGURE 43: STRUT NO. 4 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 279 ### Page 5 Table of Contents October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT FIGURE 44: STRUT NO. 4 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION AND CAP SKIN DOUBLER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . 284 FIGURE 45: STRUT NO. 4 - OPEN HOLE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION 290 FIGURE 46: STRUT NO. 4 - VARIABLE CAMBER FLAP SEAL FAIRING INSTALLATION . . . . . . 294 APPENDIX A: MASTER FASTENER CODE LIST. . . . . . . . . . . . . . . . . . . . . . . . . . . . 296 APPENDIX B: SCOPE OF CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 299 ### Page 6 Table of Contents October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT BLANK PAGE ### Page 7 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 300 ALERT ALERT Commercial Airplane Group 747 ALERTALERT Service Bulletin Number: 747-54A2230 Summary Date: October 30, 2008 ATA System: 5400 5430 SUBJECT: NACELLES / PYLONS - Front Spar Chord Inspection and Strut Cap Skin Installation 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 and modification in this service bulletin will detect and help prevent cracking and fracture of the nacelle strut front spar chord assembly forward of the upper link attachment. Fracture of the front spar chord assembly will result in the loss of the strut upper link load path. Continued operation without the strut upper link load path could result in the fracture of the diagonal brace and result in an in-flight separation of the strut and engine. The front spar chord assembly is used to connect the strut to the upper link. Subsequent to the original issue of Boeing Service Bulletin 747-54A2224 Original Issue, an operator reported finding a fractured chord on Strut no. 3 on an airplane with approximately 79,800 flight-hours and 15,100 flight-cycles. The fracture occurred forward of the rear engine mount bulkhead due to cracking that initiated and was propagated by fatigue from a fastener hole. Loss of the upper link load path would result in the transfer of additional loads to the diagonal brace load path. The additional loads could result in the fracture of the diagonal brace. The loss of the upper link load path combined with the loss of the diagonal brace load path could result in the in-flight separation of the strut and engine. Inspection of the front spar chord assembly will detect cracks or fractures of the front spar chord assembly. Installation of a cap skin doubler, if not previously accomplished, and oversizing of the holes will reduce the potential for cracks from developing in the front spar chord assembly fastener holes and help prevent cracks or fractures in the front spar chord assemblies. Boeing Service Related Problem (SRP) 747OP-SRP-54-0117 is related to this service bulletin. ### Page 8 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT ACTION Part 1 - Outboard Strut Inspection and Modification Remove the strut access panels as required. Remove the variable camber flap fairing (not required on JT9D-3 / -7 powered airplanes which have already installed the cap skin doubler in accordance with 747-54-2125). Relieve the load from the front spar chord, as required. Remove the fasteners common to the front spar chord from the rear engine mount bulkhead forward to the next frame. Do an open hole High Frequency Eddy Current (HFEC) inspection for cracks. If any crack is found, contact The Boeing Company for additional instructions. If the cap skin doubler was not previously installed in accordance with 747-54-2125, install the cap skin doubler. Install the variable camber flap fairing, if removed. Install the strut access panels. Part 2 - Inboard Strut Inspection and Modification Remove the strut access panels. For airplanes that have not installed the cap skin doubler in accordance with 747-54-2125, remove the engine and strut. For airplanes that have not installed the cap skin doubler in accordance with 747-54-2125, remove and cut the skirt seal. For airplanes that have already installed the cap skin doubler in accordance with 747-54-2125, remove the skirt seal. Relieve the load from the front spar chord, as required. For JT9D-3/ -7 powered airplanes that have already installed the cap skin doubler in accordance with 747-54-2125, remove the cap skin doubler to gain access to fasteners that are covered by the doubler. Remove the fasteners common to the front spar chord from the rear engine mount bulkhead forward to the next frame. Do an open hole High Frequency Eddy Current (HFEC) inspection for cracks. If any crack is found, contact The Boeing Company for additional instructions. Reinstall the cap skin doubler or If the cap skin doubler was not previously installed in accordance with 747-54-2125, install the cap skin doubler. Reinstall the skirt seal or for airplanes that have not installed the cap skin doubler, rework the skirt seal to accommodate the cap skin doubler and reinstall. Install the engine and strut, if removed. Install the strut access panels EFFECTIVITY 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -SP, and -SR airplanes with JT9D-3/-7 (except -70) and CF6-45/-50 series engines. COMPLIANCE See paragraph 1.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. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair procedures given in this service bulletin. ### Page 9 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT MANPOWER MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Airplane Group Configuration Total Task Hours Elapsed Hours 1 1 371.00 134.50 2 78.30 41.30 3 79.00 42.00 2 1 309.00 103.5 2 55.70 30.70 3 56.40 31.40 3 1 337.00 117.50 2 72.30 39.30 3 73.00 40.00 ### Page 10 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT DO AN OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE FASTENER HOLES COMMON TO THE FRONT SPAR CHORD FOR CRACKS. LEFT INBOARD STRUT SHOWN (OTHER STRUTS SIMILAR) STRUTS WHICH HAVE NOT PREVIOUSLY INSTALLED THE CAP SKIN DOUBLER________________________________ (INBOARD STRUTS ONLY). REWORK LEADING EDGE SECTION OR FAIRING TO ACCOMMODATE DOUBLER ISTALLATION. FRONT SPAR CHORD FRAME REAR ENGINE MOUNT BULKHEAD STRUTS WHICH HAVE NOT PREVIOUSLY INSTALLED THE CAP SKIN DOUBLER________________________________ INSTALL CAP SKIN DOUBLER. FWD 1544976 ### Page 11 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 300 ALERT ALERT Commercial Airplane Group 747 ALERTALERT Service Bulletin Number: 747-54A2230 Date: October 30, 2008 ATA System: 5400 5430 SUBJECT: NACELLES / PYLONS - Front Spar Chord Inspection and Strut Cap Skin Installation 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 D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. GROUP CONFIGURATION DESCRIPTION 1 - 747-100, -100B, -100SUD, -200B, -200C, - 200F, -300, -SP, and -SR airplanes powered by JT9D-3/-7 (except-70) series engines. 1 Airplanes which have not incorporated Service Bulletin 747-54-2125. 2 Airplanes which installed the strut cap skin doubler in accordance with Service Bulletin 747- 54-2125 Original Issue or Revision 1. 3 Airplanes which installed the strut cap skin doubler in accordance with 747-54-2125 Revision 2 or later releases. ### Page 12 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Airplane models: 747-100 747-100B 747-100B SUD 747-200B 747-200C 747-200F 747-300 747SP 747SR IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AAR A/C ENG. SALES & LEASING (AFD) 2 RB681–RB682 AERO CONTROLS (AEO) 1 RA722–RA723 AEROLINEAS ARGENTINAS (ARG) 1 RD122–RD127 AFRICA UNITED HOLDING CO. (UHD) 1 RB010 RD513 AFX (AXL) 1 RD201 AGES AIRCRAFT SALES & LEASING (AGJ) 1R B 0 0 4 2 - 747-200B, -200C, -200F, -300, and -SR airplanes powered by CF6-45/-50 series engines. 1 Airplanes which have not incorporated Service Bulletin 747-54-2125. 2 Airplanes which installed the strut cap skin doubler in accordance with Service Bulletin 747- 54-2125 Original Issue or Revision 1. 3 Airplanes which installed the strut cap skin doubler in accordance with 747-54-2125 Revision 2 or later releases. 3 - 747-200B airplanes powered by CF6-45/-50 series engines with modified JT9D-3/-7 inboard struts. 1 Airplanes which have not incorporated Service Bulletin 747-54-2125. 2 Airplanes which installed the strut cap skin doubler in accordance with Service Bulletin 747- 54-2125 Original Issue or Revision 1. 3 Airplanes which installed the strut cap skin doubler in accordance with 747-54-2125 Revision 2 or later releases. GROUP CONFIGURATION DESCRIPTION ### Page 13 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT AIR ATLANTA ICELANDIC (AID) 1 RB421 RS211 RS222 RS233 RS235 RS237 2 RD414 RD456 RD647–RD648 RD755 RD771 RD774 RR204 RR206 RR332 AIR CANADA (ACN) 1 RA749–RA750 RD531 AIR CHINA (BEJ) 1 RD782–RD783 RR451 AIR FRANCE (AFA) 2 RD655 RD657–RD659 RD721–RD722 RD791 RR306 RR308–RR309 AIR GULF FALCON (GFG) 1 RA535 RA537 AIR INDIA (AIN) 1 RA729 RA731 AIR UNIVERSAL (UVL) 2 RD231–RD232 RD291–RD292 RD649 RD775 ALBARAKA (AAB) 1 RB102 AMERICAN AIRLINES (AAL) 1 RA266 ARKIA ISRAELI AIRLINES (ARK) 1 RA253 ATLAS AIR (TLS) 2 RB684 RD361–RD366 RD641 RD646 RD691–RD692 RD753–RD754 RJ333 RR301 RS722 BAHRAIN ROYAL FLIGHT (BHR) 1 RG009 BANC OF AMERICA LEASING (SBC) 1 RA106 RD001–RD002 BOEING AIRCRAFT HOLDING CO. (BHC) 1 RJ132 2 RB691 RB693 RD181 RD451–RD454 BOEING WICHITA MOD CENTER (WMC) 2 RD455 ### Page 14 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT C.A.L. CARGO AIR LINES (CRG) 2 RJ331–RJ332 C.I.T. LEASING CORPORATION (TCI) 1 RB011 RD047 CAPITAL ASSET MANAGEMENT (CPG) 1 RD053 CARGAIR (CGL) 1 RD203 CARGO 360, INC. (CGN) 1 RR024–RR025 RS786 CARGO B AIRLINES (CBO) 2 RD751 RR307 RR561 CATHAY PACIFIC AIRWAYS (CAT) 2 RD581–RD583 CORSAIR (COR) 1 RS239–RS240 DRAGONAIR (DRG) 1 RR522 RS741 RS743 RS771 DUBAI AIR WING (DAW) 1 RD622 EL AL ISRAEL AIRLINES (ELA) 1 RD442 RJ152 RR225–RR226 EVERGREEN A/C SALES & LEASING (EVG) 1R A 3 7 1 EVERGREEN INTERNATIONAL A/L (EVR) 1 RA028 RA631 RA633 RB604 RB607 RD004 RD041–RD043 RJ131 RJ133 2 RD772–RD773 EXPORT RESTRICTED AIRPLANES (YWV) 1 RA101–RA103 RA112 RA161–RA163 RB711 RD681–RD682 RG101–RG104 RG141–RG142 RG171 RR001–RR004 2 RS751–RS752 FINOVA (GRB) 1R A 6 5 1 2R S 7 6 1 ### Page 15 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT GE (GEC) 1 RA016 GECAS (GEF) 1 RA007 RA013 RA027 GENERIC CUSTOMER/SUPPLIER (XXX) 1 RD055 RD104 RD261 2 RD382 RR202–RR203 GIRJET (GRJ) 2 RJ321 GLOBAL AIR LEASING (GAO) 1 RG164 GLOBAL PEACE INITIATIVE (GPI) 1 RG174 GRACE CATHEDRAL INC. (GCI) 1 RG193 GUGGENHEIM AVIATION PARTNERS (GPR) 2 RB692 RB697 HORTA (HOB) 1 RG163 IBERIA AIRLINES (IBE) 1 RD431–RD435 INTERNATIONAL AIR LEASES (IAL) 1 RB006 IRAQI AIRWAYS (IRQ) 1 RG095 RG172 RJ301–RJ303 JAL INTERNATIONAL (JAL) 1 RD227 RR265–RR267 RS251–RS254 RS256 RS259 RS265–RS267 JET AERO HOLDINGS (JHD) 1 RG122 JOHNSON SPACE CENTER (ZBR) 1 RA908 RB601 JUMBO JET LEASING (JJL) 1 RA526 RA532–RA534 RA539 KABO AIR (KAB) 1 RA305 RA316 RA560 RB008 RD121 ### Page 16 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT KALITTA AIR (KAC) 1 RA401–RA402 RA524 RA545–RA548 RA635 RA913 RB605 RD054 RD082–RD083 RD221 RD223–RD225 RD571 RD621 RD623 RR261–RR262 RR361–RR362 RR501 RR521 KUWAIT AIRWAYS (KUW) 1 RD202 RD204 LOGISTIC AIR, INC. (LGA) 1 RA015 RA217 RA910 RB722–RB723 MARTINAIR HOLLAND (MTH) 2 RJ322 RR310 MK AIRLINES (MKA) 1 RD441 RD781 RR022–RR023 RR336 NASA (NAS) 1 RG091 NEA HOLDINGS, INC. (NEA) 1 RB001 RD045–RD046 NIPPON CARGO AIRLINES (NCA) 2 RB696 RD233–RD235 RD461 RR553 RR555 NORTHWEST AIRLINES (NWA) 1 RD056–RD057 RD241–RD243 RD251–RD255 RD257–RD259 RD262 RD301–RD302 RR005 RR341–RR342 RR344–RR345 RR431–RR432 RR503 RR566 OMAN ROYAL FLIGHT (RFO) 1 RG161 ORIENT THAI AIRLINES (OTH) 1 RA528 RA540 RA543–RA544 RD222 RD516 RR264 RS001–RS002 RS257 RS292 2R S 7 1 2 PAKISTAN INT'L AIRLINES (PIA) 2 RD701–RD702 PHUKET AIRLINES (PHK) 1 RD421–RD424 RS238 RS241 2 RD381 RD605 RS711 POLAR AIR CARGO (PAO) 1 RR504 2 RD752 ### Page 17 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT PRATT & WHITNEY ENGINE SERVICE (PWE) 1 RG213 RG222 ROYAL AIR MAROC (RAM) 1 RD671 SATAIR (SAI) 2 RD606 SAUDI ROYAL FLIGHT (SRF) 1 RS699 SOUTH AFRICAN AIRWAYS (SAA) 1 RG123 RG125 RS212 RS232 RS236 SOUTHERN AIR (SOF) 2 RB695 RD272 RD383 RD411–RD412 RD601–RD602 RD607 RD642–RD643 RD792 RR302–RR305 RR551 RR554 RS721 SUO1 (UO1) 3 RB013–RB016 SURINAM AIRWAYS (SUR) 2 RS713 TAAG (ANGOLA AIRLINES) (ANG) 1 RS703 RS742 TESIS AVIATION ENTERPRISE (TEV) 1 RA784 TRADEWINDS AIRLINES (TWN) 1 RA726 RD052 RD426 TRANSAERO AIRLINES (TRX) 1 RD226 RS255 RS258 RS263 RS268 TRANSATLANTIC INTL AIRLINES (TIB) 1 RG173 UPS (UPS) 1 RA026 RA029 RA033 RA902 RA912 RA915–RA916 RD051 RD058–RD059 RD593 VOLGA-DNEPR AIRLINES (VDA) 2 RR552 RR556 RS762 WHIRLPOOL FINANCIAL CORP. (ZZW) 1 RB005 ### Page 18 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT WINGS WORLD WIDE (WWW) 1 RG221 WORLDWIDE AIRCRAFT HOLDING CO. (WAH) 1 RG008 YEMENIA (YEM) 1 RG162 YONA (IOP) 1 RG191 IDENTIFICATION BY VARIABLE NUMBER Variable Group RA001–RA034 1 RA101–RA115 1 RA161–RA164 1 RA201–RA203 1 RA216–RA217 1 RA245–RA246 1 RA251–RA266 1 RA301–RA318 1 RA351–RA360 1 RA369–RA373 1 RA401–RA418 1 RA501–RA502 1 RA521–RA528 1 RA532–RA548 1 RA551–RA552 1 RA559–RA561 1 RA581–RA582 1 RA585 1 RA601–RA602 1 RA631–RA635 1 RA651–RA652 1 RA671–RA677 1 RA701–RA702 1 RA721–RA731 1 RA741–RA745 1 RA749–RA750 1 RA761–RA762 1 RA781–RA784 1 ### Page 19 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT RA901–RA916 1 RB001–RB012 1 RB013–RB016 3 RB041–RB044 1 RB071–RB075 1 RB101–RB102 1 RB421 1 RB601–RB607 1 RB681–RB697 2 RB711 1 RB721–RB723 1 RD001–RD004 1 RD021–RD022 1 RD041–RD043 1 RD044 2 RD045–RD059 1 RD071–RD072 1 RD081–RD083 1 RD091–RD092 1 RD101–RD104 1 RD121–RD127 1 RD171–RD172 2 RD181–RD183 2 RD201–RD204 1 RD221–RD227 1 RD231–RD235 2 RD241–RD243 1 RD251–RD262 1 RD271–RD272 2 RD291–RD292 2 RD301–RD302 1 RD361–RD366 2 RD381–RD383 2 RD411–RD414 2 RD421–RD426 1 RD431–RD435 1 RD441–RD442 1 RD451–RD456 2 RD461 2 Variable Group ### Page 20 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT RD513–RD516 1 RD531 1 RD551 1 RD571 1 RD581–RD583 2 RD593 1 RD601–RD607 2 RD621–RD623 1 RD641–RD649 2 RD651–RD659 2 RD661 2 RD671 1 RD681–RD682 1 RD691–RD692 2 RD701–RD702 2 RD721–RD722 2 RD741–RD742 1 RD751–RD755 2 RD761 1 RD771–RD775 2 RD781–RD783 1 RD791–RD792 2 RE001 1 RG001–RG009 1 RG091 1 RG095 1 RG101–RG104 1 RG121–RG126 1 RG141–RG142 1 RG161–RG164 1 RG171–RG174 1 RG191–RG193 1 RG211–RG213 1 RG221–RG222 1 RJ131–RJ133 1 RJ151–RJ152 1 RJ301–RJ303 1 RJ321–RJ322 2 RJ331–RJ333 2 Variable Group ### Page 21 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT RR001–RR005 1 RR021–RR025 1 RR031 1 RR201 1 RR202–RR206 2 RR225–RR226 1 RR261–RR267 1 RR301–RR310 2 RR331–RR332 2 RR336 1 RR341–RR345 1 RR361–RR362 1 RR422 1 RR431–RR432 1 RR451 1 RR501–RR504 1 RR521–RR522 1 RR551–RR556 2 RR561 2 RR566 1 RS001–RS002 1 RS201 2 RS211–RS212 1 RS221–RS222 1 RS231–RS241 1 RS251–RS259 1 RS263 1 RS265–RS268 1 RS291–RS292 1 RS699 1 RS701–RS703 1 RS711–RS713 2 RS721–RS722 2 RS731–RS732 1 RS741–RS743 1 RS751–RS752 2 RS761–RS762 2 RS771 1 RS786 1 Variable Group ### Page 22 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Accomplishment of the inspection and modification in this service bulletin will detect and help prevent cracking and fracture of the nacelle strut front spar chord assembly forward of the upper link attachment. Fracture of the front spar chord assembly will result in the loss of the strut upper link load path. Continued operation without the strut upper link load path could result in the fracture of the diagonal brace and result in an in-flight separation of the strut and engine. The front spar chord assembly is used to connect the strut to the upper link. Subsequent to the original issue of Boeing Service Bulletin 747-54A2224 Original Issue, an operator reported finding a fractured chord on Strut no. 3 on an airplane with approximately 79,800 flight-hours and 15,100 flight-cycles. The fracture occurred forward of the rear engine mount bulkhead due to cracking that initiated and was propagated by fatigue from a fastener hole. Loss of the upper link load path would result in the transfer of additional loads to the diagonal brace load path. The additional loads could result in the fracture of the diagonal brace. The loss of the upper link load path combined with the loss of the diagonal brace load path could result in the in-flight separation of the strut and engine. Inspection of the front spar chord assembly will detect cracks or fractures of the front spar chord assembly. Installation of a cap skin doubler, if not previously accomplished, and oversizing of the holes will reduce the potential for cracks from developing in the front spar chord assembly fastener holes and help prevent cracks or fractures in the front spar chord assemblies. Boeing Service Related Problem (SRP) 747OP-SRP-54-0117 is related to this service bulletin. D. Description Part 1 - Outboard Strut Inspection and Modification Remove the strut access panels as required. Remove the variable camber flap fairing (not required on JT9D-3 / -7 powered airplanes which have already installed the cap skin doubler in accordance with 747-54-2125). Relieve the load from the front spar chord, as required. Remove the fasteners common to the front spar chord from the rear engine mount bulkhead forward to the next frame. Do an open hole High Frequency Eddy Current (HFEC) inspection for cracks. If any crack is found, contact The Boeing Company for additional instructions. If the cap skin doubler was not previously installed in accordance with 747-54-2125, install the cap skin doubler. Install the variable camber flap fairing, if removed. Install the strut access panels. ### Page 23 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Part 2 - Inboard Strut Inspection and Modification Remove the strut access panels. For airplanes that have not installed the cap skin doubler in accordance with 747-54-2125, remove the engine and strut. For airplanes that have not installed the cap skin doubler in accordance with 747-54-2125, remove and cut the skirt seal. For airplanes that have already installed the cap skin doubler in accordance with 747-54-2125, remove the skirt seal. Relieve the load from the front spar chord, as required. For JT9D-3/ -7 powered airplanes that have already installed the cap skin doubler in accordance with 747-54-2125, remove the cap skin doubler to gain access to fasteners that are covered by the doubler. Remove the fasteners common to the front spar chord from the rear engine mount bulkhead forward to the next frame. Do an open hole High Frequency Eddy Current (HFEC) inspection for cracks. If any crack is found, contact The Boeing Company for additional instructions. Reinstall the cap skin doubler or If the cap skin doubler was not previously installed in accordance with 747-54-2125, install the cap skin doubler. Reinstall the skirt seal or for airplanes that have not installed the cap skin doubler, rework the skirt seal to accommodate the cap skin doubler and reinstall. Install the engine and strut, if removed. Install the strut access panels ### Page 24 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT E. Compliance The Inspection and modification in this service bulletin terminates the Part 2 - Forward side Inspection in service bulletin 747-54A2224 (747-54-2224). 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. Table 1: Part 1 - Outboard Strut Inspection and Modification Condition Action Compliance Time Airplanes on which the cap skin doubler is installed Do an open hole High Frequency Eddy Current inspection of the holes in the front chord assemblies in accordance with Accomplishment Instructions, Part 1 - Outboard Strut Inspection and Modification. Within 48 months after the date on this service bulletin. Airplanes on which the cap skin doubler is not installed Do an open hole High Frequency Eddy Current inspection of the holes in the front chord assemblies and install the cap skin doubler in accordance with Accomplishment Instructions, Part 1 - Outboard Strut Inspection and Modification. Within 48 months after the date on this service bulletin. Condition 1: No crack is found. No further action is required. - Condition 2: If any crack is found. Contact the boeing company for additional instructions and do the repair. Before further flight. Table 2: Part 2 - Inboard Strut Inspection and Modification Condition Action Compliance Time Airplanes on which the cap skin doubler is installed Do an open hole High Frequency Eddy Current inspection of the holes in the front chord assemblies in accordance with Accomplishment Instructions, Part 2 - Inboard Strut Inspection and Modification. Within 36 months after the date on this service bulletin. Airplanes on which the cap skin doubler is not installed Do an open hole High Frequency Eddy Current inspection of the holes in the front chord assemblies, install the cap skin doubler, and rework the skirt seal in accordance with Accomplishment Instructions, Part 2 - Inboard Strut Inspection and Modification. Within 36 months after the date on this service bulletin. Condition 1: No crack is found. No further action is required. - Condition 2: If any crack is found. Contact the boeing company for additional instructions and do the repair. Before further flight. ### Page 25 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 300 BOEING SERVICE BULLETIN 747-54A2230 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. This service bulletin has been approved by the FAA. In addition, the Manager of the Seattle Aircraft Certification approves the repair procedures and inspection methods with corresponding compliance times specified in Tables 1 and 2, under paragraph 1.E., "Compliance," of SB 747-54A2230, Revision 0 - Nacelles/Pylons-Front Spar Chord Inspection and Strut Cap Skin Installation as an AMOC (terminating action) to the inspections and corrective action with the corresponding compliance times specified in SB 747-54A2224, Revision 1, dated November 16, 2006, required by paragraphs (j) and (k) of AD 2007-01-15. All provisions of AD 2007-01-15 that are not specifically referenced in the previous sentence remain fully applicable and must be complied with. 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. ### Page 26 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 1, Configuration 1: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 Open Access (a) 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 2 2 29.00 14.50 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 35.00 18.00 Strut No. 2 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 7 1 2.00 2.00 Inspect and Change - Figure 13 2 29.00 14.50 Install Skirt Seal - Figure 18 2 11.50 5.75 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 150.50 49.25 Strut No. 3 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 24 1 2.00 2.00 Inspect and Change - Figure 30 2 29.00 14.50 Install Skirt Seal - Figure 35 2 11.50 5.75 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 150.50 49.25 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 42 2 29.00 14.50 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 35.00 18.00 TOTAL FOR EACH AIRPLANE 371.00 134.50 (a) Does not include time required to remove or install engine or strut. ### Page 27 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 1, Configuration 2: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Inspect and Change - Figure 3 2 9.00 4.25 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 14.00 7.00 Strut No. 2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 9 1 1.00 1.00 Inspect and Change - Figure 14 2 18.00 9.00 Install Skirt Seal - Figure 20 1 1.15 1.15 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.15 13.65 Strut No. 3 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 26 1 1.00 1.00 Inspect and Change - Figure 31 2 18.00 9.00 Install Skirt Seal - Figure 37 1 1.15 1.15 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.15 13.65 Strut No. 4 (a) Open Access 2 2.50 1.25 Inspect and Change - Figure 43 2 9.00 4.25 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 14.00 7.00 TOTAL FOR EACH AIRPLANE 78.30 41.30 (a) Does not include time required to remove or install engine or strut. ### Page 28 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 1, Configuration 3: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Inspect and Change - Figure 3 2 9.00 4.25 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 14.00 7.00 Strut No. 2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 11 1 1.10 1.10 Inspect and Change - Figure 14 2 18.00 9.00 Install Skirt Seal - Figure 22 1 1.40 1.40 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.50 14.00 Strut No. 3 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 28 1 1.10 1.10 Inspect and Change - Figure 31 2 18.00 9.00 Install Skirt Seal - Figure 39 1 1.40 1.40 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.50 14.00 Strut No. 4 (a) Open Access 2 2.50 1.25 Inspect and Change - Figure 43 2 9.00 4.25 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 14.00 7.00 TOTAL FOR EACH AIRPLANE 79.00 42.00 (a) Does not include time required to remove or install engine or strut. ### Page 29 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 2, Configuration 1: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 4 2 12.00 6.00 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 18.00 9.50 Strut No. 2 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 8 1 2.00 2.00 Inspect and Change - Figure 15 2 18.00 9.00 Install Skirt Seal - Figure 19 2 8.50 4.25 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 136.50 42.25 Strut No. 3 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 25 1 2.00 2.00 Inspect and Change - Figure 32 2 18.00 9.00 Install Skirt Seal - Figure 36 2 8.50 4.25 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 136.50 42.25 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 44 2 12.00 6.00 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 18.00 9.50 TOTAL FOR EACH AIRPLANE 309.00 103.5 (a) Does not include time required to remove or install engine or strut. ### Page 30 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 2, Configuration 2: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 5 2 5.00 2.50 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 Strut No. 2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 10 1 0.85 0.85 Inspect and Change - Figure 16 2 10.00 5.00 Install Skirt Seal - Figure 21 1 1.00 1.00 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 16.85 9.35 Strut No. 3 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 27 1 0.85 0.85 Inspect and Change - Figure 33 2 10.00 5.00 Install Skirt Seal - Figure 38 1 1.00 1.00 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 16.85 9.35 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 45 2 5.00 2.50 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 TOTAL FOR EACH AIRPLANE 55.70 30.70 (a) Does not include time required to remove or install engine or strut. ### Page 31 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 2, Configuration 3: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 5 2 5.00 2.50 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 Strut No. 2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 12 1 1.00 1.00 Inspect and Change - Figure 17 2 10.00 5.00 Install Skirt Seal - Figure 23 1 1.20 1.20 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 17.20 9.70 Strut No. 3 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 29 1 1.00 1.00 Inspect and Change - Figure 34 2 10.00 5.00 Install Skirt Seal - Figure 40 1 1.20 1.20 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 17.20 9.70 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 45 2 5.00 2.50 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 TOTAL FOR EACH AIRPLANE 56.40 31.40 (a) Does not include time required to remove or install engine or strut. ### Page 32 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 3, Configuration 1: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 4 2 12.00 6.00 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 18.00 9.50 Strut No. 2 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 7 1 2.00 2.00 Inspect and Change - Figure 13 2 29.00 14.50 Install Skirt Seal - Figure 18 2 11.50 5.75 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 150.50 49.25 Strut No. 3 Open Access 4 51.00 12.75 Remove Skirt Seal - Figure 24 1 2.00 2.00 Inspect and Change - Figure 30 2 29.00 14.50 Install Skirt Seal - Figure 35 2 11.50 5.75 Close Access 4 57.00 14.25 TOTAL FOR EACH STRUT 150.50 49.25 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 44 2 12.00 6.00 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 18.00 9.50 TOTAL FOR EACH AIRPLANE 337.00 117.50 (a) Does not include time required to remove or install engine or strut. ### Page 33 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 3, Configuration 2: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 5 2 5.00 2.50 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 Strut No. 2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 9 1 1.00 1.00 Inspect and Change - Figure 14 2 18.00 9.00 Install Skirt Seal - Figure 20 1 1.15 1.15 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.15 13.65 Strut No. 3 Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 26 1 1.00 1.00 Inspect and Change - Figure 31 2 18.00 9.00 Install Skirt Seal - Figure 37 1 1.15 1.15 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.15 13.65 Strut No. 4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 45 2 5.00 2.50 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 TOTAL FOR EACH AIRPLANE 72.30 39.30 (a) Does not include time required to remove or install engine or strut. ### Page 34 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 3, Configuration 3: Task Number of Persons Task Hours Elapsed Hours Strut No. 1 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 1 1 0.50 0.50 Inspect and Change - Figure 5 2 5.00 2.50 Install variable camber flap seal fairing - Figure 6 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 Strut No.2 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 11 1 1.10 1.10 Inspect and Change - Figure 14 2 18.00 9.00 Install Skirt Seal - Figure 22 1 1.40 1.40 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.50 14.00 Strut No.3 (a) Open Access 2 2.50 1.25 Remove Skirt Seal - Figure 28 1 1.10 1.10 Inspect and Change - Figure 31 2 18.00 9.00 Install Skirt Seal - Figure 39 1 1.40 1.40 Close Access 1 2.50 1.25 TOTAL FOR EACH STRUT 25.50 14.00 Strut No.4 (a) Open Access 2 2.50 1.25 Remove variable camber flap seal fairing - Figure 41 1 0.50 0.50 Inspect and Change - Figure 45 2 5.00 2.50 Install variable camber flap seal fairing - Figure 46 1 0.50 0.50 Close Access 2 2.50 1.25 TOTAL FOR EACH STRUT 11.00 6.00 TOTAL FOR EACH AIRPLANE 73.00 40.00 (a) Does not include time required to remove or install engine or strut. ### Page 35 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT H. Weight and Balance Changes 1 I. Electrical Load Data Not applicable. J. References 1. Existing Data: a. 747-100/200/300 Aircraft Maintenance Manual (AMM) 12-09-08, 12-09-09, 27-81-00, 51-24-04, 54-10-01, 54-10-03, 71-00-02 b. 747 Non-Destructive Testing (NDT) Manual, Part 6, 51-00-00 c. Boeing Parts Standards Document D-590 d. Boeing Service Related Problem (SRP) 747OP-SRP-54-0117 e. Boeing Service Bulletin 747-54-2125, 747-54A2224 (747-54-2224) f. Federal Aviation Administration (FAA) Airworthiness Directive 2007-01-15 g. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-44-01, 20-50-12, 20-60-04 2. Data supplied with this Service Bulletin: None. Airplane Change in Weight (Pounds) Change in Moment (Pound-Inches)Group Configuration 1 1 + 25.0 + 36,675.0 2 None None 3 None None 2 1 + 22.9 + 32,678.0 2 None None 3 None None 3 1 + 25.5 + 36,388.5 2 None None 3 None None ### Page 36 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT 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 65B90314 SKIN INSTL - OUTBOARD NACELLE STRUT. 65B90307 RIB INSTL, NAC STA 210.00, OUTBD NACELLE STRUT. 65B90310 BULKHEAD INSTALLATION - REAR ENGINE MOUNT, NACELLE, STA 221.90, OUTBD STRUT. 65B94130 SKIN INSTL - OUTBOARD NACELLE STRUT. 65B94107 BULKHEAD INSTL - STA 270.00, OUTBOARD NACELLE STRUT. 65B94120 RIB INSTL - NAC STA 259.00, NACELLE STRUT. 65B90416 SKIN INSTL - INBOARD NACELLE STRUT. 65B90412 BULKHEAD INSTALLATION - REAR ENG MT, NAC STA 221.90, INBD STRUT. 65B90407 RIB INSTL - NAC STA 210.00, INBD NACELLE STRUT. 65B90424 FAIRING INSTL - STRUT TO WING, INBOARD NACELLE STRUT. 65B89051 FAIRING INSTL, WING TO STRUT, INBD STRUT. 65B94052 SKIN INSTL - INBD NAC STRUT (CF6-50). 65B89049 BULKHEAD INSTALLATION - NACELLE STA 286.000, NAC STRUT, INBD. 65B89047 BULKHEAD INSTALLATION - STA 270.000, INBOARD NACELLE STRUT. ### Page 37 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits/parts, a supply sequence is given by Spares. More kits/parts become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. Group 1, Configuration 1: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru Dec 31/08 015U1830-1 Top Kit - Upper Spar Chord - Inspection and Modification Mar 4/08 5 60 $ 24,577.00 Apr 8/08 5 May 13/08 5 Jun 24/08 5 Aug 1/08 5 Sep 8/08 5 Oct 13/08 5 Nov 17/08 5 015U1830-11 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 38 $ 4,324.00 015U1830-15 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 7,965.00 Group 1, Configuration 2: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru Dec 31/08 015U1830-4 Top Kit - Upper Spar Chord - Inspection and Modification Mar 14/08 5 60 $ 838.00 Apr 18/08 2 015U1830-12 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 32 $ 111.00 015U1830-17 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 309.00 ### Page 38 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 1, Configuration 3: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru Dec 31/08 015U1830-7 Top Kit - Upper Spar Chord - Inspection and Modification Mar 14/08 5 60 $ 838.00 Apr 18/08 5 May 23/08 5 Jun 30/08 5 Aug 6/08 5 015U1830-12 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 32 $ 111.00 015U1830-16 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 309.00 Group 2, Configuration 1: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru Dec 31/08 015U1830-2 Top Kit - Upper Spar Chord - Inspection and Modification Mar 14/08 4 60 $ 23,996.00 015U1830-13 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 38 $ 4,281 015U1830-18 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 7,718 Group 2, Configuration 2: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru MMM Dd/Yy 015U1830-5 Top Kit - Upper Spar Chord - Inspection and Modification Mar 6/08 3 60 $ 595.00 015U1830-14 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 32 $ 59.00 015U1830-20 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 239.00 ### Page 39 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Group 2, Configuration 3: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru MMM Dd/Yy 015U1830-8 Top Kit - Upper Spar Chord - Inspection and Modification Mar 5/08 60 $ 595.00 Apr 9/08 May 14/08 Jun 19/08 015U1830-14 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 32 $ 59.00 015U1830-19 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 239.00 Group 3, Configuration 1: Kit Number Name Date QTY ROLT (Weeks) Unit Price thru MMM Dd/Yy 015U1830-3 Top Kit - Upper Spar Chord - Inspection and Modification Jan 25/08 1 60 $ 24,491.00 015U1830-13 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification - - 38 $ 4,281.00 015U1830-15 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification - - 60 $ 7,965.00 Group 3, Configuration 2: Kit Number Name ROLT (Weeks) Unit Price thru MMM Dd/Yy 015U1830-6 Top Kit - Upper Spar Chord - Inspection and Modification 60 $ 736.00 015U1830-14 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification 32 $ 59.00 015U1830-17 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification 60 $ 309.00 Group 3, Configuration 3: Kit Number Name ROLT (Weeks) Unit Price thru MMM Dd/Yy 015U1830-9 Top Kit - Upper Spar Chord - Inspection and Modification 60 $ 736.00 015U1830-14 Sub Kit - Strut No. 1 or 4 - Upper Spar Chord - Inspection and Modification 32 $ 59.00 015U1830-16 Sub Kit - Strut No. 2 or 3 - Upper Spar Chord - Inspection and Modification 60 $ 309.00 ### Page 40 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT The kits/parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair procedures given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts: To get the top kits / stut kits shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One top kit or one strut kit for each strut, and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the tables below. 015U1830 Kit Group 1 2 3 C o n f i g u r a t i o n 123123123 T o p K i t - 1- 4- 7- 2- 5- 8- 3- 6- 9 Strut Kit Strut No. 1 -11 -12 -12 -13 -14 -14 -13 -14 -14 Strut No. 2 -15 -17 -16 -18 -20 -19 -15 -17 -16 Strut No. 3 -15 -17 -16 -18 -20 -19 -15 -17 -16 Strut No. 4 -11 -12 -12 -13 -14 -14 -13 -14 -14 Figure Kit T o p K i t 2 3 4 5 1 31 41 51 61 71 8 015U1830-1 1 - - - 1 - - - - 1 015U1830-2 - - 1 - - - 1 - - - 015U1830-3 - - 1 - 1 - - - - 1 015U1830-4 - 1 - - - 1 - - - - 015U1830-5 - - - 1 - - - 1 - - ### Page 41 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT 015U1830-6 - - - 1 - 1 - - - - 015U1830-7 - 1 - - - 1 - - - - 015U1830-8 - - - 1 - - - - 1 - 015U1830-9 - - - 1 - 1 - - - - Figure Kit T o p K i t 1 92 02 12 22 33 03 13 23 33 4 0 1 5 U 1 8 3 0 - 1 -----1---- 015U1830-2 1 - - - - - - 1 - - 0 1 5 U 1 8 3 0 - 3 -----1---- 015U1830-4 - 1 - - - - 1 - - - 015U1830-5 - - 1 - - - - - 1 - 015U1830-6 - 1 - - - - 1 - - - 015U1830-7 - - - 1 - - 1 - - - 015U1830-8 - - - - 1 - - - - 1 015U1830-9 - - - 1 - - 1 - - - Figure Kit T o p K i t 3 53 63 73 83 94 04 24 34 44 5 015U1830-1 1 - - - - - 1 - - - 015U1830-2 - 1 - - - - - - 1 - 015U1830-3 1 - - - - - - - 1 - 015U1830-4 - - 1 - - - - 1 - - 015U1830-5 - - - 1 - - - - - 1 015U1830-6 - - 1 - - - - - - 1 015U1830-7 - - - - 1 - - 1 - - 015U1830-8 - - - - - 1 - - - 1 015U1830-9 - - - - 1 - - - - 1 Figure Kit T o p K i t 2 3 4 5 1 31 41 51 61 71 8 ### Page 42 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-1 - Group 1, Configuration 1: New Part Number Figure Name Existing Part Number Notes 2 1 31 83 03 54 2 Qty 302U0000-11 - - 1 - 1 - FILLER 302U0000-12 - - 1 - 1 - FILLER 3 0 2 U 0 0 0 0 - 1 6 1----1 D O U B L E R 302U0000-19 - - 2 - 2 - SPLICE PLATE 302U0000-2 - 1 - 1 - - DOUBLER 302U0000-20 - - 2 - 2 - FILLER 6 6 - 2 9 5 5 - 3 1 5 ---- 1 5 W A S H E R 66-2955-4 70 90 - 90 - 70 WASHER B A C B 3 0 M Y 1 0 K 1 1 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 2 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 3 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 3 X 8----8 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 3 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 9 X 1 8 ---- 1 8 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 9 Y 2----2 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 15 - 15 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4 - 18 - 18 - - BOLT BACB30NW6K4X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11X - 8 - 8 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW8K7X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 2 - 2 - - BOLT, 100 DEG HEX DR B A C B 3 0 N X 6 K 6 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 N X 6 K 9 X 1 6 ---- 1 6 B O L T , P R O T RUDING HD B A C B 3 0 N X 6 K 9 Y 2----2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 2 2 ---- 2 2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 2 2 2 ---- 2 2 B O L T , P R O T RUDING HD ### Page 43 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT B A C B 3 0 V T 1 0 K 1 3 5----5 B O L T , P R O T RUDING HD B A C B 3 0 V T 6 K 6 1 4 ---- 1 4 B O L T BACC30AG10 1 2 - 2 - 1 COLLAR ASSEMBLY BACC30AG8 4 4 - 4 - 4 COLLAR B A C C 3 0 B L 1 0 4 8 ---- 4 8 C O L L A R , S H E A R B A C C 3 0 B L 6 1 4 ---- 1 4 C O L L A R BACC30M10 5 50 - 50 - 5 COLLAR BACC30M6 18 18 - 18 - 18 COLLAR BACC30M8 22 22 - 22 - 22 COLLAR B A C C 3 0 R 6 2----2 C O L L A R B A C C 3 0 R 8 33-3-3 C O L L A R BACF3F006J007NN - - 2 - 2 - FILLER BACF3F010J032NN - - 2 - 2 - FILLER B A C F 3 T 0 2 J 0 8 C 1 5 2----2 F I L L E R , T A P E R E D BACF3T03L10-18 - 2 - 2 - - FILLER, TAPERED BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD2C - - 23 - 23 - RIVET, 100 DEG BACR15BA5AD3C - - 30 - 30 - RIVET, 100 DEG BACR15BA5AD5C - - 23 - 23 - RIVET, 100 DEG BACR15BA5AD7C - - 16 - 16 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG B A C R 1 5 B B 1 0 D 1 8 C 6----6 R I V E T , U N I V E R S A L H D Top Kit 015U1830-1 - Group 1, Configuration 1: New Part Number Figure Name Existing Part Number Notes 2 1 31 83 03 54 2 Qty ### Page 44 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-2 - Group 2, Configuration 1: New Part Number Figure Name Existing Part Number Notes 4 1 51 93 23 64 4 Qty 302U0000-1 - 1 - 1 - - DOUBLER 3 0 2 U 0 0 0 0 - 1 5 1----1 D O U B L E R 302U0000-17 - - 1 - 1 - FILLER 302U0000-18 - - 1 - 1 - FILLER 302U0000-21 - - 1 - 1 - FILLER 302U0000-22 - - 1 - 1 - FILLER 302U0000-23 - - 1 - 1 - SPLICE 302U0000-24 - - 1 - 1 - SPLICE PLATE 302U0000-25 - - 1 - 1 - GUSSET BRACKET 302U0000-26 - - 1 - 1 - GUSSET BRACKET 66-2955-40 - 20 - 20 - - WASHER 66-2955-41 - 90 - 90 - - WASHER B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 0 X 1 2 ---- 1 2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 0 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 4 X 4----4 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 4 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 6 X 4----4 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 6 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 30 - 30 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 4 - 4 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 6 - 6 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K14 - 14 - 14 - - BOLT, 100 DEG HEX DR BACB30NW10K14X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K16 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K16X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW6K4 - 22 - 22 - - BOLT ### Page 45 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT BACB30NW6K4X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW6K8X - 14 - 14 - - BOLT, 100 DEG HEX DR BACB30NW6K8Y - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW8K13X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K13Y - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW8K15X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K15Y - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW8K8X - 12 - 12 - - BOLT, 100 DEG HEX DR BACB30NW8K8Y - 2 - 2 - - BOLT, 100 DEG HEX DR B A C B 3 0 N X 6 K 9 X 8----8 B O L T , P R O T RUDING HD B A C B 3 0 N X 6 K 9 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD B A C B 3 0 V T 8 K 6 1 0 ---- 1 0 H I - L O K B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R B A C C 3 0 B L 8 1 0 ---- 1 0 C O L L A R BACC30M10 4 58 - 58 - 4 COLLAR BACC30M6 8 36 - 36 - 8 COLLAR BACC30M8 21 24 - 24 - 21 COLLAR B A C C 3 0 R 6 14-4-1 C O L L A R B A C C 3 0 R 8 35-5-3 C O L L A R BACF3T02E06-06 4 4 - 4 - 4 FILLER, TAPERED BACF3T02G06-06 4 4 - 4 - 4 FILLER, TAPERED BACF3T02H06-06 - 4 - 4 - - FILLER, TAPERED BACR15BA5AD2C - - 13 - 13 - RIVET, 100 DEG BACR15BA5AD3C - - 16 - 16 - RIVET, 100 DEG BACR15BA5AD5C - - 12 - 12 - RIVET, 100 DEG BACR15BA5AD6C - - 22 - 22 - RIVET, 100 DEG BACR15BA5AD7C - - 4 - 4 - RIVET, 100 DEG BACR15BA5D8C - - 2 - 2 - RIVET, 100 DEG BACR15BB5AD5C - - 5 - 5 - RIVET Top Kit 015U1830-2 - Group 2, Configuration 1: New Part Number Figure Name Existing Part Number Notes 4 1 51 93 23 64 4 Qty ### Page 46 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-3 - Group 3, Configuration 1: New Part Number Figure Name Existing Part Number Notes 4 1 31 83 03 54 4 Qty 302U0000-11 - - 1 - 1 - FILLER 302U0000-12 - - 1 - 1 - FILLER 3 0 2 U 0 0 0 0 - 1 5 1----1 D O U B L E R 302U0000-19 - - 2 - 2 - SPLICE PLATE 302U0000-2 - 1 - 1 - - DOUBLER 302U0000-20 - - 2 - 2 - FILLER 66-2955-4 - 90 - 90 - - WASHER B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 0 X 1 2 ---- 1 2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 0 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 4 X 4----4 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 4 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 6 X 4----4 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 1 6 Y 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 8 K 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 15 - 15 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4 - 18 - 18 - - BOLT BACB30NW6K4X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11X - 8 - 8 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW8K7X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 2 - 2 - - BOLT, 100 DEG HEX DR B A C B 3 0 N X 6 K 9 X 8----8 B O L T , P R O T RUDING HD B A C B 3 0 N X 6 K 9 Y 1----1 B O L T , P R O T RUDING HD ### Page 47 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD B A C B 3 0 V T 8 K 6 1 0 ---- 1 0 H I - L O K BACC30AG10 - 2 - 2 - - COLLAR ASSEMBLY BACC30AG8 - 4 - 4 - - COLLAR B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R B A C C 3 0 B L 8 1 0 ---- 1 0 C O L L A R BACC30M10 4 50 - 50 - 4 COLLAR BACC30M6 8 18 - 18 - 8 COLLAR BACC30M8 21 22 - 22 - 21 COLLAR B A C C 3 0 R 6 1----1 C O L L A R B A C C 3 0 R 8 33-3-3 C O L L A R BACF3F006J007NN - - 2 - 2 - FILLER BACF3F010J032NN - - 2 - 2 - FILLER B A C F 3 T 0 2 E 0 6 - 0 6 4----4 F I L L E R , T A P E R E D B A C F 3 T 0 2 G 0 6 - 0 6 4----4 F I L L E R , T A P E R E D BACF3T03L10-18 - 2 - 2 - - FILLER, TAPERED BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD2C - - 23 - 23 - RIVET, 100 DEG BACR15BA5AD3C - - 30 - 30 - RIVET, 100 DEG BACR15BA5AD5C - - 23 - 23 - RIVET, 100 DEG BACR15BA5AD7C - - 16 - 16 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG Top Kit 015U1830-3 - Group 3, Configuration 1: New Part Number Figure Name Existing Part Number Notes 4 1 31 83 03 54 4 Qty ### Page 48 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-4 - Group 1, Configuration 2: New Part Number Figure Name Existing Part Number Notes 3 1 42 03 13 74 3 Qty 66-2955-4 - 25 - 25 - - WASHER B A C B 3 0 M Y 1 0 K 1 1 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 2 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 3 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 19 - 19 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K7 - 2 - 2 - - BOLT PROT HD TENSION BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW6K4Y - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 18 - 18 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 1 2 2 ---- 2 2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 2 2 2 ---- 2 2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 3 4----4 B O L T , P R O T RUDING HD BACC30AG10 - 4 - 4 - - COLLAR ASSEMBLY B A C C 3 0 B L 1 0 4 8 ---- 4 8 C O L L A R , S H E A R BACC30M10 5 51 - 51 - 5 COLLAR BACC30M6 - 18 - 18 - - COLLAR B A C C 3 0 R 6 -2-2-- C O L L A R BACC30R8 - 22 - 22 - - COLLAR BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD5C - - 27 - 27 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG B A C R 1 5 B B 1 0 D 1 8 C 6----6 R I V E T , U N I V E R S A L H D ### Page 49 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-5 - Group 2, Configuration 2: New Part Number Figure Name Existing Part Number Notes 5 1 62 13 33 84 5 Qty B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 30 - 30 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 6 - 6 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K14 - 14 - 14 - - BOLT, 100 DEG HEX DR BACB30NW10K14X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K16 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K16X - 1 - 1 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R BACC30M10 4 54 - 54 - 4 COLLAR BACR15BA5AD5C - - 17 - 17 - RIVET, 100 DEG BACR15BA5D8C - - 2 - 2 - RIVET, 100 DEG ### Page 50 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-6 - Group 3, Configuration 2: New Part Number Figure Name Existing Part Number Notes 5 1 42 03 13 74 5 Qty 66-2955-4 - 25 - 25 - - WASHER B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 19 - 19 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K7 - 2 - 2 - - BOLT PROT HD TENSION BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW6K4Y - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 18 - 18 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD BACC30AG10 - 4 - 4 - - COLLAR ASSEMBLY B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R BACC30M10 4 51 - 51 - 4 COLLAR BACC30M6 - 18 - 18 - - COLLAR B A C C 3 0 R 6 -2-2-- C O L L A R BACC30R8 - 22 - 22 - - COLLAR BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD5C - - 27 - 27 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG ### Page 51 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-7 - Group 1, Configuration 3: New Part Number Figure Name Existing Part Number Notes 3 1 42 23 13 94 3 Qty 66-2955-4 - 25 - 25 - - WASHER B A C B 3 0 M Y 1 0 K 1 1 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 2 X 2----2 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 3 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 19 - 19 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K7 - 2 - 2 - - BOLT PROT HD TENSION BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW6K4Y - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 18 - 18 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 1 2 2 ---- 2 2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 2 2 2 ---- 2 2 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 3 4----4 B O L T , P R O T RUDING HD BACC30AG10 - 4 - 4 - - COLLAR ASSEMBLY B A C C 3 0 B L 1 0 4 8 ---- 4 8 C O L L A R , S H E A R BACC30M10 5 51 - 51 - 5 COLLAR BACC30M6 - 18 - 18 - - COLLAR B A C C 3 0 R 6 -2-2-- C O L L A R BACC30R8 - 22 - 22 - - COLLAR BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD5C - - 19 - 19 - RIVET, 100 DEG BACR15BA5AD7C - - 8 - 8 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG B A C R 1 5 B B 1 0 D 1 8 C 6----6 R I V E T , U N I V E R S A L H D ### Page 52 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-8 - Group 2, Configuration 3: New Part Number Figure Name Existing Part Number Notes 5 1 72 33 44 04 5 Qty B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 30 - 30 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 6 - 6 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K14 - 14 - 14 - - BOLT, 100 DEG HEX DR BACB30NW10K14X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K16 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K16X - 1 - 1 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R BACC30M10 4 54 - 54 - 4 COLLAR BACR15BA5AD5C - - 8 - 8 - RIVET, 100 DEG BACR15BA5AD6C - - 10 - 10 - RIVET, 100 DEG BACR15BA5AD7C - - 4 - 4 - RIVET, 100 DEG BACR15BA5D8C - - 2 - 2 - RIVET, 100 DEG ### Page 53 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Top Kit 015U1830-9 - Group 3, Configuration 3: New Part Number Figure Name Existing Part Number Notes 5 1 42 23 13 94 5 Qty 66-2955-4 - 25 - 25 - - WASHER B A C B 3 0 M Y 1 0 K 1 0 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 1 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 4 X 1----1 B O L T , P R O T RUDING HD B A C B 3 0 M Y 1 0 K 1 6 X 1----1 B O L T , P R O T RUDING HD BACB30NW10K10 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K10X - 1 - 1 - - BOLT, 100 DEG HEX DR BACB30NW10K11 - 19 - 19 - - BOLT 100 DEG SHEAR BACB30NW10K11X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K12 - 4 - 4 - - BOLT, 100 DEG HEX D BACB30NW10K12X - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW10K7 - 2 - 2 - - BOLT PROT HD TENSION BACB30NW10K9 - 26 - 26 - - BOLT, 100 DEG HEX D BACB30NW10K9X - 3 - 3 - - BOLT, 100 DEG HEX DR BACB30NW6K4X - 18 - 18 - - BOLT, 100 DEG HEX DR BACB30NW6K4Y - 2 - 2 - - BOLT, 100 DEG HEX DR BACB30NW8K11Y - 4 - 4 - - BOLT, 100 DEG HEX DR BACB30NW8K7Y - 18 - 18 - - BOLT, 100 DEG HEX DR B A C B 3 0 V T 1 0 K 1 0 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 1 6----6 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 4 1 0 ---- 1 0 B O L T , P R O T RUDING HD B A C B 3 0 V T 1 0 K 1 6 4----4 B O L T , P R O T RUDING HD BACC30AG10 - 4 - 4 - - COLLAR ASSEMBLY B A C C 3 0 B L 1 0 2 6 ---- 2 6 C O L L A R , S H E A R BACC30M10 4 51 - 51 - 4 COLLAR BACC30M6 - 18 - 18 - - COLLAR B A C C 3 0 R 6 -2-2-- C O L L A R BACC30R8 - 22 - 22 - - COLLAR BACR15BA10D15C - 2 - 2 - - RIVET, 100 DEG BACR15BA10D18C - 4 - 4 - - RIVET, 100 DEG BACR15BA5AD5C - - 19 - 19 - RIVET, 100 DEG BACR15BA5AD7C - - 8 - 8 - RIVET, 100 DEG BACR15BA5D8C - - 1 - 1 - RIVET, 100 DEG ### Page 54 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Strut Kit 015U1830-11 - Group 1, Configuration 1: New Part Number -11 Name Existing Part Number NotesQty 302U0000-16 1 DOUBLER 66-2955-3 15 WASHER 66-2955-4 70 WASHER BACB30MY10K11X 2 BOLT, PROTRUDING HD BACB30MY10K12X 2 BOLT, PROTRUDING HD BACB30MY10K13X 1 BOLT, PROTRUDING HD BACB30MY8K13X 8 BOLT, PROTRUDING HD BACB30MY8K13Y 1 BOLT, PROTRUDING HD BACB30MY8K9X 18 BOLT, PROTRUDING HD BACB30MY8K9Y 2 BOLT, PROTRUDING HD BACB30NX6K6X 2 BOLT, PROTRUDING HD BACB30NX6K9X 16 BOLT, PROTRUDING HD BACB30NX6K9Y 2 BOLT, PROTRUDING HD BACB30VT10K11 22 BOLT, PROTRUDING HD BACB30VT10K12 22 BOLT, PROTRUDING HD BACB30VT10K13 5 BOLT, PROTRUDING HD BACB30VT6K6 14 BOLT BACC30AG10 1 COLLAR ASSEMBLY BACC30AG8 4 COLLAR BACC30BL10 48 COLLAR, SHEAR BACC30BL6 14 COLLAR BACC30M10 5 COLLAR BACC30M6 18 COLLAR BACC30M8 22 COLLAR BACC30R6 2 COLLAR BACC30R8 3 COLLAR BACF3T02J08C15 2 FILLER, TAPERED BACR15BB10D18C 6 RIVET, UNIVERSAL HD ### Page 55 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Strut Kit 015U1830-12 - Group 1, Configuration 2; Group 1, Configuration 3: New Part Number -12 Name Existing Part Number NotesQty BACB30MY10K11X 2 BOLT, PROTRUDING HD BACB30MY10K12X 2 BOLT, PROTRUDING HD BACB30MY10K13X 1 BOLT, PROTRUDING HD BACB30VT10K11 22 BOLT, PROTRUDING HD BACB30VT10K12 22 BOLT, PROTRUDING HD BACB30VT10K13 4 BOLT, PROTRUDING HD BACC30BL10 48 COLLAR, SHEAR BACC30M10 5 COLLAR BACR15BB10D18C 6 RIVET, UNIVERSAL HD Strut Kit 015U1830-13 - Group 2, Configuration 1; Group 3, Configuration 1: New Part Number -13 Name Existing Part Number NotesQty 302U0000-15 1 DOUBLER BACB30MY10K10X 1 BOLT, PROTRUDING HD BACB30MY10K11X 1 BOLT, PROTRUDING HD BACB30MY10K14X 1 BOLT, PROTRUDING HD BACB30MY10K16X 1 BOLT, PROTRUDING HD BACB30MY8K10X 12 BOLT, PROTRUDING HD BACB30MY8K10Y 1 BOLT, PROTRUDING HD BACB30MY8K14X 4 BOLT, PROTRUDING HD BACB30MY8K14Y 1 BOLT, PROTRUDING HD BACB30MY8K16X 4 BOLT, PROTRUDING HD BACB30MY8K16Y 1 BOLT, PROTRUDING HD BACB30MY8K6X 1 BOLT, PROTRUDING HD BACB30NX6K9X 8 BOLT, PROTRUDING HD BACB30NX6K9Y 1 BOLT, PROTRUDING HD BACB30VT10K10 6 BOLT, PROTRUDING HD BACB30VT10K11 6 BOLT, PROTRUDING HD BACB30VT10K14 10 BOLT, PROTRUDING HD BACB30VT10K16 4 BOLT, PROTRUDING HD BACB30VT8K6 10 HI-LOK BACC30BL10 26 COLLAR, SHEAR BACC30BL8 10 COLLAR BACC30M10 4 COLLAR ### Page 56 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT BACC30M6 8 COLLAR BACC30M8 21 COLLAR BACC30R6 1 COLLAR BACC30R8 3 COLLAR BACF3T02E06-06 4 FILLER, TAPERED BACF3T02G06-06 4 FILLER, TAPERED Strut Kit 015U1830-14 - Group 2, Configuration 2; Group 2, Configuration 3; Group 3, Configuration 2; Group 3, Configuration 3: New Part Number -14 Name Existing Part Number NotesQty BACB30MY10K10X 1 BOLT, PROTRUDING HD BACB30MY10K11X 1 BOLT, PROTRUDING HD BACB30MY10K14X 1 BOLT, PROTRUDING HD BACB30MY10K16X 1 BOLT, PROTRUDING HD BACB30VT10K10 6 BOLT, PROTRUDING HD BACB30VT10K11 6 BOLT, PROTRUDING HD BACB30VT10K14 10 BOLT, PROTRUDING HD BACB30VT10K16 4 BOLT, PROTRUDING HD BACC30BL10 26 COLLAR, SHEAR BACC30M10 4 COLLAR Strut Kit 015U1830-15 - Group 1, Configuration 1; Group 3, Configuration 1: New Part Number -15 Name Existing Part Number NotesQty 302U0000-11 1 FILLER 302U0000-12 1 FILLER 302U0000-19 2 SPLICE PLATE 302U0000-2 1 DOUBLER 302U0000-20 2 FILLER 66-2955-4 90 WASHER BACB30NW10K10 4 BOLT, 100 DEG HEX D BACB30NW10K10X 1 BOLT, 100 DEG HEX DR BACB30NW10K11 15 BOLT 100 DEG SHEAR BACB30NW10K11X 2 BOLT, 100 DEG HEX DR BACB30NW10K12 4 BOLT, 100 DEG HEX D BACB30NW10K12X 2 BOLT, 100 DEG HEX DR Strut Kit 015U1830-13 - Group 2, Configuration 1; Group 3, Configuration 1: New Part Number -13 Name Existing Part Number NotesQty ### Page 57 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT BACB30NW10K9 26 BOLT, 100 DEG HEX D BACB30NW10K9X 3 BOLT, 100 DEG HEX DR BACB30NW6K4 18 BOLT BACB30NW6K4X 2 BOLT, 100 DEG HEX DR BACB30NW8K11X 8 BOLT, 100 DEG HEX DR BACB30NW8K11Y 1 BOLT, 100 DEG HEX DR BACB30NW8K7X 18 BOLT, 100 DEG HEX DR BACB30NW8K7Y 2 BOLT, 100 DEG HEX DR BACC30AG10 2 COLLAR ASSEMBLY BACC30AG8 4 COLLAR BACC30M10 50 COLLAR BACC30M6 18 COLLAR BACC30M8 22 COLLAR BACC30R8 3 COLLAR BACF3F006J007NN 2 FILLER BACF3F010J032NN 2 FILLER BACF3T03L10-18 2 FILLER, TAPERED BACR15BA10D15C 2 RIVET, 100 DEG BACR15BA10D18C 4 RIVET, 100 DEG BACR15BA5AD2C 23 RIVET, 100 DEG BACR15BA5AD3C 30 RIVET, 100 DEG BACR15BA5AD5C 23 RIVET, 100 DEG BACR15BA5AD7C 16 RIVET, 100 DEG BACR15BA5D8C 1 RIVET, 100 DEG Strut Kit 015U1830-15 - Group 1, Configuration 1; Group 3, Configuration 1: New Part Number -15 Name Existing Part Number NotesQty ### Page 58 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Strut Kit 015U1830-16 - Group 1, Configuration 3; Group 3, Configuration 3: New Part Number -16 Name Existing Part Number NotesQty 66-2955-4 25 WASHER BACB30NW10K10 4 BOLT, 100 DEG HEX D BACB30NW10K10X 1 BOLT, 100 DEG HEX DR BACB30NW10K11 19 BOLT 100 DEG SHEAR BACB30NW10K11X 2 BOLT, 100 DEG HEX DR BACB30NW10K12 4 BOLT, 100 DEG HEX D BACB30NW10K12X 2 BOLT, 100 DEG HEX DR BACB30NW10K7 2 BOLT PROT HD TENSION BACB30NW10K9 26 BOLT, 100 DEG HEX D BACB30NW10K9X 3 BOLT, 100 DEG HEX DR BACB30NW6K4X 18 BOLT, 100 DEG HEX DR BACB30NW6K4Y 2 BOLT, 100 DEG HEX DR BACB30NW8K11Y 4 BOLT, 100 DEG HEX DR BACB30NW8K7Y 18 BOLT, 100 DEG HEX DR BACC30AG10 4 COLLAR ASSEMBLY BACC30M10 51 COLLAR BACC30M6 18 COLLAR BACC30R6 2 COLLAR BACC30R8 22 COLLAR BACR15BA10D15C 2 RIVET, 100 DEG BACR15BA10D18C 4 RIVET, 100 DEG BACR15BA5AD5C 19 RIVET, 100 DEG BACR15BA5AD7C 8 RIVET, 100 DEG BACR15BA5D8C 1 RIVET, 100 DEG ### Page 59 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Strut Kit 015U1830-17 - Group 1, Configuration 2; Group 3, Configuration 2: New Part Number -17 Name Existing Part Number NotesQty 66-2955-4 25 WASHER BACB30NW10K10 4 BOLT, 100 DEG HEX D BACB30NW10K10X 1 BOLT, 100 DEG HEX DR BACB30NW10K11 19 BOLT 100 DEG SHEAR BACB30NW10K11X 2 BOLT, 100 DEG HEX DR BACB30NW10K12 4 BOLT, 100 DEG HEX D BACB30NW10K12X 2 BOLT, 100 DEG HEX DR BACB30NW10K7 2 BOLT PROT HD TENSION BACB30NW10K9 26 BOLT, 100 DEG HEX D BACB30NW10K9X 3 BOLT, 100 DEG HEX DR BACB30NW6K4X 18 BOLT, 100 DEG HEX DR BACB30NW6K4Y 2 BOLT, 100 DEG HEX DR BACB30NW8K11Y 4 BOLT, 100 DEG HEX DR BACB30NW8K7Y 18 BOLT, 100 DEG HEX DR BACC30AG10 4 COLLAR ASSEMBLY BACC30M10 51 COLLAR BACC30M6 18 COLLAR BACC30R6 2 COLLAR BACC30R8 22 COLLAR BACR15BA10D15C 2 RIVET, 100 DEG BACR15BA10D18C 4 RIVET, 100 DEG BACR15BA5AD5C 27 RIVET, 100 DEG BACR15BA5D8C 1 RIVET, 100 DEG ### Page 60 October 30, 2008 747-54A2230 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 300 BOEING SERVICE BULLETIN 747-54A2230 ALERT ALERT Strut Kit 015U1830-18 - Group 2, Configuration 1: New Part Number -18 Name Existing Part Number NotesQty 302U0000-1 1 DOUBLER 302U0000-17 1 FILLER 302U0000-18 1 FILLER 302U0000-21 1 FILLER 302U0000-22 1 FILLER 302U0000-23 1 SPLICE 302U0000-24 1 SPLICE PLATE 302U0000-25 1 GUSSET BRACKET 302U0000-26 1 GUSSET BRACKET 66-2955-40 20 WASHER 66-2955-41 90 WASHER BACB30NW10K10 30 BOLT, 100 DEG HEX D BACB30NW10K10X 4 BOLT, 100 DEG HEX DR BACB30NW10K11 4 BOLT 100 DEG SHEAR BACB30NW10K11X 1 BOLT, 100 DEG HEX DR BACB30NW10K12 6 BOLT, 100 DEG HEX D BACB30NW10K12X 1 BOLT, 100 DEG HEX DR BACB30NW10K14 14 BOLT, 100 DEG HEX DR BACB30NW10K14X 2 BOLT, 100 DEG HEX DR BACB30NW10K16 4 BOLT, 100 DEG HEX D BACB30NW10K16X 1 BOLT, 100 DEG HEX DR BACB30NW6K4 22 BOLT BACB30NW6K4X 2 BOLT, 100 DEG HEX DR BACB30NW6K8X 14 BOLT, 100 DEG HEX DR BACB30NW6K8Y 2 BOLT, 100 DEG HEX DR BACB30NW8K11X 4 BOLT, 100 DEG HEX DR BACB30NW8K11Y 1 BOLT, 100 DEG HEX DR BACB30NW8K13X 4 BOLT, 100 DEG HEX DR BACB30NW8K13Y 1 BOLT, 100 DEG HEX DR BACB30NW8K15X 4 BOLT, 100 DEG HEX DR BACB30NW8K15Y 1 BOLT, 100 DEG HEX DR BACB30NW8K8X 12 BOLT, 100 DEG HEX DR BACB30NW8K8Y 2 BOLT, 100 DEG HEX DR BACC30M10 58 COLLAR BACC30M6 36 COLLAR The text continues at https://openairdocs.org/service-documents/boeing/747-54a2230/file/5ebac956f66d.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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