# Boeing Alert Service Bulletin 747-57A2331: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0492; AD 2012-20-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-57A2331](https://openairdocs.org/service-documents/boeing/747-57a2331.md) - Title as filed: Service Bulletin - Pages: 186 - PDF: https://openairdocs.org/files/sha256/7c/e9/7ce989c4358096ab72a127082eff70acf2943fee5dc3bdca622a8b578cdb90bf - Page: https://openairdocs.org/service-documents/boeing/747-57a2331/file/7ce989c43580 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-57A2331 Original Issue: November 12, 2009 ATA System: 5715 SUBJECT: WINGS - Center Wing - Wing Landing Gear Support Beam End Fittings - Inspection, Repair and Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2009 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 1 of 186 7.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 2 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary ...................................................... 5 1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1 1. Airplanes ............................................ 1 1 2. Spares Affected ........................................ 2 2 B. Concurrent Requirements ...................................... 2 2 C. Reason ................................................ 2 2 D. Description .............................................. 2 4 E. Compliance .............................................. 2 7 F. Approval ............................................... 3 9 G. Manpower .............................................. 4 0 H. Weight and Balance Changes .................................... 4 6 I. Electrical Load Data ......................................... 4 6 J. References .............................................. 4 6 1. Existing Data .......................................... 4 6 2. Data supplied with this Service Bulletin ............................ 4 7 3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 4 7 K. Publications Affected ........................................ 4 7 L. Interchangeability and Intermixability of Parts ........................... 4 7 2. MATERIAL INFORMATION ........................................ 4 9 A. Material - Price and Availability ................................... 4 9 B. Industry Support Information .................................... 5 0 C. Parts Necessary For Each Airplane ................................. 5 0 1. Kits/Parts ............................................ 5 0 2. Parts and Materials Supplied by the Operator ........................ 5 2 3. Parts Modified and Reidentified ................................ 5 5 4. Parts Removed and Not Replaced .............................. 5 8 D. Parts Necessary to Change Spares ................................. 5 8 E. Special Tooling - Price and Availability ............................... 5 9 F. Special Tooling Necessary to do this Service Bulletin ....................... 5 9 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 1 A. GENERAL INFORMATION ..................................... 6 1 B. WORK INSTRUCTIONS ....................................... 6 2 FIGURE 1: LEFT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND ULTRASONIC INSPECTION [Group 1, 3-5] .................................. 8 0 FIGURE 2: LEFT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND ULTRASONIC INSPECTION [Group 2] .................................... 8 2 FIGURE 3: LEFT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED INSPECTION .................................................. 8 4 FIGURE 4: RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND ULTRASONIC INSPECTION [Group 1, 3-5] .................................. 8 7 FIGURE 5: RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND ULTRASONIC INSPECTION [Group 2] .................................... 8 9 FIGURE 6: RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED INSPECTION .................................................. 9 1 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 3 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 4 FIGURE 7: LEFT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND HIGH FREQUENCY EDDY CURRENT INSPECTION ....................... 9 4 FIGURE 8: RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING - DETAILED AND HIGH FREQUENCY EDDY CURRENT INSPECTION ....................... 9 7 FIGURE 9: LEFT WING LANDING GEAR SUPPORT BEAM END FITTING - CORROSION INHIBITING COMPOUND APPLICATION ................................. 1 0 0 FIGURE 10: RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING - CORROSION INHIBITING COMPOUND APPLICATION ................................. 1 0 2 FIGURE 11: WING LANDING GEAR SUPPORT BEAM END FITTING - BUSHING REMOVAL AND INSPECTION [Group 1] .................................... 1 0 4 FIGURE 12: WING LANDING GEAR SUPPORT BEAM END FITTING - BUSHING REMOVAL AND INSPECTION [Group 2] .................................... 1 0 7 FIGURE 13: WING LANDING GEAR SUPPORT BEAM END FITTING - BUSHING REMOVAL AND INSPECTION [Group 3-5] .................................. 1 1 0 FIGURE 14: WING LANDING GEAR SUPPORT BEAM END FITTING - BUSHING REMOVAL AND INSPECTION [Group 6] .................................... 1 1 3 FIGURE 15: WING LANDING GEAR SUPPORT BEAM END FITTING - CRACK/CORROSION REMOVAL, LUG BORE OVERSIZE AND FINISHES APPLICATION [Group 1] ............ 1 1 6 FIGURE 16: WING LANDING GEAR SUPPORT BEAM END FITTING - CRACK/CORROSION REMOVAL, LUG BORE OVERSIZE AND FINISHES APPLICATION [Group 3-5] ........... 1 2 2 FIGURE 17: WING LANDING GEAR SUPPORT BEAM END FITTING - CRACK/CORROSION REMOVAL, LUG BORE OVERSIZE AND FINISHES APPLICATION [Group 2] ............ 1 2 9 FIGURE 18: WING LANDING GEAR SUPPORT BEAM END FITTING - CRACK/CORROSION REMOVAL, LUG BORE OVERSIZE AND FINISH APPLICATION [Group 6] .............. 1 3 5 FIGURE 19: NEW HIGHER INTERFERENCE FIT WING LANDING GEAR SUPPORT BEAM END FITTING LUG BORE BUSHINGS - MAKE ............................... 1 4 1 FIGURE 20: NEW HIGHER INTERFERENCE FIT WING LANDING GEAR SUPPORT BEAM END FITTING BOLT HOLE BUSHINGS - MAKE .............................. 1 4 5 FIGURE 21: WING LANDING GEAR SUPPORT BEAM END FITTING NEW HIGHER INTERFERENCE FIT LUG BORE AND BOLT HOLE BUSHINGS - INSTALLATION [Group 1] ......... 1 5 6 FIGURE 22: WING LANDING GEAR SUPPORT BEAM END FITTING NEW HIGHER INTERFERENCE FIT LUG BORE AND BOLT HOLE BUSHINGS - INSTALLATION [Group 2] ......... 1 6 0 FIGURE 23: WING LANDING GEAR SUPPORT BEAM END FITTING NEW HIGHER INTERFERENCE FIT LUG BORE AND BOLT HOLE BUSHINGS - INSTALLATION [Group 3-5] ........ 1 6 4 FIGURE 24: WING LANDING GEAR SUPPORT BEAM END FITTING NEW HIGHER INTERFERENCE FIT LUG BORE AND BOLT HOLE BUSHINGS - INSTALLATION [Group 6] ......... 1 6 8 FIGURE 25: LEFT WING LANDING GEAR SUPPORT BEAM BUSHINGS - REPLACEMENT [Group 1] . 172 FIGURE 26: LEFT WING LANDING GEAR SUPPORT BEAM BUSHINGS - REPLACEMENT [Group 2-6] ................................................. 1 7 4 FIGURE 27: RIGHT WING LANDING GEAR SUPPORT BEAM BUSHINGS - REPLACEMENT [Group 1] ................................................. 1 7 6 FIGURE 28: RIGHT WING LANDING GEAR SUPPORT BEAM BUSHINGS - REPLACEMENT [Group 2-6] ................................................. 1 7 8 APPENDIX A: COMPLIANCE TABLES USAGE INDEX .......................... 1 8 0 APPENDIX B: INSPECTION AND REPAIR OR CHANGE OF END FITTINGS - GENERAL SCOPE OF WORK DIAGRAM ........................................... 1 8 2 APPENDIX C: WING LANDING GEAR SUPPORT BEAM END FITTING - ALTERNATIVE CRACK/CORROSION REMOVAL, LUG BORE OVERSIZE AND FINISHES APPLICATION ........... 1 8 4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 4 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 5 Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-57A2331Original Issue: November 12, 2009 ATA System: 5715 SUBJECT: WINGS - Center Wing - Wing Landing Gear Support Beam End Fittings - Inspection, Repair and Change 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 repair or change work given in this service bulletin will give increased corrosion protection to the end fittings of the Wing Landing Gear (WLG) support beams, which will subsequently give them better crack resistance. Undetected corrosion can result in the occurrence of cracks in the end fittings. Undetected cracks in the end fittings could result in their separation from the gate fittings and subsequently cause damage to flight control cables and hydraulic systems that are located in the adjacent areas. Continued safe flight and landing could be affected if the separation of an end fitting from a gate fitting occurs. Three 747-400 operators have told Boeing of corrosion damage to the end fittings of the WLG support beams, where one operator also found cracks in the end fittings in addition to the corrosion. This same condition was told to Boeing earlier, which was related to 747-100/200/300 and 747-SP airplanes and addressed by Boeing service bulletin 747-57-2244, which was the subject of Federal Aviation Administration (FAA) Airworthiness Directive 89-15-07. The end fittings are installed on the outboard ends of the WLG support beams and they attach to gate fittings installed on the rear wing spars. There are two types of end fitting used on the 747 fleet. One type is a two-piece end fitting, which is installed on the end of the WLG support beams in a 'back-to-back' configuration, the other type is a one-piece end fitting. Boeing service bulletin 747-57-2244 was applicable to all 747 Classic airplanes from Line Number 1 thru 695 and gave inspection instructions, repair work and terminating action for the end fittings. The terminating action replaced each of the end fitting lug bore and bolt hole bushings with new standard or oversize bushings. The new bushings and the end fittings were installed with sealant to give better corrosion prevention. That terminating action was incorporated into the design of replacement end fittings, which were used on production airplanes from Line Number 696 and subsequent. While the terminating action worked well, the most recent reports to Boeing were from operators of 747 airplanes after Line Number 695, which showed that the problem had occurred again. As a result of the more recent reports, Boeing has further investigated the cracks and corrosion of the end fittings. The investigation found that the cracks occur at the corroded areas on the end fittings. The corrosion is found to start at the lug bore and bushing interface, because moisture continues to get into this area, from exposure of the end fittings to environmental conditions. Metallurgy analysis showed that cracks were a result of fatigue and their growth direction identified that they had started in the lug bore surface. The end fitting that was analysed, had a 0.806 inch length crack but also BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 5 of 186 ### Page 6 was found to have a secondary crack approximately 0.7 inches away from the reported crack, that was only identified by magnetic particle inspection. Boeing has found that the terminating action given in Boeing service bulletin 747-57-2244 cannot continue to be classed as 'terminating' because the occurrence of cracks and corrosion has come back. Subsequently, Boeing has changed the retrofit solution from what was given in Boeing service bulletin 747-57-2244, to install higher interference fit bushings in the lug bore(s) and bolt holes of the end fittings. The changed retrofit solution also makes follow-on repeat inspections of the end fittings necessary after the new bushings are installed. The follow-on repeat inspection intervals are up to two times longer than the shorter inspection interval that was given in Boeing service bulletin 747-57-2244. The changed retrofit solution will give increased corrosion protection and better crack prevention to the end fittings. Boeing has issued this service bulletin to incorporate the changed retrofit solution and to replace Boeing service bulletin 747-57-2244. As Boeing has had reports of cracked or corroded end fittings from operators of airplanes from Line Number 696 and subsequent, which have had the terminating action of Boeing service bulletin 747-57-2244 incorporated into their design, this service bulletin relates to all 747 airplanes from Line Number 1 thru 1419. This includes the airplanes that were applicable to Boeing service bulletin 747-57-2244 and those that were beyond its effectivity range. This service bulletin gives instructions to inspect the end fittings of the left and right WLG support beams for cracks and corrosion. If no crack is found and no corrosion is found, the end fittings can continue to be repetitively inspected, or they can be changed to have higher interference fit bushings installed in their lug bore and bolt holes. If any crack or corrosion is found in an end fitting, each one is repaired to remove the cracks and corrosion and to have higher interference fit bushings installed in its lug bore(s) and bolt holes. The new higher interference fit bushings in the end fittings give increased corrosion protection and better crack prevention. After the repair or change work is done to the end fitting(s), post repair or change follow-on inspections will be necessary, but at a different interval. Boeing Service Related Problem (SRP) 747-SRP-57-0217 is related to this service bulletin. Boeing Service Letter (SL) 747-SL-57-050-A is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 57-08001 is related to this service bulletin. ACTION Part 7 can be done as an option to Parts 1 thru 6. After Part 7 is accomplished, Part 1, Part 2 and Part 3 are terminated but Part 4, Part 5 and Part 6 continue to be necessary. Part 1 - Wing Landing Gear (WLG) Support Beam End Fittings Inspection Group 1-5: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a detailed (DET) inspection and an ultrasonic (UT) inspection of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, one of two options can be done. One option is to repeat Part 1 to do DET and UT inspections of the end fittings at the same interval. The other option is to do Part 2 to do repeat DET and High Frequency Eddy Current (HFEC) inspections of the end fittings at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 6 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 7 Group 6: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a detailed (DET) inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, do Part 2 to do repeat DET and High Frequency Eddy Current (HFEC) inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 3 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 2 - Wing Landing Gear (WLG) Support Beam End Fittings Repeat Detailed and High Frequency Eddy Current Inspection (Fillet Seal Remaining) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, repeat Part 2 to do DET and HFEC inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 3 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 3 - Wing Landing Gear (WLG) Support Beam End Fittings Repeat Detailed and High Frequency Eddy Current Inspection (Fillet Seal Removed) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do DET and HFEC inspections of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound again on each end fitting and repeat Part 3 to do DET and HFEC inspections of the end fittings at the same interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 4 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Follow-On Inspection Group 1-5: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET and UT inspection of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, one of two options can be done. One option is to repeat Part 4 to do DET and UT inspections of the end fittings at the same interval. The other option is to do Part 5 to do repeat DET and HFEC inspections of the end fittings at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 7 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 8 Group 6: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, do Part 5 to do repeat DET and HFEC inspections at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 6 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 5 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Repeat Detailed and High Frequency Eddy Current Follow-On Inspection (Fillet Seal Remaining) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, repeat Part 5 to do DET and HFEC inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 6 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 6 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Repeat Detailed and High Frequency Eddy Current Follow-On Inspection (Fillet Seal Removed) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do DET and HFEC inspections of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound again on each end fitting and repeat Part 6 to do DET and HFEC inspections of the end fittings at the same interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 7 - Wing Landing Gear (WLG) Support Beam End Fitting - Higher Interference Fit Bushings Installation Remove the end fitting(s) from the left and/or right WLG support beam, or get serviceable end fittings or new end fittings. Remove the lug bore bushings, bolt hole bushings and protective finishes from each end fitting. For removed end fittings and serviceable end fittings only, do DET and Magnetic Particle Inspections (MPI) of the lug bore, Fluorescent Penetrant Inspections (FPI) or MPI of the bolt holes and flat surfaces of each end fitting for cracks or corrosion. If no crack is found and no corrosion is found, insurance cut the lug bore(s) of each end fitting. If any crack or corrosion is found, oversize the lug bore(s) and bolt holes of each end fitting by the minimum necessary up to the maximum repair diameter, remove material from the flat surfaces up to the limit of material removal, to remove cracks and corrosion, and do repeat inspections until no crack is found and no corrosion is found. As an insurance cut, do an additional oversize of the lug bore(s) and, as applicable, do an additional oversize of the machined bolt holes and remove additional material from the machined flat surfaces. For all end fittings, do post machine work treatments and inspections, apply plating, finishes and make new higher interference fit lug bore and bolt hole bushings. Additionally, more post machine treatment work is necessary on 65B14472-23/-24 end fittings to shot peen all surfaces. If necessary, make new WLG support beam bushings. Wet install the new lug bore and bolt holes bushings in each end fitting and fillet seal their edges. If new WLG support beam bushing were made, replace the WLG support beam bushings. Install the repaired or changed end fitting(s) back on the left and/or right WLG support beam. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 8 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 9 EFFECTIVITY 747-100/100B/100B SUD/200B/200C/200F/300/400/400D/400F, 747SP, 747SR Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing and Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 9 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 10 (OCR) BOEING SERVICE BULLETIN 747-57A2331 ALERT ALERT PART 1 GROUP 1 THRU 5: DO A DETAILED (DET) INSPECTION AND ULTRASONIC (UT) INSPECTION OF EACH END FITTING FOR CRACKS AND CORROSION. GROUP 6: DO A DETAILED INSPECTION (DET) AND HIGH FREQUENCY EDDY CURENT (HFEC) INSPECTION OF EACH END FITTING FOR CRACKS AND CORROSION. PART 2 DO REPEAT DET AND HFEC INSPECTIONS OF EACH END FITTING (FILLET SEAL REMAINING), FOR CRACKS AND CORROSION. PART 3 LEFT WING LANDING GEAR (WLG) (RIGHT WLG OPPOSITE) DO REPEAT DET AND HFEC INSPECTIONS OF EACH END FITTING (FILLET SEAL REMOVED), FOR CRACKS AND CORROSION. WING REAR SPAR PART 4 GROUP 1 THRU 5; AFTER AN END FITTING IS REPAIRED OR CHANGED, DO FOLLOW-ON DET AND UT INSPECTIONS FOR CRACKS AND CORROSION. GROUP 6; AFTER AN END FITTING IS REPAIRED OR CHANGED, DO FOLLOW-ON DET AND HFEC INSPECTIONS FOR CRACKS AND CORROSION. PART 5 DO POST REPAIR OR CHANGE REPEAT DET AND HFEC FOLLOW-ON INSPECTIONS OF EACH END FITTING (FILLET SEAL REMAINING) FOR CRACKS AND CORROSION. PART 6 DO POST REPAIR OR CHANGE REPEAT DET AND HFEC FOLLOW-ON INSPECTIONS OF EACH END FITTING (FILLET SEAL REMOVED) FOR CRACKS AND CORROSION. PART 7 REMOVE END FITTING(S), OR GET SERVICEABLE END FITTINGS OR NEW END FITTINGS. REPAIR OF CHANGE EACH END FITTING TO INSTALL HIGHER INTERFERENCE FIT BUSHINGS. LEFT WLG GATE FITTING (RIGHT WLG GATE FITTING OPPOSITE) 1702508 Original Issue: November 12, 2009 747-57A2331 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 186 ### Page 11 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-57A2331 Original Issue: November 12, 2009 ATA System: 5715 SUBJECT: WINGS - Center Wing - Wing Landing Gear Support Beam End Fittings - Inspection, Repair and Change 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. DESCRIPTIONCONFIGURATIONGROUP 747-100 airplanes, from Line Number 1 to 133, delivered with Wing Landing Gear (WLG) support beam end fittings part number 65B01042-1/-2, or -9/-10 installed -1 That have not done the terminating action for the WLG support beam end fittings in accordance with Boeing service bulletin 747-57-2244 1 That have done the terminating action for the WLG support end fittings in accordance with Boeing service bulletin 747-57-2244 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 11 of 186 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP 747SP airplanes, from Line Number 265 to 676, delivered with Wing Landing Gear (WLG) support beam end fittings part number 65B14472-8 installed -2 That have not done the terminating action for the WLG support beam end fittings in accordance with Boeing service bulletin 747-57-2244 1 That have done the terminating action for the WLG support beam end fittings in accordance with Boeing service bulletin 747-57-2244 2 747-100/100B/100B SUD/200B/200C/200F/300 and 747SR airplanes, from Line Number 88 to 695, delivered with Wing Landing Gear (WLG) support beam end fittings part number 65B14472-1/-2 installed -3 That have not done the terminating action for the WLG support beam end fittings in accordance with Boeing service bulletin 747-57-2244 1 That have done the terminating action for the WLG support beam end fittings in accordance with Boeing service bulletin 747-57-2244 2 747-200B/200C/200F/300 airplanes, from Line Number 697 to 886, delivered with Wing Landing Gear (WLG) support beam end fittings part number 65B14472-25/-26 installed, which have the intent of the terminating action in accordance with Boeing service bulletin 747-57-2244 incorporated during production -4 747-400/400D airplanes, from Line Number 696 to 929, delivered with Wing Landing Gear (WLG) support beam end fittings part number 65B14472-23/-24 installed -5 747-400/400D/400F airplanes, Line Numbers 930 thru 1419, delivered with Wing Landing Gear (WLG) support beam end fittings part number 112U1701-1 installed -6 Airplane Models: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR GroupVariable Number 1RA001 - RA033 3RA034 1RA101 - RA115 1RA161 - RA162 3RA163 - RA164 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 12 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 13 GroupVariable Number 1RA201 - RA203 3RA216 - RA217 3RA245 - RA246 1RA251 - RA255 3RA256 - RA266 1RA301 - RA306 3RA307 - RA318 1RA351 - RA360 3RA369 - RA373 1RA401 - RA409 3RA410 - RA418 1RA501 - RA502 1RA521 - RA523 3RA524 - RA528 3RA532 - RA548 1RA551 - RA552 3RA559 - RA561 1RA581 - RA582 3RA585 1RA601 - RA602 1RA631 - RA633 3RA634 - RA635 3RA651 - RA652 3RA671 - RA677 3RA701 - RA702 3RA721 - RA731 1RA741 - RA742 3RA743 - RA745 3RA749 - RA750 1RA761 - RA762 3RA781 - RA784 1RA901 - RA914 3RA915 - RA916 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 13 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 14 GroupVariable Number 3RB001 - RB016 1RB041 - RB043 3RB044 3RB071 - RB075 1RB101 - RB102 3RB411 - RB412 4RB413 4RB421 3RB601 - RB607 3RB681 - RB697 3RB711 3RB721 - RB723 3RB741 - RB748 3RD001 - RD004 3RD021 - RD022 3RD041 - RD059 3RD071 - RD072 3RD081 - RD083 3RD091 - RD092 3RD101 - RD104 3RD121 - RD127 3RD131 - RD144 3RD166 - RD167 3RD171 - RD172 3RD181 - RD183 3RD201 - RD204 3RD221 - RD227 3RD231 - RD234 4RD235 3RD241 - RD243 3RD251 - RD262 3RD271 - RD272 3RD291 - RD292 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 14 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 15 GroupVariable Number 3RD301 - RD302 3RD311 3RD351 - RD358 3RD361 - RD366 3RD381 - RD383 3RD411 - RD414 3RD421 - RD426 3RD431 - RD435 3RD441 - RD442 3RD451 - RD456 3RD461 3RD471 - RD475 3RD513 - RD519 3RD531 - RD533 3RD551 3RD561 3RD571 3RD581 - RD583 3RD591 - RD593 3RD601 - RD607 3RD621 - RD623 3RD641 - RD649 3RD651 - RD659 3RD661 3RD671 3RD681 - RD682 3RD691 - RD692 3RD701 - RD702 3RD721 - RD722 3RD741 - RD742 3RD751 - RD755 3RD761 3RD771 - RD775 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 15 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 16 GroupVariable Number 3RD781 - RD783 3RD791 4RD792 3RE001 6RF001 - RF006 2RG001 - RG009 2RG091 2RG095 2RG101 - RG104 2RG121 - RG126 2RG141 - RG142 2RG161 - RG164 2RG171 - RG174 2RG191 - RG193 2RG211 - RG213 2RG221 - RG222 2RH101 - RH102 2RH111 - RH112 2RH121 - RH122 3RJ131 - RJ133 3RJ151 - RJ152 3RJ301 - RJ303 3RJ321 4RJ322 3RJ331 - RJ333 6RL401 - RL403 6RL411 - RL436 6RL451 - RL456 6RL461 - RL462 6RL471 - RL481 6RL491 - RL492 6RL501 - RL502 6RL511 - RL516 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 16 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 17 GroupVariable Number 6RL521 - RL522 6RL531 - RL534 6RL551 6RL561 - RL568 6RL571 - RL572 6RL576 - RL577 6RL579 6RL581 - RL586 6RL651 - RL655 6RL671 - RL675 6RL681 - RL684 6RL751 - RL752 6RM001 - RM007 6RM010 - RM013 6RM021 - RM024 6RM026 - RM030 6RM036 - RM045 6RM051 - RM053 6RM071 6RM081 - RM084 6RM091 6RM096 - RM097 6RM116 - RM117 6RM126 - RM132 6RM136 - RM147 6RM156 - RM158 6RM166 - RM177 6RM191 - RM192 6RM231 - RM233 6RM241 - RM246 6RM261 - RM264 6RM316 - RM318 6RM331 - RM333 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 17 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 18 GroupVariable Number 6RM341 6RM351 - RM355 6RM366 - RM367 6RM401 - RM403 6RM426 6RM431 6RM441 - RM443 6RM445 6RM801 - RM803 6RM811 - RM813 6RM851 - RM859 6RM861 - RM863 6RM871 - RM899 6RM901 - RM906 6RM911 3RR001 - RR005 3RR021 - RR023 4RR024 - RR025 3RR031 3RR201 - RR205 4RR206 3RR221 - RR226 3RR261 - RR267 3RR301 - RR306 4RR307 - RR310 3RR331 - RR332 3RR336 3RR341 - RR345 3RR361 - RR362 3RR421 - RR422 3RR431 - RR432 3RR441 4RR442 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 18 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 19 GroupVariable Number 4RR451 3RR501 - RR504 3RR521 4RR522 4RR526 3RR531 3RR551 - RR554 4RR555 - RR556 3RR561 4RR566 6RR701 6RR721 - RR724 6RR746 - RR748 6RR851 - RR856 6RR861 - RR862 6RR951 - RR952 3RS001 - RS002 3RS201 3RS211 - RS212 3RS221 - RS222 3RS231 - RS241 3RS251 - RS259 4RS263 3RS265 - RS268 3RS271 - RS276 3RS291 - RS292 3RS301 - RS305 4RS306 3RS311 - RS320 4RS331 - RS333 3RS341 - RS342 3RS699 3RS701 - RS703 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 19 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 20 GroupVariable Number 3RS711 - RS713 3RS721 - RS722 4RS731 - RS732 3RS741 - RS743 3RS751 - RS752 3RS761 4RS762 3RS771 4RS781 - RS782 4RS786 5RT001 - RT008 6RT009 - RT014 5RT021 - RT022 5RT031 - RT033 6RT034 - RT035 5RT041 - RT047 5RT061 5RT071 - RT073 6RT074 - RT075 5RT101 - RT103 5RT121 5RT131 - RT132 6RT133 - RT137 6RT151 - RT152 6RT161 - RT168 5RT401 - RT410 6RT411 - RT412 5RT431 - RT441 6RT442 - RT447 5RT451 - RT461 6RT462 - RT469 5RT471 - RT493 6RT494 - RT499 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 20 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 21 GroupVariable Number 5RT501 - RT514 6RT515 - RT530 5RT531 - RT534 6RT535 5RT551 - RT567 6RT568 5RT571 - RT578 6RT579 - RT590 5RT591 5RT601 - RT615 6RT616 - RT630 5RT631 - RT633 6RT634 - RT640 5RT641 - RT655 6RT656 - RT657 5RT671 - RT672 6RT673 5RT681 - RT682 5RT691 - RT694 6RT695 - RT699 5RT701 - RT704 5RT711 - RT716 6RT717 5RT741 - RT742 6RT743 - RT750 5RT751 - RT754 6RT755 - RT757 5RT776 - RT777 5RT781 - RT782 6RT783 - RT784 6RT801 - RT803 6RT811 - RT814 6RT831 - RT837 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 21 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 22 GroupVariable Number 5RT861 - RT864 5RT876 - RT877 6RT878 - RT880 5RT931 6RT932 6RT945 - RT949 6RT951 - RT955 6RT966 - RT967 6RU001 - RU006 6RU016 - RU017 6RU031 - RU032 6RU051 - RU052 6RU059 - RU062 6RU081 - RU083 6RU101 - RU102 6RU121 - RU132 5RU801 - RU803 6RU804 - RU809 5RU831 - RU834 6RU835 - RU841 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. B. Concurrent Requirements None. C. Reason Accomplishment of the repair or change work given in this service bulletin will give increased corrosion protection to the end fittings of the Wing Landing Gear (WLG) support beams, which will subsequently give them better crack resistance. Undetected corrosion can result in the occurrence of cracks in the end fittings. Undetected cracks in the end fittings could result in their separation from the gate fittings and subsequently cause damage to flight control cables and hydraulic systems that are located in the adjacent areas. Continued safe flight and landing could be affected if the separation of an end fitting from a gate fitting occurs. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 22 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 23 Three 747-400 operators have told Boeing of corrosion damage to the end fittings of the WLG support beams, where one operator also found cracks in the end fittings in addition to the corrosion. This same condition was told to Boeing earlier, which was related to 747-100/200/300 and 747-SP airplanes and addressed by Boeing service bulletin 747-57-2244, which was the subject of Federal Aviation Administration (FAA) Airworthiness Directive 89-15-07. The end fittings are installed on the outboard ends of the WLG support beams and they attach to gate fittings installed on the rear wing spars. There are two types of end fitting used on the 747 fleet. One type is a two-piece end fitting, which is installed on the end of the WLG support beams in a 'back-to-back' configuration, the other type is a one-piece end fitting. Boeing service bulletin 747-57-2244 was applicable to all 747 Classic airplanes from Line Number 1 thru 695 and gave inspection instructions, repair work and terminating action for the end fittings. The terminating action replaced each of the end fitting lug bore and bolt hole bushings with new standard or oversize bushings. The new bushings and the end fittings were installed with sealant to give better corrosion prevention. That terminating action was incorporated into the design of replacement end fittings, which were used on production airplanes from Line Number 696 and subsequent. While the terminating action worked well, the most recent reports to Boeing were from operators of 747 airplanes after Line Number 695, which showed that the problem had occurred again. As a result of the more recent reports, Boeing has further investigated the cracks and corrosion of the end fittings. The investigation found that the cracks occur at the corroded areas on the end fittings. The corrosion is found to start at the lug bore and bushing interface, because moisture continues to get into this area, from exposure of the end fittings to environmental conditions. Metallurgy analysis showed that cracks were a result of fatigue and their growth direction identified that they had started in the lug bore surface. The end fitting that was analysed, had a 0.806 inch length crack but also was found to have a secondary crack approximately 0.7 inches away from the reported crack, that was only identified by magnetic particle inspection. Boeing has found that the terminating action given in Boeing service bulletin 747-57-2244 cannot continue to be classed as 'terminating' because the occurrence of cracks and corrosion has come back. Subsequently, Boeing has changed the retrofit solution from what was given in Boeing service bulletin 747-57-2244, to install higher interference fit bushings in the lug bore(s) and bolt holes of the end fittings. The changed retrofit solution also makes follow-on repeat inspections of the end fittings necessary after the new bushings are installed. The follow-on repeat inspection intervals are up to two times longer than the shorter inspection interval that was given in Boeing service bulletin 747-57-2244. The changed retrofit solution will give increased corrosion protection and better crack prevention to the end fittings. Boeing has issued this service bulletin to incorporate the changed retrofit solution and to replace Boeing service bulletin 747-57-2244. As Boeing has had reports of cracked or corroded end fittings from operators of airplanes from Line Number 696 and subsequent, which have had the terminating action of Boeing service bulletin 747-57-2244 incorporated into their design, this service bulletin relates to all 747 airplanes from Line Number 1 thru 1419. This includes the airplanes that were applicable to Boeing service bulletin 747-57-2244 and those that were beyond its effectivity range. This service bulletin gives instructions to inspect the end fittings of the left and right WLG support beams for cracks and corrosion. If no crack is found and no corrosion is found, the end fittings can continue to be repetitively inspected, or they can be changed to have higher interference fit bushings installed in their lug bore and bolt holes. If any crack or corrosion is found in an end fitting, each one is repaired to remove the cracks and corrosion and to have higher interference fit bushings installed in its lug bore(s) and bolt holes. The new higher interference fit bushings in the end fittings give increased corrosion protection and better crack prevention. After the repair or change work is done to the end fitting(s), post repair or change follow-on inspections will be necessary, but at a different interval. Boeing Service Related Problem (SRP) 747-SRP-57-0217 is related to this service bulletin. Boeing Service Letter (SL) 747-SL-57-050-A is related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD 57-08001 is related to this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 23 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 24 D. Description Part 7 can be done as an option to Parts 1 thru 6. After Part 7 is accomplished, Part 1, Part 2 and Part 3 are terminated but Part 4, Part 5 and Part 6 continue to be necessary. Part 1 - Wing Landing Gear (WLG) Support Beam End Fittings Inspection Group 1-5: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a detailed (DET) inspection and an ultrasonic (UT) inspection of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, one of two options can be done. One option is to repeat Part 1 to do DET and UT inspections of the end fittings at the same interval. The other option is to do Part 2 to do repeat DET and High Frequency Eddy Current (HFEC) inspections of the end fittings at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Group 6: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a detailed (DET) inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, do Part 2 to do repeat DET and High Frequency Eddy Current (HFEC) inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 3 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 2 - Wing Landing Gear (WLG) Support Beam End Fittings Repeat Detailed and High Frequency Eddy Current Inspection (Fillet Seal Remaining) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, repeat Part 2 to do DET and HFEC inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 3 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 3 - Wing Landing Gear (WLG) Support Beam End Fittings Repeat Detailed and High Frequency Eddy Current Inspection (Fillet Seal Removed) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do DET and HFEC inspections of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound again on each end fitting and repeat Part 3 to do DET and HFEC inspections of the end fittings at the same interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 24 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 25 Part 4 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Follow-On Inspection Group 1-5: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET and UT inspection of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, one of two options can be done. One option is to repeat Part 4 to do DET and UT inspections of the end fittings at the same interval. The other option is to do Part 5 to do repeat DET and HFEC inspections of the end fittings at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Group 6: Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, do Part 5 to do repeat DET and HFEC inspections at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 6 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 5 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Repeat Detailed and High Frequency Eddy Current Follow-On Inspection (Fillet Seal Remaining) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do a DET inspection of each end fitting for fillet seal damage and for cracks and corrosion. If the fillet seal is not damaged, no crack is found and no corrosion is found, repeat Part 5 to do DET and HFEC inspections of the end fittings at the same interval. If the fillet seal is damaged, but no crack is found and no corrosion is found, remove the fillet seal from each end fitting and do DET and HFEC inspections for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound on each end fitting and do Part 6 to do repeat DET and HFEC inspections for cracks and corrosion at a different interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 6 - Wing Landing Gear (WLG) Support Beam End Fittings Post Repair or Change Repeat Detailed and High Frequency Eddy Current Follow-On Inspection (Fillet Seal Removed) Prepare the airplane and remove wing panels to get access to the end fittings of the left and right WLG support beams. Do DET and HFEC inspections of each end fitting for cracks and corrosion. If no crack is found and no corrosion is found, apply corrosion inhibiting compound again on each end fitting and repeat Part 6 to do DET and HFEC inspections of the end fittings at the same interval. If any crack or corrosion is found, do Part 7 to repair each removed end fitting, or to change each serviceable end fitting or new end fitting to install higher interference fit bushings. Part 7 - Wing Landing Gear (WLG) Support Beam End Fitting - Higher Interference Fit Bushings Installation BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 25 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 26 Remove the end fitting(s) from the left and/or right WLG support beam, or get serviceable end fittings or new end fittings. Remove the lug bore bushings, bolt hole bushings and protective finishes from each end fitting. For removed end fittings and serviceable end fittings only, do DET and Magnetic Particle Inspections (MPI) of the lug bore, Fluorescent Penetrant Inspections (FPI) or MPI of the bolt holes and flat surfaces of each end fitting for cracks or corrosion. If no crack is found and no corrosion is found, insurance cut the lug bore(s) of each end fitting. If any crack or corrosion is found, oversize the lug bore(s) and bolt holes of each end fitting by the minimum necessary up to the maximum repair diameter, remove material from the flat surfaces up to the limit of material removal, to remove cracks and corrosion, and do repeat inspections until no crack is found and no corrosion is found. As an insurance cut, do an additional oversize of the lug bore(s) and, as applicable, do an additional oversize of the machined bolt holes and remove additional material from the machined flat surfaces. For all end fittings, do post machine work treatments and inspections, apply plating, finishes and make new higher interference fit lug bore and bolt hole bushings. Additionally, more post machine treatment work is necessary on 65B14472-23/-24 end fittings to shot peen all surfaces. If necessary, make new WLG support beam bushings. Wet install the new lug bore and bolt holes bushings in each end fitting and fillet seal their edges. If new WLG support beam bushing were made, replace the WLG support beam bushings. Install the repaired or changed end fitting(s) back on the left and/or right WLG support beam. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 572, 672747-100 Group 2: Affected Maintenance Zones ZoneModel 572, 672747SP Group 3: Affected Maintenance Zones ZoneModel 572, 672747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR Group 4: Affected Maintenance Zones ZoneModel 572, 672747-200B, 747-200C, 747-200F, 747-300 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 26 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 27 Group 5: Affected Maintenance Zones ZoneModel 572, 672747-400, 747-400D Group 6: Affected Maintenance Zones ZoneModel 572, 672747-400, 747-400D, 747-400F 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. The conditions, actions and compliance times in Table 1 and 2 below are based on total flight cycles and calendar time on each end fitting since new or its last overhaul. If the flight cycles or calendar time on the end fitting cannot be positively determined, use the calendar time (grace period) after the date on this service bulletin in accordance with the second Compliance Time column in Tables 1 and 2 below. – Do Part 1 thru Part 7 as applicable in Tables 1 thru 12 below in accordance with Paragraph 3., Accomplishment Instructions. – Evaluate the conditions and do the applicable actions in Tables 1 thru 12 separately for each WLG support beam end fitting. – Refer to Paragraph 3.A., General Information for the definition of 'serviceable' and 'overhauled' end fittings. – Refer to APPENDIX A for a usage index and a guide to the tables below. Table 1: Part 7 - Initial and Repeat End Fitting Repair or Change Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) Action (a) (b)Condition (Airplanes) End Fitting Flight Cycles Within Months After the Origi- nal Issue Date on this Service Bulletin Before Total Flight Cycles on an End Fit- ting Repair or Change End Fitting in Accordance With 13,0001820,000Part 7Group 1, Configuration 1 13,0002420,000Part 7Group 1, Configuration 2 16,0001820,000Part 7Group 2, Configuration 1 16,0002420,000Part 7Group 2, Configuration 2 13,0001820,000Part 7Group 3, Configuration 1 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 27 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 28 Table 1: Part 7 - Initial and Repeat End Fitting Repair or Change Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) Action (a) (b)Condition (Airplanes) End Fitting Flight Cycles Within Months After the Origi- nal Issue Date on this Service Bulletin Before Total Flight Cycles on an End Fit- ting Repair or Change End Fitting in Accordance With 13,0002420,000Part 7Group 3, Configuration 2 13,0002420,000Part 7Group 4 13,0001820,000Part 7Group 5 16,0002420,000Part 7Group 6 (a) Part 1, Part 2 and Part 3 inspections are terminated by the accomplishment of Part 7. (b) Part 4, Part 5 and Part 6 inspections continue to be necessary after the accomplishment of Part 7. Refer to Table 3 for the necessary work after the accomplishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 28 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 29 Table 2: Part 1 - End Fitting Inspections (Before Accomplishment of Part 7) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) Action (a) (b)Condition (Airplanes) -Within 18 months after the original issue date on this ser- vice bulletin. Within 8 years on each end fit- ting since new or its last over- haul. Do a detailed (DET) and an ultrasonic (UT) inspec- tion of the end fittings for cracks and corrosion in accordance with Part 1. Group 1, Configuration 1; Group 2, Configuration 1; Group 3, Configuration 1; Group 5 Refer to Table 4 for the necessary work because of the Part 1 inspection results and for subse- quent actions. -Within 24 months after the original issue date on this ser- vice bulletin. Within 10 years on each end fit- ting since the terminating ac- tion in accor- dance with Boe- ing service bul- letin 747-57- 2244 was done. Do a detailed (DET) and an ultrasonic (UT) inspec- tion of the end fittings for cracks and corrosion in accordance with Part 1. Group 1, Configuration 2; Group 2, Configuration 2; Group 3, Configuration 2 Refer to Table 5 for the necessary work because of the Part 1 inspection results and for subse- quent actions. -Within 24 months after the original issue date on this ser- vice bulletin. Within 10 years on each end fit- ting since new or its last over- haul. Do a detailed (DET) and an ultrasonic (UT) inspec- tion of the end fittings for cracks and corrosion in accordance with Part 1. Group 4 Refer to Table 5 for the necessary work because of the Part 1 inspection results and for subse- quent actions. -Within 24 months after the original issue date on this ser- vice bulletin. Within 10 years on each end fit- ting since new or its last over- haul. Do a detailed (DET) in- spection of the end fit- tings for fillet seal dam- age and for cracks and corrosion in accordance with Part 1. Group 6 Refer to Table 6 for the necessary work because of the Part 1 inspection results and for subse- quent actions. (a) Part 7 can be done as an option to Part 1 inspections. (b) Part 1 is terminated by the accomplishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 29 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 30 Table 3: Part 4 - Follow-On End Fitting Inspections (After Accomplishment of Part 7) Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition (Airplanes) -Within 12 years af- ter the date each end fitting was last repaired or changed in accor- dance with Part 7. Do a detailed (DET) and an ultrasonic (UT) inspec- tion of the end fittings for cracks and corrosion in accordance with Part 4. Group 1, Group 2, Group 3, Group 4, Group 5 Refer to Table 9 for the necessary work because of the Part 4 follow-on in- spection results and for subsequent actions. -Within 12 years af- ter the date each end fitting was last repaired or changed in accor- dance with Part 7. Do a detailed (DET) in- spection of the end fit- tings for fillet seal dam- age and for cracks and corrosion in accordance with Part 4. Group 6 Refer to Table 10 for the necessary work because of the Part 4 follow-on in- spection results and for subsequent actions. (a) Part 7 can be done as an option to the Part 4 follow-on inspections. (b) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 30 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 31 Group 1-3, Configuration 1; Group 5: Table 4: Part 1 - End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition 18 months.-Option 1A: Do repeat DET and UT inspections of the end fittings for cracks and corrosion in accordance with Part 1. Condition 1 - No crack is found and no corrosion is found. Or -Within 18 months from the date each end fitting was last inspected in accor- dance with Part 1. Option 1B: Do a repeat DET inspection of the end fittings for fillet seal dam- age and for cracks and corrosion in accordance with Part 2. Refer to Table 7 for the necessary work because of the Part 2 inspection results and for subse- quent actions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 2 - Any crack or corrosion is found. (a) Part 7 can be done as an option to the Part 1 and Part 2 inspections. (b) Part 1 and Part 2 are terminated by the accomplishment of Part 7. (c) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 31 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 32 Group 1-3, Configuration 2; Group 4: Table 5: Part 1 - End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition 24 months.-Option 1A: Do repeat DET and UT inspections of the end fittings for cracks and corrosion in accordance with Part 1. Condition 1 - No crack is found and no corrosion is found. Or -Within 24 months from the date each end fitting was last inspected in accor- dance with Part 1. Option 1B: Do a repeat DET inspection of the end fittings for fillet seal dam- age and for cracks and corrosion in accordance with Part 2. Refer to Table 7 for the necessary work because of the Part 2 inspection results and for subse- quent actions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 2 - Any crack or corrosion is found. (a) Part 7 can be done as an option to the Part 1 and Part 2 inspections. (b) Part 1 and Part 2 are terminated by the accomplishment of Part 7. (c) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 32 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 33 Group 6: Table 6: Part 1 - End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition -Within 12 months from the date each end fitting was last inspected in accor- dance with Part 1. Do a repeat DET inspec- tion of the end fittings for fillet seal damage and for cracks and corrosion in accordance with Part 2. Condition 3 - Fillet seal is not damaged, no crack is found and no corrosion is found. Refer to Table 7 for the necessary work because of the Part 2 inspection results and for subse- quent actions. -Before further flight. Remove the fillet seal and do DET and HFEC inspec- tions of each end fitting for cracks and corrosion in accordance with Part 1, Condition 4. Condition 4 - Fillet seal is damaged, but no crack is found and no corrosion is found. -Before further flight. Apply corrosion inhibiting compound on each end fitting in accordance with Part 1, Condition 4.1. Condition 4.1 - No crack is found and no corrosion is found during the inspection specified in Condition 4. And -Within 12 months from the date each end fitting was last inspected in accor- dance with Part 1. Do repeat DET and HFEC inspections of each end fitting for cracks and corrosion in accor- dance with Part 3. Refer to Table 8 for the necessary work because of the Part 3 inspection results and for subse- quent actions. Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 4.2 - Any crack or corrosion found during the inspection specified in Condition 4. Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 5 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 1, Part 2 and Part 3 inspections. (b) Part 1, Part 2 and Part 3 are terminated by the accomplishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 33 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 34 Group 6: Table 6: Part 1 - End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition (c) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. Table 7: Part 2 - Repeat End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition - All Airplanes 12 months.-Do a repeat DET inspec- tion of each end fitting fil- let seal damage and for cracks and corrosion in accordance with Part 2. Condition 6 - Fillet seal is not damaged, no crack is found and no corrosion is found. -Before further flight. Remove the fillet seal and do DET and HFEC inspec- tions of each end fitting for cracks and corrosion in accordance with Part 2, Condition 7. Condition 7 - Fillet seal is damaged, but no crack is found and no corrosion is found. -Before further flight. Apply corrosion inhibiting compound on each end fitting in accordance with Part 2, Condition 7.1. Condition 7.1 - No crack is found and no corrosion is found during the inspection specified in Condition 7. And -Within 12 months from the date each end fitting was last inspected in accor- dance with Part 2. Do repeat DET and HFEC inspections of each end fitting for cracks and corrosion in accor- dance with Part 3. Refer to Table 8 for the necessary work because of the Part 3 inspection results and subsequent actions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 7.2 - Any crack or corrosion found during the inspection specified in Condition 7. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 8 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 2 and Part 3 inspections. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 34 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 35 Table 7: Part 2 - Repeat End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition - All Airplanes (b) Part 2 and Part 3 are terminated by the accomplishment of Part 7. (c) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. Table 8: Part 3 - Repeat End Fitting Inspection Results and Subsequent Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a) (b)Condition - All Airplanes -Before further flight. Apply corrosion inhibiting compound again on each the end fitting in accor- dance with Part 3, Condi- tion 9. Condition 9 - No crack is found and no corrosion is found. And 12 months.-Do repeat DET and HFEC inspections of each end fitting for cracks and corrosion in accor- dance with Part 3. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) (c) Condition 10 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 3 inspections. (b) Part 3 is terminated by the accomplishment of Part 7. (c) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 35 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 36 Group 1-5: Table 9: Part 4 - Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition 36 months.-Do repeat follow-on DET and UT inspections of each end fitting for cracks and corrosion in accor- dance with Part 4. Condition 11 - No crack is found and no corrosion is found. Or -Within 36 months from the date each end fitting was last inspected in accor- dance with Part 4. Do a repeat follow-on DET inspection of each end fitting for fillet seal damage and for cracks and corrosion in accor- dance with Part 5. Refer to Table 11 for the necessary work because of the Part 5 follow-on in- spection results and for subsequent follow-on ac- tions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 12 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 4 and Part 5 follow-on inspections. (b) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 36 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 37 Group 6: Table 10: Part 4- Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition -Within 24 months from the date each end fitting was last inspected in accor- dance with Part 4. Do repeat follow-on DET inspections of each end fitting for fillet seal dam- age and for cracks and corrosion in accordance with Part 5. Condition 13 - Fillet seal is not damaged, no crack is found and no corrosion is found. Refer to Table 11 for the necessary work because of the Part 5 follow-on in- spection results and for subsequent follow-on ac- tions. -Before further flight. Remove the fillet seal and do a DET and HFEC in- spection of each end fit- ting for cracks and corro- sion in accordance with Part 4, Condition 14. Condition 14 - Fillet seal is damaged, but no crack is found and no corrosion is found. -Before further flight. Apply corrosion inhibiting compound on each end fitting in accordance with Part 4, Condition 14.1. Condition 14.1 - No crack is found and no corrosion is found during the inspec- tion specified in Condition 14. And -Within 12 months from the date each end fitting was last inspected in accor- dance with Part 5. Do a repeat follow-on DET and HFEC inspec- tions of each end fitting for cracks and corrosion in accordance with Part 6. Refer to Table 12 for the necessary work because of the Part 6 follow-on in- spection results and for subsequent follow-on ac- tions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 14.2 - Any crack or corrosion found during the inspection specified in Condition 14. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 15 - Any crack or corrosion found. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 37 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 38 Group 6: Table 10: Part 4- Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition (a) Part 7 can be done as an option to the Part 4, Part 5 and Part 6 follow-on inspections. (b) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. Table 11: Part 5 - Repeat Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition - All Airplanes 24 months.-Do repeat follow-on DET inspections of each end fitting for fillet seal dam- age and for cracks and corrosion in accordance with Part 5. Condition 16 - Fillet seal is not damaged, no crack is found and no corrosion is found. -Before further flight. Remove the fillet seal and do a DET and HFEC in- spection of each end fit- ting for cracks and corro- sion in accordance with Part 5, Condition 17. Condition 17 - Fillet seal is damaged, but no crack is found and no corrosion is found. -Before further flight. Apply corrosion inhibiting compound on each end fitting in accordance with Part 5, Condition 17.1. Condition 17.1 - No crack is found and no corrosion is found during the inspec- tion specified in Condition 17. And -Within 12 months from the date each end fitting was last inspected in accor- dance with Part 5. Do a repeat follow-on DET and HFEC inspec- tions of each end fitting for cracks and corrosion in accordance with Part 6. Refer to Table 12 for the necessary work because of the Part 6 follow-on in- spection results and sub- sequent follow-on ac- tions. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 17.2 - Any crack or corrosion found during the inspection specified in Condition 17. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 38 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 39 Table 11: Part 5 - Repeat Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition - All Airplanes -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 18 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 5 and Part 6 follow-on inspections. (b) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. Table 12: Part 6 - Repeat Follow-On End Fitting Inspection Results and Subsequent Follow-On Actions Repeat Interval (Not to Exceed) Compliance TimeAction (a)Condition - All Airplanes -Before further flight. Apply corrosion inhibiting compound again on each end fitting in accordance with Part 6, Condition 19. Condition 19 - No crack is found and no corrosion is found And 12 months.-Do repeat follow-on DET and HFEC inspections of each end fitting for cracks and corrosion in accor- dance with Part 6. -Before further flight. Repair or change each end fitting in accordance with Part 7. (b) Condition 20 - Any crack or corrosion found. (a) Part 7 can be done as an option to the Part 6 follow-on inspections. (b) Part 4, Part 5 and Part 6 follow-on inspections continue to be necessary after the accom- plishment of Part 7. 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 39 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 40 This service bulletin has been approved by the FAA. In addition, the manager of the FAA Seattle Aircraft Certification Office approves the inspections defined in this service bulletin as an alternate method of compliance to the inspections required by paragraphs A and B of AD 89-15-07. The manager of the FAA Seattle Aircraft Certification Office also approves the rework defined in this service bulletin as an alternate method of compliance to the rework required by paragraphs C, D, and E of AD 89-15-07. All other provisions of AD 89-15-07 that are not specifically referenced in the above statement remain fully applicable and must be complied with. G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin for each end fitting or for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:  Time to adjust to the workplace  Time to schedule the work  Time to inspect the work  Time to cure the materials  Time to make the parts  Time to find the tools Group 1: Elapsed HoursTask HoursNumber of Per- sons Task 5.2521.004Prepare Airplane and Open Access 1.001.001FIGURE 1 (d) 1.001.001FIGURE 4 (d) 2.002.001FIGURE 11 (e) 11.0022.002FIGURE 15 (a) (f) -FIGURE 19 (b) -FIGURE 20 (b) 2.002.001FIGURE 21 2.502.501FIGURE 25 (c) 2.502.501FIGURE 27 (c) 5.2521.004Close Access 27.2570.00TOTAL FOR EACH WLG SUPPORT BEAM END FITTING 55.00140.00TOTAL FOR EACH AIRPLANE (a) The work in this Figure includes instructions for the removal of cracks and/or corrosion from the lug bore(s), bolt hole(s) and the surface of each removed or serviceable end fitting. It is possible that not all of the instructions for crack and corrosion removal will be necessary for each end fitting, but the estimate BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 40 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 41 Group 1: Elapsed HoursTask HoursNumber of Per- sons Task values given are the maximum times it will take to do all of the work in this Figure. (b) An estimate value is not given for the time to make parts. (c) This Figure is only applicable if new WLG support beam bushings were made because new higher interference fit bolt hole bushings for the end fitting(s) were made from 17-4PH stainless steel. The estimate values for this Figure are not included in the total. (d) If operators choose to do repeat inspections of the WLG support beam end fittings by the DET and HFEC procedures, refer to 'Supplemental Table A' or 'Supplemental Table B', as applicable, below and use those estimate values to replace these. (e) The estimate values given are for the removal of bushings and for the inspec- tions of removed or serviceable end fittings. The estimate values for new end fittings, will not be the same, as the work for these end fittings in this Figure is different. (f) Operators can choose to use a different procedure to repair removed or ser- viceable end fittings. Refer to the 'Alternative End Fitting Repair Procedure' table below and use those estimate values to replace these. Group 2: Elapsed HoursTask HoursNumber of Per- sons Task 5.0020.004Prepare Airplane and Open Access 1.001.001FIGURE 2 (d) 1.001.001FIGURE 5 (d) 1.001.001FIGURE 12 (e) 5.5011.002FIGURE 17 (a) (f) -FIGURE 19 (b) -FIGURE 20 (b) 1.001.001FIGURE 22 5.005.001FIGURE 26 (c) 5.005.001FIGURE 28 (c) 5.0020.004Close Access 19.5055.00TOTAL FOR EACH WLG SUPPORT BEAM END FITTING BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 41 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 42 Group 2: Elapsed HoursTask HoursNumber of Per- sons Task 39.00110.00TOTAL FOR EACH AIRPLANE (a) The work in this Figure includes instructions for the removal of cracks and/or corrosion from the lug bore, bolt hole(s) and the surface of each removed or serviceable end fitting. It is possible that not all of the instructions for crack and corrosion removal will be necessary for each end fitting, but the estimate values given are the maximum time it will take to do all of the work in this Figure. (b) An estimate value is not given for the time to make parts. (c) This Figure is only applicable if new WLG support beam bushings were made because new higher interference fit bolt hole bushings for the end fitting(s) were made from 17-4PH stainless steel. The estimate values for this Figure are not included in the total. (d) If operators choose to do repeat inspections of the WLG support beam end fittings by the DET and HFEC procedures, refer to 'Supplemental Table A' or 'Supplemental Table B', as applicable, below and use those estimate values to replace these. (e) The estimate values given are for the removal of bushings and for the inspec- tions of removed or serviceable end fittings. The estimate values for new end fittings, will not be the same, as the work for these end fittings in this Figure is different. (f) Operators can choose to use a different procedure to repair removed or ser- viceable end fittings. Refer to the 'Alternative End Fitting Repair Procedure' table below and use those estimate values to replace these. Group 3-5: Elapsed HoursTask HoursNumber of Per- sons Task 5.2521.004Prepare Airplane and Open Access 1.001.001FIGURE 1 (d) 1.001.001FIGURE 4 (d) 2.002.001FIGURE 13 (e) (65B14472-1 and - 2, or 65B14472-25 and -26 end fittings) 3.003.001FIGURE 13 (e) (65B14472-23 and -24 end fittings) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 42 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 43 Group 3-5: Elapsed HoursTask HoursNumber of Per- sons Task 11.0022.002FIGURE 16 (a) (f) (65B14472-1 and - 2, or 65B14472-25 and -26 end fittings) 8.2516.502FIGURE 16 (a) (65B14472-23 and -24 end fittings) -FIGURE 19 (b) -FIGURE 20 (b) 2.002.001FIGURE 23 5.005.001FIGURE 26 (c) 5.005.001FIGURE 28 (c) 5.2521.004Close Access 27.5070.00TOTAL FOR EACH 65B14472-1/-2/-25/- 26 WLG SUPPORT BEAM END FITTING 55.00140.00TOTAL FOR EACH AIRPLANE 25.7565.50TOTAL FOR EACH 65B14472-23/-24 WLG SUPPORT BEAM END FITTING 51.50131.00TOTAL FOR EACH AIRPLANE (a) The work in this Figure includes instructions for the removal of cracks and/or corrosion from the lug bore(s), bolt hole(s) and the surface of each removed or serviceable end fitting. It is possible that not all of the instructions for crack and corrosion removal will be necessary for each end fitting, but the estimate values given are the maximum times it will take to do all of the work in this Figure. (b) An estimate value is not given for the time to make parts. (c) This Figure is only applicable if new WLG support beam bushings were made because new higher interference fit bolt hole bushings for the end fitting(s) were made from 17-4PH stainless steel. The estimate values for this Figure are not included in the total. (d) If operators choose to do repeat inspections of the WLG support beam end fittings by the DET and HFEC procedures, refer to 'Supplemental Table A' or 'Supplemental Table B', as applicable, below and use those estimate values to replace these. (e) The estimate values given are for the removal of bushings and for the inspec- tions of removed or serviceable end fittings. The estimate values for new end fittings, will not be the same, as the work for these end fittings in this Figure is different. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 43 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 44 Group 3-5: Elapsed HoursTask HoursNumber of Per- sons Task (f) Operators can choose to use a different procedure to repair removed or ser- viceable end fittings. Refer to the 'Alternative End Fitting Repair Procedure' table below and use those estimate values to replace these. Group 6: Elapsed HoursTask HoursNumber of Per- sons Task 5.2521.004Prepare Airplane and Open Access 1.001.001FIGURE 3 1.001.001FIGURE 6 3.503.501FIGURE 7 (d) 3.503.501FIGURE 8 (d) 1.001.001FIGURE 9 (d) 1.001.001FIGURE 10 (d) 1.001.001FIGURE 14 5.5011.002FIGURE 18 (a) -FIGURE 19 (b) -FIGURE 20 (b) 1.001.001FIGURE 24 5.005.001FIGURE 26 (c) 5.005.001FIGURE 28 (c) 5.2521.004Close Access 29.0066.00TOTAL FOR EACH WLG SUPPORT BEAM END FITTING 58.00132.00TOTAL FOR EACH AIRPLANE (a) The work in this Figure includes instructions for the removal of cracks and/or corrosion from the lug bores, bolt holes and the surface of each removed or serviceable end fitting. It is possible that not all of the instructions for crack and corrosion removal will be necessary for each end fitting, but the estimate values given are the maximum times it will take to do all of the work in this Figure. (b) An estimate value is not given for the time to make parts. (c) This Figure is only applicable if new WLG support beam bushings were made because new higher interference fit bolt hole bushings for the end fitting(s) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 44 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 45 Group 6: Elapsed HoursTask HoursNumber of Per- sons Task were made from 17-4PH stainless steel. The estimate values for this Figure are not included in the total. (d) The work in this Figure is only necessary if the fillet seal is damaged. The manpower estimate values for this Figure are not included in the Totals. (e) The estimate values given are for the removal of bushings and for the inspec- tions of removed or serviceable end fittings. The estimate values for new end fittings, will not be the same, as the work for these end fittings in this Figure is different. (f) Operators can choose to use a different procedure to repair removed or ser- viceable end fittings. Refer to the 'Alternative End Fitting Repair Procedure' table below and use those estimate values to replace these. Group 1-5: Supplemental Table A: Part 2 and Part 5 Elapsed HoursTask HoursNumber of Per- sons Task 1.001.001FIGURE 3 1.001.001FIGURE 6 3.503.501FIGURE 7 (a) 3.503.501FIGURE 8 (a) 1.001.001FIGURE 9 (a) 1.001.001FIGURE 10 (a) 2.002.00TOTAL FOR EACH WLG SUPPORT BEAM END FITTING 4.004.00TOTAL FOR EACH AIRPLANE (a) The work in this Figure is only necessary if the fillet seal is damaged. The manpower estimate values for this Figure are not included in the Totals. Group 1-5: Supplemental Table B: Part 3 and Part 6 Elapsed HoursTask HoursNumber of Per- sons Task 3.503.501FIGURE 7 3.503.501FIGURE 8 1.001.001FIGURE 9 1.001.001FIGURE 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 45 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 46 Group 1-5: Supplemental Table B: Part 3 and Part 6 Elapsed HoursTask HoursNumber of Per- sons Task 9.009.00TOTAL FOR EACH WLG SUPPORT BEAM END FITTING 18.0018.00TOTAL FOR EACH AIRPLANE Alternative End Fitting Repair Procedure Elapsed HoursTask HoursNumber of Per- sons Task 9.0018.002APPENDIX C - Two Piece End Fitting 9.009.001APPENDIX C - One Piece End Fitting H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data a. Boeing Service Related Problem (SRP) 747-SRP-57-0217. b. Boeing Fleet Team Digest (FTD) 747 FTD 57-08001. c. 747-100/200/300 Aircraft Maintenance Manual (AMM) 07-11-01, 12-09-08, 27-51-00, 32-00-15, 32-00-30, 57-15-01. d. 747-100/200/300 Structural Repair Manual (SRM) 51-20-01. e. 747-400 Aircraft Maintenance Manual (AMM) 06-09-08, 07-11-01, 27-51-00, 32-00-15, 32-00-30, 57-15-01. f. 747-400 Structural Repair Manual (SRM) 51-20-01. g. 747-400F Structural Repair Manual (SRM) 51-20-01. h. 747-400LCF Structural Repair Manual (SRM) 51-20-01. i. 747-400SF Structural Repair Manual (SRM) 51-20-01. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 46 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 47 j. 747-SP Structural Repair Manual (SRM) 51-20-01. k. 747 Non-Destructive Testing (NDT) Manual Part 4, 57-40-03, Part 4, 57-40-05, Part 6, 51-00-00. l. Boeing Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-10-09, 20-20-01, 20-20-02, 20-30-02, 20-30-03, 20-41-02, 20-41-05, 20-42-02, 20-42-05, 20-42-10, 20-50-03, 20-50-10, 20-50-19. m. Boeing Service Bulletin 747-57-2244. n. Boeing Service Letter 747-SL-57-050-A. o. FAA Airworthiness Directive (AD) 89-15-07. p. Boeing Drawing 012W6100. 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin None. K. Publications Affected 1. Publications: Chapter-SectionPublication 57-15747-100/200/300 Illustrated Parts Catalog 57-15747-400/400LCF Illustrated Parts Catalog 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS and new DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 47 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 48 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 48 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT BLANK PAGE ### Page 49 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane and Paragraph 2.D., Parts Necessary to Change Spares, as shown below. Parts availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. Group 1: Unit Price thru DEC 31/09 ROLT (Weeks) NamePart Number $13,218.0036End Fitting Assy65B01042-13 $4,000.00 (a)3565B01042-14 (a) Sale price until surplus inventory is depleted. Group 2: Unit Price thru DEC 31/09 ROLT (Weeks) NamePart Number $4,000.00 (a)(b)End Fitting Assy65B14472-27 (a) Sale price until surplus inventory is depleted. (b) Contact Spares for ROLT information. Group 3-4: Unit Price thru DEC 31/09 ROLT (Weeks) NamePart Number $13,218.00(a)End Fitting Assy65B14472-25 $13,218.00(a)65B14472-26 (a) Contact Spares for ROLT information. Group 5: Unit Price thru DEC 31/09 ROLT (Weeks) NamePart Number $13,218.0055End Fitting Assy65B14472-23 $13,218.005565B14472-24 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 49 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 50 Group 6: Unit Price thru DEC 31/09 ROLT (Weeks) NamePart Number Contact Boeing for price. (a)End Fitting Assy112U1701-1 (a) Contact Spares for ROLT information. The 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. Mail to: 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 kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: The parts shown below and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane, unless specified differently. 1. 2. The new end fittings shown below are only necessary if the ones removed from the airplane or serviceable ones cannot be repaired because their damage is more than the limits. Or, these parts will be necessary for operators that choose to install new end fittings as an option to the repair or change work to removed end fittings or serviceable end fittings. 3. Each new end fitting must be changed in accordance with 'Part 7 - Wing Landing Gear (WLG) Support Beam End Fitting - Higher Interference Fit Bushings Installation' of Paragraph 3., Accomplishment Instructions, before it is installed on an airplane. Additionally in Part 7, all surfaces of each new 65B14472-23/-24 end fitting must be shot peened. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 50 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 51 Group 1: NotesExisting Part NumberNameQTYNew Part Number The 65B01042-14 end fitting is opposite to the 65B01042-13 end fitting. 65B01042-1, or 65B01042- 9 End Fitting Assy265B01042-13 65B01042-2, or 65B01042- 10 265B01042-14 Group 2: NotesExisting Part NumberNameQTYNew Part Number 65B14472-8End Fitting Assy265B14472-27 Group 3-4: NotesExisting Part NumberNameQTYNew Part Number The 65B14472-26 end fitting is opposite to the 65B14472-25 end fitting. 65B14472-1, or 65B14472- 25 End Fitting Assy265B14472-25 65B14472-2, or 65B14472- 26 265B14472-26 Group 5: NotesExisting Part NumberNameQTYNew Part Number The 65B14472-24 end fitting is opposite to the 65B14472-23 end fitting. 65B14472-23End Fitting Assy265B14472-23 65B14472-24265B14472-24 Group 6: NotesExisting Part NumberNameQTYNew Part Number 112U1701-1End Fitting Assy2112U1701-1 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 51 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 52 2. Parts and Materials Supplied by the Operator Group 1, 3-4: NotesExisting Part NumberNameQTYPart Number / Specification (a)65B11261-1, or 65B11261- 2, or 65B11261-4 Pin265B11261-1, or 65B11261-2, or 65B11261-4 (g)-Washer, Flat-Metal, Round (Shim)56MS15795-825 (g) (h)-Raw Stock, 2.250 inches diameter by 0.165 inches thick. Passivated. (Shim) CRES per ASTM A380 (c) (d)-Copper Beryllium Alloy, Condition AT - 5.0 inch (max) diameter bar stock -QQ-C-530 (f)-Stainless Steel, Heat Treated to 180ksi - 5.0 inch (max) diameter bar stock -17-4PH per AMS 5643 (e)-Aluminum Nickel Bronze - 5.0 inch (max) diameter bar stock -Al-Ni-Br per AMS 4640 (b)-Sealant1 PtBMS 5-95 (b)-Primer1 PtBMS 10-11, Type I (b)-Corrosion Inhibiting Compound1 PtBMS 3-23, Type II (a) These new parts, as applicable, are necessary if each removed pin is found to be corroded. Use the same part number of pin that was removed. The quantity given is for each airplane. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Used to make new higher interference fit end fitting lug bore bushings as shown in FIGURE 19. (d) Used to make new higher interference fit end fitting bolt hole bushings as shown in FIGURE 20. (e) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit lug bore bushings. (f) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit bolt hole bushings. (g) This part is only necessary if corrosion was found around the bolt holes of the end fittings and face cuts were made. The quantity given is the quantity necessary for each bolt hole on each surface of each end fitting for each airplane. Adjust the quantity as necessary. (h) This material can be used as an alternative to make equivalent 'shims' if the MS15795-825 washers are not available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 52 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 53 Group 2: NotesExisting Part NumberNameQTYPart Number / Specification (a)65B19191-1Pin265B19191-1 (g)-Washer, Flat-Metal, Round (Shim)28MS15795-825 (g) (h)-Raw Stock, 2.250 inches diameter by 0.165 inches thick. Passivated. (Shim) CRES per ASTM A380 (c) (d)-Copper Beryllium Alloy, Condition AT - 5.0 inch (max) diameter bar stock -QQ-C-530 (f)-Stainless Steel, Heat Treated to 180ksi - 5.0 inch (max) diameter bar stock -17-4PH per AMS 5643 (e)-Aluminum Nickel Bronze - 5.0 inch (max) diameter bar stock -Al-Ni-Br per AMS 4640 (b)-Sealant1 PtBMS 5-95 (b)Primer1 PtBMS 10-11, Type I (b)-Corrosion Inhibiting Compound1 PtBMS 3-23, Type II (a) These new parts, as applicable, are necessary if each removed pin is found to be corroded. The quan- tity given is for each airplane. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Used to make new higher interference fit end fitting lug bore bushings in accordance with FIGURE 19. (d) Used to make new higher interference fit end fitting bolt hole bushings in accordance with FIGURE 20. (e) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit lug bore bushings. (f) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit bolt hole bushings. (g) This part is only necessary if corrosion was found around the bolt holes of the end fittings and face cuts were made. The quantity given is the quantity necessary for each bolt hole on each surface of each for each airplane. Adjust the quantity as necessary. (h) This material can be used as an alternative to make equivalent 'shims' if the MS15795-825 washers are not available. Group 5: NotesExisting Part NumberNameQTYPart Number / Specification (a)65B11261-3, or 65B11261- 5, or 65B11261-6 Pin265B11261-3, or 65B11261-5, or 65B11261-6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 53 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 54 Group 5: NotesExisting Part NumberNameQTYPart Number / Specification (g)-Washer, Flat-Metal, Round (Shim)56MS15795-825 (g) (h)-Raw Stock, 2.250 inches diameter by 0.165 inches thick. Passivated. (Shim) CRES per ASTM A380 (c) (d)-Copper Beryllium Alloy, Condition AT - 5.0 inch (max) diameter bar stock -QQ-C-530 (f)-Stainless Steel, Heat Treated to 180ksi - 5.0 inch (max) diameter bar stock -17-4PH per AMS 5643 (e)-Aluminum Nickel Bronze - 5.0 inch (max) diameter bar stock -Al-Ni-Br per AMS 4640 (b)-Sealant1 PtBMS 5-95 (b)-Primer1 PtBMS 10-11, Type I (b)-Corrosion Inhibiting Compound1 PtBMS 3-23, Type II (a) These new parts, as applicable, are necessary if each removed pin is found to be corroded. Use the same part number of pin that was removed. The quantity given is for each airplane. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Used to make new higher interference fit end fitting lug bore bushings in accordance with FIGURE 19. (d) Used to make new higher interference fit end fitting bolt hole bushings in accordance with FIGURE 20. (e) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit lug bore bushings. (f) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit bolt hole bushings. (g) This part is only necessary if corrosion was found around the bolt holes of the end fittings and face cuts were made. The quantity given is the quantity necessary for each bolt hole on each surface of each end fitting for each airplane. Adjust the quantity as necessary. (h) This material can be used as an alternative to make equivalent 'shims' if the MS15795-825 washers are not available. Group 6: NotesExisting Part NumberNameQTYPart Number / Specification (a)65B11261-3, or 65B11261- 5, or 65B11261-6 Pin265B11261-3, or 65B11261-5, or 65B11261-6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 54 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 55 Group 6: NotesExisting Part NumberNameQTYPart Number / Specification (g)-Washer, Flat-Metal, Round (Shim)28MS15795-825 (g) (h)-Raw Stock, 2.250 inches diameter by 0.165 inches thick. Passivated. (Shim) CRES per ASTM A380 (c) (f)-Copper Beryllium Alloy, Condition AT - 5.0 inch (max) diameter bar stock -QQ-C-530 (d)-Stainless Steel, Heat Treated to 180ksi - 5.0 inch (max) diameter bar stock -17-4PH per AMS 5643 (e)-Aluminum Nickel Bronze - 5.0 inch (max) diameter bar stock -Al-Ni-Br per AMS 4640 (b)-Sealant1 PtBMS 5-95 (b)-Primer1 PtBMS 10-11, Type I (b)-Corrosion Inhibiting Compound1 PtBMS 3-23, Type II (a) These new parts, as applicable, are necessary if each removed pin is found to be corroded. Use the same part number of pin that was removed. The quantity given is for each airplane. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) Used to make new higher interference fit end fitting lug bore bushings in accordance with FIGURE 19. (d) Used to make new higher interference fit end fitting bolt hole bushings in accordance with FIGURE 20. (e) This material can be used as an alternative to QQ-C-530 Copper Beryllium Alloy to make new higher interference fit lug bore bushings. (f) This material can be used as an alternative to 17-4PH Stainless Steel to make new higher interference fit bolt hole bushings. (g) This part is only necessary if corrosion was found around the bolt holes of the end fittings and face cuts were made. The quantity given is the quantity necessary for each bolt hole on each surface of each end fitting for each airplane. Adjust the quantity as necessary. (h) This material can be used as an alternative to make equivalent 'shims' if the MS15795-825 washers are not available. 3. Parts Modified and Reidentified The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the number of parts changed on each airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 55 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 56 Group 1: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)-End Fitting Assy265B01042-1 (a) (b) (c)-265B01042-2 (a) (b) (d)-End Fitting Assy265B01042-9 (a) (b) (d)-265B01042-10 (a) (b) (e)-End Fitting Assy265B01042-13 (a) (b) (e)-265B01042-14 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. (c) The 65B01042-2 end fitting is opposite to the 65B01042-1 end fitting. (d) The 65B01042-10 end fitting is opposite to the 65B01042-9 end fitting. (e) The 65B01042-14 end fitting is opposite to the 65B01042-13 end fitting. The 65B01042- 13/-14 end fittings were created for spares usage only as replacements to supersede the obsolete 65B01042-1/-2 and 65B01042-9/-10 end fittings. Thus it is possible that operators could have installed the 65B01042-13/-14 end fittings on airplanes since delivery. Group 2: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)-End Fitting Assy265B14472-8 (a) (b) (c)-End Fitting Assy265B14472-27 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. (c) The 65B14472-27 end fitting was created for spares usage only as a replacement to super- sede the obsolete 65B14472-8 end fitting. Thus it is possible that operators could have in- stalled the 65B14472-27 end fittings on airplanes since delivery. Group 3: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)-End Fitting Assy265B14472-1 (a) (b) (c)-265B14472-2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 56 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 57 Group 3: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (d)-End Fitting Assy265B14472-25 (a) (b) (d)-265B14472-26 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. (c) The 65B14472-2 end fitting is opposite to the 65B14472-1 end fitting. (d) The 65B14472-26 end fitting is opposite to the 65B14472-25 end fitting. The 65B14472- 25/-26 end fittings have the intent of Boeing service bulletin 747-57-2244 in their design and were installed during production on Group 4 airplanes, but were made applicable for spares usage for these airplanes as replacements to supersede the obsolete 65B14472- 1/-2 end fittings. Thus it is possible that operators could have installed the 65B14472-25/- 26 end fittings on airplanes since delivery. Group 4: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)-End Fitting Assy265B14472-25 (a) (b) (c)-265B14472-26 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. (c) The 65B14472-26 end fitting is opposite to the 65B14472-25 end fitting. Group 5: NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)-End Fitting Assy265B14472-23 (a) (b) (c)-265B14472-24 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. (c) The 65B14472-24 end fitting is opposite to the 65B14472-23 end fitting. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 57 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 58 Group 6: NotesNew Part NumberNameQTYExisting Part Number (a) (b)-End Fitting Assy2112U1701-1 (a) Make the change given in this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the repair or change given in this service bulletin was made. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares It is recommended that operators check their records to find the age of serviceable end fittings and the number of the flight cycles they have accumulated. Once this data is known, use the compliance times in accordance with Tables 1 thru 12 of Paragraph 1.E., Compliance to evaluate the conditions and do the applicable actions. Each serviceable end fitting must be changed in accordance with 'Part 7 - Wing Landing Gear (WLG) Support Beam End Fitting - Higher Interference Fit Bushings Installation' of Paragraph 3., Accomplishment Instructions, before it is installed on an airplane. To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability. The QTY given is for each WLG support beam end fitting. QTYNamePart Number / Specification 28 (max) Washer, Flat-Metal, Round (Shim) MS15795-825 Bar Stock, 2.250 inches diameter by 0.165 inches thick. Passivated. (Shim) CRES per ASTM A380 -Copper Beryllium Al- loy, Condition AT - 5.0 inch (max) diame- ter bar stock QQ-C-530 -Stainless Steel, Heat Treated to 180ksi - 5.0 inch (max) diame- ter bar stock 17-4PH per AMS 5643 -Aluminum Nickel Bronze - 5.0 inch (max) diameter bar stock Al-Ni-Br per AMS 4640 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 58 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 59 E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary and a Borescope or Videoscope is recommended for the detailed (DET) inspection of the end fittings. Examine operator tool supply to make sure all necessary tools are available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 12, 2009 747-57A2331 59 of 186 BOEING SERVICE BULLETIN 747-57A2331 ALERTALERT ### Page 60 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 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