# Boeing Alert Service Bulletin 747-53A2808: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2014-0774; AD 2016-06-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-53A2808](https://openairdocs.org/service-documents/boeing/747-53a2808.md) - Title as filed: U.S. DOT/FAA - Service Bulletin 747-53A2808-00 - Pages: 93 - PDF: https://openairdocs.org/files/sha256/b0/58/b058ef43bad80d5e30afb4b22968491d681d0a9be4815a7985287cafaf974772 - Page: https://openairdocs.org/service-documents/boeing/747-53a2808/file/b058ef43bad8 ## 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: 747-53A2808 Original Issue: November 30, 2012 ATA System: 5311 SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2012 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management Company. Original Issue: November 30, 2012 747-53A2808 1 of 93 3.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 2 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary ...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity ................................................ 9 1. Airplanes ............................................. 9 2. Spares Affected ........................................ 1 0 B. Concurrent Requirements ...................................... 1 0 C. Reason ................................................ 1 1 D. Description .............................................. 1 1 E. Compliance .............................................. 1 2 F. Approval ............................................... 1 5 G. Manpower .............................................. 1 6 H. Weight and Balance Changes .................................... 1 6 I. Electrical Load Data ......................................... 1 6 J. References .............................................. 1 7 1. Existing Data: ......................................... 1 7 2. Data Supplied with this Service Bulletin: ........................... 1 7 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8 K. Publications Affected ........................................ 1 8 L. Interchangeability and Intermixability of Parts ........................... 1 8 M. Software Accomplishment Summary ................................ 1 9 2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 1 C. Parts Necessary for Each Airplane ................................. 2 1 1. Kits/Parts: ........................................... 2 1 2. Parts and Materials Supplied by the Operator: ........................ 3 6 3. Parts Modified and Reidentified: ............................... 3 6 4. Parts Removed and Not Replaced: .............................. 3 6 D. Parts Necessary to Change Spares ................................. 3 6 E. Special Tooling - Price and Availability ............................... 3 6 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 6 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7 A. GENERAL INFORMATION ..................................... 3 7 B. WORK INSTRUCTIONS ....................................... 3 8 FIGURE 1: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 260 BULKHEAD ....... 4 8 FIGURE 2: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 340 BULKHEAD ....... 5 0 FIGURE 3: REMOVAL OF TOP PANEL [Group 1] ............................ 5 2 FIGURE 4: LEFT SIDE PANEL REPLACEMENT [Group 1] ....................... 5 5 FIGURE 5: RIGHT SIDE PANEL REPLACEMENT [Group 1] ....................... 5 8 FIGURE 6: INSTALLATION OF TOP PANEL [Group 1] .......................... 6 1 FIGURE 7: RESTORATION AT NOSE WHEEL WELL STA 340 BULKHEAD .............. 6 4 FIGURE 8: RESTORATION AT NOSE WHEEL WELL STA 260 BULKHEAD .............. 6 6 FIGURE 9: REMOVAL OF TOP PANEL COMPONENTS [Group 2] ................... 6 8 FIGURE 10: LEFT SIDE PANEL REPLACEMENT [Group 2] ....................... 7 1 FIGURE 11: RIGHT SIDE PANEL REPLACEMENT ............................ 7 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 3 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 4 FIGURE 12: INSTALLATION OF NEW TOP PANEL COMPONENTS [Group 2] ............. 7 7 FIGURE 13: POST MODIFICATION INSPECTION - SIDE PANEL WEB EXTERNAL DETAILED INSPECTION .................................................. 8 0 FIGURE 14: POST MODIFICATION INSPECTION - TOP PANEL WEB EXTERNAL DETAILED INSPECTION .................................................. 8 3 FIGURE 15: POST MODIFICATION INSPECTION - TOP AND SIDE PANEL STIFFENER INTERNAL DETAILED AND HFEC INSPECTIONS ............................ 8 6 APPENDIX A: NOSE WHEEL WELL MODIFICATION - SUGGESTED SEQUENCE OF STEPS ..... 8 9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 4 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 5 Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-53A2808Original Issue: November 30, 2012 ATA System: 5311 SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND Accomplishment of the modification in this service bulletin will ensure the structural integrity of the nose wheel well top and side panels. Widespread Fatigue Damage (WFD) in the nose wheel well top and side panels could result in a depressurization event with damage significant enough to adversely affect the structural integrity of the fuselage. Boeing has received 16 reports of cracking in the nose wheel well top panel and side panel webs and/or stiffeners. One airplane lost pressurization due to cracking in a nose wheel well side panel. Boeing has determined that all the cracks were caused by fatigue. The nose wheel well top and side panels have been determined to be structure that is susceptible to develop WFD. Although loss of pressurization due to cracks in the nose wheel well structure is not necessarily an airplane safety concern, WFD could result in a nose wheel well depressurization event severe enough to reduce the structural integrity of the fuselage. Due to the concern of WFD in the nose wheel well top and side panel structure, Boeing recommends that operators accomplish the modification given in this service bulletin. Group 1: This service bulletin gives instructions to modify the nose wheel well top panel and side panels by replacing the existing webs, support beams, and stiffeners with improved parts. The modifications in this service bulletin will eliminate the concern of WFD in the nose wheel well. Group 2: This service bulletin gives instructions to modify the nose wheel well side panels by replacing the existing webs, support beams, and stiffeners with improved parts. This service bulletin will also modify the nose wheel well top panel by replacing the existing support beams and stiffeners with improved parts. The modifications in this service bulletin will eliminate the concern of WFD in the nose wheel well. For more information about WFD, refer to Boeing Service Letter 747-SL-53-088. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 5 of 93 ### Page 6 The modification given in this service bulletin terminates the repetitive inspections given in Service Bulletin 747-53A2465. Boeing Service Related Problem (SRP) 747-SRP-53-0339 is related to this Service Bulletin. Boeing Fleet Team Digest articles 747 FTD 53-04002 and 747 FTD 53-12006 are related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION (PRR 85901-99RS) Open the nose landing gear doors, and jack the airplane. Remove the nose landing gear, nose landing gear doors, nose landing gear door actuator, passenger seats, floor covering, floor panels, and insulation as necessary to get access to the upper, left, and right hand webs in the nose wheel well. Group 1: Modify the nose wheel well top and side panels by replacing the existing webs, support beams, and stiffeners with improved parts. Group 2: Modify the nose wheel well side panels by replacing the existing webs, support beams, and stiffeners with improved parts. Modify the nose wheel well top panel by replacing the existing support beams and stiffeners with improved parts. Install all parts removed for access at completion of the modification, and return the airplane to a serviceable condition. Do post-modification detailed and high frequency eddy current (HFEC) inspections at the time specified in Paragraph 1.E., Compliance. If any crack is found, contact Boeing for repair instructions and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 6 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 7 EFFECTIVITY 747-400/400F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service bulletin. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the modification given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 7 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 8 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT 00000000000000 GROUP 1: MODIFY THE TOP PANEL BY REPLACING THE EXISTING WEB, SUPPORT BEAMS, AND STIFFENERS WITH IMPROVED PARTS GROUP 2: MODIFY THE TOP PANEL BY REPLACING THE EXISTING SUPPORT BEAMS AND STIFFENERS WITH IMPROVED PARTS. STA 280 STA 400 STA 340 STA 400 BL GROUP 1-2: MODIFY THE LEFT AND RIGHT SIDE PANELS BY REPLACING IMPROVED PARTSENERS WIN INSIDE NOSE WHEEL WELL LEFT SIDE SHOWN 2178510 RIGHT SIDE OPPOSITE Original Issue: November 30, 2012 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2808 Work - See page 1 for details. 8 of 93 ### Page 9 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2808 Original Issue: November 30, 2012 ATA System: 5311 SUBJECT: FUSELAGE - Main Frame - Nose Wheel Well Side and Top Panel - Web and Stiffener Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Refer to PRR 85901-99RS for data about this change. DESCRIPTIONCONFIGURATIONGROUP 747-400 airplanes, line numbers 1308 - 1419.-1 747-400F airplanes, line numbers 1315 - 1419.-2 Airplane Models: 747-400, 747-400F GroupVariable Number 1RF001 - RF006 2RL421 - RL436 2RL451 - RL456 2RL461 - RL462 2RL471 - RL481 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 9 of 93 ### Page 10 GroupVariable Number 2RL491 - RL492 2RL501 - RL502 2RL511 - RL516 2RL521 - RL522 2RL531 - RL534 2RL551 2RL561 - RL568 2RL571 - RL572 2RL576 - RL577 2RL579 2RL581 - RL586 2RL671 - RL675 2RL681 - RL684 1RM030 1RM053 1RM401 - RM403 1RM426 1RM431 1RM441 - RM443 1RM445 2RM859 2RM863 2RM877 - RM880 2RM888 - RM890 2RM906 2. Spares Affected None. B. Concurrent Requirements None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 10 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 11 C. Reason Accomplishment of the modification in this service bulletin will ensure the structural integrity of the nose wheel well top and side panels. Widespread Fatigue Damage (WFD) in the nose wheel well top and side panels could result in a depressurization event with damage significant enough to adversely affect the structural integrity of the fuselage. Boeing has received 16 reports of cracking in the nose wheel well top panel and side panel webs and/or stiffeners. One airplane lost pressurization due to cracking in a nose wheel well side panel. Boeing has determined that all the cracks were caused by fatigue. The nose wheel well top and side panels have been determined to be structure that is susceptible to develop WFD. Although loss of pressurization due to cracks in the nose wheel well structure is not necessarily an airplane safety concern, WFD could result in a nose wheel well depressurization event severe enough to reduce the structural integrity of the fuselage. Due to the concern of WFD in the nose wheel well top and side panel structure, Boeing recommends that operators accomplish the modification given in this service bulletin. Group 1: This service bulletin gives instructions to modify the nose wheel well top panel and side panels by replacing the existing webs, support beams, and stiffeners with improved parts. The modifications in this service bulletin will eliminate the concern of WFD in the nose wheel well. Group 2: This service bulletin gives instructions to modify the nose wheel well side panels by replacing the existing webs, support beams, and stiffeners with improved parts. This service bulletin will also modify the nose wheel well top panel by replacing the existing support beams and stiffeners with improved parts. The modifications in this service bulletin will eliminate the concern of WFD in the nose wheel well. For more information about WFD, refer to Boeing Service Letter 747-SL-53-088. The modification given in this service bulletin terminates the repetitive inspections given in Service Bulletin 747-53A2465. Boeing Service Related Problem (SRP) 747-SRP-53-0339 is related to this Service Bulletin. Boeing Fleet Team Digest articles 747 FTD 53-04002 and 747 FTD 53-12006 are related to this service bulletin. D. Description Open the nose landing gear doors, and jack the airplane. Remove the nose landing gear, nose landing gear doors, nose landing gear door actuator, passenger seats, floor covering, floor panels, and insulation as necessary to get access to the upper, left, and right hand webs in the nose wheel well. Group 1: Modify the nose wheel well top and side panels by replacing the existing webs, support beams, and stiffeners with improved parts. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 11 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 12 Group 2: Modify the nose wheel well side panels by replacing the existing webs, support beams, and stiffeners with improved parts. Modify the nose wheel well top panel by replacing the existing support beams and stiffeners with improved parts. Install all parts removed for access at completion of the modification, and return the airplane to a serviceable condition. Do post-modification detailed and high frequency eddy current (HFEC) inspections at the time specified in Paragraph 1.E., Compliance. If any crack is found, contact Boeing for repair instructions and do the repair. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 113, 114747-400 Group 2: Affected Maintenance Zones ZoneModel 113, 114747-400F E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2006-22-15 is related to this service bulletin. Table 1: Nose Wheel Well Modification Compliance TimeActionCondition Before 22,000 total flight cycles. (a) Do the nose wheel well modification (and detailed inspection of attaching structural elements) in ac- cordance with paragraph 3.B., Work Instructions, PART 2. All airplanes. Before further flight.Contact Boeing for repair instructions, and do the re- pair. Any crack found during detailed inspections of at- taching structural elements while accomplishing the modification. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 12 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 13 Table 1: Nose Wheel Well Modification Compliance TimeActionCondition (a) Boeing recommends that the modification not be installed prior to 15,000 total flight cycles. If the modification is installed prior to 15,000 total flight cycles, then Post Modification Inspections will be required prior to 35,000 total flight cycles. 35,000 total flight cycles is the Limit of Validity (LOV) for the affected airplanes. Group 1: Table 2: Nose Wheel Well - Post Modification Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 20,000 flight cycles after modifi- cation in accor- dance with para- graph 3.B., Work Instructions, PART 2. Do an external detailed inspection for cracks in the side panel webs, and do internal detailed and high frequency eddy cur- rent (HFEC) inspections for cracks in the top and side panel stiffeners in accordance with para- graph 3.B., Work Instruc- tions, PART 6. All airplanes. Do an external detailed inspection for cracks in the top panel web in ac- cordance with paragraph 3.B., Work Instructions, PART 7. -Before further flight. Contact Boeing for repair instructions, and do the repair. Any crack found. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 13 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 14 Group 1: Table 2: Nose Wheel Well - Post Modification Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition 6,000 flight cycles.-Repeat the external de- tailed inspection for cracks in the side panel webs, and repeat the in- ternal detailed and HFEC inspections for cracks in the top and side panel stiffeners in accordance with paragraph 3.B., Work Instructions, PART 6. No crack found, or crack has been repaired. 6,000 flight cycles.-Repeat the external de- tailed inspection for cracks in the top panel web in accordance with paragraph 3.B., Work In- structions, PART 7. Group 2: Table 3: Nose Wheel Well - Post Modification Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 20,000 flight cycles after modifi- cation in accor- dance with para- graph 3.B., Work Instructions, PART 2. Do an external detailed inspection for cracks in the side panel webs, and do internal detailed and high frequency eddy cur- rent (HFEC) inspections for cracks in the top and side panel stiffeners in accordance with para- graph 3.B., Work Instruc- tions, PART 6. All airplanes. Do an external detailed inspection for cracks in the top panel web in ac- cordance with paragraph 3.B., Work Instructions, PART 7. -Before further flight. Contact Boeing for repair instructions, and do the repair. Any crack found. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 14 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 15 Group 2: Table 3: Nose Wheel Well - Post Modification Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition 6,000 flight cycles.-Repeat the external de- tailed inspection for cracks in the side panel webs, and repeat the in- ternal detailed and HFEC inspections for cracks in the top and side panel stiffeners in accordance with paragraph 3.B., Work Instructions, PART 6. No crack found, or crack has been repaired. 3,000 flight cycles.-Repeat the external de- tailed inspection for cracks in the top panel web in accordance with paragraph 3.B., Work In- structions, 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. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the accomplishment of the modification action with the corresponding compliance times specified in paragraph 1.E., "Compliance", of Service Bulletin 747-53A2808, Original Issue, as a Method of Compliance (MOC) to the actions with corresponding compliance times required by paragraph (o) of AD 2006-22-15. All provisions of AD 2006-22-15 that are not specifically referenced in the above statement remain fully applicable and must be complied with accordingly. Modification in accordance with this service bulletin is consistent with AD 2006-22-15, except AD 2006-22-15 paragraph (o) requires top panel replacement for all airplanes. Boeing analysis, however, has shown that top panel web replacement is not required for Group 2 airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 15 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 16 G. Manpower The table below shows an estimate of the task-hours necessary to do this modification for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine 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 15604Open Access 30012004Change 20804Close Access 3.06.02Test 3381346TOTAL FOR EACH AIRPLANE Group 2: Elapsed HoursTask-HoursNumber of Per- sons Task 14.5584Open Access 2008004Change 19.5784Close Access 3.06.02Test 237942TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Due to this service bulletin usually being accomplished as part of a heavy maintenance check of the airplane, Boeing recommends that the operator should weigh the airplane and determine the center of gravity after completing this work, and before return to service. The actual data will be recorded and placed in Chapter 2 of the Weight and Balance Manual. I. Electrical Load Data Not applicable. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 16 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 17 J. References 1. Existing Data: a. Engineering Change Memo PRR 85901-99RS b. Boeing Service Bulletin 747-00-2158, 747-53A2465, 747-53A2562 c. Boeing Service Letter 747-SL-00-018, 747-SL-53-088 d. Boeing Service Related Problem (SRP) 747-SRP-53-0339 e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-22-15 f. Service Bulletin Index D6-30300 g. Standard Overhaul Practices Manual (SOPM) 20-50-01 h. 747 Fleet Team Digest (FTD) 53-04002, 53-12006 i. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 j. 747-400 Aircraft Maintenance Manual (AMM) 05-51-08, 07-11-01, 09-11-00, 12-15-05, 20-11-05, 24-22-00, 25-25-01, 25-27-01, 25-28-03, 25-57-01, 25-57-04, 29-11-00, 32-00-30, 32-09-03, 32-21-01, 32-22-01, 32-22-03, 32-22-05, 32-34-05, 32-34-06, 32-34-07, 32-34-08, 32-34-10, 32-34-14, 32-34-15, 32-35-04, 32-45-05, 33-31-00, 53-21-02 2. Data Supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No -B1Kit - Nose Wheel Well Modification, STA 260 - STA 340 141U1192 --10 --11 --12 --13 --14 --15 --16 --17 -A5 -B8 --PSDL -AKPLTop Panel Modification - Kit (Passenger)141U1192-13 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 17 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 18 ADCNDCN/REVSheetTitleDrawing No -AKPLTop Panel Modification - Kit (Freighter)141U1192-15 -AKPLLeft Side Panel Modification - Kit (Passen- ger) 141U1192-17 -AKPLRight Side Panel Modification - Kit (Passen- ger) 141U1192-18 -AKPLLeft Side Panel Modification - Kit (Freighter)141U1192-19 -AKPLRight Side Panel Modification - Kit (Freighter) 141U1192-20 -AKPLNose Wheel Well Modification, STA 260 to STA 340 - Top Kit (Passenger) 141U1192-3 -AKPLTop Panel Modification Fasteners - Kit (Passenger) 141U1192-39 -AKPLNose Wheel Well Modification, STA 260 to STA 340 - Top Kit (Freighter) 141U1192-4 -AKPLSide Panel Modification Fasteners - Kit (Passenger) 141U1192-41 -AKPLTop Panel Modification Fasteners - Kit (Freighter) 141U1192-43 -AKPLSide Panel Modification Fasteners - Kit (Freighter) 141U1192-45 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. K. Publications Affected 1. Publications: Chapter-SectionPublication 32-34747 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. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 18 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 19 M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 19 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 20 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 20 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT BLANK PAGE ### Page 21 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The are kits subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the date of this Service Bulletin (US Dollars) ROLT as of the date of this Ser- vice Bulletin (Cal- endar Days) NameKit Number (c)(c)Nose Wheel Well Modification, STA 260 to STA 340 - Top Kit 141U1192-3 (a) (c)(c)Nose Wheel Well Modification, STA 260 to STA 340 - Top Kit 141U1192-4 (b) (a) Group 1 (Passenger). (b) Group 2 (Freighter). (c) Boeing Spares does not have a stocking plan for this top kit. Therefore, the top kit will not available at the time of release of this service bulletin. Reorder Lead Time (ROLT) and Price information is not provided. Operators should contact Boeing and order parts at least 2 years prior to planned modification incorporation to ensure that parts can be made available. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes 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: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 21 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 22 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -4-3 (a)NOSE WHEEL WELL MODIFICA- TION, STA 260 TO STA 340 - TOP KIT .-141U1192-3 (b)NOSE WHEEL WELL MODIFICA- TION, STA 260 TO STA 340 - TOP KIT -.141U1192-4 TOP PANEL MOD- IFICATION - KIT .1141U1192-13 TOP PANEL MOD- IFICATION - KIT 1.141U1192-15 LEFT SIDE PANEL MODIFICATION - KIT .1141U1192-17 RIGHT SIDE PAN- EL MODIFICA- TION - KIT .1141U1192-18 LEFT SIDE PANEL MODIFICATION - KIT 1.141U1192-19 RIGHT SIDE PAN- EL MODIFICA- TION - KIT 1.141U1192-20 TOP PANEL MOD- IFICATION FAS- TENERS - KIT .1141U1192-39 SIDE PANEL MODIFICATION FASTENERS - KIT .1141U1192-41 TOP PANEL MOD- IFICATION FAS- TENERS - KIT 1.141U1192-43 SIDE PANEL MODIFICATION FASTENERS - KIT 1.141U1192-45 (a) Group 1. (b) Group 2. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 22 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 23 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 TOP PANEL MOD- IFICATION - KIT .....-141U1192-13 TOP PANEL MOD- IFICATION - KIT ....-.141U1192-15 LEFT SIDE PANEL MODIFICATION - KIT ...-..141U1192-17 RIGHT SIDE PAN- EL MODIFICA- TION - KIT ..-...141U1192-18 LEFT SIDE PANEL MODIFICATION - KIT .-....141U1192-19 RIGHT SIDE PAN- EL MODIFICA- TION - KIT -.....141U1192-20 WEB - ROUGH MACHINED 1111..141U1193-1 WEB.....1141U1193-3 BEAM....11141U1193-4 BEAM....66141U1193-5 BEAM.....1141U1193-6 BEAM.....1141U1193-7 BEAM.....1141U1193-8 BEAM....22141U1193-9 BEAM....22141U1193-10 ANGLE....22141U1193-11 ANGLE....22141U1193-12 BEAM.....1141U1193-13 BEAM.....1141U1193-14 BEAM....1.141U1193-15 ANGLE....11141U1193-16 BEAM....77141U1193-17 BEAM....88141U1193-18 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 23 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 24 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 BEAM.....1141U1193-19 CLIP....11141U1193-20 CLIP....55141U1193-21 BEAM3333..141U1193-23 ANGLE111111141U1193-25 BEAM2222..141U1193-27 BEAM1111..141U1193-29 BEAM.2.2..141U1193-31 BEAM2.2...141U1193-32 BEAM.7.7..141U1193-33 BEAM7.7...141U1193-34 ANGLE....1414141U1193-35 BEAM.1.1..141U1193-37 BEAM1.1...141U1193-38 BEAM.1.1..141U1193-39 BEAM1.1...141U1193-40 BEAM.1.1..141U1193-41 BEAM1.1...141U1193-42 BEAM.3.3..141U1193-43 BEAM3.3...141U1193-44 BEAM.1.1..141U1193-45 BEAM1.1...141U1193-46 BEAM.7.7..141U1193-47 BEAM8.8...141U1193-48 BEAM...1..141U1193-49 BEAM.1.1..141U1193-51 BEAM1.1...141U1193-52 BEAM.1.1..141U1193-53 BEAM1.1...141U1193-54 BEAM....1.141U1193-55 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 24 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 25 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 BEAM....2.141U1193-56 BEAM....1.141U1193-57 FILLER11....141U1193-58 FILLER.1....141U1193-59 FILLER.1....141U1193-60 SPLICE ANGLE....5.141U1193-61 BEAM....1.141U1193-62 BEAM....1.141U1193-63 BEAM....1.141U1193-64 BEAM....1.141U1193-65 BEAM....1.141U1193-66 BEAM....1.141U1193-67 BEAM....1.141U1193-68 (a)TRIPLER2222..141U1195U18 (a)TRIPLER2222..141U1195U19 (a)TRIPLER3333..141U1195U20 (a)TRIPLER4444..141U1195U21 (a)TRIPLER5555..141U1195U22 (a)TRIPLER2222..141U1195U23 STIFFENER.....3141U5190-219 STIFFENER.....2141U5190-220 STIFFENER....1.141U5385-34 (a)STIFFENER....1.141U5385U353 (a)STIFFENER....1.141U5385U391 (a)STIFFENER....1.141U5385U392 (a)STIFFENER....1.141U5385U393 (a)STIFFENER....1.141U5385U394 (a)ANGLE - SIDE.....165B07941U145 (a)ANGLE - SIDE.....165B07941U146 (a)ANGLE-SIDE.....165B07941U147 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 25 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 26 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 (a)ANGLE-SIDE.....165B07941U148 (a)ANGLE-FWD.....165B07941U163 (a)GUSSET-AFT.....265B07941U21 (a)CLIP....2265B07941U60 (a)GUSSET-FWD.....165B07941U76 (a)BEAM1.1...65B07942U100 (a)CLIP.1.1..65B07942U103 (a)CLIP1.1...65B07942U104 (a)CLIP..22..65B07942U113 (a)ANGLE.3.3..65B07942U127 (a)ANGLE3.3...65B07942U128 (a)CHORD.1.1..65B07942U15 (a)BEAM.1.1..65B07942U151 (a)BEAM1.1...65B07942U152 (a)CHORD1.1...65B07942U16 (a)CLIP1111..65B07942U329 (a)CLIP.1.1..65B07942U47 (a)CLIP1.1...65B07942U48 (a)CLIP.1.1..65B07942U49 (a)CLIP1.1...65B07942U50 (a)CHORD.1....65B07942U519 (a)CHORD1.....65B07942U520 (a)CLIP.2....65B07942U545 (a)CLIP2.....65B07942U546 (a)CHORD...1..65B07942U67 (a)CHORD..1...65B07942U68 (a)CHORD.1.1..65B07942U71 (a)CHORD1.1...65B07942U72 (a)CHORD.1.1..65B07942U75 (a)CHORD1.1...65B07942U76 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 26 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 27 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 (a)BEAM.1.1..65B07942U85 (a)BEAM1.1...65B07942U86 (a)BEAM.1.1..65B07942U87 (a)BEAM1.1...65B07942U88 (a)CLIP.1.1..65B07942U89 (a)CLIP1.1...65B07942U90 (a)CLIP.1.1..65B07942U93 (a)CLIP1.1...65B07942U94 (a)BEAM.1.1..65B07942U95 (a)CLIP1.1...65B07942U96 (a)BEAM.1.1..65B07942U97 (a)CLIP1.1...65B07942U98 (a)BEAM.1.1..65B07942U99 FILLER11....65B07953-544 (a)ANGLE.1.1..65B07953U17 (a)ANGLE1.1...65B07953U18 (a)ANGLE.1.1..65B07953U19 (a)ANGLE1.1...65B07953U20 (a)FITTING, LS.1.1..65B07953U229 (a)FITTING, RS1.1...65B07953U230 (a)FITTING.1.1..65B07953U3 (a)FITTING1.1...65B07953U4 (a)FITTING.1....65B07953U541 (a)FITTING1.....65B07953U542 (a)FILLER11....65B07953U543 (a)FILLER11....65B07953U549 (a)FITTING...1..65B07953U7 (a)FITTING..1...65B07953U8 FITTING ASSY...1..65B11111-501 FITTING ASSY.1....65B11111-503 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 27 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 28 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 (a)ANGLE.1....65B11784U507 (a)ANGLE1.....65B11784U508 (a)ZEE.....165B13792U59 (a)ZEE.....165B13792U60 (a)STRAP.....265B13797U501 (a)STRAP.....265B13797U502 (a)FITTING.1....65B14749U7 (a)FITTING1.....65B14749U8 (a)CLIP.2....69B13450Y5 (a)CLIP2.....69B13450Y6 (a)CORNER FITTING...1..69B17168U1 (a)CORNER FITTING..1...69B17168U2 FILLER....2.BACF3F005L008NN FILLER, FLAT11....BACF3F008B104NN FILLER, FLAT, ALUMINUM AL- LOY 22....BACF3F010B010NN FILLER, FLAT.1....BACF3F010B104NN FILLER, RECTAN- GULAR ....5.BACF3H09RF085AN FILLER, RECTAN- GULAR ....22BACF3H10JM020BN FILLER, RECTAN- GULAR .....3BACF3H10RM020BN FILLER, RECTAN- GULAR ....3.BACF3H11RM020BN FILLER16161616..BACF3T01D07-07 FILLER-TAPERED....3.BACF3T01E04-06 FILLER....6.BACF3T01E04-08 FILLER.....5BACF3T01E05-07 FILLER - TA- PERED ....5.BACF3T01E05-08 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 28 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 29 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-15-13 FILLER, TAPERED....3030BACF3T01EE08- 08 FILLER-TAPERED....2.BACF3T01F06- 07B TAPERED FILLER....1.BACF3T01F06-08 FILLER5555.5BACF3T01G07-07 FILLER, TAPERED....1.BACF3T01H08-08 TAPERED FILLER....1.BACF3T01H08-15 FILLER....1.BACF3T01L11-08 TAPERED FILLER....2.BACF3T01L12-08 FILLER, TAPERED3333..BACF3T02F07-08 FILLER2222..BACF3T02G08-08 SHIM,LAMINATED....3030BACS40R008B008F SHIM, LAMINAT- ED .....2BACS40R010C023F SHIM-LAMINATED.....2BACS40R013B013F (a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed in accordance with the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 747-SL-00-018 for more information. ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 TOP PANEL MOD- IFICATION FAS- TENERS - KIT ...-141U1192-39 SIDE PANEL MODIFICATION FASTENERS - KIT ..-.141U1192-41 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 29 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 30 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 TOP PANEL MOD- IFICATION FAS- TENERS - KIT .-..141U1192-43 SIDE PANEL MODIFICATION FASTENERS - KIT -...141U1192-45 (a)BOLT4...BACB30FP8A3 (a)BOLT, HEX HEAD...2BACB30LM4-9 (a)BOLT10...BACB30MC6A3 (a)BOLT8...BACB30MC6A4 (a)BOLT60...BACB30MC6A6 (a)BOLT8...BACB30MC6A9 (a)BOLT, PROTRUD- ING HD ..2.BACB30MY6K4X (a)BOLT, PROTRUD- ING HD 6...BACB30MY8K10X (a)BOLT, PROTRUD- ING HD 22.2BACB30MY8K11X (a)BOLT, PROTRUD- ING HD ...2BACB30MY8K12X (a)BOLT, PROTRUD- ING HD ...8BACB30MY8K13X (a)BOLT, PROTRUD- ING HD ...2BACB30MY8K15X (a)BOLT, PROTRUD- ING HD ...2BACB30MY8K16X (a)BOLT, PROTRUD- ING HD ...2BACB30MY8K17X (a)BOLT, PROTRUD- ING HD ...2BACB30MY8K20X (a)BOLT, PROTRUD- ING HD 16.1616BACB30MY8K4X (a)BOLT, PROTRUD- ING HD 12.1212BACB30MY8K5X Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 30 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 31 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 (a)BOLT, PROTRUD- ING HD ...8BACB30MY8K6X (a)BOLT, PROTRUD- ING HD ...6BACB30MY8K7X (a)BOLT, PROTRUD- ING HD ...14BACB30MY8K8X (a)BOLT, PROTRUD- ING HD ..1010BACB30MY8K9X (a)BOLT, HEX HEAD...8BACB30NM4K18 (a)BOLT, HEX HEAD.5.5BACB30NR4K10 (a)BOLT..33BACB30NR4K11 (a)BOLT, HEX HEAD5...BACB30NR4K12 (a)BOLT3...BACB30NR4K15 (a)BOLT, HEX HEAD.5..BACB30NR4K9 (a)BOLT, 100 DEG HEX DR ..3.BACB30NW6K3X (a)BOLT, 100 DEG HEX DR 12...BACB30NW8K14X (a)BOLT, PROTRUD- ING HD 1..1BACB30NX5HK5 (a)BOLT, PROTRUD- ING HD 3.3.BACB30NX5HK6 (a)HEX DRIVE BOLT...6BACB30NX6K10 (a)BOLT, PROTRUD- ING HD .9.9BACB30NX6K10X (a)BOLT...4BACB30NX6K11 (a)BOLT, PROTRUD- ING HD .6..BACB30NX6K11X (a)BOLT, PROTRUD- ING HD ...4BACB30NX6K12X (a)BOLT, PROTRUD- ING HD 6...BACB30NX6K2 (a)BOLT, PROTRUD- ING HD .2..BACB30NX6K3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 31 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 32 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 (a)BOLT, PROTRUD- ING HD 2222BACB30NX6K3X (a)BOLT, PROTRUD- ING HD .2..BACB30NX6K3Y (a)BOLT, PROTRUD- ING HD .85.85BACB30NX6K4 (a)BOLT, PROTRUD- ING HD 84848484BACB30NX6K4X (a)BOLT, PROTRUD- ING HD .2..BACB30NX6K4Y (a)BOLT4444.44BACB30NX6K5 (a)BOLT, PROTRUD- ING HD 82828282BACB30NX6K5X (a)BOLT53..53BACB30NX6K6 (a)BOLT, PROTRUD- ING HD 60606060BACB30NX6K6X (a)HI-LOK...47BACB30NX6K7 (a)BOLT, PROTRUD- ING HD .50.50BACB30NX6K7X (a)BOLT, PROTRUD- ING HD ...20BACB30NX6K8 (a)BOLT, PROTRUD- ING HD 36363636BACB30NX6K8X (a)BOLT...19BACB30NX6K9 (a)BOLT, PROTRUD- ING HD .6.6BACB30NX6K9X (a)BOLT, PROTRUD- ING HD 2...BACB30NX8K10X (a)BOLT, PROTRUD- ING HD .4..BACB30NX8K12X (a)HI-LOK..4.BACB30NX8K3 (a)BOLT, PROTRUD- ING HD 11.11.BACB30NX8K5X (a)BOLT..4.BACB30NX8K6 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 32 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 33 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 (a)BOLT, PROTRUD- ING HD 11...BACB30NX8K6X (a)BOLT, PROTRUD- ING HD ..6.BACB30NX8K7X (a)BOLT, 100 DEG HEX DR ...3BACB30YP5K4 (a)BOLT, 100 DEG HEX DR .3..BACB30YP6K3 COLLAR.4..BACC30AC6 COLLAR.33.33BACC30AG6 COLLAR, PRELOAD 1.11BACC30BH5 COLLAR575575575575BACC30BH6 COLLAR323232.BACC30BH8 COLLAR, SHEAR...3BACC30BL5 COLLAR.3..BACC30BL6 COLLAR..5.BACC30M6 COLLAR95959595BACC30M8 NUT, SPACER PLATE .1..BACN10GH3A10 NUT,SELF-LOCK- ING ...2BACN10JC4CD NUTPLATE...2BACN10JR3CD NUTPLATE, SELF- LOCK 6.6.BACN10JR3CKD NUT PLATE8.8.BACN10JR4CFD NUTPLATE6.6.BACN10JR5CFD NUTPLATE6.6.BACN10JR6CFD NUTPLATE, SELF- LOCK ...6BACN10JZ4A2CD- MU NUTPLATE...2BACN10JZ4B2CDM NUT8.8.BACN10YR4CD (a)RIVET, 100 DEG...8BACR15BA3D11C Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 33 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 34 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 (a)RIVET, 100 DEG...4BACR15BA3D5C (a)RIVET, 100 DEG...4BACR15BA3D9C (a)RIVET...4BACR15BA4D9C (a)RIVET, 100 DEG.1..BACR15BA5D6C (a)RIVET, 100 DEG...4BACR15BA6D7C (a)RIVET, UNIVER- SAL HEAD .2..BACR15BB4D5C (a)RIVET, UNIVER- SAL HD .3..BACR15BB5D10C (a)RIVET107107107107BACR15BB5D5C (a)RIVET, UNIVER- SAL HD 81818181BACR15BB5D6C (a)RIVET, UNIVER- SAL HD 15151515BACR15BB5D7C (a)RIVET, UNIVER- SAL HD 2.22BACR15BB5D8C (a)RIVET, UNIVER- SAL HD 12.12.BACR15BB6D10C (a)RIVET, UNIVER- SAL HD 6.6.BACR15BB6D11C (a)RIVET.2.2BACR15BB6D12C (a)RIVET, UNIVER- SAL HD .2..BACR15BB6D4C (a)RIVET, UNIVER- SAL HD 4.44BACR15BB6D5C (a)RIVET, UNIVER- SAL HD 378378378378BACR15BB6D6C (a)RIVET, UNIVER- SAL HD 593593593593BACR15BB6D7C (a)RIVET, UNIVER- SAL HD 75757575BACR15BB6D8C (a)RIVET, UNIVER- SAL HD 8.88BACR15BB6D9C (a)RIVET, UNIVER- SAL HD 2.2.BACR15BB8D10C Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 34 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 35 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 (a)RIVET, UNIVER- SAL HD 47.47.BACR15BB8D11C (a)RIVET, UNIVER- SAL HD ...2BACR15BB8D18C (a)RIVET, UNIVER- SAL HD .2..BACR15BB8D19C (a)RIVET, UNIVER- SAL HD 62.62.BACR15BB8D6C (a)RIVET, UNIVER- SAL HD 139.139.BACR15BB8D7C (a)RIVET, UNIVER- SAL HD 9999BACR15BB8D8C (a)RIVET, UNIVER- SAL HD 2222BACR15BB8D9C (a)RIVET, 100 DEG..4.BACR15GF3D7 (a)RIVET, 100 DEG24.24.BACR15GF3D8 (a)RIVET, 100 DEG16.16.BACR15GF3D9 (a)RIVET, 100 DEG12.12.BACR15GF4D10 (a)RIVET12...BACR15GF4D13 (a)RIVET, 100 DEG..12.BACR15GF4D8 (a)RIVET, 100 DEG.7..BACR15GF5D4 (a)RIVET, 100 DEG1...BACR15GF6D10 (a)RIVET3...BACR15GF6D5 (a)RIVET, 100 DEG3.3.BACR15GF6D6 (a)RIVET, 100 DEG4.44BACR15GF6D7 (a)RIVET, 100 DEG...4BACR15GF6D9 (a)RIVET, 100 DEG3...BACR15GF8D9 (a)BOLT6.6.BACS12HN3-14 WASHER8.88BACW10BN4AC WASHER, SPRING 6.6.BACW10EC3CD WASHER12.12.NAS1149D0316H WASHER...2NAS1149D0416J Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 35 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 36 ALL Kit 141U1192 NotesExisting Part Number NameQtyNew Part Number -45-43-41-39 WASHER8.8.NAS1149D0463J (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specification (a)Chemical Conversion Coating8 OuncesType 2, Class A (b)Primer8 OuncesBMS 10-11, Type 1 (b)Sealant16 OuncesBMS5-95 (a) Refer to the Boeing Standard Overhaul Practices Manual 20-43-03, or 747 Structural Repair Manual, Chapter 51, for material sources. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 36 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 37 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 6. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 7. Boeing Service Letter 747-SL-51-048, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 8. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 37 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 38 9. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 10. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 11. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 12. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. 13. Use caution when using old parts as templates, and when transferring holes from removed parts to new parts to avoid transferring any possible mis-located holes, short edge margins, or incorrect profiles from the old parts to the new. 14. It is acceptable if the number of fasteners common to any individual side panel horizontal stiffener is one more or one less than the number shown on drawing 141U1192, sheet 14, 15 and 16. The number of fasteners can vary if the old side panel horizontal stiffeners are used as drill templates for the new stiffeners. 15. Keep removed parts as necessary for re-use and/or to use as templates. 16. Clecos are not considered fasteners for jacking purposes. 17. Fasteners may be oversized 1/64 or 1/32 inch in diameter as needed, provided that the e/D in all parts common to the oversized hole is greater than or equal to 1.7. "e" is defined as the distance from the edge of the part to the center of the hole. "D" is the final hole diameter. 18. Refer to Appendix A for a suggested sequence of steps for nose wheel well modification. 19. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 20. Shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. B. WORK INSTRUCTIONS PART 1: Access and Jacking 1. Print out the EICAS (Engine Indication and Crew Alerting System) fault list prior to disturbing any systems. This will limit the scope of any post-modification troubleshooting to only those systems that were disturbed during the modification. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 38 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 39 2. Install landing gear ground lock pins and chock the wheels. Refer to 747-400 AMM 09-11-00 as an accepted procedure. WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR DOOR OPERATIONAL AREA. FAST MOVEMENT OF THE LANDING GEAR DOORS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 3. Open the nose landing gear doors and install door locks. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 4. Install the safety/tow lock pin on the nose gear steering. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 5. Remove electrical power to airplane and ground airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. CAUTION: DO NOT EXCEED ALLOWABLE CAPACITY OF A JACK OR PAD. CAUTION: RAISING NOSE JACK POINT IN EXCESS OF 6 INCHES OF TIRE CLEARANCE CAN IMPOSE SIDE LOADS IN EXCESS OF ALLOWABLE SIDE LOADS ON JACK RAM AND JACK PAD AS THE JACK PAD IS TRAVELING IN AN ARC. 6. Jack the airplane. Refer to 747-400 AMM 07-11-01 as an accepted procedure. 7. Depressurize the hydraulic system. Refer to 747-400 AMM 29-11-00 as an accepted procedure. WARNING: DO NOT GET THE HYDRAULIC FLUID IN YOUR MOUTH OR EYES, OR ON YOUR SKIN. YOU CAN ABSORB POISONOUS MATERIALS FROM THE FLUID THROUGH YOUR SKIN. IF YOU GET THE FLUID IN YOUR EYES OR YOUR MOUTH, OR ON YOUR SKIN, INTERNAL INJURY CAN OCCUR. CAUTION: TO PREVENT CONTAMINATION OF THE HYDRAULIC SYSTEM, USE CLEAN EQUIPMENT WHEN YOU DO THE SERVICING OF THE SYSTEM. OTHERWISE, DAMAGE TO THE AIRPLANE HYDRAULIC SYSTEM CAN OCCUR. CAUTION: PUT CAPS ON THE HYDRAULIC LINES AND FITTINGS. UNWANTED MATERIAL CAN CAUSE CONTAMINATION OF HYDRAULIC LINES, DAMAGE TO SYSTEM COMPONENTS, AND LEAKAGE OF HYDRAULIC LINES. 8. Do one of the following options to prepare the nose landing gear before wheel well modification: a. OPTION 1 - Remove the nose landing gear. Refer to 747-400 AMM 32-21-01 as an accepted procedure. b. OPTION 2 - Deflate the nose landing gear and leave open to atmosphere. Rest the tires on the ground or an appropriate stand to support the weight of the nose landing gear. Refer to 747-400 AMM 12-15-05 as an accepted procedure. 9. Remove the forward nose wheel well doors. Refer to 747-400 AMM 32-22-01 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 39 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 40 10. Group 1: Remove the nose landing gear tire snubbers from the top panel. Refer to 747-400 AMM 32-45-05 as an accepted procedure. 11. Remove components from the nose wheel well forward bulkhead at STA 260 in accordance with FIGURE 1. 12. Remove components from the nose wheel well aft bulkhead at STA 340 in accordance with FIGURE 2. 13. Group 1: Remove the light from the top panel as given on drawing 141U1192. 14. Group 1: Remove the equipment that follows from the main deck as necessary for access to the nose wheel well top panel and side panels from Station (STA) 260 to STA 340, between LBL 20 and RBL 20: AMM Subject (Refer to these as accepted procedures) Equipment 747-400 AMM 25-25-01Passenger Seats 747-400 AMM 25-27-01Floor Covering 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-28-03Insulation Blankets 15. Group 2: Remove the equipment that follows from the main deck as necessary for access to the nose wheel well top panel and side panels from Station (STA) 260 to STA 340, between LBL 20 and RBL 20: AMM Subject (Refer to these as accepted procedures) Equipment 747-400 AMM 25-57-01Main Deck Cargo Compartment Power Drive Unit 747-400 AMM 25-57-04Main Deck Cargo Compartment Caster/Roller Tray 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-28-03Insulation Blankets PART 2: Nose Wheel Well Modification CAUTION: DO NOT REMOVE MORE THAN TWO PANELS (TOP AND SIDE WEBS) AT THE SAME TIME. REMOVING MORE THAN TWO PANELS WILL COMPROMISE STRUCTURAL INTEGRITY OF THE AIRPLANE IN THE AREA OF THE NOSE WHEEL WELL. A PANEL IS CONSIDERED REMOVED WHEN MORE THAN FIFTY PERCENT OF THE FASTENERS ARE REMOVED (EVERY OTHER FASTENER). A PANEL IS CONSIDERED Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 40 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 41 INSTALLED WHEN MORE THAN FIFTY PERCENT OF THE FASTENERS ARE INSTALLED (EVERY OTHER FASTENER). POWER CLECOS ARE CONSIDERED FASTENERS WHEN DEFINING A REMOVED OR INSTALLED PANEL. SPRING CLECOS ARE NOT CONSIDERED FASTENERS WHEN DEFINING A REMOVED OR AN INSTALLED PANEL. 1. Group 1: Remove the top panel from the nose wheel well in accordance with FIGURE 3. 2. Group 1: Do a detailed inspection for cracks in all attaching structural elements that were common to the removed top panel. a. If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. b. If any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. 3. Group 1: Remove and replace either the left side panel or the right side panel of the nose wheel well, as follows: a. For the left side panel, remove the existing panel structure in accordance with FIGURE 4. For the right side panel, remove the existing panel structure in accordance with FIGURE 5. b. Before installation of the new panel, do a detailed inspection for cracks in all attaching structural elements that were common to the removed side panel. (1) If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. (2) If any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. c. For the left side panel, install new panel structure in accordance with FIGURE 4. For the right side panel, install new panel structure in accordance with FIGURE 5. 4. Group 1: Remove and replace the other side panel of the nose wheel well, as follows: a. For the left side panel, remove the existing panel structure in accordance with FIGURE 4. For the right side panel, remove the existing panel structure in accordance with FIGURE 5. b. Before installation of the new panel, do a detailed inspection for cracks in all attaching structural elements that were common to the removed side panel. (1) If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. (2) If any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 41 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 42 c. For the left side panel, install new panel structure in accordance with FIGURE 4. For the right side panel, install new panel structure in accordance with FIGURE 5. 5. Group 1: Install the new top panel in the nose wheel well in accordance with FIGURE 6. 6. Group 2: Remove top panel components from the nose wheel well in accordance with FIGURE 9. 7. Group 2: Do a detailed inspection for cracks in all attaching structural elements that were common to the removed top panel components. a. If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. b. If any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. 8. Group 2: Remove and replace either the left side panel or the right side panel of the nose wheel well, as follows: a. For the left side panel, remove the existing panel structure in accordance with FIGURE 10. For the right side panel, remove the existing panel structure in accordance with FIGURE 11. b. Before installation of the new panel, do a detailed inspection for cracks in all attaching structural elements that were common to the removed side panel. (1) If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. (2) if any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. c. For the left side panel, install new panel structure in accordance with FIGURE 10. For the right side panel, install new panel structure in accordance with FIGURE 11. 9. Group 2: Remove and replace the other side panel of the nose wheel well, as follows: a. For the left side panel, remove the existing panel structure in accordance with FIGURE 10. For the right side panel, remove the existing panel structure in accordance with FIGURE 11. b. Before installation of the new panel, do a detailed inspection for cracks in all attaching structural elements that were common to the removed side panel. (1) If no cracks are found in the attaching structural elements, continue with the nose wheel well modification. (2) if any crack is found in an attaching structural element, contact Boeing for repair instructions, and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 42 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 43 c. For the left side panel, install new panel structure in accordance with FIGURE 10. For the right side panel, install new panel structure in accordance with FIGURE 11. 10. Group 2: Install the new top panel components in the nose wheel well in accordance with FIGURE 12. PART 3: Close Access 1. Group 1: Install the light on the top panel as given on drawing 141U1192. 2. Install components on the nose wheel well aft bulkhead at STA 340 in accordance with FIGURE 7. 3. Install components on the nose wheel well forward bulkhead at STA 260 in accordance with FIGURE 8. 4. Group 1: Install the nose landing gear tire snubbers on the top panel. Refer to 747-400 AMM 32-45-05 as an accepted procedure. 5. Install the forward nose wheel well doors. Refer to 747-400 AMM 32-22-01 as an accepted procedure. 6. If the nose landing gear was removed for access, install the nose landing gear. Refer to 747-400 AMM 32-21-01 as an accepted procedure. 7. If necessary, inflate the nose landing gear. Refer to 747-400 AMM 12-15-05 as an accepted procedure. 8. Group 1: Refer to the procedures that follow, as necessary, to re-install any equipment that was removed from the main deck for internal access to the nose wheel well top panel and side panels: AMM Subject (Refer to these as ac- cepted procedures) Equipment 747-400 AMM 25-28-03Insulation Blankets 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-27-01Floor Covering 747-400 AMM 25-25-01Passenger Seats 9. Group 2: Refer to the procedures that follow, as necessary, to re-install any equipment that was removed from the main deck for internal access to the nose wheel well top panel and side panels: AMM Subject (Refer to these as ac- cepted procedures) Equipment 747-400 AMM 25-28-03Insulation Blankets Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 43 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 44 AMM Subject (Refer to these as ac- cepted procedures) Equipment 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-57-04Main Deck Cargo Compartment Caster/Roller Tray 747-400 AMM 25-57-01Main Deck Cargo Compartment Power Drive Unit PART 4: Test 1. Supply electrical power to airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. 2. Pressurize the cabin and check for air leakage in the modified area of the nose wheel well. Refer to 747-400 AMM 05-51-08 as an accepted procedure. 3. Pressurize the hydraulic system and check for leaks. Refer to 747-400 AMM 29-11-00 as an accepted procedure. WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR DOOR OPERATIONAL AREA. FAST MOVEMENT OF THE LANDING GEAR DOORS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 4. Remove the nose landing gear locks and close the nose landing gear doors. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 5. Remove ground locks on the landing gear. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 6. Remove the safety/tow lock pin on the nose gear steering. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 7. Test nose gear sequencing valve. Refer to 747-400 AMM 32-34-08 as an accepted procedure. 8. Test nose gear proximity switch. Refer to 747-400 AMM 32-09-03 as an accepted procedure. 9. Test the nose wheel well light. Refer to 747-400 AMM 33-31-00 as an accepted procedure. PART 5: De-jack Airplane 1. Install ground locks on the landing gear. Refer to 747-400 AMM 09-11-00 as an accepted procedure. CAUTION: REMOVE ALL OF THE AEROSTANDS, JACKS, WORK PLATFORMS, AND ENTRY STANDS OUT OF THE AREA THAT ARE NOT NECESSARY 2. De-jack the airplane. Refer to 747-400 AMM 07-11-01 as an accepted procedure. 3. Remove ground locks on the landing gear. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 4. Put the airplane back to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 44 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 45 PART 6: Post Modification Inspections - External Detailed Inspections of Side Panel Webs, and Internal Detailed and HFEC Inspections of Top and Side Panel Stiffeners 1. If not already done, install landing gear ground lock pins and chock the wheels. Refer to 747-400 AMM 09-11-00 as an accepted procedure. WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR DOOR OPERATIONAL AREA. FAST MOVEMENT OF THE LANDING GEAR DOORS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 2. If not already done, open the nose landing gear doors and install door locks. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 3. Group 1: Remove the equipment that follows from the main deck, as necessary, for access to the nose wheel well top panel and side panels from Station (STA) 260 to STA 340, between LBL 20 and RBL 20: AMM Subject (Refer to these as accepted procedures) Equipment 747-400 AMM 25-25-01Passenger Seats 747-400 AMM 25-27-01Floor Covering 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-28-03Insulation Blankets 4. Group 2: Remove the equipment that follows from the main deck, as necessary, for access to the nose wheel well top panel and side panels from Station (STA) 260 to STA 340, between LBL 20 and RBL 20: AMM Subject (Refer to these as accepted procedures) Equipment 747-400 AMM 25-57-01Main Deck Cargo Compartment Power Drive Unit 747-400 AMM 25-57-04Main Deck Cargo Compartment Caster/Roller Tray 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-28-03Insulation Blankets 5. Do an external detailed inspection for cracks in the side panel webs in accordance with FIGURE 13, and do internal detailed and high frequency eddy current inspections for cracks in the top and side panel stiffeners in accordance with FIGURE 15. a. If any crack is found: Contact Boeing for repair instructions, and do the repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 45 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 46 b. If no crack is found, or cracks have been repaired: Repeat the external detailed inspection for cracks in the side panel webs in accordance with FIGURE 13, and repeat the internal detailed and high frequency eddy current inspections for cracks in the top and side panel stiffeners in accordance with FIGURE 15. Do the repeat inspections at the interval specified in Paragraph 1.E., Compliance. 6. Group 1: Refer to the procedures that follow, as necessary, to re-install any equipment that was removed from the main deck for internal access to the nose wheel well top panel and side panels: AMM Subject (Refer to these as ac- cepted procedures) Equipment 747-400 AMM 25-28-03Insulation Blankets 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-27-01Floor Covering 747-400 AMM 25-25-01Passenger Seats 7. Group 2: Refer to the procedures that follow, as necessary, to re-install any equipment that was removed from the main deck for internal access to the nose wheel well top panel and side panels: AMM Subject (Refer to these as ac- cepted procedures) Equipment 747-400 AMM 25-28-03Insulation Blankets 747-400 AMM 53-21-02Floor Panels 747-400 AMM 25-57-04Main Deck Cargo Compartment Caster/Roller Tray 747-400 AMM 25-57-01Main Deck Cargo Compartment Power Drive Unit 8. Remove the nose landing gear door locks and close the nose landing gear doors. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 9. Remove the ground locks on the landing gear. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 10. Put the airplane back to a serviceable condition. PART 7: Post Modification Inspections - External Detailed Inspections of Top Panel Web 1. If not already done, install landing gear ground lock pins and chock the wheels. Refer to 747-400 AMM 09-11-00 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 46 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 47 WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR DOOR OPERATIONAL AREA. FAST MOVEMENT OF THE LANDING GEAR DOORS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 2. If not already done, open the nose landing gear doors and install door locks. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 3. Do an external detailed inspection for cracks in the top panel web in accordance with FIGURE 14. a. If any crack is found: Contact Boeing for repair instructions, and do the repair. b. If no crack is found, or cracks have been repaired: Repeat the external detailed inspection for cracks in the top panel web in accordance with FIGURE 14, at the interval specified in Paragraph 1.E., Compliance. 4. Remove the nose landing gear door locks and close the nose landing gear doors. Refer to 747-400 AMM 32-00-30 as an accepted procedure. 5. Remove the ground locks on the landing gear. Refer to 747-400 AMM 09-11-00 as an accepted procedure. 6. Put the airplane back to a serviceable condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 47 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT STATION 260 • BULKHEAD DOOR SAFETY 8 VALVE ALT EXTENSION MECHANISM •STATION 260 BULKHEAD UPPER ACTUATOR 6 SUPPORT FITTING FORWARD DOOR BELLCRANK ACTUATOR 2 FITTING SHIM 7 LOWER ACTUATOR ( 7 SUPPORT FITTING SHIM T DOOR OPERATOR RODS 2178508 FIGURE 1: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 260 BULKHEAD (SHEET 1 OF 2) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2808 Work - See page 1 for details. 48 of 93 ### Page 49 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. WARNING: DO NOT GET THE HYDRAULIC FLUID IN YOUR MOUTH OR EYES, OR ON YOUR SKIN. YOU CAN ABSORB POISONOUS MATERIALS FROM THE FLUID THROUGH YOUR SKIN. IF YOU GET THE FLUID IN YOUR EYES OR MOUTH, INTERNAL INJURY CAN OCCUR. CAUTION: TO PREVENT CONTAMINATION OF THE HYDRAULIC SYSTEM, USE CLEAN EQUIPMENT WHEN YOU DO THE SERVICING OF THE SYSTEM. DAMAGE TO THE AIRPLANE HYDRAULIC SYSTEM CAN OCCUR. CAUTION: PUT CAPS ON THE HYDRAULIC LINES AND FITTINGS. UNWANTED MATERIAL CAN CAUSE CONTAMINATION OF HYDRAULIC LINES, DAMAGE TO SYSTEM COMPONENTS, AND LEAKAGE OF HYDRAULIC FLUID. MORE DATAQTYNAMETASKSTEP Refer to 747-400 AMM 32-22-03 as an accepted procedure. 2Nose Wheel Well Forward Door Operator Rods Remove/Keep1 Refer to 747-400 AMM 32-34-14 as an accepted procedure. 1Nose Landing Gear Door ActuatorRemove/Keep2 Refer to 747-400 AMM 32-22-05 as an accepted procedure. 1Nose Landing Gear Forward Door Bellcrank Remove/Keep3 Refer to 747-400 AMM 32-34-15 as an accepted procedure. 1Door Unlock Safety ValveRemove/Keep4 As necessary. Refer to 747-400 AMM 32-35-04 as an accepted pro- cedure. 1Nose Landing Gear Alternate Exten- sion Door Unlock and Safety Valve Mechanism Remove/Keep5 Refer to SOPM 20-50-01 as an ac- cepted procedure. 1Nose Landing Gear Actuator Upper Support Fitting Remove/Keep6 Refer to SOPM 20-50-01 as an ac- cepted procedure. 1Nose Landing Gear Actuator Lower Support Fitting Remove/Keep7 A bonded shim is under each "leg" of the support fitting common to the left side panel of the nose wheel well. Remove and keep the shims with the fitting for re-installation. 2Nose Landing Gear Actuator Lower Support Fitting Shims As necessary for access.-Hydraulic Lines, Tubes, and Clamps Remove/Keep8 Refer to 747-400 AMM 20-11-05 as an accepted procedure. FIGURE 1: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 260 BULKHEAD (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 49 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 50 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT STATION 340 BULKHEAD 2178504 FIGURE 2: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 340 BULKHEAD (SHEET 1 OF 2) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2808 Work - See page 1 for details. 50 of 93 ### Page 51 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. WARNING: DO NOT GET THE HYDRAULIC FLUID IN YOUR MOUTH OR EYES, OR ON YOUR SKIN. YOU CAN ABSORB POISONOUS MATERIALS FROM THE FLUID THROUGH YOUR SKIN. IF YOU GET THE FLUID IN YOUR EYES OR MOUTH, INTERNAL INJURY CAN OCCUR. CAUTION: TO PREVENT CONTAMINATION OF THE HYDRAULIC SYSTEM, USE CLEAN EQUIPMENT WHEN YOU DO THE SERVICING OF THE SYSTEM. DAMAGE TO THE AIRPLANE HYDRAULIC SYSTEM CAN OCCUR. CAUTION: PUT CAPS ON THE HYDRAULIC LINES AND FITTINGS. UNWANTED MATERIAL CAN CAUSE CONTAMINATION OF HYDRAULIC LINES, DAMAGE TO SYSTEM COMPONENTS, AND LEAKAGE OF HYDRAULIC FLUID. MORE DATAQTYNAMETASKSTEP Refer to 747-400 AMM 32-34-06 as an accepted procedure. 1Nose Landing Gear Door-Operated Sequence Valve Mechanism Remove/Keep1 Refer to 747-400 AMM 32-34-05 as an accepted procedure. 1Nose Landing Gear Door-Operated Sequence Valve Remove/Keep2 Refer to 747-400 AMM 32-34-07 as an accepted procedure. 1Nose Landing Gear-Operated Se- quence Valve Remove/Keep3 Refer to 747-400 AMM 32-34-10 as an accepted procedure. 1Pressure-Operated Restrictor Check Valve Remove/Keep4 As necessary for access.-Hydraulic Lines, Tubes, and Clamps Remove/Keep5 Refer to 747-400 AMM 20-11-05 as an accepted procedure. FIGURE 2: REMOVALS FOR ACCESS AT NOSE WHEEL WELL STA 340 BULKHEAD (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 51 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 52 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT This Figure applies only to: Group 1. TOP PANEL A STA 280 STA RBL 300 30 STA CANTED 320 BULKHEAD STA LBL 340 30 STA STA 380 360 STA 400 BL SIA 340 BULKHEAD STA 400 BULKHEAD 2178505 FIGURE 3: REMOVAL OF TOP PANEL (SHEET 1 OF 3) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING 747-53A2808 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 93 ### Page 53 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT RBL REL BL LBL LBL 20 10 20 ..... CANTED BULKHEAD - STA 280 - STA 300 - STA 320 STA 340 TOP PANEL 2178506 FIGURE 3: REMOVAL OF TOP PANEL (SHEET 2 OF 3) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING 747-53A2808 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 93 ### Page 54 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE: A panel is considered removed when more than fifty percent of the fasteners are removed. NOTE: Power clecos are considered fasteners when defining a removed panel. Spring clecos are not considered fasteners when defining a removed panel. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP (a) (b) (c)1-Top PanelRemove1 (a) Remove the top panel in accordance with Drawing 141U1192, Sheets 1, 10, 11, and 17. (b) Keep the removed top panel web to use as a template. (c) Some top panel components will be kept for rework and/or re-installation in a another Figure. Determine which components are to be kept, reworked, and re-installed, in accordance with Drawing 141U1192, Sheets 1, 10, 11, and 17. FIGURE 3: REMOVAL OF TOP PANEL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 54 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 55 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT This Figure applies only to: Group 1. STA — RBL 300 30 STA CANTED 320 BULKHEAD STA • LBL 340 30 STA STA 360 380 STA 400 SIDEWALL PANEL STA 340 BULKHEAD STA 400 BULKHEAD 2178502 FIGURE 4: LEFT SIDE PANEL REPLACEMENT (SHEET 1 OF 3) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING 747-53A2808 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 93 ### Page 56 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT STA STA STA STA CANTED 340 320 300 280 BULKHEAD 00000009 ........... -WL170 -WL 160 -WL150 FWD LEFT SIDE PANEL SHOWN 2178503 FIGURE 4: LEFT SIDE PANEL REPLACEMENT (SHEET 2 OF 3) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2808 Work - See page 1 for details. 56 of 93 ### Page 57 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this Figure. NOTE: A panel is considered removed when more than fifty percent of the fasteners are removed. NOTE: Power clecos are considered fasteners when defining a removed panel. Spring clecos are not considered fasteners when defining a removed panel. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP (b) (c) (d)1-Left Side PanelRemove1 (b) (e)1(a)Left Side PanelInstall (New) 2 (a) For identification refer to drawing 141U1192. (b) Replace the left side panel in accordance with 141U1192, Sheets 1, 5, 14, 15, and 16. (c) Keep the removed left side panel web to use as a template. (d) Some left side panel components will be kept for rework and/or re-installation. Determine which components are to be kept, reworked, and re-installed, in accordance with Drawing 141U1192, Sheets 1, 5, 14, 15, and 16. (e) Use Left Side Panel Modification Kit 141U1192-17 and Side Panel Modification Fastener Kit 141U1192-41. FIGURE 4: LEFT SIDE PANEL REPLACEMENT (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 57 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT ### Page 58 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT This Figure applies only to: Group 1. STA LBL _280 30 STA _300 CANTED BULKHEAD RBL 30 STA 360 STA 380 FWD STA . 400 SIDEWALL → BL PANEL STA 340 BULKHEAD STA 400 BULKHEAD 2178498 FIGURE 5: RIGHT SIDE PANEL REPLACEMENT (SHEET 1 OF 3) Original Issue: November 30, 2012 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 747-53A2808 Work - See page 1 for details. 58 of 93 ### Page 59 (OCR) BOEING SERVICE BULLETIN 747-53A2808 ALERT ALERT CANTED STA STA STA STA • BULKHEAD 280 300 320 340 WL170 WL 160- WL150 FWD RIGHT SIDE PANEL SHOWN 2178497 FIGURE 5: RIGHT SIDE PANEL REPLACEMENT (SHEET 2 OF 3) Original Issue: November 30, 2012 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2808 Work - See page 1 for details. 59 of 93 ### Page 60 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE: A panel is considered removed when more than fifty percent of the fasteners are removed. NOTE: Power clecos are considered fasteners when defining a removed panel. Spring clecos are not considered fasteners when defining a removed panel. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP (b) (c) (d)1-Right Side PanelRemove1 (b) (e)1(a)Right Side PanelInstall (New) 2 (a) For identification refer to drawing 141U1192. (b) Replace the right side panel in accordance with 141U1192, Sheets 1, 5, 14, 15, and 16. (c) Keep the removed right side panel web to use as a template. (d) Some right side panel components will be kept for rework and/or re-installation. Determine which components are to be kept, reworked, and re-installed, in accordance with Drawing 141U1192, Sheets 1, 5, 14, 15, and 16. (e) Use Right Side Panel Modification Kit 141U1192-18 and Side Panel Modification Fastener Kit 141U1192-41. FIGURE 5: RIGHT SIDE PANEL REPLACEMENT (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 30, 2012 747-53A2808 60 of 93 BOEING SERVICE BULLETIN 747-53A2808 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/747-53a2808/file/b058ef43bad8.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.