### Commercial **Airplanes** 

# 747 Service Bulletin **SPECIAL ATTENTION Number: 747-57-2332**  Original Issue: November 09, 2010 ATA System: 5740 **SUBJECT:**WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage Path 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.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 1 of 85 6.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 2 of 85 **BOEING SERVICE BULLETIN 747-57-2332**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 7 A. Effectivity................................................ 7 1. Airplanes............................................. 7 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 37 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 38 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION. . . . . . . . . 42 FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION. . . . . . . . 45 FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE. . . . . . . . . . . . . . . . 48 FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE. . . . . . . . . . . . . . . 50 FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . 52 FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL. . . . . . . . . . . . . . . . . . . . . . . 54 FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE. . . . . . . . . . . . . . . . . . . . . . . . 56 FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE. . . . . . . . . . . . . . . . . . . . . . . 58 FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION . . . 60 FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION . . . 64 FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION [Group 1-6]. . . . 68 FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION [Group 1-6] . . . 71

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 3 of 85 **BOEING SERVICE BULLETIN 747-57-2332**APPENDIX A: MASTER FASTENER CODE TABLE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 4 of 85 **BOEING SERVICE BULLETIN 747-57-2332**

### Commercial **Airplanes** 

# 747 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 747-57-2332** Original Issue: November 09, 2010 ATA System: 5740 **SUBJECT:**WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage Path Change BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area, forward of the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating in the wing leading edge may drain inboard and onto the engine exhaust nozzle, which could result in a fire. Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the number 5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection with a fuel quantity of over 2500 lbs. Subsequent investigation found that the leak occurred in an area of the front spar that does not have a proper drain path. This led to the fuel draining onto the engine exhaust nozzle. The leak appears to have been caused by a loose retaining nut of the slat track down stop and is the subject of Boeing Service Letter 737-SL-57-084. Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid leakages from the wing leading edge away from the engine exhaust area. Boeing Service Related Problem (SRP) 747-SRP-57-0214 is related to this service bulletin. **ACTION (PRR 85901-96RS)** Get access to the leading edge of the wing by extending the variable camber flaps. Install the applicable fuel dam assemblies, seal assemblies and drain assemblies. Repair the leading edge lower skin panel. Close access. **EFFECTIVITY** 747-100, -100B, -100B SUD, -200B, -200F, -200C, -300, -400, -400D, -400F, 747SR and 747SP Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 5 of 85**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. Boeing recommends that the change given in this service bulletin be done within 60 months after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of November 15, 2007. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  55.00 94.50 GROUP 1-6 50.50 90.00 GROUP 7-10
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 6 of 85 **BOEING SERVICE BULLETIN 747-57-2332**

### Commercial **Airplanes** 

# 747 Service Bulletin **SPECIAL ATTENTION Number: 747-57-2332**  Original Issue: November 09, 2010 ATA System: 5740 **SUBJECT:**WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage Path Change BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes

**DESCRIPTION CONFIGURATION**  **GROUP** 747-100 Airplanes with line numbers 1-248.
- 1 747-100 Airplanes with line numbers 252-281 and 747SP Airplanes with JT9D-7 Engines. - 2
747SR Airplanes with line numbers 221-249.

- 3 747SR Airplane with line number 254.

- 4 747SR Airplanes with line numbers 346-572 and 747-100B Airplanes with JT9D-7 Engines and 747-100B SUD Airplanes. - 5
747-200B, 747-200C, 747-200F and 747-300 Airplanes with either JT9D-7 or CF6-50 engines. - 6
747-400, 747-400D and 747-400F Airplanes.
- 7 747SP Airplanes with RB211 series Engines.

- 8 747-100B Airplanes with RB211 series Engines.
- 9 747-200B, 747-200F and 747-300 Airplanes with either JT9D-70, CF6-80 or RB211 series Engines. - 10

Airplane Models:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 7 of 85747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR **Group Variable Number** 1 RA001 - RA034 1 RA101 - RA115 1 RA161 - RA164 1 RA201 - RA203 6 RA216 - RA217 6 RA245 - RA246 1 RA251 - RA264 2 RA265 - RA266 1 RA301 - RA317 2 RA318 1 RA351 - RA360 6 RA369 - RA373 1 RA401 - RA418 1 RA501 - RA502 1 RA521 - RA527 2 RA528 6 RA532 - RA548 1 RA551 - RA552 6 RA559 - RA561 1 RA581 - RA582 6 RA585 1 RA601 - RA602 1 RA631 - RA635 6 RA651 - RA652 6 RA671 - RA677 6 RA701 - RA702 6 RA721 - RA731 1 RA741 - RA745 6 RA749 - RA750 1 RA761 - RA762 6 RA781 - RA784

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 8 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**1 RA901 - RA916 6 RB001 - RB016 1 RB041 - RB044 6 RB071 - RB075 1 RB101 - RB102 10 RB411 - RB413 6 RB421 3 RB601 - RB606 4 RB607 5 RB681 - RB697 5 RB711 5 RB721 - RB723 9 RB741 - RB747 6 RD001 - RD004 6 RD021 - RD022 6 RD041 - RD059 6 RD071 - RD072 6 RD081 - RD083 6 RD091 - RD092 6 RD101 - RD104 6 RD121 - RD127 10 RD131 - RD144 10 RD166 - RD167 6 RD171 - RD172 6 RD181 - RD183 6 RD201 - RD204 6 RD221 - RD227 6 RD231 - RD235 6 RD241 - RD243 6 RD251 - RD262 6 RD271 - RD272 6 RD291 - RD292 6 RD301 - RD302

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 9 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**10 RD311 10 RD351 - RD358 6 RD361 - RD366 6 RD381 - RD383 6 RD411 - RD414 6 RD421 - RD426 6 RD431 - RD435 6 RD441 - RD442 6 RD451 - RD456 6 RD461 10 RD471 - RD475 6 RD513 - RD516 10 RD517 - RD519 6 RD531 10 RD532 - RD533 6 RD551 10 RD561 6 RD571 6 RD581 - RD583 10 RD591 - RD592 6 RD593 6 RD601 - RD607 6 RD621 - RD623 6 RD641 - RD649 6 RD651 - RD659 6 RD661 6 RD671 6 RD681 - RD682 6 RD691 - RD692 6 RD701 - RD702 6 RD721 - RD722 6 RD741 - RD742 6 RD751 - RD755

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 10 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**6 RD761 6 RD771 - RD775 6 RD781 - RD783 6 RD791 - RD792 6 RE001 7 RF001 - RF006 2 RG001 - RG009 2 RG091 2 RG095 2 RG101 - RG104 2 RG121 - RG126 2 RG141 - RG142 2 RG161 - RG164 2 RG171 - RG174 2 RG191 - RG193 2 RG211 - RG213 2 RG221 - RG222 8 RH101 - RH102 8 RH111 - RH112 8 RH121 - RH122 6 RJ131 - RJ133 6 RJ151 - RJ152 6 RJ301 - RJ303 6 RJ321 - RJ322 6 RJ331 - RJ333 7 RL401 - RL403 7 RL411 - RL436 7 RL451 - RL456 7 RL461 - RL462 7 RL471 - RL481 7 RL491 - RL492 7 RL501 - RL502 7 RL511 - RL516

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 11 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**7 RL521 - RL522 7 RL531 - RL534 7 RL551 7 RL561 - RL568 7 RL571 - RL572 7 RL576 - RL577 7 RL579 7 RL581 - RL586 7 RL651 - RL655 7 RL671 - RL675 7 RL681 - RL684 7 RL751 - RL752 7 RM001 - RM0077 RM010 - RM0137 RM021 - RM0247 RM026 - RM030 7 RM036 - RM045 7 RM051 - RM0537 RM071 7 RM081 - RM0847 RM091 7 RM096 - RM0977 RM116 - RM1177 RM126 - RM132 7 RM136 - RM1477 RM156 - RM158 7 RM166 - RM1777 RM191 - RM192 7 RM231 - RM2337 RM241 - RM246 7 RM261 - RM2647 RM316 - RM318 7 RM331 - RM333

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 12 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**7 RM341 7 RM351 - RM355 7 RM366 - RM3677 RM401 - RM4037 RM426 7 RM431 7 RM441 - RM4437 RM445 7 RM801 - RM8037 RM811 - RM8137 RM851 - RM859 7 RM861 - RM8637 RM871 - RM899 7 RM901 - RM906 7 RM911 6 RR001 - RR005 6 RR021 - RR025 6 RR031 6 RR201 - RR206 10 RR221 - RR224 6 RR225 - RR226 6 RR261 - RR267 6 RR301 - RR310 6 RR331 - RR332 6 RR336 6 RR341 - RR345 6 RR361 - RR362 10 RR421 6 RR422 6 RR431 - RR432 10 RR441 - RR442 6 RR451 6 RR501 - RR504

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 13 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**6 RR521 - RR522 10 RR526 10 RR531 6 RR551 - RR556 6 RR561 6 RR566 7 RR701 7 RR721 - RR724 7 RR746 - RR748 7 RR851 - RR856 7 RR861 - RR862 7 RR951 - RR952 5 RS001 - RS002 6 RS201 6 RS211 - RS212 6 RS221 - RS222 6 RS231 - RS241 6 RS251 - RS259 6 RS263 6 RS265 - RS268 10 RS271 - RS276 6 RS291 - RS292 10 RS301 - RS306 10 RS311 - RS320 10 RS331 - RS333 10 RS341 - RS342 6 RS699 6 RS701 - RS703 6 RS711 - RS713 6 RS721 - RS722 6 RS731 - RS732 6 RS741 - RS743 6 RS751 - RS752

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 14 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**6 RS761 - RS762 6 RS771 10 RS781 - RS782 6 RS786 7 RT001 - RT014 7 RT021 - RT022 7 RT031 - RT035 7 RT041 - RT047 7 RT061 7 RT071 - RT075 7 RT101 - RT103 7 RT121 7 RT131 - RT137 7 RT151 - RT152 7 RT161 - RT168 7 RT401 - RT412 7 RT431 - RT447 7 RT451 - RT469 7 RT471 - RT499 7 RT501 - RT535 7 RT551 - RT568 7 RT571 - RT591 7 RT601 - RT657 7 RT671 - RT673 7 RT681 - RT682 7 RT691 - RT699 7 RT701 - RT704 7 RT711 - RT717 7 RT741 - RT757 7 RT776 - RT777 7 RT781 - RT784 7 RT801 - RT803 7 RT811 - RT814

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 15 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group**  **Variable Number**7 RT831 - RT837 7 RT861 - RT864 7 RT876 - RT880 7 RT931 - RT932 7 RT945 - RT949 7 RT951 - RT955 7 RT966 - RT967 7 RU001 - RU006 7 RU016 - RU017 7 RU031 - RU032 7 RU051 - RU052 7 RU059 - RU062 7 RU081 - RU083 7 RU101 - RU102 7 RU121 - RU132 7 RU801 - RU809 7 RU831 - RU841 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area, forward of the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating in the wing leading edge may drain inboard and onto the engine exhaust nozzle, which could result in a fire. Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the number 5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection with a fuel quantity of over 2500 lbs. Subsequent investigation found that the leak occurred in an area of the front spar that does not have a proper drain path. This led to the fuel draining onto the engine exhaust nozzle. The leak appears to have been caused by a loose retaining nut of the slat track down stop and is the subject of Boeing Service Letter 737-SL-57-084. Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid leakages from the wing leading edge away from the engine exhaust area.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 16 of 85 **BOEING SERVICE BULLETIN 747-57-2332**Boeing Service Related Problem (SRP) 747-SRP-57-0214 is related to this service bulletin. **D. Description** Get access to the leading edge of the wing by extending the variable camber flaps. Install the applicable fuel dam assemblies, seal assemblies and drain assemblies. Repair the leading edge lower skin panel. Close access. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-100 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-100, 747SP **Group 3-4:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747SR **Group 5:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-100B, 747-100B SUD, 747SR **Group 6:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-200B, 747-200C, 747-200F, 747-300

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 17 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7:** 
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-400, 747-400D, 747-400F **Group 8:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747SP **Group 9:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-100B **Group 10:**
**Affected Maintenance Zones Zone**  **Model** 521, 531, 621, 631 747-200B, 747-200F, 747-300 **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. Boeing recommends that the change given in this service bulletin be done within 60 months after the original issue date of this service bulletin. **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 09, 2010 747-57-2332 18 of 85 **BOEING SERVICE BULLETIN 747-57-2332 G. Manpower**  The table below shows an estimate of the task hours necessary to do this change 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 1-6: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 2.25 2.25 1 Part 1: FIGURE 1 2.25 2.25 1 Part 1: FIGURE 2 1.00 1.00 1 Part 2: FIGURE 3 1.00 1.00 1 Part 2: FIGURE 4 2.75 5.50 2 Part 3: FIGURE 5 2.75 5.50 2 Part 3: FIGURE 6 1.75 1.75 1 Part 3: FIGURE 7 1.75 1.75 1 Part 3: FIGURE 8 17.00 34.00 2 Part 3: FIGURE 9 17.00 34.00 2 Part 3: FIGURE 10 2.25 2.25 1 Part 4: FIGURE 11 2.25 2.25 1 Part 4: FIGURE 12 0.50 0.50 1 Close Access 55.00 94.50 TOTAL FOR EACH AIRPLANE **Group 7-10: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 2.25 2.25 1 Part 1: FIGURE 1 2.25 2.25 1 Part 1: FIGURE 2 1.00 1.00 1 Part 2: FIGURE 3 1.00 1.00 1 Part 2: FIGURE 4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 19 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.75 5.50 2 Part 3: FIGURE 5 2.75 5.50 2 Part 3: FIGURE 6 1.75 1.75 1 Part 3: FIGURE 7 1.75 1.75 1 Part 3: FIGURE 8 17.00 34.00 2 Part 3: FIGURE 9 17.00 34.00 2 Part 3: FIGURE 10 0.50 0.50 1 Close Access 50.50 90.00 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1-6:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane** + 18290.0 + 11.8 All Airplanes **Group 7-10: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  + 17292.0 + 11.0 All Airplanes
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 85901-96RS b. Boeing Service Related Problem (SRP) 747-SRP-57-0214 c. Standard Overhaul Practices Manual (SOPM) 20-10-06, 20-30-03, 20-50-00, 20-50-10, 20-50-18, 20-50-19 d. 747-100/200/300 Aircraft Maintenance Manual (AMM) 27-81-00, 78-31-00 e. 747-100/200/300 Structural Repair Manual (SRM) 51-40-12, 51-40-14 f. 747-400 Aircraft Maintenance Manual (AMM) 27-81-00, 78-31-00

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 20 of 85 **BOEING SERVICE BULLETIN 747-57-2332**g. 747-400 Structural Repair Manual (SRM) 51-70-07, 51-70-17 h. 747-400F Structural Repair Manual (SRM) 51-70-07, 51-70-17 i. 747-400LCF Structural Repair Manual (SRM) 51-70-07, 51-70-17 j. 747-400SF Structural Repair Manual (SRM) 51-70-07, 51-70-17 k. 747-SP Structural Repair Manual (SRM) 51-40-14 2. Data supplied with this Service Bulletin a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- - 1 LEADING EDGE FLUID DAM ASSEMBLY- LOWER LEADING EDGE PANEL ASSEMBLY 624U0071

- - 2 3. Installation Drawings Used in the Preparation of this Service Bulletin None. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  51-31 747 Maintenance Manual 57-31 747 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 does not affect FCS, therefore DTIs are not necessary. **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 09, 2010 747-57-2332 21 of 85 **BOEING SERVICE BULLETIN 747-57-2332**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 22 of 85 **BOEING SERVICE BULLETIN 747-57-2332**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 23 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**Unit Price thru November 30,**  **2010 ROLT**  **(Calendar Days)**  **QTY Date**  **Name Kit Number** 

$33,609.00 420 25 May 24, 2010TOP KIT - WING LEADING EDGE DRAINAGE 015U1870-1
25 June 22, 2010 13 July 21, 2010 12 October 11, 201025 November 8, 201025 December 8, 201025 January 14, 201125 February 11, 201125 March 11, 2011 25 April 8, 2011 25 May 6, 2011 25 June 6, 2011 15 July 5, 2011 **Group 7-10:**
**Unit Price thru November 30,**  **2010 ROLT**  **(Calendar Days)**  **QTY Date**  **Name Kit Number** 

$29,304.00 420 10 May 24, 2010TOP KIT - WING LEADING EDGE DRAINAGE 015U1870-2
4 June 1, 2010 10 June 22, 2010

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 24 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**Unit Price thru November 30,**  **2010 ROLT**  **(Calendar Days)**  **QTY Date**  **Name Kit Number** 

July 21, 2010 10
10 August 18, 2010 10 September 16, 201010 October 14, 201010 November 11, 20101 December 13, 2010 The kits 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 available for 747 airplanes in warranty as of November 15, 2007. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable numbers in your purchase order. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 25 of 85 **BOEING SERVICE BULLETIN 747-57-2332 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. The Top Kit is divided into Figure kits for each installation figure shown in the table below. **Figure Kit 8**  **7 4**  **3 2**  **1 Top Kit**  1 1 1 1 1 1 015U1870-1 1 1 1 1 1 1 015U1870-2 **Figure Kit 12**  **11 10**  **9 Top Kit**  1 1 1 1 015U1870-1

- - 1 1 015U1870-2 **Group 1-6:**
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  KIT DETAIL - SEAL 1 114U9202-10
KIT DETAIL - DRAIN TUBE 114U9202-12
KIT - DRAIN FITTING ASSY 1 114U9202-15
KIT - DRAIN FITTING ASSY 1 114U9202-16
KIT DETAIL - WEB, FLUID DAM 114U9202-19
KIT DETAIL - WEB, FLUID DAM 114U9202-20
KIT DETAIL -DRAIN TUBE RETAINER 114U9202-24

KIT DETAIL - BRACKET 1 1 114U9202-3
KIT DETAIL - BRACKET 1 1 114U9202-4
KIT DETAIL - WEB, FLUID DAM 1 114U9202-5

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 26 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  KIT DETAIL - WEB, FLUID DAM 1 114U9202-6
KIT DETAIL - SEAL 1 114U9202-9
BOLT 10 10 BACB30LH3-5 BOLT-100 DEG HEAD BACB30NN3K3 BOLT, RADIUS LEAD-IN BACB30WQ5K13LY BOLT, RADIUS LEAD-IN BACB30WQ5K14LY BOLT, RADIUS LEAD-IN BACB30WQ6K10LX BOLT, RADIUS LEAD-IN BACB30WQ6K10LY BOLT, RADIUS LEAD-IN BACB30WQ6K12LY BOLT, RADIUS LEAD-IN BACB30WQ6K14LX BOLT, RADIUS LEAD-IN BACB30WQ6K15LX BOLT, RADIUS LEAD-IN BACB30WQ6K8LX BOLT, RADIUS LEAD-IN BACB30WQ6K8LY BOLT, HEX DRIVE BACB30WQ6K9LX BOLT BACB30WQ6K9LY BOLT, RADIUS LEAD-IN BACB30WQ7K14L BOLT, RADIUS LEAD-IN BACB30WQ7K15L BOLT, HEX DRIVE BACB30YN12K15X BOLT, HEX DRIVE BACB30YN12K16X BOLT, HEX DRIVE BACB30YN14K15

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 27 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  BOLT BACB30YN14K16 BOLT, 100 DEG HEX DR 2 2 BACB30YP6K4
COLLAR 2 2 BACC30BS6 NUT BACN10HY5ACX SELF-LOCKING NUT BACN10HY6AC
NUT BACN10HY6ACX SELF-LOCKING NUT BACN10HY7AC
SELF-LOCKING NUT BACN10YR6CD
NUT BACN10YR7CD RIVET, 100 DEG BACR15BA7AD10C RIVET, 100 DEG 3 3 BACR15BA7AD11C RIVET, 100 DEG BACR15BA7AD12C RIVET, 100 DEG BACR15BA7AD13C RIVET, 100 DEG BACR15BA7D10C RIVET, 100 DEG BACR15BA7D12C RIVET, 100 DEG BACR15BA7D9C RIVET, UNIVERSAL HD 6 6 BACR15BB6D6C RIVET, 100 DEG BACR15GF7D7 WASHER BACW10AT26AS WASHER BACW10AT27AS WASHER BACW10AT36AS WASHER BACW10AT37AS WASHER, FLAT BACW10P448CG WASHER BACW10P449CG WASHER, FLAT BACW10P454CG WASHER, FLAT BACW10P455CG

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 28 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  WASHER NAS1149D0663J WASHER NAS1149D0763J RIVET, BLIND NAS1399MW6A4 CLAMP, HOSE NAS1922-0050-3 **Group 1-6:**
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 12**  **11 10**  **9 QTY**  KIT DETAIL - SEAL 114U9202-10
KIT DETAIL - DRAIN TUBE 1 1 114U9202-12
KIT - DRAIN FITTING ASSY 114U9202-15
KIT - DRAIN FITTING ASSY 114U9202-16
KIT DETAIL - WEB, FLUID DAM 1 114U9202-19
KIT DETAIL - WEB, FLUID DAM 1 114U9202-20
KIT DETAIL -DRAIN TUBE RETAINER 3 3 114U9202-24

KIT DETAIL - BRACKET 1 1 114U9202-3
KIT DETAIL - BRACKET 1 1 114U9202-4
KIT DETAIL - WEB, FLUID DAM 114U9202-5
KIT DETAIL - WEB, FLUID DAM 114U9202-6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 29 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 12**  **11 10**  **9 QTY**  KIT DETAIL - SEAL 114U9202-9
BOLT BACB30LH3-5 BOLT-100 DEG HEAD 105 105 BACB30NN3K3 BOLT, RADIUS LEAD-IN 2 2 BACB30WQ5K13LY BOLT, RADIUS LEAD-IN 2 2 BACB30WQ5K14LY BOLT, RADIUS LEAD-IN 6 6 BACB30WQ6K10LX BOLT, RADIUS LEAD-IN 6 6 BACB30WQ6K10LY BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K12LY BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K14LX BOLT, RADIUS LEAD-IN 8 8 BACB30WQ6K15LX BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K8LX BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K8LY BOLT, HEX DRIVE 6 6 BACB30WQ6K9LX BOLT 6 6 BACB30WQ6K9LY BOLT, RADIUS LEAD-IN 10 10 BACB30WQ7K14L BOLT, RADIUS LEAD-IN 15 15 BACB30WQ7K15L BOLT, HEX DRIVE 6 6 BACB30YN12K15X BOLT, HEX DRIVE 6 6 BACB30YN12K16X BOLT, HEX DRIVE 2 2 BACB30YN14K15 BOLT 4 4 BACB30YN14K16

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 30 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 12**  **11 10**  **9 QTY**  BOLT, 100 DEG HEX DR BACB30YP6K4
COLLAR BACC30BS6 NUT 4 4 BACN10HY5ACX SELF-LOCKING NUT 25 25 BACN10HY6AC
NUT 15 15 BACN10HY6ACX SELF-LOCKING NUT 25 25 BACN10HY7AC
SELF-LOCKING NUT 15 15 BACN10YR6CD
NUT 6 6 BACN10YR7CD RIVET, 100 DEG 15 15 BACR15BA7AD10C RIVET, 100 DEG 51 52 BACR15BA7AD11C RIVET, 100 DEG 2 2 37 38 BACR15BA7AD12C RIVET, 100 DEG 30 30 BACR15BA7AD13C RIVET, 100 DEG 1 1 BACR15BA7D10C RIVET, 100 DEG 1 1 BACR15BA7D12C RIVET, 100 DEG 1 1 BACR15BA7D9C RIVET, UNIVERSAL HD 6 7 BACR15BB6D6C RIVET, 100 DEG 6 6 BACR15GF7D7 WASHER 25 25 BACW10AT26AS WASHER 25 25 BACW10AT27AS WASHER 25 25 BACW10AT36AS WASHER 25 25 BACW10AT37AS WASHER, FLAT 4 4 BACW10P448CG WASHER 15 15 BACW10P449CG WASHER, FLAT 4 4 BACW10P454CG WASHER, FLAT 15 15 BACW10P455CG WASHER 25 25 NAS1149D0663J

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 31 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:** 
**KIT 015U1870-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 12**  **11 10**  **9 QTY**  WASHER 15 15 NAS1149D0763J RIVET, BLIND 2 2 NAS1399MW6A4 CLAMP, HOSE 1 1 NAS1922-0050-3 **Group 7-10:**
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  KIT DETAIL - SEAL 1 114U9202-10
KIT DETAIL - DRAIN TUBE 114U9202-12
KIT - DRAIN FITTING ASSY 1 114U9202-15
KIT - DRAIN FITTING ASSY 1 114U9202-16
KIT DETAIL -DRAIN TUBE RETAINER 114U9202-24

KIT DETAIL - BRACKET 1 1 114U9202-3
KIT DETAIL - BRACKET 1 1 114U9202-4
KIT DETAIL - WEB, FLUID DAM 1 114U9202-5
KIT DETAIL - WEB, FLUID DAM 1 114U9202-6
KIT DETAIL - SEAL 1 114U9202-9
BOLT 10 10 BACB30LH3-5 BOLT-100 DEG HEAD BACB30NN3K3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 32 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  BOLT, RADIUS LEAD-IN BACB30WQ5K13LY BOLT, RADIUS LEAD-IN BACB30WQ5K14LY BOLT, RADIUS LEAD-IN BACB30WQ6K10LX BOLT, RADIUS LEAD-IN BACB30WQ6K10LY BOLT, RADIUS LEAD-IN BACB30WQ6K12LY BOLT, RADIUS LEAD-IN BACB30WQ6K14LX BOLT, RADIUS LEAD-IN BACB30WQ6K15LX BOLT, RADIUS LEAD-IN BACB30WQ6K8LX BOLT, RADIUS LEAD-IN BACB30WQ6K8LY BOLT, HEX DRIVE BACB30WQ6K9LX BOLT BACB30WQ6K9LY BOLT, RADIUS LEAD-IN BACB30WQ7K14L BOLT, RADIUS LEAD-IN BACB30WQ7K15L BOLT, HEX DRIVE BACB30YN12K15X BOLT, HEX DRIVE BACB30YN12K16X BOLT, HEX DRIVE BACB30YN14K15 BOLT BACB30YN14K16 BOLT, 100 DEG HEX DR 2 2 BACB30YP6K4
COLLAR 2 2 BACC30BS6 NUT BACN10HY5ACX

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 33 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 8**  **7 4**  **3 2**  **1 QTY**  SELF-LOCKING NUT BACN10HY6AC
NUT BACN10HY6ACX SELF-LOCKING NUT BACN10HY7AC
SELF-LOCKING NUT BACN10YR6CD
NUT BACN10YR7CD RIVET, 100 DEG BACR15BA7AD10C RIVET, 100 DEG 3 3 BACR15BA7AD11C RIVET, 100 DEG BACR15BA7AD12C RIVET, 100 DEG BACR15BA7AD13C RIVET, 100 DEG BACR15BA7D10C RIVET, 100 DEG BACR15BA7D12C RIVET, 100 DEG BACR15BA7D9C RIVET, UNIVERSAL HD 6 6 BACR15BB6D6C RIVET, 100 DEG BACR15GF7D7 WASHER BACW10AT26AS WASHER BACW10AT27AS WASHER BACW10AT36AS WASHER BACW10AT37AS WASHER, FLAT BACW10P448CG WASHER BACW10P449CG WASHER, FLAT BACW10P454CG WASHER, FLAT BACW10P455CG WASHER NAS1149D0663J WASHER NAS1149D0763J RIVET, BLIND NAS1399MW6A4 CLAMP, HOSE NAS1922-0050-3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 34 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 10**  **9 QTY** KIT DETAIL - SEAL 114U9202-10
KIT DETAIL - DRAIN TUBE 1 1 114U9202-12
KIT - DRAIN FITTING ASSY 114U9202-15
KIT - DRAIN FITTING ASSY 114U9202-16
KIT DETAIL -DRAIN TUBE RETAINER 3 3 114U9202-24

KIT DETAIL - BRACKET 114U9202-3
KIT DETAIL - BRACKET 114U9202-4
KIT DETAIL - WEB, FLUID DAM 114U9202-5
KIT DETAIL - WEB, FLUID DAM 114U9202-6
KIT DETAIL - SEAL 114U9202-9
BOLT BACB30LH3-5 BOLT-100 DEG HEAD 105 105 BACB30NN3K3 BOLT, RADIUS LEAD-IN 2 2 BACB30WQ5K13LY BOLT, RADIUS LEAD-IN 2 2 BACB30WQ5K14LY BOLT, RADIUS LEAD-IN 6 6 BACB30WQ6K10LX BOLT, RADIUS LEAD-IN 6 6 BACB30WQ6K10LY BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K12LY

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 35 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 10**  **9 QTY** BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K14LX BOLT, RADIUS LEAD-IN 8 8 BACB30WQ6K15LX BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K8LX BOLT, RADIUS LEAD-IN 1 1 BACB30WQ6K8LY BOLT, HEX DRIVE 6 6 BACB30WQ6K9LX BOLT 6 6 BACB30WQ6K9LY BOLT, RADIUS LEAD-IN 10 10 BACB30WQ7K14L BOLT, RADIUS LEAD-IN 15 15 BACB30WQ7K15L BOLT, HEX DRIVE 6 6 BACB30YN12K15X BOLT, HEX DRIVE 6 6 BACB30YN12K16X BOLT, HEX DRIVE 2 2 BACB30YN14K15 BOLT 4 4 BACB30YN14K16 BOLT, 100 DEG HEX DR BACB30YP6K4
COLLAR BACC30BS6 NUT 4 4 BACN10HY5ACX SELF-LOCKING NUT 25 25 BACN10HY6AC
NUT 15 15 BACN10HY6ACX SELF-LOCKING NUT 25 25 BACN10HY7AC
SELF-LOCKING NUT 15 15 BACN10YR6CD
NUT 6 6 BACN10YR7CD RIVET, 100 DEG 15 15 BACR15BA7AD10C RIVET, 100 DEG 51 52 BACR15BA7AD11C

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 36 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 7-10:** 
**KIT 015U1870-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 10**  **9 QTY** RIVET, 100 DEG 37 38 BACR15BA7AD12C RIVET, 100 DEG 30 30 BACR15BA7AD13C RIVET, 100 DEG 1 1 BACR15BA7D10C RIVET, 100 DEG 1 1 BACR15BA7D12C RIVET, 100 DEG 1 1 BACR15BA7D9C RIVET, UNIVERSAL HD BACR15BB6D6C RIVET, 100 DEG 6 6 BACR15GF7D7 WASHER 25 25 BACW10AT26AS WASHER 25 25 BACW10AT27AS WASHER 25 25 BACW10AT36AS WASHER 25 25 BACW10AT37AS WASHER, FLAT 4 4 BACW10P448CG WASHER 15 15 BACW10P449CG WASHER, FLAT 4 4 BACW10P454CG WASHER, FLAT 15 15 BACW10P455CG WASHER 25 25 NAS1149D0663J WASHER 15 15 NAS1149D0763J RIVET, BLIND 2 2 NAS1399MW6A4 CLAMP, HOSE 1 1 NAS1922-0050-3 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) Sealant 3 Qt BMS5-95 (a) Anti-Static Coating 3 Oz BMS10-21, TYPE III (a) Two Part Hole Filling Compound 6 Oz BMS5-16 (a) Glass Fabric 2 ft BMS8-79, CLASS III, STYLE 1581

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 37 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Notes**  **Name QTY**  **Part Number / Specification**  (a) Glass Fabric Reinforcement 2 ft BMS9-3, TYPE H- 2 (b) Two Part Resin for Composite Re- pairs 8 Oz RESIN MIX 3 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Refer to 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400 SRM 51-70-07 or 747-400 SRM 51-70-17, as applicable, for material specification and supplier information.
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.
**Notes New Part Number**  **Name QTY**  **Existing Part Number**  (a) (b) (c) (d) 65B10873 Skin Panel Assembly, Leading Edge Wing 2 65B10873 SB 747-57-2332 (a) Make the change in accordance with this service bulletin. (b) There is no equivalent Boeing part number for the changed part. Identify on the part that the change done in accordance with this service bulletin was made. (c) This is the part number after the change is done in accordance with this service bulletin. (d) This part is not used in production. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 38 of 85 **BOEING SERVICE BULLETIN 747-57-2332 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:**1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 are in 747 SRM, Chapter 51 – Torque limits to tighten nuts and bolts are in 747 SRM, Chapter 51 5. Use the approved fastener and process material substitutions in accordance with 747 SRM, Chapter 51. Alternate fasteners are listed in 747 SRM Chapter 51 and Boeing Drawing 012W6100. 6. If the length of any fastener specified in this service bulletin does not meet the installation standards in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in SRM Chapter 51 may be used. 7. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 8. Refer to APPENDIX A for Master Fastener Code Table.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 39 of 85 **BOEING SERVICE BULLETIN 747-57-2332 B. WORK INSTRUCTIONS**  **ACCESS** 1. Deactivate the thrust reverser for ground maintenance. Refer to 747-100/200/300 AMM 78-31-00 or 747-400 AMM 78-31-00 as an accepted procedure, as applicable. 2. Extend the variable camber leading edge flaps to the fully extended position and deactivate. Refer to 747-100/200/300 AMM 27-81-00 or 747-400 AMM 27-81-00 as an accepted procedure, as applicable. **Part 1 - Outboard Leading Edge Fluid Dam Installation** 1. At Outboard Leading Edge Station (OLES) 1250, install fluid dam assemblies in accordance with the figures below: **Right Wing Left Wing**  FIGURE 2 FIGURE 1 **Part 2 - Outboard Leading Edge Seal Change** 1. At OLES 1185, install seal assemblies in accordance with the figures below: **Right Wing Left Wing**  FIGURE 4 FIGURE 3 **Part 3 - Inboard Leading Edge Drain Tube Installation** 1. Between Inboard Leading Edge Station (ILES) 1116 and ILES 994, remove the lower leading edge panel in accordance with the figures below: **Right Wing Left Wing**  FIGURE 6 FIGURE 5 2. Change the lower leading edge panel in accordance with the figures below: **Right Wing Left Wing**  FIGURE 8 FIGURE 7 3. Install the lower leading edge panel and drain tube assembly in accordance with the figures below: **Right Wing Left Wing**  FIGURE 10 FIGURE 9

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 40 of 85 **BOEING SERVICE BULLETIN 747-57-2332 Group 1-6:**  **Part 4 - Inboard Leading Edge Fluid Dam Installation** 1. At ILES 770, install fluid dam assemblies in accordance with the figures below: **Right Wing Left Wing**  FIGURE 12 FIGURE 11
**Close Access** 1. Retract the variable camber leading edge flaps to the fully up position and activate. Refer to 747-100/200/300 AMM 27-81-00 or 747-400 AMM 27-81-00 as an accepted procedure, as applicable. 2. Activate the thrust reversers. Refer to 747-100/200/300 AMM 78-31-00 or 747-400 AMM 78-31-00 as an accepted procedure, as applicable. 3. Put the airplane back to serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 41 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 42 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 2
- Fastener Remove 1 as shown. 1 114U9202-3 KIT DETAIL - BRACK- ET Locate 2
as shown. 1 114U9202-4 KIT DETAIL - BRACK- ET Locate
as shown. 1 114U9202-5 KIT DETAIL - WEB, FLUID DAM Locate
8
- Hole Drill 3 and deburr. 8
- Hole Clean 1 114U9202-3 KIT DETAIL - BRACK- ET Install (New) 4 Fay surface seal between mating surface of bracket to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-4 KIT DETAIL - BRACK- ET Install (New)

Fay surface seal between mating surface of fluid dam to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-5 KIT DETAIL - WEB, FLUID DAM Install (New)

8
- Fastener Install (New) 5 as required to apply fillet seal to both sides of fluid dam. Refer to SOPM 20-50-19 as an accepted procedure. Make sure drainage hole is clear of sealant. - BMS5-95 Sealant Apply 6

**FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 43 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Apply bead of sealant extending from fluid dam to forward edge of beam panel support. Make sure sealant is flush with top of fluid dam. - BMS5-95 Sealant Apply 7

The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  6 BACR15BB6D6C RIVET, UNIVERSAL HD (a) 3 BACR15BA7AD11C RIVET, 100 DEG (a) Quantity may be in excess of requirements.

**FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 44 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 45 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 2
- Fastener Remove 1 as shown. 1 114U9202-3 KIT DETAIL - BRACK- ET Locate 2
as shown. 1 114U9202-4 KIT DETAIL - BRACK- ET Locate
as shown. 1 114U9202-6 KIT DETAIL - WEB, FLUID DAM Locate
8
- Hole Drill 3 and deburr. 8
- Hole Clean 1 114U9202-3 KIT DETAIL - BRACK- ET Install (New) 4 Fay surface seal between mating surface of bracket to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-4 KIT DETAIL - BRACK- ET Install (New)

Fay surface seal between mating surface of fluid dam to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-6 KIT DETAIL - WEB, FLUID DAM Install (New)

8
- Fastener Install (New) 5 as required to apply fillet seal to both sides of fluid dam. Refer to SOPM 20-50-19 as an accepted procedure. Make sure drainage hole is clear of sealant. - BMS5-95 Sealant Apply 6

**FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 46 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Apply bead of sealant extending from fluid dam to forward edge of beam panel support. Make sure sealant is flush with top of fluid dam. - BMS5-95 Sealant Apply 7

The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  6 BACR15BB6D6C RIVET, UNIVERSAL HD (a) 3 BACR15BA7AD11C RIVET, 100 DEG (a) Quantity may be in excess of requirements.

**FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 47 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 48 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 9
- Fastener Remove 1 1
- Retainer Remove / Keep 2 4.20 inches from edge of retainer. 1
- Bulb Seal Cut 3
with BMS5-16 - Hole Filling Compound. Refer to SOPM 20-50-19 as an accepted procedure. 1
- Drainage Hole Fill 4

in contact with the end of the existing bulb seal andaligned with the forward edge of the retainer. 1 114U9202-9 KIT DETAIL - SEAL Locate 5

as shown. 1
- Retainer Locate Mark hole locations on seal. 2
- Hole Locate 6
1
- Retainer Remove / Keep 7 1 114U9202-9 KIT DETAIL - SEAL Remove / Keep Diameter of holes is 0.35 inches. 2
- Hole Drill 8
1 114U9202-9 KIT DETAIL - SEAL Install (New) 9 1
- Retainer Install (Kept) 9 BACB30LH3-5 BOLT Install (New) The parts shown in the table below are provided as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  1 BACB30LH3-5 BOLT

**FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 49 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 50 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 9
- Fastener Remove 1 1
- Retainer Remove / Keep 2 4.20 inches from edge of retainer. 1
- Bulb Seal Cut 3
with BMS5-16 - Hole Filling Compound. Refer to SOPM 20-50-19 as an accepted procedure. 1
- Drainage Hole Fill 4

in contact with the end of the existing bulb seal andaligned with the forward edge of the retainer. 1 114U9202-10 KIT DETAIL - SEAL Locate 5

as shown. 1
- Retainer Locate Mark hole locations on seal. 2
- Hole Locate 6
1
- Retainer Remove / Keep 7 1 114U9202-10 KIT DETAIL - SEAL Remove / Keep Diameter of holes is 0.35 inches. 2
- Hole Drill 8
1 114U9202-10 KIT DETAIL - SEAL Install (New) 9 1
- Retainer Install (Kept) 9 BACB30LH3-5 BOLT Install (New) The parts shown in the table below are provided as extra parts for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  1 BACB30LH3-5 BOLT

**FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 51 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 52 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Recommend notingfastener type removed from eachhole for future reference. - - Fastener Remove 1

1 65B10873-7, -27 Skin Panel Assy, Lead- ing Edge Wing Remove / Keep 2

**FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 53 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 54 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Recommend notingfastener type removed from eachhole for future reference. - - Fastener Remove 1

1 65B10873-8, -28 Skin Panel Assy, Lead- ing Edge Wing Remove / Keep 2

**FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 55 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 56 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** as shown above. Remove existing plies, cut core and install new plies in accordance with (a).Replace the two existing plies and add two extra repair plies. 1 65B10873-7, -27 Skin Panel Assy, Lead- ing Edge Wing Change 1

Drainage hole diameter is 0.375 in. 1
- Hole Drill 2
1 114U9202-15 KIT - DRAIN FITTING ASSY Put / Hold 3
Hole diameter: 0.190 - 0.193 in. 2
- Hole Drill 4
and deburr. 3
- Hole Clean 5 1 114U9202-15 KIT - DRAIN FITTING ASSY Install (New) 6
Refer to SOPM 20-50-18 as an accepted procedure. 2 BACB30YP6K4 BOLT, 100 DEG HEX DR Install (New) 7

2 BACC30BS6 COLLAR Install (New) Rubber stamp part number on the part. Refer to SOPM 20-50-10 as an accepted procedure. 1 SB 747-57-2332 Part Number Apply 8

(a) 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400 SRM 51-70-07, 747-400 SRM 51-70-17, 747-400F SRM 51-70-07, 747-400F SRM 51-70-17, 747-400LCF SRM 51-70-07, 747- 400LCF SRM 51-70-17, 747-400SF SRM 51-70-07, 747-400SF SRM 51-70-17 or 747-SP SRM 51-40- 14, as applicable.

**FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 57 of 85 **BOEING SERVICE BULLETIN 747-57-2332 FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 58 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** as shown above. Remove existing plies, cut core and install new plies in accordance with (a).Replace the two existing plies and add two extra repair plies. 1 65B10873-8, -28 Skin Panel Assy, Lead- ing Edge Wing Change 1

Drainage hole diameter is 0.375 in. 1
- Hole Drill 2
1 114U9202-16 KIT - DRAIN FITTING ASSY Put / Hold 3
Hole diameter: 0.190 - 0.193 in. 2
- Hole Drill 4
and deburr. 3
- Hole Clean 5 1 114U9202-16 KIT - DRAIN FITTING ASSY Install (New) 6
Refer to SOPM 20-50-18 as an accepted procedure. 2 BACB30YP6K4 BOLT, 100 DEG HEX DR Install (New) 7

2 BACC30BS6 COLLAR Install (New) Rubber stamp part number on the part. Refer to SOPM 20-50-10 as an accepted procedure. 1 SB 747-57-2332 Part Number Apply 8

(a) 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400 SRM 51-70-07, 747-400 SRM 51-70-17, 747-400F SRM 51-70-07, 747-400F SRM 51-70-17, 747-400LCF SRM 51-70-07, 747- 400LCF SRM 51-70-17, 747-400SF SRM 51-70-07, 747-400SF SRM 51-70-17 or 747-SP SRM 51-40- 14, as applicable.

**FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 59 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 1 65B10873-7, -27 Skin Panel Assy, Lead- ing Edge Wing Put / Hold 1
3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Locate 2
3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Put / Hold
107
- Hole Drill / Ream 3 and deburr. 107
- Hole Clean 4 as necessary. Refer to SOPM 20-10-06as an accepted procedure. - BMS10-21, TYPE III Anti-Static Coating Apply 5

Fay surface seal between mating surface of aft edge of panel to lower wing skin with BMS5-95. 1 65B10873-7, -27 Skin Panel Assy, Lead- ing Edge Wing Install (Kept) 6

into clips of the draintube retainers. Ensure that the outboard end of the drain tube extends past the outboardedge of the rib. Remove sealant as necessary. 1 114U9202-12 KIT DETAIL - DRAIN TUBE Install (New) 7

**FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 60 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to connect the draintube to the drain fitting assembly. Refer to SOPM 20-50-00as an accepted procedure. 1 NAS1922-0050-3 CLAMP, HOSE Install (New) 8

3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Install (New) 9 For codes with optional bolts, measure the height of thestackup and diameter of the pre-existing hole. Use the bolt compatible forthe measured stackup and the corresponding smallest diameter attainable from the measured hole. 202
- Fastener Install (New) 10

to apply fillet seal. Ensure absoluteseal around outer diameter of drain tubefiling entire gap between adjacent structures. Ensure drain tube is clear of sealant. - BMS5-95 Sealant Apply 11

**FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 61 of 85 **BOEING SERVICE BULLETIN 747-57-2332**The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  (a) 6 BACB30YN12K15X BOLT, HEX DRIVE (a) 6 BACB30YN12K16X BOLT, HEX DRIVE (a) 25 NAS1149D0663J WASHER (a) 15 BACN10YR6CD SELF-LOCKING NUT (a) 2 BACB30YN14K15 BOLT, HEX DRIVE (a) 4 BACB30YN14K16 BOLT (a) 15 NAS1149D0763J WASHER (a) 6 BACN10YR7CD NUT (a) 10 BACB30WQ7K14L BOLT, RADIUS LEAD- IN (a) 15 BACB30WQ7K15L BOLT, RADIUS LEAD- IN (a) 25 BACN10HY7AC SELF-LOCKING NUT (a) 8 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN (a) 25 BACW10AT26AS WASHER (a) 25 BACW10AT36AS WASHER (a) 25 BACN10HY6AC SELF-LOCKING NUT (a) 25 BACW10AT37AS WASHER (a) 25 BACW10AT27AS WASHER (a) 2 BACB30WQ5K13LY BOLT, RADIUS LEAD- IN (a) 2 BACB30WQ5K14LY BOLT, RADIUS LEAD- IN (a) 4 BACW10P448CG WASHER, FLAT (a) 4 BACW10P454CG WASHER, FLAT (a) 4 BACN10HY5ACX NUT (a) 1 BACB30WQ6K8LX BOLT, RADIUS LEAD- IN (a) 6 BACB30WQ6K9LX BOLT, HEX DRIVE (a) 6 BACB30WQ6K10LX BOLT, RADIUS LEAD- IN

**FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 62 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME** (a) 1 BACB30WQ6K8LY BOLT, RADIUS LEAD- IN (a) 6 BACB30WQ6K9LY BOLT (a) 6 BACB30WQ6K10LY BOLT, RADIUS LEAD- IN (a) 15 BACW10P449CG WASHER (a) 15 BACW10P455CG WASHER, FLAT (a) 15 BACN10HY6ACX NUT (a) 1 BACB30WQ6K12LY BOLT, RADIUS LEAD- IN (a) 1 BACB30WQ6K14LX BOLT, RADIUS LEAD- IN (a) 2 NAS1399MW6A4 RIVET, BLIND (a) 1 BACR15BA7D9C RIVET, 100 DEG (a) 1 BACR15BA7D10C RIVET, 100 DEG (a) 1 BACR15BA7D12C RIVET, 100 DEG (a) 105 BACB30NN3K3 BOLT-100 DEG HEAD (a) 6 BACR15GF7D7 RIVET, 100 DEG (a) 15 BACR15BA7AD10C RIVET, 100 DEG (a) 52 BACR15BA7AD11C RIVET, 100 DEG (a) 38 BACR15BA7AD12C RIVET, 100 DEG (a) 30 BACR15BA7AD13C RIVET, 100 DEG (a) Quantity may be in excess of requirements.

**FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 63 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 1 65B10873-8, -28 Skin Panel Assy, Lead- ing Edge Wing Put / Hold 1
3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Locate 2
3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Put / Hold
107
- Hole Drill / Ream 3 and deburr. 107
- Hole Clean 4 as necessary. Refer to SOPM 20-10-06as an accepted procedure. - BMS10-21, TYPE III Anti-Static Coating Apply 5

Fay surface seal between mating surface of aft edge of panel to lower wing skin with BMS5-95. 1 65B10873-8, -28 Skin Panel Assy, Lead- ing Edge Wing Install (Kept) 6

into clips of the draintube retainers. Ensure that the outboard end of the drain tube extends past the outboardedge of the rib. Remove sealant as necessary. 1 114U9202-12 KIT DETAIL - DRAIN TUBE Install (New) 7

**FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 64 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** to connect the draintube to the drain fitting assembly. Refer to SOPM 20-50-00as an accepted procedure. 1 NAS1922-0050-3 CLAMP, HOSE Install (New) 8

3 114U9202-24 KIT DETAIL - DRAIN TUBE RETAINER Install (New) 9 For codes with optional bolts, measure the height of thestackup and diameter of the pre-existing hole. Use the bolt compatible forthe measured stackup and the corresponding smallest diameter attainable from the measured hole. 202
- Fastener Install (New) 10

as required to apply fillet seal. Ensure absolute seal around outer diameter ofdrain tube filing entire gap between adjacent structures. Ensure drain tube is clear of sealant. - BMS5-95 Sealant Apply 11

**FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 65 of 85 **BOEING SERVICE BULLETIN 747-57-2332**The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  (a) 6 BACB30YN12K15X BOLT, HEX DRIVE (a) 6 BACB30YN12K16X BOLT, HEX DRIVE (a) 25 NAS1149D0663J WASHER (a) 15 BACN10YR6CD SELF-LOCKING NUT (a) 2 BACB30YN14K15 BOLT, HEX DRIVE (a) 4 BACB30YN14K16 BOLT (a) 15 NAS1149D0763J WASHER (a) 6 BACN10YR7CD NUT (a) 10 BACB30WQ7K14L BOLT, RADIUS LEAD- IN (a) 15 BACB30WQ7K15L BOLT, RADIUS LEAD- IN (a) 25 BACN10HY7AC SELF-LOCKING NUT (a) 8 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN (a) 25 BACW10AT26AS WASHER (a) 25 BACW10AT36AS WASHER (a) 25 BACN10HY6AC SELF-LOCKING NUT (a) 25 BACW10AT37AS WASHER (a) 25 BACW10AT27AS WASHER (a) 2 BACB30WQ5K13LY BOLT, RADIUS LEAD- IN (a) 2 BACB30WQ5K14LY BOLT, RADIUS LEAD- IN (a) 4 BACW10P448CG WASHER, FLAT (a) 4 BACW10P454CG WASHER, FLAT (a) 4 BACN10HY5ACX NUT (a) 1 BACB30WQ6K8LX BOLT, RADIUS LEAD- IN (a) 6 BACB30WQ6K9LX BOLT, HEX DRIVE (a) 6 BACB30WQ6K10LX BOLT, RADIUS LEAD- IN

**FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 66 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME** (a) 1 BACB30WQ6K8LY BOLT, RADIUS LEAD- IN (a) 6 BACB30WQ6K9LY BOLT (a) 6 BACB30WQ6K10LY BOLT, RADIUS LEAD- IN (a) 15 BACW10P449CG WASHER (a) 15 BACW10P455CG WASHER, FLAT (a) 15 BACN10HY6ACX NUT (a) 1 BACB30WQ6K12LY BOLT, RADIUS LEAD- IN (a) 1 BACB30WQ6K14LX BOLT, RADIUS LEAD- IN (a) 2 NAS1399MW6A4 RIVET, BLIND (a) 1 BACR15BA7D9C RIVET, 100 DEG (a) 1 BACR15BA7D10C RIVET, 100 DEG (a) 1 BACR15BA7D12C RIVET, 100 DEG (a) 105 BACB30NN3K3 BOLT-100 DEG HEAD (a) 6 BACR15GF7D7 RIVET, 100 DEG (a) 15 BACR15BA7AD10C RIVET, 100 DEG (a) 51 BACR15BA7AD11C RIVET, 100 DEG (a) 37 BACR15BA7AD12C RIVET, 100 DEG (a) 30 BACR15BA7AD13C RIVET, 100 DEG (a) Quantity may be in excess of requirements.

**FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 67 of 85 **BOEING SERVICE BULLETIN 747-57-2332 This Figure applies only to: Group 1-6.** 

**FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 68 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 2
- Fastener Remove 1 as shown. 1 114U9202-3 KIT DETAIL - BRACK- ET Locate 2
as shown. 1 114U9202-4 KIT DETAIL - BRACK- ET Locate
as shown. 1 114U9202-19 KIT DETAIL - WEB, FLUID DAM Locate
8
- Hole Drill 3 and deburr. 8
- Hole Clean 1 114U9202-3 KIT DETAIL - BRACK- ET Install (New) 4 Fay surface seal between mating surface of bracket to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-4 KIT DETAIL - BRACK- ET Install (New)

Fay surface seal between mating surface of fluid dam to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-19 KIT DETAIL - WEB, FLUID DAM Install (New)

8
- Fastener Install (New) 5 as required to apply fillet seal on both sides of fluid dam. Refer to SOPM 20-50-19 as an accepted procedure. Make sure drainage hole is clear of sealant. - BMS5-95 Sealant Apply 6

**FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 69 of 85 **BOEING SERVICE BULLETIN 747-57-2332**The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  7 BACR15BB6D6C RIVET, UNIVERSAL HD 2 BACR15BA7AD12C RIVET, 100 DEG

**FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 70 of 85 **BOEING SERVICE BULLETIN 747-57-2332 This Figure applies only to: Group 1-6.** 

**FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 71 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 2
- Fastener Remove 1 as shown. 1 114U9202-3 KIT DETAIL - BRACK- ET Locate 2
as shown. 1 114U9202-4 KIT DETAIL - BRACK- ET Locate
as shown. 1 114U9202-20 KIT DETAIL - WEB, FLUID DAM Locate
8
- Hole Drill 3 and deburr. 8
- Hole Clean 1 114U9202-3 KIT DETAIL - BRACK- ET Install (New) 4 Fay surface seal between mating surface of bracket to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-4 KIT DETAIL - BRACK- ET Install (New)

Fay surface seal between mating surface of fluid dam to lower wing skin with BMS5-95. Refer to SOPM 20-50-19 asan accepted procedure. Make sure drainage hole is clear of sealant. 1 114U9202-20 KIT DETAIL - WEB, FLUID DAM Install (New)

8
- Fastener Install (New) 5 as required to apply fillet seal on both sides of fluid dam. Refer to SOPM 20-50-19 as an accepted procedure. Make sure drainage hole is clear of sealant. - BMS5-95 Sealant Apply 6

**FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 72 of 85 **BOEING SERVICE BULLETIN 747-57-2332**The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.
**MORE DATA QTY**  **IDENTIFICATION NAME**  6 BACR15BB6D6C RIVET, UNIVERSAL HD 2 BACR15BA7AD12C RIVET, 100 DEG

**FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 73 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE**  0.191 - 0.202 BACR15BB6D6C RIVET, UNIVERSAL HD A
0.223 - 0.233 BACR15BA7AD11C RIVET, 100 DEG B

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 1 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 74 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** GROUP 1-5, 8, 9: C Determine grip lengthfrom hole before installation. (a) 0.4385 - 0.4406 BACB30WQ7K14L BOLT, RADIUS LEAD- IN Determine grip lengthfrom hole before installation. (a) 0.4385 - 0.4406 BACB30WQ7K15L BOLT, RADIUS LEAD- IN
Install under the nut.
- BACW10AT27AS WASHER Install under the nut.
- BACW10AT37AS WASHER Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT GROUP 6, 10: If removed fastener was a straight shank bolt. Determine grip lengthfrom hole before installation. (a) 0.3866 - 0.3886 BACB30YN12K15X BOLT, HEX DRIVE

If removed fastener was a straight shank bolt. Determine grip lengthfrom hole before installation. (a) 0.3866 - 0.3886 BACB30YN12K16X BOLT, HEX DRIVE

If removed fastener wasa straight shank bolt. Install 2 washers under the nut. - NAS1149D0663J WASHER

If removed fastener was a straight shank bolt.Torque to 213 - 227 inlbs. - BACN10YR6CD SELF-LOCKING NUT

If removed fastener wasa taper shank bolt. Determine grip length from hole before installation. (a) 0.4335 - 0.4355 BACB30YN14K15 BOLT, HEX DRIVE

If removed fastener wasa taper shank bolt. Determine grip length from hole before installation. (a) 0.4335 - 0.4355 BACB30YN14K16 BOLT

- NAS1149D0763J WASHER

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 2 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 75 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE**  If removed fastener was a taper shank bolt. Install 2 washers under the nut. If removed fastener was a taper shank bolt.Torque to 291 - 309 inlbs. - BACN10YR7CD NUT

GROUP 7: Determine grip lengthfrom hole before installation. (a) 0.3866 - 0.3886 BACB30YN12K15X BOLT, HEX DRIVE

Determine grip lengthfrom hole before installation. (a) 0.3866 - 0.3886 BACB30YN12K16X BOLT, HEX DRIVE

Install 2 washers under the nut. - NAS1149D0663J WASHER Torque to 213 - 227 inlbs. - BACN10YR6CD SELF-LOCKING NUT

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 3 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 76 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** GROUP 1-5, 8, 9: D Determine grip lengthfrom hole before installation. (a) 0.4385 - 0.4406 BACB30WQ7K14L BOLT, RADIUS LEAD- IN Determine grip lengthfrom hole before installation. (a) 0.4385 - 0.4406 BACB30WQ7K15L BOLT, RADIUS LEAD- IN
Install under the nut.
- BACW10AT27AS WASHER Install under the nut.
- BACW10AT37AS WASHER Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT GROUP 6, 10: If removed fastener was a straight shank bolt. (a) 0.3856 - 0.3877 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN If removed fastener wasa straight shank bolt. Install under the nut. - BACW10AT26AS WASHER

If removed fastener wasa straight shank bolt. Install under the nut. - BACW10AT36AS WASHER

If removed fastener was a straight shank bolt.Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

If removed fastener was a taper shank bolt. (a) 0.4385 - 0.4406 BACB30WQ7K15L BOLT, RADIUS LEAD- IN If removed fastener was a taper shank bolt. Install under the nut. - BACW10AT27AS WASHER

If removed fastener was a taper shank bolt. Install under the nut. - BACW10AT37AS WASHER

If removed fastener was a taper shank bolt.Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT

GROUP 7: (a) 0.3856 - 0.3877 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 4 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 77 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** WASHER Install under the nut.

- BACW10AT26AS Install under the nut.
- BACW10AT36AS WASHER Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 5 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 78 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** GROUP 1-4, 8: E Determine grip lengthfrom hole before installation. (a) 0.3387 - 0.3408 BACB30WQ5K13LY BOLT, RADIUS LEAD- IN Determine grip lengthfrom hole before installation. (a) 0.3387 - 0.3408 BACB30WQ5K14LY BOLT, RADIUS LEAD- IN
Install under the nut.
- BACW10P448CG WASHER, FLAT Install under the nut.
- BACW10P454CG WASHER, FLAT Torque to 150 - 155 inlbs. - BACN10HY5ACX NUT GROUP 5, 9: (a) 0.4385 - 0.4406 BACB30WQ7K15L BOLT, RADIUS LEAD- IN Install under the nut.
- BACW10AT27AS WASHER Install under the nut.
- BACW10AT37AS WASHER Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT GROUP 6, 10: If removed fastener was a straight shank bolt. (a) 0.3856 - 0.3877 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN If removed fastener wasa straight shank bolt. Install under the nut. - BACW10AT26AS WASHER

If removed fastener wasa straight shank bolt. Install under the nut. - BACW10AT36AS WASHER

If removed fastener was a straight shank bolt.Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

If removed fastener was a taper shank bolt. (a) 0.4385 - 0.4406 BACB30WQ7K15L BOLT, RADIUS LEAD- IN If removed fastener was a taper shank bolt. Install under the nut. - BACW10AT27AS WASHER

- BACW10AT37AS WASHER

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 6 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 79 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE**  If removed fastener was a taper shank bolt. Install under the nut. If removed fastener was a taper shank bolt.Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT

GROUP 7: (a) 0.3856 - 0.3877 BACB30WQ6K15LX BOLT, RADIUS LEAD- IN Install under the nut.
- BACW10AT26AS WASHER Install under the nut.
- BACW10AT36AS WASHER Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 7 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 80 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** GROUP 1, 2, 8: F If removed fastener was a radius lead-in bolt. (a) 0.3856 - 0.3877 BACB30WQ6K9LX BOLT, HEX DRIVE
If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT26AS WASHER

If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT36AS WASHER

If removed fastener was a radius lead-in bolt.Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

If removed fastener was a taper shank bolt. (a) 0.4012 - 0.4033 BACB30WQ6K9LY BOLT
If removed fastener was a taper shank bolt. Install under the nut. - BACW10P449CG WASHER

If removed fastener was a taper shank bolt. Install under the nut. - BACW10P455CG WASHER, FLAT

If removed fastener was a taper shank bolt.Torque to 235 - 245 inlbs. - BACN10HY6ACX NUT

GROUP 3- 6, 9, 10: If removed fastener wasa radius lead-in bolt. Determine grip length from hole before installation. (a) 0.3856 - 0.3877 BACB30WQ6K8LX BOLT, RADIUS LEAD- IN

If removed fastener wasa radius lead-in bolt. Determine grip length from hole before installation. (a) 0.3856 - 0.3877 BACB30WQ6K9LX BOLT, HEX DRIVE

If removed fastener wasa radius lead-in bolt. Determine grip length from hole before installation. (a) 0.3856 - 0.3877 BACB30WQ6K10LX BOLT, RADIUS LEAD- IN

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 8 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 81 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** WASHER If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT26AS

If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT36AS WASHER

If removed fastener was a radius lead-in bolt.Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

If removed fastener wasa taper shank bolt. Determine grip length from hole before installation. (a) 0.4012 - 0.4033 BACB30WQ6K8LY BOLT, RADIUS LEAD- IN

If removed fastener wasa taper shank bolt. Determine grip length from hole before installation. (a) 0.4012 - 0.4033 BACB30WQ6K9LY BOLT

If removed fastener wasa taper shank bolt. Determine grip length from hole before installation. (a) 0.4012 - 0.4033 BACB30WQ6K10LY BOLT, RADIUS LEAD- IN

If removed fastener was a taper shank bolt. Install under the nut. - BACW10P449CG WASHER

If removed fastener was a taper shank bolt. Install under the nut. - BACW10P455CG WASHER, FLAT

If removed fastener was a taper shank bolt.Torque to 235 - 245 inlbs. - BACN10HY6ACX NUT

GROUP 7: If removed fastener was a radius lead-in bolt. (a) 0.3856 - 0.3877 BACB30WQ6K10LX BOLT, RADIUS LEAD- IN If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT26AS WASHER

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 9 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 82 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** WASHER If removed fastener wasa radius lead-in bolt. Install under the nut. - BACW10AT36AS

If removed fastener was a radius lead-in bolt.Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT

If removed fastener was a taper shank bolt. (a) 0.4012 - 0.4033 BACB30WQ6K10LY BOLT, RADIUS LEAD- IN If removed fastener was a taper shank bolt. Install under the nut. - BACW10P449CG WASHER

If removed fastener was a taper shank bolt. Install under the nut. - BACW10P455CG WASHER, FLAT

If removed fastener was a taper shank bolt.Torque to 235 - 245 inlbs. - BACN10HY6ACX NUT

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 10 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 83 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE** GROUP 1, 3: G (a) 0.4012 - 0.4033 BACB30WQ6K12LY BOLT, RADIUS LEAD- IN Install under the nut.
- BACW10P449CG WASHER Install under the nut.
- BACW10P455CG WASHER, FLAT Torque to 235 - 245 inlbs. - BACN10HY6ACX NUT GROUP 2, 4-6, 8-10: (a) 0.4385 - 0.4406 BACB30WQ7K14L BOLT, RADIUS LEAD- IN Install under the nut.
- BACW10AT27AS WASHER Install under the nut.
- BACW10AT37AS WASHER Torque to 330 - 340 inlbs. - BACN10HY7AC SELF-LOCKING NUT
GROUP 7: (a) 0.3856 - 0.3877 BACB30WQ6K14LX BOLT, RADIUS LEAD- IN Install under the nut.
- BACW10AT26AS WASHER Install under the nut.
- BACW10AT36AS WASHER Torque to 235 - 245 inlbs. - BACN10HY6AC SELF-LOCKING NUT
Clean underside of fastener head prior to installation. Refer SOPM 20- 30-03, Solvent CleaningMethod 3 as an accepted procedure. (b) 0.192 - 0.196 NAS1399MW6A4 RIVET, BLIND H

(b) 0.223 - 0.233 BACR15BA7D9C RIVET, 100 DEG I (b) 0.223 - 0.233 BACR15BA7D10C RIVET, 100 DEG (b) 0.223 - 0.233 BACR15BA7D12C RIVET, 100 DEG (b) 0.190 - 0.194 BACB30NN3K3 BOLT-100 DEG HEAD J (b) 0.223 - 0.229 BACR15GF7D7 RIVET, 100 DEG K

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 11 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 84 of 85 **BOEING SERVICE BULLETIN 747-57-2332 MORE DATA**  **HOLE DIA IDENTIFICATION**  **NAME CODE**  Determine grip lengthfrom hole before installation. (b) 0.223 - 0.233 BACR15BA7AD10C RIVET, 100 DEG L

Determine grip lengthfrom hole before installation. (b) 0.223 - 0.233 BACR15BA7AD11C RIVET, 100 DEG

Determine grip lengthfrom hole before installation. (b) 0.223 - 0.233 BACR15BA7AD12C RIVET, 100 DEG

Determine grip lengthfrom hole before installation. (b) 0.223 - 0.233 BACR15BA7AD13C RIVET, 100 DEG

0.223 - 0.233 BACR15BA7AD12C RIVET, 100 DEG M(a) Install with BMS5-95 wet sealant. Refer to SOPM 20-50-19, Method 2 as an accepted procedure. (b) Refer to SOPM 20-50-18 as an accepted procedure for installation.

**APPENDIX A: MASTER FASTENER CODE TABLE (SHEET 12 OF 12)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 09, 2010 747-57-2332 85 of 85 **BOEING SERVICE BULLETIN 747-57-2332**