### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-54-1043**  Original Issue: May 02, 2007 Revision 2: November 04, 2011 ATA System: 5455 **SUBJECT:**NACELLES/PYLONS - Strut Drains and Seals - Aft Fairing Drain Tube Assembly Replacement. 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 1 of 90 5.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 2 of 90 **BOEING SERVICE BULLETIN 737-54-1043**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 30 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 30 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 31 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 35 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 36 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38 FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE. . . . . . . . . . 41 FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE. . . . . . . . . . 46 FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE [Group 1] . . 51 FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE [Group 2] . . 61 FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE [Group 1] . . 71 FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE [Group 2] . . 81

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 3 of 90 **BOEING SERVICE BULLETIN 737-54-1043**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 4 of 90 **BOEING SERVICE BULLETIN 737-54-1043**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Revision Transmittal Sheet**  **Number: 737-54-1043** Original Issue: May 02, 2007 Revision 2: November 04, 2011 ATA System: 5455 **SUBJECT:**NACELLES/PYLONS - Strut Drains and Seals - Aft Fairing Drain Tube Assembly Replacement. This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** More work is necessary on the airplane(s) changed in accordance with the original issue or Revision 1 of this service bulletin. The engine strut aft fairing drain tube assembly will have to be replaced with a new engine strut aft fairing drain tube assembly with integral support clamp. Airplanes were added to this service bulletin's effectivity. Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-08-24 is related to this service bulletin. **REASON FOR REVISION** This revision is sent to replace the engine strut aft fairing drain tube assembly with a new engine strut aft fairing drain tube assembly with integral support clamp.. These sections were changed: 1. In Paragraph 1.A.1, Planning, Effectivity, Airplanes - added additional airplanes. 2. Divided effectivity into 2 groups. 3. In Paragraph 1.H., Weight and Balance Changes - updated change in weight and moment. 4. Paragraph 2.A., Material - Price and Availability, and paragraph 2.C., Parts Necessary For Each Airplane, inserted new topkit. 5. Paragraph 2.B., Industry Support Information, updated warranty statement. 6. Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added optional Hi-Lok fasteners. 7. Paragraph 3.A., Accomplishment Instructions, General Information, updated the General Notes. 8. Paragraph 3.B.1.b. and 3.B.2.b., added note about parts removal for gaining access.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 5 of 909. Paragraph 3.B.1.f. and 3.B.2.f., 3.B.2.g. and 3.B.2.g, added caution for removing excess sealant from the aft strut drain tube assembly. 10. Illustrations for Figure 1, view A-A, view C, and Figure 2, view A-A, view C, added note about different configurations. 11. Step Tables for Figures 1 and 2, removed all part numbers. 12. Added two new Figures: 4 and 6. 13. Figures 1 and 2, revised step 6 to check and make sure the fastener holes on the sump are not damaged, after removing any sealant that may be present. 14. Figures 3 and 5, updated illustration views with new aft strut drain tube assembly. Updated steps 1, 2 and 3 with new drain tube assembly part number. Revised steps 3 and 4 in the step tables to install the new strut drain tube assembly. Updated the fastener tables with some new fasteners, including oversize fasteners. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. The data given in Information Notice 737-54-1043 IN 02 is included in this revision. Pages with no vertical lines have no important changes. **REVISION HISTORY** May 02, 2007 Original Issue: October 19, 2009 Revision 1: November 04, 2011 Revision 2:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 6 of 90 **BOEING SERVICE BULLETIN 737-54-1043**

### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 737-54-1043** Original Issue: May 02, 2007 Revision 2: November 04, 2011 ATA System: 5455 **SUBJECT:**NACELLES/PYLONS - Strut Drains and Seals - Aft Fairing Drain Tube Assembly Replacement. BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Accomplishment of this service bulletin replaces the engine strut aft fairing drain tube assembly and the support clamp. Boeing has received seven reports of failure of the engine strut aft fairing drain tube assembly. In most of the reports the failure occurred at the brazed joint between the tube and the drain fitting. The flight hours for the affected airplanes ranged from 794 to 9,373 hours and the flight cycles ranged from 531 to 6,848 cycles. On an airplane that had the intent of the service bulletin incorporated in production, one operator reported finding the left engine strut aft fairing drain tube assembly broken in service at the clamp support location under the aft fairing compartment, inside the aft fairing heat shield cavity. The airplane had flown approximately 4,127 flight cycles and 6,845 flight hours. There have also been several reports of tube wear at the clamp location for this design. The failure of the engine strut aft fairing drain tube assembly would allow flammable fluids in the drain system to discharge directly onto the aft fairing heat shield which may result in a fire. Revision 2 of this service bulletin gives instructions to replace the engine strut aft fairing drain tube assembly with a new engine strut aft fairing drain tube assembly with integral support clamp, and is made from nickel alloy 625. The new engine strut aft fairing drain tube assembly is designed to eliminate wear damage on the drain tube from the clamp and subsequent tube failure. This will help to make sure the drain system integrity is maintained and that drained fluids do not come in contact with the aft fairing heat shield. Boeing Service Related Problem 737NG-SRP-54-0134 is related to this service bulletin. **ACTION (PRR 38275-178S)** Remove access panels from the aft fairings on the left and right engine strut. Remove the aft fairing heat shield sections, as required, from the left and right engine strut aft fairing drain tube assemblies. Remove the two sections of the engine strut aft fairing drain tube assembly. Install the new aft section of the engine strut aft fairing drain tube assembly to the aft fairing sump and the existing rear support bracket. Add radius filler to the bracket. Reinstall the forward section of the engine strut aft fairing drain tube assembly. Reinstall the aft fairing heat shield sections that were removed and the aft strut access panels on the left and right engine strut.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 7 of 90**EFFECTIVITY** 737-600/700/700C/800/900/900ER Series Airplanes with CFM56-7 engines. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration Airworthiness Directive FAA AD 2008-08-24 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of September 29, 2005. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  10.00 13.50 737-600/-700/-700C/-800/- 900/-900ER
**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: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 8 of 90 **BOEING SERVICE BULLETIN 737-54-1043**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 9 of 90 **BOEING SERVICE BULLETIN 737-54-1043**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 10 of 90 **BOEING SERVICE BULLETIN 737-54-1043**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-54-1043**  Original Issue: May 02, 2007 Revision 2: November 04, 2011 ATA System: 5455 **SUBJECT:**NACELLES/PYLONS - Strut Drains and Seals - Aft Fairing Drain Tube Assembly Replacement. BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 38275-178S for data about this change. Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
**DESCRIPTION CONFIGURATION**  **GROUP** 737-600/700/700C/800/900/900ER Series Airplanes Line Numbers 1 through 619 with CFM56-7 engines. - 1
737-600/700/700C/800/900/900ER Series Airplanes Line Numbers 620 through 3699 with CFM56-7 engines, minus Airplane Line Number 3464. - 2

Airplane Models: 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **Group Variable Number** 1 YA001 - YA073 2 YA074 - YA099 2 YA101 - YA199 1 YA201 - YA207

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 11 of 90**Group Variable Number** 2 YA208 - YA211 2 YA221 1 YA231 - YA242 1 YA251 - YA254 2 YA255 - YA256 1 YA271 - YA272 1 YA291 1 YA301 - YA302 1 YA311 - YA314 1 YA321 - YA322 2 YA323 2 YA336 - YA345 2 YA351 2 YA356 - YA357 2 YA366 - YA367 2 YA371 - YA377 1 YA501 - YA536 1 YA541 - YA548 2 YA549 - YA552 1 YA571 - YA578 1 YA601 - YA612 2 YA613 - YA615 2 YA621 - YA622 2 YA626 - YA631 2 YA635 - YA636 2 YA641 - YA642 2 YA645 - YA650 2 YA656 - YA659 2 YA666 - YA667 2 YA671 - YA672 2 YA681 - YA691 1 YA701 - YA704 2 YA705 - YA710

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 12 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**1 YA721 - YA722 1 YA731 - YA733 2 YA734 1 YA751 - YA756 2 YA801 - YA803 2 YA809 1 YA811 - YA814 1 YA831 - YA834 2 YA835 1 YA841 - YA850 2 YA851 - YA862 1 YA881 - YA882 1 YA891 - YA892 1 YA961 - YA966 2 YA967 - YA978 1 YB001 - YB006 2 YB101 - YB132 2 YB151 - YB153 2 YB156 - YB158 2 YB161 - YB164 2 YB171 - YB172 2 YB181 - YB184 2 YB201 - YB208 2 YB271 2 YB276 2 YB301 - YB310 2 YB371 - YB392 2 YB501 - YB502 2 YB521 - YB526 2 YB541 - YB544 2 YB551 2 YB561 - YB598 2 YB601 - YB635

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 13 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YB651 2 YB656 2 YB671 - YB672 2 YB851 - YB863 2 YB871 - YB874 2 YB881 - YB893 2 YB901 - YB903 2 YB911 2 YB961 - YB975 2 YB981 2 YB986 - YB998 1 YC001 - YC019 2 YC020 - YC030 1 YC051 - YC064 2 YC065 - YC070 1 YC071 - YC080 2 YC081 - YC084 2 YC091 - YC095 1 YC101 - YC103 2 YC104 1 YC111 - YC112 2 YC113 1 YC121 1 YC126 - YC127 1 YC136 - YC139 2 YC140 - YC141 2 YC146 - YC147 2 YC151 - YC156 2 YC166 - YC171 2 YC176 - YC179 2 YC186 - YC190 2 YC201 - YC203 2 YC206 - YC207

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 14 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**1 YC301 - YC303 2 YC304 - YC305 1 YC321 - YC367 2 YC368 - YC380 1 YC381 - YC382 2 YC383 - YC387 1 YC391 2 YC392 - YC394 1 YC396 1 YC401 - YC410 2 YC411 - YC417 2 YC421 - YC422 2 YC426 - YC428 2 YC436 - YC439 1 YC441 - YC445 2 YC446 - YC448 1 YC451 - YC455 2 YC459 1 YC461 - YC466 2 YC467 1 YC471 - YC480 2 YC481 - YC499 1 YC501 - YC522 2 YC523 - YC526 1 YC571 - YC580 2 YC581 - YC583 2 YC587 - YC589 1 YC591 - YC593 1 YC601 - YC624 2 YC625 - YC655 1 YC681 2 YC682 - YC696 1 YC701 - YC709

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 15 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YC710 - YC715 2 YC720 - YC725 2 YC727 - YC730 1 YC731 - YC736 2 YC737 - YC750 1 YC751 - YC752 1 YC761 - YC770 1 YC781 - YC787 2 YC788 - YC793 1 YC801 - YC839 2 YC840 - YC892 1 YC901 - YC903 2 YC904 - YC905 1 YC906 2 YC907 2 YC921 - YC922 1 YC931 - YC932 1 YC941 - YC947 2 YC948 - YC951 1 YC971 - YC972 2 YC973 - YC978 1 YC981 - YC983 1 YD001 - YD005 2 YD006 - YD007 1 YD021 - YD023 2 YD024 - YD025 1 YD041 - YD045 2 YD046 - YD057 2 YD081 - YD084 1 YD101 2 YD102 - YD117 2 YD121 - YD126 2 YD151 - YD159

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 16 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YD171 - YD172 2 YD201 - YD203 2 YD206 - YD209 2 YD216 - YD219 2 YD251 - YD254 2 YD256 - YD257 2 YD261 2 YD301 - YD334 2 YD391 2 YD401 - YD410 2 YD412 - YD417 2 YD481 - YD485 2 YD491 - YD499 1 YD501 2 YD502 - YD512 2 YD531 - YD535 2 YD541 - YD547 2 YD561 - YD564 2 YD571 - YD572 2 YD591 - YD595 2 YD601 - YD612 2 YD651 - YD655 1 YE001 - YE020 1 YE051 1 YE101 - YE109 1 YE151 - YE156 2 YE157 1 YE171 - YE172 2 YE201 - YE206 2 YE301 - YE305 2 YE321 - YE326 2 YE371 - YE383 2 YF001 - YF011

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 17 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YF021 - YF049 2 YF051 - YF067 2 YF086 - YF087 2 YF106 - YF107 2 YF111 - YF114 2 YF116 - YF119 2 YF121 - YF130 2 YF176 - YF178 2 YF191 - YF192 2 YF201 - YF276 2 YF401 - YF402 2 YF431 - YF432 2 YF441 - YF442 2 YF451 - YF460 2 YF501 - YF599 2 YF601 - YF621 2 YF701 - YF707 2 YF801 - YF805 2 YF831 - YF832 2 YF836 - YF838 2 YF901 - YF905 2 YF921 - YF928 2 YF951 - YF953 1 YG001 - YG037 2 YG038 - YG044 1 YG061 - YG064 1 YG066 - YG072 2 YG073 - YG089 2 YG091 - YG099 2 YG101 - YG104 2 YG111 - YG114 2 YG116 - YG129 2 YG201 - YG205

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 18 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YG211 - YG214 2 YG221 - YG224 2 YG251 - YG252 1 YG501 - YG502 2 YG503 - YG512 2 YG601 - YG602 2 YG701 2 YG711 2 YH001 - YH012 2 YH031 - YH055 2 YH071 - YH080 2 YH101 - YH132 2 YH201 - YH202 2 YH206 - YH207 2 YH301 - YH306 2 YH321 - YH322 2 YH501 - YH504 2 YH551 2 YH601 - YH602 2 YH611 - YH612 2 YJ001 - YJ013 2 YJ021 2 YJ471 - YJ480 2 YJ501 - YJ517 2 YJ531 - YJ579 2 YJ591 - YJ599 2 YJ631 - YJ632 2 YJ671 - YJ694 2 YJ801 - YJ867 2 YJ871 - YJ880 2 YJ901 - YJ904 2 YJ908 - YJ929 2 YJ931 - YJ937

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 19 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YJ941 - YJ956 2 YJ961 2 YJ976 - YJ977 2 YK001 - YK007 2 YK101 - YK104 2 YK111 - YK112 2 YK121 - YK122 2 YK131 - YK133 2 YK136 - YK139 2 YK141 - YK142 2 YK146 - YK148 2 YK151 - YK154 2 YK161 - YK167 2 YK171 2 YK176 - YK177 2 YK186 2 YK191 2 YK196 2 YK201 - YK202 2 YK301 - YK314 2 YK321 - YK340 2 YK361 - YK378 2 YK401 - YK406 2 YK426 - YK427 2 YK431 - YK450 2 YK456 - YK467 2 YK471 - YK473 2 YK476 2 YK480 - YK487 2 YK491 - YK492 2 YK495 - YK498 2 YK511 - YK516 2 YK521 - YK530

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 20 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YK551 - YK571 2 YK576 - YK577 2 YK580 - YK585 2 YK601 - YK602 2 YK606 - YK607 2 YK611 - YK616 2 YK621 - YK634 2 YK641 - YK644 2 YK651 - YK665 2 YK671 - YK672 2 YK676 - YK677 2 YK681 - YK686 2 YK691 2 YK701 - YK713 2 YK716 - YK719 2 YK721 - YK741 2 YK751 - YK770 2 YK776 - YK778 2 YK781 - YK785 2 YK791 - YK792 2 YK796 - YK797 2 YK801 - YK899 2 YK901 - YK912 2 YK918 - YK919 2 YK921 - YK929 2 YK941 - YK997 2 YL001 - YL005 2 YL011 - YL016 2 YL021 - YL024 2 YL051 - YL052 2 YL056 - YL057 2 YL061 2 YL066 - YL069

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 21 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YL076 - YL077 2 YL101 - YL137 2 YL201 - YL230 2 YL241 - YL242 2 YL271 - YL272 2 YL281 - YL284 2 YL301 - YL303 2 YL311 - YL314 2 YL316 - YL321 2 YL351 - YL353 2 YL371 - YL374 2 YL401 2 YL421 - YL429 2 YL431 - YL444 2 YL461 - YL478 2 YL501 - YL509 2 YL531 - YL534 2 YL541 - YL549 2 YL561 - YL575 2 YL591 - YL598 2 YL601 - YL606 2 YL611 - YL612 2 YL616 - YL617 2 YL621 2 YL626 2 YL631 - YL634 2 YL636 - YL637 2 YL661 - YL664 2 YL676 - YL685 2 YL691 2 YL696 - YL697 2 YL701 - YL707 2 YL731

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 22 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YL751 - YL752 2 YL756 - YL757 2 YL761 - YL780 2 YL796 - YL797 2 YL801 - YL815 2 YL901 - YL910 2 YL921 - YL940 2 YL951 - YL968 2 YM101 - YM1032 YM201 - YM2442 YM251 - YM2992 YM301 - YM3992 YM401 - YM4052 YM471 2 YM481 - YM4842 YM501 - YM5152 YM521 - YM5222 YM541 2 YM551 - YM5532 YM571 - YM5722 YM581 - YM5822 YM591 - YM5992 YM631 - YM6342 YM641 - YM6522 YM671 - YM6742 YM691 - YM6992 YM701 - YM7102 YM761 - YM7652 YM771 - YM7742 YN001 - YN016 2 YN021 - YN024 2 YN061 2 YN071 - YN082

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 23 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YN091 - YN092 2 YN101 - YN112 2 YN121 2 YN201 - YN202 2 YN211 - YN219 2 YN231 - YN236 2 YN261 2 YN501 2 YN531 2 YN701 2 YQ001 - YQ003 2 YQ011 - YQ019 2 YQ026 - YQ029 2 YQ036 - YQ044 2 YQ201 2 YQ231 2 YQ241 - YQ251 2 YQ281 2 YQ291 - YQ295 2 YQ301 - YQ302 2 YQ401 - YQ403 2 YQ451 - YQ452 2 YR001 - YR010 2 YR051 - YR054 2 YR101 - YR102 2 YR111 - YR116 2 YR126 - YR129 2 YR141 - YR142 2 YR166 - YR169 2 YR202 - YR204 2 YR231 - YR243 2 YR271 - YR274 2 YR291 - YR292

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 24 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group**  **Variable Number**2 YR301 - YR305 2 YR401 - YR403 2 YR421 2 YR451 2 YR501 - YR503 2 YR511 2 YR601 - YR602 2 YR701 - YR703 2 YR801 - YR802 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Accomplishment of this service bulletin replaces the engine strut aft fairing drain tube assembly and the support clamp. Boeing has received seven reports of failure of the engine strut aft fairing drain tube assembly. In most of the reports the failure occurred at the brazed joint between the tube and the drain fitting. The flight hours for the affected airplanes ranged from 794 to 9,373 hours and the flight cycles ranged from 531 to 6,848 cycles. On an airplane that had the intent of the service bulletin incorporated in production, one operator reported finding the left engine strut aft fairing drain tube assembly broken in service at the clamp support location under the aft fairing compartment, inside the aft fairing heat shield cavity. The airplane had flown approximately 4,127 flight cycles and 6,845 flight hours. There have also been several reports of tube wear at the clamp location for this design. The failure of the engine strut aft fairing drain tube assembly would allow flammable fluids in the drain system to discharge directly onto the aft fairing heat shield which may result in a fire. Revision 2 of this service bulletin gives instructions to replace the engine strut aft fairing drain tube assembly with a new engine strut aft fairing drain tube assembly with integral support clamp, and is made from nickel alloy 625. The new engine strut aft fairing drain tube assembly is designed to eliminate wear damage on the drain tube from the clamp and subsequent tube failure. This will help to make sure the drain system integrity is maintained and that drained fluids do not come in contact with the aft fairing heat shield. Boeing Service Related Problem 737NG-SRP-54-0134 is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 25 of 90 **BOEING SERVICE BULLETIN 737-54-1043**As a part of a service bulletin validation program, this change was completed on airplane YG023 by Service Bulletin 737-54-1043 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane YG023 by Service Bulletin 737-54-1043 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane YG023 has the configuration of a Group 1 airplane. Revision 1 is sent to make changes to the service bulletin as a result of the validation findings. These sections were changed: 1. Summary section and Paragraph 1.E., Compliance - FAA AD 2008-08-24 is added. 2. Paragraph 1.F., Approval - An Alternative Method of Compliance (AMOC) is added. 3. Paragraph 1.G., Manpower - The allocated task hours are revised. 4. Paragraph 3.B., Work Instructions - Access panels 434AL and 444AR are removed from PART 1 and PART 2 of the work instructions respectively. 5. Figure 3 and Figure 4 - Step table, Footnote (a) is changed. Revision 2 is sent to replace the engine strut aft fairing drain tube assembly with a new engine strut aft fairing drain tube assembly which contains a welded monolithic support fitting with integrated mounting pad. These sections were changed: 1. In Paragraph 1.A.1, Planning, Effectivity, Airplanes - added additional airplanes. 2. Divided effectivity into 2 groups. 3. In Paragraph 1.H., Weight and Balance Changes - updated change in weight and moment. 4. Paragraph 2.A., Material - Price and Availability, and paragraph 2.C., Parts Necessary For Each Airplane, inserted new topkit. 5. Paragraph 2.B., Industry Support Information, updated warranty statement. 6. Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added optional Hi-Lok fasteners. 7. Paragraph 3.A., Accomplishment Instructions, General Information, updated the General Notes. 8. Paragraph 3.B.1.b. and 3.B.2.b., added note about parts removal for gaining access. 9. Paragraph 3.B.1.f. and 3.B.2.f., 3.B.2.g. and 3.B.2.g, added caution for removing excess sealant from the aft strut drain tube assembly. 10. Illustrations for Figure 1, view A-A, view C, and Figure 2, view A-A, view C, added note about different configurations. 11. Step Tables for Figures 1 and 2, removed all part numbers.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 26 of 90 **BOEING SERVICE BULLETIN 737-54-1043**12. Added two new Figures: 4, and 6. 13. Figures 1 and 2, revised step 6 to check and make sure the fastener holes on the sump are not damaged, after removing any sealant that may be present. 14. Figures 3 and 5, updated illustration views with new aft strut drain tube assembly. Updated steps 1, 2 and 3 with new drain tube assembly part number. Revised steps 3 and 4 in the step tables to install the new strut drain tube assembly. Updated the fastener tables with some new fasteners, including oversize fasteners. The data given in Information Notice 737-54-1043 IN 02 is included in this revision. **D. Description** Remove access panels from the aft fairings on the left and right engine strut. Remove the aft fairing heat shield sections, as required, from the left and right engine strut aft fairing drain tube assemblies. Remove the two sections of the engine strut aft fairing drain tube assembly. Install the new aft section of the engine strut aft fairing drain tube assembly to the aft fairing sump and the existing rear support bracket. Add radius filler to bracket. Reinstall the forward section of the engine strut aft fairing drain tube assembly. Reinstall the aft fairing heat shield sections that were removed and the aft strut access panels on the left and right engine strut. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Revision 2 - More work is necessary on airplanes changed in accordance with Revision 1 of this service bulletin. Revision 2 requires the engine strut aft fairing drain tube assembly be replaced with a new engine strut aft fairing drain tube assembly with integral support clamp. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 434, 444 737-600, 737-700, 737-700C, 737-800, 737-900 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 434, 444 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **E. Compliance** Federal Aviation Administration Airworthiness Directive FAA AD 2008-08-24 is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 27 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 sixty months after the Revision 2 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. This service bulletin has been approved by the FAA. In addition, the Manager of the Seattle Aircraft Certification Office approves the replacement of the drain tube assemblies and support clamps in accordance with SB 737-54-1043 Revision 2 as an AMOC to replacement of the drain tube assemblies and support clamps in accordance with SB 737-54-1043, dated May 2, 2007, as required by paragraphs (f) and (h) of AD 2008-08-24. All provisions of AD 2008-08-24 that are not specifically referenced in the preceding sentence remain fully applicable and must be complied with. **G. Manpower** The table below shows an estimate of the task hours necessary to do this modification for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Group 1: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
1.75 3.50 2 Open Access 1.50 1.50 1 Figure 1 1.50 1.50 1 Figure 2 2.00 2.00 1 Figure 3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 28 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group 1:**  **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**
2.00 2.00 1 Figure 5 1.75 3.50 2 Close Access 10.50 14.00 TOTAL FOR EACH AIRPLANE(a) (a) Estimate does not include time to make parts. More time will be required to make parts. **Group 2: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
1.75 3.50 2 Open Access 1.50 1.50 1 Figure 1 1.50 1.50 1 Figure 2 2.00 2.00 1 Figure 4 2.00 2.00 1 Figure 6 1.75 3.50 2 Close Access 10.50 14.00 TOTAL FOR EACH AIRPLANE(a) (a) Estimate does not include time to make parts. More time will be required to make parts. **H. Weight and Balance Changes NOTE:** The following Weight and Balance changes are for airplanes in their delivered configuration. **Group 1: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+ 518 + 0.81 737-600/-700/-700C/-800/- 900/-900ER **Group 2: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+499 + 0.78 737-600/-700/-700C/-800/- 900/-900ER up to and including Line Number 2091

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 29 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Group 2:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane**
+179 +0.28 737-600/-700/-700C/-800/- 900/-900ER after Line Number 2091
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Engineering Change Memo PRR 38275-178S b. Boeing Service Letter 737-SL-51-042 c. Boeing Service Related Problem (SRP) 737NG-SRP-54-0134 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2008-08-24 e. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-19 f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-12, 20-10-19 g. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 54-52-06, 54-52-08, 54-55-02 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number** Drain Installation, Aft Fairing CFM56-7 313A2500 This drawing was used to prepare this service bulletin. This drawing is not necessary to make the specified changes, and is not supplied with this service bulletin. This drawing may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 30 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Chapter-Section**  **Publication** 54-55 737 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: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 31 of 90 **BOEING SERVICE BULLETIN 737-54-1043**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 32 of 90 **BOEING SERVICE BULLETIN 737-54-1043**

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. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are 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 RE SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE**  **INFORMATION**
**Unit Price thru August 31, 2012**  **QTY Date**  **Name Kit Number**  $12,326.00 60 10/31/2011 Top Kit 002A0001-108 (a) 60 11/14/201160 11/30/201160 12/14/201160 01/06/201260 01/20/201260 02/03/201260 02/17/201220 03/02/2012 (a) This topkit replaces the 002A0001-76 topkit. **B. Industry Support Information** Boeing warranty remedies are available for 737 airplanes in warranty as of September 29, 2005. 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. Please contact Boeing Spares for disposition of any unused (purchased and/or no charge) kits. **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: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 33 of 90 **BOEING SERVICE BULLETIN 737-54-1043 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 6**  **5 4**  **3 Top Kit**  1 1 1 1 002A0001-108
**ALL**
**KIT 002A0001-108**

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

**New Part Number 6**  **5 4**  **3 QTY**  DRAIN TUBE ASSY 1 1 1 1 313A2501-24
RADIUS FILLER 1 1 1 1 313A2503-20 BOLT 2 2 2 2 BACB30LM3U6 BOLT, PROTRUDING HD 4 4 4 4 BACB30NX6K4X BOLT, PROTRUDING HD 4 4 4 4 BACB30NX6K4Y BOLT, PROTRUDING HD 4 4 4 4 BACB30NX8K4X BOLT, PROTRUDING HD 4 4 4 4 BACB30NX8K4Y BOLT, 100 DEG HEX DR 2 2 2 2 BACB30NY6K4Y
HI-LOK 2 2 2 2 BACB30YM6K10 BOLT, HEX DRIVE 2 2 2 2 BACB30YM6K10X BOLT, HEX DRIVE 2 2 2 2 BACB30YM6K10Y COLLAR 2 2 2 2 BACC30AC6 COLLAR, PRELOAD 4 4 4 4 BACC30AC6S COLLAR, PRELOAD 4 4 4 4 BACC30AC8S
COLLAR 4 4 4 4 BACC30BH6S COLLAR 4 4 4 4 BACC30BH8S COLLAR, PRELOAD 4 4 4 4 BACC30CP6C

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 34 of 90 **BOEING SERVICE BULLETIN 737-54-1043 ALL** 
**KIT 002A0001-108**

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

**New Part Number 6**  **5 4**  **3 QTY**  COLLAR, PRELOAD 2 2 2 2 BACC30CP6CY
NUT 2 2 2 2 BACN11Z3C SHIM, LAMINATED 1 1 1 1 BACS40R007B020F WASHER, PLAIN 4 4 4 4 BACW10BP31NA- PU WASHER, PLAIN 4 4 4 4 BACW10BP32NA- PU WASHER 2 2 2 2 BACW10BP3ACU WASHER, PLAIN 4 4 4 4 BACW10BP41NA- PU WASHER, PLAIN 4 4 4 4 BACW10BP42NA- PU 2 surplus washers in the kit WASHER 2 2 2 2 NAS1149C0332R

2. Parts and Materials Supplied by the Operator:
**Notes Name**  **QTY Part Number /**  **Specification** (a) Firewall Sealant, Hydraulic Fluid Resistant 16oz BMS 5-63, Type II (b) BOLT

- BACB30NX6K4 (b) BOLT

- BACB30NX8K4 COLLAR

- BACC30BH6S COLLAR

- BACC30BH8S Filler for Group 1 airplanes Aluminum Stock 2 2024-T3 or 2024- T42, 2.0 x 1.0 x 0.080 Chemical Conversion Coating, SOPM 20-43-03 - Alodine 1200s, Type II, Class A (or equivalent)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 35 of 90 **BOEING SERVICE BULLETIN 737-54-1043 Notes**  **Name QTY**  **Part Number / Specification**  Primer

- BMS 10-11, Type 1 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) These fasteners are not included in the topkit. BACB30NX6K4 may be installedas long as all the hole was not damaged when the existing fasteners was removed. BACB30NX8K4 may be installed as an optional oversize fastener for a BACB30NX6K4() bolt.
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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 36 of 90 **BOEING SERVICE BULLETIN 737-54-1043 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. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 7. 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. 8. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 37 of 90 **BOEING SERVICE BULLETIN 737-54-1043**9. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 10. 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 "as given in" are included in the instruction, the procedure in the Boeing document must be used. 11. Boeing Service Letter 737-SL-51-042, 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. 12. 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. 13. 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. 14. 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. 15. 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. 16. 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. **B. WORK INSTRUCTIONS** 1. PART 1: NUMBER 1 ENGINE a. Remove the aft fairing access panels 434AR and 434BL from the number 1 engine. Refer to 737-600/700/800/900 AMM 54-52-06 as an accepted procedure. b. Remove the aft fairing heat shield and insulation blankets (if installed) from the number 1 engine. Refer to 737-600/700/800/900 AMM 54-52-08 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 38 of 90 **BOEING SERVICE BULLETIN 737-54-1043 NOTE:** Remove heat shield segments as required. Keep any shims that may have been removed. c. Remove the aft strut fairing drain tube and bracket for the number 1 engine as given in FIGURE 1. d.**Group 1:** Make a filler from 0.080 inch thick 2024-T3 or T42 aluminum stock, 2.0 inches long by 1.0 inch wide. Break sharp edges. Apply alodine and let dry. Refer to SOPM 20-43-03 as an accepted procedure. Then apply two coats BMS 10-11 Type I Primer and let dry. Refer to SOPM 20-41-02 as an accepted procedure.

e.**Group 1:** Install the new aft strut fairing drain tube and bracket for the number 1 engine as given in FIGURE 3. **CAUTION:**REMOVE EXCESS SEALANT (SQUEEZE OUT) FROM THE INNER DIAMETER OF THE DRAIN TUBE ASSEMBLY AFTER IT'S INSTALLED ON THE DRAIN SUMP. f.**Group 2:** Install the new aft strut fairing drain tube and bracket for the number 1 engine as given in FIGURE 4. **CAUTION:**REMOVE EXCESS SEALANT (SQUEEZE OUT) FROM THE INNER DIAMETER OF THE DRAIN TUBE ASSEMBLY AFTER IT'S INSTALLED ON THE DRAIN SUMP. g. Install the aft fairing heat shield and any other parts that were removed to gain access, to the number 1 engine. Refer to 737-600/700/800/900 AMM 54-52-08 as an accepted procedure. h. Install the aft fairing access panels 434AR and 434BL to the number 1 engine. Refer to 737-600/700/800/900 AMM 54-52-06 as an accepted procedure. 2. PART 2: NUMBER 2 ENGINE a. Remove the aft fairing access panels 444AL and 444BR from the number 2 engine. Refer to 737-600/700/800/900 AMM 54-52-06 as an accepted procedure. b. Remove the aft fairing heat shield and insulation blankets (if installed) from the number 2 engine. Refer to 737-600/700/800/900 AMM 54-52-08 as an accepted procedure. **NOTE:**Remove heat shield segments as required. Keep any shims that may have been removed. c. Remove the aft strut fairing drain tube and bracket for the number 2 engine as given in FIGURE 2. d.**Group 1:** Make a filler from 0.080 inch thick 2024-T3 or T42 aluminum stock, 2.0 inches long by 1.0 inch wide. Break sharp edges. Apply alodine and let dry. Refer to SOPM 20-43-03 as an accepted procedure. Then apply two coats BMS 10-11 Type I Primer and let dry. Refer to SOPM 20-41-02 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 39 of 90 **BOEING SERVICE BULLETIN 737-54-1043**e.**Group 1:** Install the new aft strut fairing drain tube and bracket for the number 2 engine as given in FIGURE 5. **CAUTION:**REMOVE EXCESS SEALANT (SQUEEZE OUT) FROM THE INNER DIAMETER OF THE DRAIN TUBE ASSEMBLY AFTER IT'S INSTALLED ON THE DRAIN SUMP. f.**Group 2:** Install the new aft strut fairing drain tube and bracket for the number 2 engine as given in FIGURE 6. **CAUTION:**REMOVE EXCESS SEALANT (SQUEEZE OUT) FROM THE INNER DIAMETER OF THE DRAIN TUBE ASSEMBLY AFTER IT'S INSTALLED ON THE DRAIN SUMP. g. Install the aft fairing heat shield and any other parts that were removed to gain access, to the number 2 engine. Refer to 737-600/700/800/900 AMM 54-52-08 as an accepted procedure. h. Install the aft fairing access panels 444AL and 444BR to the number 2 engine. Refer to 737-600/700/800/900 AMM 54-52-06 as an accepted procedure. 3. Do a drainage test to verify that there is nothing blocking the drain tube: a. Place a dry container, no less than a quart in volume, below the aft fairing drain to collect the drain water. b. Using a funnel and rubber tubing, pour 32 fluid ounces of clean water slowly into the drain sump. Do not pour the water so fast that it overwhelms the drain sump or the funnel. c. As the water is being poured, verify that there is no leak from either around the sump fitting or the drain tube. d. Within one minute of having poured all the water, remove the collection container. e. Verify that there is at least 30 fluid ounces of water in the container. If there is at least 30 fluid ounces of water, then the drainage test was passed. f. If there is less than 30 fluid ounces of water in the container, clean the drain tube and repeat the test until you pass the drainage test. Refer to the Aft Fairing Drain Tube and Sump Drain Clean procedure in 737-600/700/800/900 AMM 54-55-02, as an accepted procedure. g. Remove any remaining water from inside the fairing. 4. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2: November 04, 2011 40 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 41 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 42 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 43 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step** 

- 1
- UNION Disconnect 1

- 3
- BOLT Remove / Keep 2

- 3
- WASHER, COUNTER- SUNK Remove / Keep

- 3
- CLAMP Remove / Keep

- 1
- FORWARD DRAIN TUBE ASSY Remove / Keep 3 Do not damage the fastener holes on the support angle orthe airplane structure. 1
- ANGLE Remove / Keep 4

- 2
- BOLT Remove 5

- 2
- WASHER, COUNTER- SUNK Remove

- 2
- WASHER, FLAT Remove

- 2
- NUT, SELF-LOCKING, HEX Remove

- 1
- CLAMP, UPPER BLOCK Remove

- 1
- CLAMP, LOWER BLOCK Remove After removing any sealant present,make sure the fastener holes on the drain sump are not damaged. 4
- BOLT Remove 6

- 4
- WASHER Remove

- 4
- COLLAR Remove

- 1
- AFT DRAIN TUBE AS- SY Remove 7 Used as a fay sealant between the drain sump and the drain tube fitting. - - FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Remove 8

**FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 44 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Do not damage the fastener holes on the bracket or the airplane structure. 1
- BRACKET Remove / Keep 9

Note shim thickness if there is a shim. If the shim is in good condition, you may want to reuse it. - - SHIM Remove 10

**FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 45 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 46 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE**  **(SHEET 2 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 47 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 48 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step** 

- 1
- UNION Disconnect 1

- 3
- BOLT Remove / Keep 2

- 3
- WASHER, COUNTER- SUNK Remove / Keep

- 3
- CLAMP Remove / Keep

- 1
- FORWARD DRAIN TUBE ASSY Remove / Keep 3 Do not damage the fastener holes on the support angle orthe airplane structure. 1
- ANGLE Remove / Keep 4

- 2
- BOLT Remove 5

- 2
- WASHER, COUNTER- SUNK Remove

- 2
- WASHER, FLAT Remove

- 2
- NUT, SELF-LOCKING, HEX Remove

- 1
- CLAMP, UPPER BLOCK Remove

- 1
- CLAMP, LOWER BLOCK Remove After removing any sealant present,make sure the fastener holes on the drain sump are not damaged. 4
- BOLT Remove 6

- 4
- WASHER Remove

- 4
- COLLAR Remove

- 1
- AFT DRAIN TUBE AS- SY Remove 7 Used as a fay sealant between the drain sump and the drain tube fitting. - - FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Remove 8

**FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 49 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Do not damage the fastener holes on the bracket or the airplane structure. 1
- BRACKET Remove / Keep 9

Note shim thickness if there is a shim. If the shim is in good condition, you may want to reuse it. - - SHIM Remove 10

**FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 50 of 90 **BOEING SERVICE BULLETIN 737-54-1043 This Figure applies only to: Group 1.** 

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 1 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 51 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE**  **(SHEET 2 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 52 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE**  **(SHEET 3 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 53 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  **CAUTION:**DO NOT BACKDRILL TO FINAL HOLE SIZE WHEN INSTALLING THE SHIM AND FILLERS. THE HOLE SIZE IN THE WEB AND BRACKET IS CLOSE REAM, WHEREAS THE HOLE IN THE SHIM, FILLER, AND RADIUS FILLER IS CLASS I. IF YOU DRILL ALL THE PARTS TO CLASS I HOLE SIZES, THEN YOU WILL NEED TO INSTALL OVERSIZE FASTENERS, WHICH COULD LEAD TO UNSCHEDULED DOWNTIME.
Install with 0.190- 0.194 inch diameter holes. Make sure the long axis of the filler is centered on the centerline of the two existing fastener holes. Make sure the short axis of the filler is centered half waybetween the two existing fastener holes. Maintain 0.38 inchedge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1
- FILLER Install (New) 1

If a shim was removed when thebracket was disassembled, then reinstall a new laminated shim that has the same thickness asthe original shim. Install with Class I (0.190-0.194 inch diameter) holes. As anoption you may reinstall the original shim if it is still ingood condition. Install with BMS 5-63 Type II fay surface seal. 1 BACS40R007B020F SHIM, LAMINATED Install (New)

1
- BRACKET Install (Kept)

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 4 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 54 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Use existing fastener holes. Install with BMS 5-63 Type II fay surface seal. Install with 0.190- 0.194 inch diameter holes. Make sure theshort axis of the radius filler is centered on the center of the bracket and that the radius of the radius filler rests against the inner radius of the bracket. 0.38 inch edge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1 313A2503-20 RADIUS FILLER Install (New)

Locate the drain tube assembly in place. Temporarily install drain tube to bracket fasteners.Use the sump fastener holes as a guideto mark the hole locations in the drain tube assembly. 1 313A2501-24 DRAIN TUBE ASSY Align 2

- 1 313A2501-24 DRAIN TUBE ASSY Remove

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 5 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 55 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Drill holes up to 1/32 inches under final size. Do not ream the holes to final size at this time. See fastener code table below for final hole sizes.(a) 1 313A2501-24 DRAIN TUBE ASSY Drill 3

Fit the drain tube assembly to the sump and hold firmly using assembly pins or temporary fasteners. 1 313A2501-24 DRAIN TUBE ASSY Align

Ream the holes to the final hole size. Make sure each hole is perpendicular to the surface of the drain tube fitting within 2 degrees. See fastener code table below for final hole sizes.(a) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Ream

- 1 313A2501-24 DRAIN TUBE ASSY Remove

- 1 313A2501-24 DRAIN TUBE ASSY Deburr

- 1
- DRAIN SUMP Deburr To the mating surface of the drain fitting and the drain sump. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 4

Assemble drain tube assembly to drain sump. See fastener code table below.(b) (c) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Install (New)

Assemble drain tube assembly to bracket. See fastener code table below. 1 313A2501-24 DRAIN TUBE ASSY Install (New) 5

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 6 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 56 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** See fastener code table below. 1
- ANGLE Install (Kept) 6

- 1
- FORWARD DRAIN TUBE ASSY Install (Kept) 7 Tighten loosely initially until all clamps are in position, then tighten fully. 1
- UNION Connect

See fastener code table below. 3
- CLAMP Install (Kept) 8
Fillet seal the drain fitting. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 9

(a) The drain tube fitting and the drain sump are made of nickel alloy 625. Nickel alloy 625 is very tough to drill, care should be taken to make sure no cracks are introduced during drilling. (b) Up to 0.060 sealant thickness allowed to achieve desired drain tube position. Nominal gap for concentric tube engagement is 0.086, minimum gap between the tubes is 0.030 inch. (c) Clean any excess sealant from drain tube after installation. Refer to 737-600/700/800/900 AMM 54-55- 02 as an accepted procedure.

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 7 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 57 of 90 **BOEING SERVICE BULLETIN 737-54-1043**The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 65-88700 are used to determine the part numbers used as substitutes.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.2026-0.2036 4 BACB30NX6K4X BOLT, PROTRUDING HD A (a)

- 4 BACW10BP31NAPU WASHER, PLAIN (a)

- 4 BACC30BH6S COLLAR

- - - OR (a) 0.2182-0.2192 4 BACB30NX6K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP32NAPU WASHER, PLAIN (a)

- 4 BACC30AC6S COLLAR, PRELOAD

- - - - OR (a) 0.2651-0.2661 4 BACB30NX8K4X BOLT, PROTRUDING HD (a)

- 4 BACW10BP41NAPU WASHER, PLAIN (a)

- 4 BACC30BH8S COLLAR

- - - OR (a) 0.2807-0.2817 4 BACB30NX8K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP42NAPU WASHER, PLAIN (a)

- 4 BACC30AC8S COLLAR, PRELOAD

- 2 BACB30LM3U6 BOLT B Install under the bolt head.

- 2 BACW10BP3ACU WASHER Install one washer under the nut. (c) - 2 NAS1149C0332R WASHER

- - 2 BACN11Z3C NUT

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 8 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 58 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (b)

- 2 BACB30NY6K4 BOLT C

- - 2 BACC30BH6 COLLAR

- - - OR (b) (d)

- 2 BACB30NY6K4X BOLT

- 2 BACC30BH6 COLLAR

- - - OR (b)

- 2 BACB30NY6K4Y BOLT, 100 DEG HEX DR

- 2 BACC30AC6 COLLAR Install all bolts loose initially to enable proper alignment of the drain tube. Tighten bolts fully after drain tube is properly aligned. - 3 (KEPT) BOLT, HEX HEAD, LONG THREAD D

- - 3 (KEPT) WASHER, COUNTER- SUNK (e)

- 2 BACB30YM6K10 HI-LOK E

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10X BOLT, HEX DRIVE

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10Y BOLT, HEX DRIVE

- 2 BACC30CP6CY COLLAR, PRELOAD (a) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. For proper fit, if the gap between the parts is large, but less than 0.060, the drain fitting can be installed using a two step seal procedure: use temporary fasteners to attach the drain fitting to the sump with BMS 5-63, Type II sealant between faying surfaces making sure there is proper squeeze out to ensure complete sealant coverage. After the sealant cures, install the permanent fasteners in accordance with the fastener table. Washer collapse acceptable on fastener installation. Refer to SOPM 20-50-19 as an accepted procedure. (b) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. (c) NOTE: Two additional washers provided in kit are surplus. (d) Oversize fastener, if necessary. May be obtained from operator supplied parts or topkit.

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 9 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 59 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (e) Install wet with BMS 5-63 Type II sealant. Install fastener with head on bottom side.

**FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 10 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 60 of 90 **BOEING SERVICE BULLETIN 737-54-1043 This Figure applies only to: Group 2.** 

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 1 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 61 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE**  **(SHEET 2 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 62 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE**  **(SHEET 3 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 63 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  **CAUTION:**DO NOT BACKDRILL TO FINAL HOLE SIZE WHEN INSTALLING THE SHIM AND FILLERS. THE HOLE SIZE IN THE WEB AND BRACKET IS CLOSE REAM, WHEREAS THE HOLE IN THE SHIM AND RADIUS FILLER IS CLASS I. IF YOU DRILL ALL THE PARTS TO CLASS I HOLE SIZES, THEN YOU WILL NEED TO INSTALL OVERSIZE FASTENERS, WHICH COULD LEAD TO UNSCHEDULED DOWNTIME.
If a shim was removed when thebracket was disassembled, then reinstall a new laminated shim that has the same thickness asthe original shim. Install with Class I (0.190-0.194 inch diameter) holes. As anoption you may reinstall the original shim if it is still ingood condition. Install with BMS 5-63 Type II fay surface seal. 1 BACS40R007B020F SHIM, LAMINATED Install (New) 1

Use existing fastener holes. Install with BMS 5-63 Type II fay surface seal. 1
- BRACKET Install (Kept)

Install with 0.190- 0.194 inch diameter holes. Make sure theshort axis of the radius filler is centered on the center of the bracket and that the radius of the radius filler rests against the inner radius of the bracket. 0.38 inch edge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1 313A2503-20 RADIUS FILLER Install (New)

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 4 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 64 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Locate the drain tube assembly in place. Temporarily install drain tube to bracket fasteners.Use the sump fastener holes as a guideto mark the hole locations in the drain tube assembly. 1 313A2501-24 DRAIN TUBE ASSY Align 2

- 1 313A2501-24 DRAIN TUBE ASSY Remove Drill holes up to 1/32 inches under final size. Do not ream the holes to final size at this time. See fastener code table below for final hole sizes. (a) 1 313A2501-24 DRAIN TUBE ASSY Drill 3

Fit the drain tube assembly to the sump and hold firmly using assembly pins or temporary fasteners. 1 313A2501-24 DRAIN TUBE ASSY Align

Ream the holes to the final hole size. Make sure each hole is perpendicular to the surface of the drain tube fitting within 2 degrees. See fastener code table below for final hole sizes. (a) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Ream

- 1 313A2501-24 DRAIN TUBE ASSY Remove

- 1 313A2501-24 DRAIN TUBE ASSY Deburr

- 1
- DRAIN SUMP Deburr

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 5 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 65 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** To the mating surface of the drain fitting and the drain sump. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 4

Assemble drain tube assembly to drain sump. See fastener code table below. (b)(c) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Install (New)

Assemble drain tube assembly to bracket. See fastener code table below. 1 313A2501-24 DRAIN TUBE ASSY Install (New) 5

See fastener code table below. 1
- ANGLE Install (Kept) 6

- 1
- FORWARD DRAIN TUBE ASSY Install (Kept) 7 Tighten loosely initially until all clamps are in position, then tighten fully. 1
- UNION Connect

See fastener code table below. 3
- CLAMP Install (Kept) 8
Fillet seal the drain fitting. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 9

(a) The drain tube fitting and the drain sump are made of nickel alloy 625. Nickel alloy 625 is very tough to drill, care should be taken to make sure no cracks are introduced during drilling. (b) Up to 0.060 sealant thickness allowed to achieve desired drain tube position. Nominal gap for concentric tube engagement is 0.086, minimum gap between the tubes is 0.030 inch. (c) Clean any excess sealant from drain tube after installation. Refer to 737-600/700/800/900 AMM 54-55- 02 as an accepted procedure.

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 6 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 66 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE**  **(SHEET 7 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 67 of 90 **BOEING SERVICE BULLETIN 737-54-1043**The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 65-88700 are used to determine the part numbers used as substitutes.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.2026-0.2036 4 BACB30NX6K4X BOLT, PROTRUDING HD A (a)

- 4 BACW10BP31NAPU WASHER, PLAIN (a)

- 4 BACC30BH6S COLLAR

- - - OR (a) 0.2182-0.2192 4 BACB30NX6K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP32NAPU WASHER, PLAIN (a)

- 4 BACC30AC6S COLLAR, PRELOAD

- - - - OR (a) 0.2651-0.2661 4 BACB30NX8K4X BOLT, PROTRUDING HD (a)

- 4 BACW10BP41NAPU WASHER, PLAIN (a)

- 4 BACC30BH8S COLLAR

- - - OR (a) 0.2807-0.2817 4 BACB30NX8K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP42NAPU WASHER, PLAIN (a)

- 4 BACC30AC8S COLLAR, PRELOAD

- 2 BACB30LM3U6 BOLT B Install under the bolt head.

- 2 BACW10BP3ACU WASHER Install one washer under the nut.(c) - 2 NAS1149C0332R WASHER

- - 2 BACN11Z3C NUT

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 8 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 68 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (b)

- 2 BACB30NY6K4 BOLT C

- - 2 BACC30BH6 COLLAR

- - - OR (b) (d)

- 2 BACB30NY6K4X BOLT

- 2 BACC30BH6 COLLAR

- - - OR (b)

- 2 BACB30NY6K4Y BOLT, 100 DEG HEX DR

- 2 BACC30AC6 COLLAR Install all bolts loose initially to enable proper alignment of the drain tube. Tighten bolts fully after drain tube is properly aligned. - 3 (KEPT) BOLT, HEX HEAD, LONG THREAD D

- - 3 (KEPT) WASHER, COUNTER- SUNK (e)

- 2 BACB30YM6K10 HI-LOK E

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10X BOLT, HEX DRIVE

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10Y BOLT, HEX DRIVE

- 2 BACC30CP6CY COLLAR, PRELOAD (a) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. For proper fit, if the gap between the parts is large, but less than 0.060, the drain fitting can be installed using a two step seal procedure: use temporary fasteners to attach the drain fitting to the sump with BMS 5-63, Type II sealant between faying surfaces making sure there is proper squeeze out to ensure complete sealant coverage. After the sealant cures, install the permanent fasteners in accordance with the fastener table. Washer collapse acceptable on fastener installation. Refer to SOPM 20-50-19 as an accepted procedure. (b) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. (c) NOTE: Two additional washers provided in kit are surplus. (d) Oversize fastener, if necessary. May be obtained from operator supplied parts or topkit.

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 9 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 69 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (e) Install wet with BMS 5-63 Type II sealant. Install fastener with head on bottom side.

**FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE (SHEET 10 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 70 of 90 **BOEING SERVICE BULLETIN 737-54-1043 This Figure applies only to: Group 1.** 

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 1 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 71 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE**  **(SHEET 2 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 72 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE**  **(SHEET 3 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 73 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  **CAUTION:**DO NOT BACKDRILL TO FINAL HOLE SIZE WHEN INSTALLING THE SHIM AND FILLERS. THE HOLE SIZE IN THE WEB AND BRACKET IS CLOSE REAM, WHEREAS THE HOLE IN THE SHIM AND FILLER AND RADIUS FILLER IS CLASS I. IF YOU DRILL ALL THE PARTS TO CLASS I HOLE SIZES, THEN YOU WILL NEED TO INSTALL OVERSIZE FASTENERS, WHICH COULD LEAD TO UNSCHEDULED DOWNTIME.
Install with 0.190- 0.194 inch diameter holes. Make sure the long axis of the filler is centered on the centerline of the two existing fastener holes. Make sure the short axis of the filler is centered half waybetween the two existing fastener holes. Maintain 0.38 inchedge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1
- FILLER Install (New) 1

If a shim was removed when thebracket was disassembled, then reinstall a new laminated shim that has the same thickness asthe original shim. Install with Class I (0.190-0.194 inch diameter) holes. As anoption you may reinstall the original shim if it is still ingood condition. Install with BMS 5-63 Type II fay surface seal. 1 BACS40R007B020F SHIM, LAMINATED Install (New)

1
- BRACKET Install (Kept)

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 4 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 74 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Use existing fastener holes. Install with BMS 5-63 Type II fay surface seal. Install with 0.190- 0.194 inch diameter holes. Make sure theshort axis of the radius filler is centered on the center of the bracket and that the radius of the radius filler rests against the inner radius of the bracket. 0.38 inch edge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1 313A2503-20 RADIUS FILLER Install (New)

Locate the drain tube assembly in place. Temporarily install drain tube to bracket fasteners.Use the sump fastener holes as a guideto mark the hole locations in the drain tube assembly. 1 313A2501-24 DRAIN TUBE ASSY Align 2

- 1 313A2501-24 DRAIN TUBE ASSY Remove

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 5 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 75 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Drill holes up to 1/32 inches under final size. Do not ream the holes to final size at this time. See fastener code table below for final hole sizes. (a) 1 313A2501-24 DRAIN TUBE ASSY Drill 3

Fit the drain tube assembly to the sump and hold firmly using assembly pins or temporary fasteners. 1 313A2501-24 DRAIN TUBE ASSY Align

Ream the holes to the final hole size. Make sure each hole is perpendicular to the surface of the drain tube fitting within 2 degrees. See fastener code table below for final hole sizes. (a) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Ream

- 1 313A2501-24 DRAIN TUBE ASSY Remove

- 1 313A2501-24 DRAIN TUBE ASSY Deburr

- 1
- DRAIN SUMP Deburr To the mating surface of the drain fitting and the drain sump. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 4

Assemble drain tube assembly to drain sump. See fastenercode table below.(b)(c) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Install (New)

Assemble drain tube assembly to bracket. See fastener code table below. 1 313A2501-24 DRAIN TUBE ASSY Install (New) 5

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 6 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 76 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** See fastener code table below. 1
- ANGLE Install (Kept) 6

- 1
- FORWARD DRAIN TUBE ASSY Install (Kept) 7 Tighten loosely initially until all clamps are in position, then tighten fully. 1
- UNION Connect

See fastener code table below. 3
- CLAMP Install (Kept) 8
Fillet seal the drain fitting. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 9

(a) The drain tube fitting and the drain sump are made of nickel alloy 625. Nickel alloy 625 is very tough to drill, care should be taken to make sure no cracks are introduced during drilling. (b) Up to 0.060 sealant thickness allowed to achieve desired drain tube position. Nominal gap for concentric tube engagement is 0.086, minimum gap between the tubes is 0.030 inch. (c) Clean any excess sealant from drain tube after installation. Refer to 737-600/700/800/900 AMM 54-55- 02 as an accepted procedure.

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 7 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 77 of 90 **BOEING SERVICE BULLETIN 737-54-1043**The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 65-88700 are used to determine the part numbers used as substitutes.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.2026-0.2036 4 BACB30NX6K4X BOLT, PROTRUDING HD A (a)

- 4 BACW10BP31NAPU WASHER, PLAIN (a)

- 4 BACC30BH6S COLLAR

- - - OR (a) 0.2182-0.2192 4 BACB30NX6K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP32NAPU WASHER, PLAIN (a)

- 4 BACC30AC6S COLLAR, PRELOAD

- - - - OR (a) 0.2651-0.2661 4 BACB30NX8K4X BOLT, PROTRUDING HD (a)

- 4 BACW10BP41NAPU WASHER, PLAIN (a)

- 4 BACC30BH8S COLLAR

- - - OR (a) 0.2807-0.2817 4 BACB30NX8K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP42NAPU WASHER, PLAIN (a)

- 4 BACC30AC8S COLLAR, PRELOAD

- 2 BACB30LM3U6 BOLT B Install under the bolt head.

- 2 BACW10BP3ACU WASHER Install one washer under the nut.(c) - 2 NAS1149C0332R WASHER

- - 2 BACN11Z3C NUT

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 8 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 78 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (b)

- 2 BACB30NY6K4 BOLT C

- - 2 BACC30BH6 COLLAR

- - - OR (b) (d)

- 2 BACB30NY6K4X BOLT

- 2 BACC30BH6 COLLAR

- - - OR (b)

- 2 BACB30NY6K4Y BOLT, 100 DEG HEX DR

- 2 BACC30AC6 COLLAR Install all bolts loose initially to enable proper alignment of the drain tube. Tighten bolts fully after drain tube is properly aligned. - 3 (KEPT) BOLT, HEX HEAD, LONG THREAD D

- - 3 (KEPT) WASHER, COUNTER- SUNK (e)

- 2 BACB30YM6K10 HI-LOK E

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10X BOLT, HEX DRIVE

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10Y BOLT, HEX DRIVE

- 2 BACC30CP6CY COLLAR, PRELOAD (a) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. For proper fit, if the gap between the parts is large, but less than 0.060, the drain fitting can be installed using a two step seal procedure: use temporary fasteners to attach the drain fitting to the sump with BMS 5-63, Type II sealant between faying surfaces making sure there is proper squeeze out to ensure complete sealant coverage. After the sealant cures, install the permanent fasteners in accordance with the fastener table. Washer collapse acceptable on fastener installation. Refer to SOPM 20-50-19 as an accepted procedure. (b) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. (c) NOTE: Two additional washers provided in kit are surplus. (d) Oversize fastener, if necessary. May be obtained from operator supplied parts or topkit.

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 9 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 79 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (e) Install wet with BMS 5-63 Type II sealant. Install fastener with head on bottom side.

**FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 10 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 80 of 90 **BOEING SERVICE BULLETIN 737-54-1043 This Figure applies only to: Group 2.** 

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 1 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 81 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE**  **(SHEET 2 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 82 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE**  **(SHEET 3 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 83 of 90 **BOEING SERVICE BULLETIN 737-54-1043**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 one engine strut.
**More Data Qty**  **Identification Name**  **Task Step**  **CAUTION:**DO NOT BACKDRILL TO FINAL HOLE SIZE WHEN INSTALLING THE SHIM AND FILLERS. THE HOLE SIZE IN THE WEB AND BRACKET IS CLOSE REAM, WHEREAS THE HOLE IN THE SHIM AND RADIUS FILLER IS CLASS I. IF YOU DRILL ALL THE PARTS TO CLASS I HOLE SIZES, THEN YOU WILL NEED TO INSTALL OVERSIZE FASTENERS, WHICH COULD LEAD TO UNSCHEDULED DOWNTIME.
If a shim was removed when thebracket was disassembled, then reinstall a new laminated shim that has the same thickness asthe original shim. Install with Class I (0.190-0.194 inch diameter) holes. As anoption you may reinstall the original shim if it is still ingood condition. Install with BMS 5-63 Type II fay surface seal. 1 BACS40R007B020F SHIM, LAMINATED Install (New) 1

Use existing fastener holes. Install with BMS 5-63 Type II fay surface seal. 1
- BRACKET Install (Kept)

Install with 0.190- 0.194 inch diameter holes. Make sure theshort axis of the radius filler is centered on the center of the bracket and that the radius of the radius filler rests against the inner radius of the bracket. 0.38 inch edge margin minimum. Install with BMS 5-63 Type II fay surface seal. 1 313A2503-20 RADIUS FILLER Install (New)

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 4 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 84 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** Locate the drain tube assembly in place. Temporarily install drain tube to bracket fasteners.Use the sump fastener holes as a guideto mark the hole locations in the drain tube assembly. 1 313A2501-24 DRAIN TUBE ASSY Align 2

- 1 313A2501-24 DRAIN TUBE ASSY Remove Drill holes up to 1/32 inches under final size. Do not ream the holes to final size at this time. See fastener code table below for final hole sizes.(a) 1 313A2501-24 DRAIN TUBE ASSY Drill 3

Fit the drain tube assembly to the sump and hold firmly using assembly pins or temporary fasteners. 1 313A2501-24 DRAIN TUBE ASSY Align

Ream the holes to the final hole size. Make sure each hole is perpendicular to the surface of the drain tube fitting within 2 degrees. See fastener code table below for final hole sizes.(a) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Ream

- 1 313A2501-24 DRAIN TUBE ASSY Remove

- 1 313A2501-24 DRAIN TUBE ASSY Deburr

- 1
- DRAIN SUMP Deburr

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 5 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 85 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Qty Identification**  **Name Task**  **Step** To the mating surface of the drain fitting and the drain sump. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 4

Assemble drain tube assembly to drain sump. See fastenercode table below.(b)(c) 1
- DRAIN TUBE AS- SY/DRAIN SUMP Install (New)

Assemble drain tube assembly to bracket. See fastener code table below. 1 313A2501-24 DRAIN TUBE ASSY Install (New) 5

See fastener code table below. 1
- ANGLE Install (Kept) 6

- 1
- FORWARD DRAIN TUBE ASSY Install (Kept) 7 Tighten loosely initially until all clamps are in position, then tighten fully. 1
- UNION Connect

See fastener code table below. 3
- CLAMP Install (Kept) 8
Fillet seal the drain fitting. Refer to SOPM 20-50-19 asan accepted procedure. - BMS 5-63, TYPE II FIREWALL SEALANT, HYDRAULIC FLUID RESISTANT Apply 9

(a) The drain tube fitting and the drain sump are made of nickel alloy 625. Nickel alloy 625 is very tough to drill, care should be taken to make sure no cracks are introduced during drilling. (b) Up to 0.060 sealant thickness allowed to achieve desired drain tube position. Nominal gap for concentric tube engagement is 0.086, minimum gap between the tubes is 0.030 inch. (c) Clean any excess sealant from drain tube after installation. Refer to 737-600/700/800/900 AMM 54-55- 02 as an accepted procedure.

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 6 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 86 of 90 **BOEING SERVICE BULLETIN 737-54-1043 FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE**  **(SHEET 7 OF 10)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 87 of 90 **BOEING SERVICE BULLETIN 737-54-1043**The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 65-88700 are used to determine the part numbers used as substitutes.
**More Data Hole Dia**  **Qty Identification**  **Name Code**  (a) 0.2026-0.2036 4 BACB30NX6K4X BOLT, PROTRUDING HD A (a)

- 4 BACW10BP31NAPU WASHER, PLAIN (a)

- 4 BACC30BH6S COLLAR

- - - OR (a) 0.2182-0.2192 4 BACB30NX6K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP32NAPU WASHER, PLAIN (a)

- 4 BACC30AC6S COLLAR, PRELOAD

- - - - OR (a) 0.2651-0.2661 4 BACB30NX8K4X BOLT, PROTRUDING HD (a)

- 4 BACW10BP41NAPU WASHER, PLAIN (a)

- 4 BACC30BH8S COLLAR

- - - OR (a) 0.2807-0.2817 4 BACB30NX8K4Y BOLT, PROTRUDING HD (a)

- 4 BACW10BP42NAPU WASHER, PLAIN (a)

- 4 BACC30AC8S COLLAR, PRELOAD

- 2 BACB30LM3U6 BOLT B Install under the bolt head.

- 2 BACW10BP3ACU WASHER Install one washer under the nut. (c) - 2 NAS1149C0332R WASHER

- - 2 BACN11Z3C NUT

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 8 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 88 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (b)

- 2 BACB30NY6K4 BOLT C

- - 2 BACC30BH6 COLLAR

- - - OR (b) (d)

- 2 BACB30NY6K4X BOLT

- 2 BACC30BH6 COLLAR

- - - OR (b)

- 2 BACB30NY6K4Y BOLT, 100 DEG HEX DR

- 2 BACC30AC6 COLLAR Install all bolts loose initially to enable proper alignment of the drain tube. Tighten bolts fully after drain tube is properly aligned. - 3 (KEPT) BOLT, HEX HEAD, LONG THREAD D

- - 3 (KEPT) WASHER, COUNTER- SUNK (e)

- 2 BACB30YM6K10 HI-LOK E

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10X BOLT, HEX DRIVE

- 2 BACC30CP6C COLLAR, PRELOAD

- - - OR (e)

- 2 BACB30YM6K10Y BOLT, HEX DRIVE

- 2 BACC30CP6CY COLLAR, PRELOAD (a) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. For proper fit, if the gap between the parts is large, but less than 0.060, the drain fitting can be installed using a two step seal procedure: use temporary fasteners to attach the drain fitting to the sump with BMS 5-63, Type II sealant between faying surfaces making sure there is proper squeeze out to ensure complete sealant coverage. After the sealant cures, install the permanent fasteners in accordance with the fastener table. Washer collapse acceptable on fastener installation. Refer to SOPM 20-50-19 as an accepted procedure. (b) Install the washer under the collar. Washer collapse acceptable on fastener installation. Install fasteners wet with BMS 5-63, Type II. Refer to SOPM 20-50-19 as an accepted procedure. (c) NOTE: Two additional washers provided in kit are surplus. (d) Oversize fastener, if necessary. May be obtained from operator supplied parts or topkit.

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 9 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 89 of 90 **BOEING SERVICE BULLETIN 737-54-1043 More Data**  **Hole Dia Qty**  **Identification Name**  **Code** (e) Install wet with BMS 5-63 Type II sealant. Install fastener with head on bottoms side.

**FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE (SHEET 10 OF 10)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: May 02, 2007 737-54-1043 Revision 2 November 04, 2011 90 of 90 **BOEING SERVICE BULLETIN 737-54-1043**