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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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.

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5.0
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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

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BOEING SERVICE BULLETIN 737-54-1043
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BOEING SERVICE BULLETIN 737-54-1043

BLANK PAGE
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.

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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.

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

Original Issue: May 02, 2007

Revision 1: October 19, 2009

Revision 2: November 04, 2011

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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.

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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

Airplanes Total Task Hours Elapsed Hours

737-600/-700/-700C/-800/- 13.50 10.00

900/-900ER

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 737-54-1043

BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

YA001 - YA073 1

YA074 - YA099 2

YA101 - YA199 2

YA201 - YA207 1

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Variable Number Group

YA208 - YA211 2

YA221 2

YA231 - YA242 1

YA251 - YA254 1

YA255 - YA256 2

YA271 - YA272 1

YA291 1

YA301 - YA302 1

YA311 - YA314 1

YA321 - YA322 1

YA323 2

YA336 - YA345 2

YA351 2

YA356 - YA357 2

YA366 - YA367 2

YA371 - YA377 2

YA501 - YA536 1

YA541 - YA548 1

YA549 - YA552 2

YA571 - YA578 1

YA601 - YA612 1

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 2

YA701 - YA704 1

YA705 - YA710 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

YA721 - YA722 1

YA731 - YA733 1

YA734 2

YA751 - YA756 1

YA801 - YA803 2

YA809 2

YA811 - YA814 1

YA831 - YA834 1

YA835 2

YA841 - YA850 1

YA851 - YA862 2

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA966 1

YA967 - YA978 2

YB001 - YB006 1

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

YC001 - YC019 1

YC020 - YC030 2

YC051 - YC064 1

YC065 - YC070 2

YC071 - YC080 1

YC081 - YC084 2

YC091 - YC095 2

YC101 - YC103 1

YC104 2

YC111 - YC112 1

YC113 2

YC121 1

YC126 - YC127 1

YC136 - YC139 1

YC140 - YC141 2

YC146 - YC147 2

YC151 - YC156 2

YC166 - YC171 2

YC176 - YC179 2

YC186 - YC190 2

YC201 - YC203 2

YC206 - YC207 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

YC301 - YC303 1

YC304 - YC305 2

YC321 - YC367 1

YC368 - YC380 2

YC381 - YC382 1

YC383 - YC387 2

YC391 1

YC392 - YC394 2

YC396 1

YC401 - YC410 1

YC411 - YC417 2

YC421 - YC422 2

YC426 - YC428 2

YC436 - YC439 2

YC441 - YC445 1

YC446 - YC448 2

YC451 - YC455 1

YC459 2

YC461 - YC466 1

YC467 2

YC471 - YC480 1

YC481 - YC499 2

YC501 - YC522 1

YC523 - YC526 2

YC571 - YC580 1

YC581 - YC583 2

YC587 - YC589 2

YC591 - YC593 1

YC601 - YC624 1

YC625 - YC655 2

YC681 1

YC682 - YC696 2

YC701 - YC709 1

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

YC710 - YC715 2

YC720 - YC725 2

YC727 - YC730 2

YC731 - YC736 1

YC737 - YC750 2

YC751 - YC752 1

YC761 - YC770 1

YC781 - YC787 1

YC788 - YC793 2

YC801 - YC839 1

YC840 - YC892 2

YC901 - YC903 1

YC904 - YC905 2

YC906 1

YC907 2

YC921 - YC922 2

YC931 - YC932 1

YC941 - YC947 1

YC948 - YC951 2

YC971 - YC972 1

YC973 - YC978 2

YC981 - YC983 1

YD001 - YD005 1

YD006 - YD007 2

YD021 - YD023 1

YD024 - YD025 2

YD041 - YD045 1

YD046 - YD057 2

YD081 - YD084 2

YD101 1

YD102 - YD117 2

YD121 - YD126 2

YD151 - YD159 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

YD501 1

YD502 - YD512 2

YD531 - YD535 2

YD541 - YD547 2

YD561 - YD564 2

YD571 - YD572 2

YD591 - YD595 2

YD601 - YD612 2

YD651 - YD655 2

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE156 1

YE157 2

YE171 - YE172 1

YE201 - YE206 2

YE301 - YE305 2

YE321 - YE326 2

YE371 - YE383 2

YF001 - YF011 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

YG001 - YG037 1

YG038 - YG044 2

YG061 - YG064 1

YG066 - YG072 1

YG073 - YG089 2

YG091 - YG099 2

YG101 - YG104 2

YG111 - YG114 2

YG116 - YG129 2

YG201 - YG205 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

YG211 - YG214 2

YG221 - YG224 2

YG251 - YG252 2

YG501 - YG502 1

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 - YM103 2

YM201 - YM244 2

YM251 - YM299 2

YM301 - YM399 2

YM401 - YM405 2

YM471 2

YM481 - YM484 2

YM501 - YM515 2

YM521 - YM522 2

YM541 2

YM551 - YM553 2

YM571 - YM572 2

YM581 - YM582 2

YM591 - YM599 2

YM631 - YM634 2

YM641 - YM652 2

YM671 - YM674 2

YM691 - YM699 2

YM701 - YM710 2

YM761 - YM765 2

YM771 - YM774 2

YN001 - YN016 2

YN021 - YN024 2

YN061 2

YN071 - YN082 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

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 2

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BOEING SERVICE BULLETIN 737-54-1043
Variable Number Group

YR301 - YR305 2

YR401 - YR403 2

YR421 2

YR451 2

YR501 - YR503 2

YR511 2

YR601 - YR602 2

YR701 - YR703 2

YR801 - YR802 2

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.

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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.

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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

Model Zone

737-600, 737-700, 737-700C, 434, 444

737-800, 737-900

Group 2:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 434, 444

737-800, 737-900, 737-900ER

E. Compliance

Federal Aviation Administration Airworthiness Directive FAA AD 2008-08-24 is related to this service

bulletin.

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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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 3.50 1.75

Figure 1 1 1.50 1.50

Figure 2 1 1.50 1.50

Figure 3 1 2.00 2.00

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BOEING SERVICE BULLETIN 737-54-1043
Group 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Figure 5 1 2.00 2.00

Close Access 2 3.50 1.75

TOTAL FOR EACH AIRPLANE(a) 14.00 10.50

(a) Estimate does not include time to make parts. More time will be required

to make parts.

Group 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 2 3.50 1.75

Figure 1 1 1.50 1.50

Figure 2 1 1.50 1.50

Figure 4 1 2.00 2.00

Figure 6 1 2.00 2.00

Close Access 2 3.50 1.75

TOTAL FOR EACH AIRPLANE(a) 14.00 10.50

(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

737-600/-700/-700C/-800/- + 0.81 + 518

900/-900ER

Group 2:

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

737-600/-700/-700C/-800/- + 0.78 +499

900/-900ER up to and including

Line Number 2091

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BOEING SERVICE BULLETIN 737-54-1043
Group 2:

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

737-600/-700/-700C/-800/- +0.28 +179

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:

Drawing Number Title

313A2500 Drain Installation, Aft Fairing CFM56-7

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:

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BOEING SERVICE BULLETIN 737-54-1043
Publication Chapter-Section

737 Illustrated Parts Catalog 54-55

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.

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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 RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE

INFORMATION

Unit Price thru

August 31, 2012

Kit Number Name Date QTY

002A0001-108 (a) Top Kit 10/31/2011 60 $12,326.00

11/14/2011 60

11/30/2011 60

12/14/2011 60

01/06/2012 60

01/20/2012 60

02/03/2012 60

02/17/2012 60

03/02/2012 20

(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.

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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

Top Kit 3 4 5 6

002A0001-108 1 1 1 1

ALL

KIT 002A0001-108

NOTES

Existing Part

Name Number

Figure

New Part Number

3 4 5 6

QTY

DRAIN TUBE ASSY313A2501-24 1 1 1 1

313A2503-20 1 1 1 1 RADIUS FILLER

BACB30LM3U6 2 2 2 2 BOLT

BOLT, PROTRUDING HDBACB30NX6K4X 4 4 4 4

BOLT, PROTRUDING HDBACB30NX6K4Y 4 4 4 4

BOLT, PROTRUDING HDBACB30NX8K4X 4 4 4 4

BOLT, PROTRUDING HDBACB30NX8K4Y 4 4 4 4

BOLT, 100 DEG

HEX DR

BACB30NY6K4Y 2 2 2 2

BACB30YM6K10 2 2 2 2 HI-LOK

BACB30YM6K10X 2 2 2 2 BOLT, HEX DRIVE

BACB30YM6K10Y 2 2 2 2 BOLT, HEX DRIVE

BACC30AC6 2 2 2 2 COLLAR

COLLAR,

PRELOAD

BACC30AC6S 4 4 4 4

COLLAR,

PRELOAD

BACC30AC8S 4 4 4 4

BACC30BH6S 4 4 4 4 COLLAR

BACC30BH8S 4 4 4 4 COLLAR

COLLAR,

PRELOAD

BACC30CP6C 4 4 4 4

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BOEING SERVICE BULLETIN 737-54-1043
ALL

KIT 002A0001-108

NOTES

Existing Part

Name Number

Figure

New Part Number

3 4 5 6

QTY

COLLAR,

PRELOAD

BACC30CP6CY 2 2 2 2

BACN11Z3C 2 2 2 2 NUT

SHIM, LAMINATEDBACS40R007B020F 1 1 1 1

BACW10BP31NA- 4 4 4 4 WASHER, PLAIN

PU

BACW10BP32NA- 4 4 4 4 WASHER, PLAIN

PU

BACW10BP3ACU 2 2 2 2 WASHER

BACW10BP41NA- 4 4 4 4 WASHER, PLAIN

PU

BACW10BP42NA- 4 4 4 4 WASHER, PLAIN

PU

2 surplus

washers

in the kit

NAS1149C0332R 2 2 2 2 WASHER

2. Parts and Materials Supplied by the Operator:

Part Number / QTY Name Notes

Specification

Firewall Sealant, Hydraulic Fluid (a)

Resistant

BMS 5-63, Type II 16oz

BACB30NX6K4 - BOLT (b)

BACB30NX8K4 - BOLT (b)

BACC30BH6S - COLLAR

BACC30BH8S - COLLAR

Filler for Group

1 airplanes

2024-T3 or 2024- 2 Aluminum Stock

T42, 2.0 x 1.0 x

0.080

Chemical Conversion Coating,

SOPM 20-43-03

Alodine 1200s, -

Type II, Class A (or

equivalent)

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BOEING SERVICE BULLETIN 737-54-1043
Part Number / QTY Name Notes

Specification

BMS 10-11, Type - Primer

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 installed

as 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.

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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.

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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.

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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.

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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.

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE

(SHEET 3 OF 5)

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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.

Step Task Name Identification Qty More Data

1 Disconnect UNION - 1 -

2 Remove / Keep BOLT - 3 -

WASHER, COUNTER- - 3 -

SUNK

Remove / Keep

Remove / Keep CLAMP - 3 -

FORWARD DRAIN - 1 -

TUBE ASSY

3 Remove / Keep

Do not damage the

fastener holes on

the support angle or

the airplane structure.

4 Remove / Keep ANGLE - 1

5 Remove BOLT - 2 -

WASHER, COUNTER- - 2 -

SUNK

Remove

Remove WASHER, FLAT - 2 -

NUT, SELF-LOCKING, - 2 -

HEX

Remove

CLAMP, UPPER - 1 -

BLOCK

Remove

CLAMP, LOWER - 1 -

BLOCK

Remove

After removing any

sealant present,

make sure the fastener holes on the

drain sump are not

damaged.

6 Remove BOLT - 4

Remove WASHER - 4 -

Remove COLLAR - 4 -

AFT DRAIN TUBE AS- - 1 -

SY

7 Remove

Used as a fay

sealant between the

drain sump and the

drain tube fitting.

FIREWALL SEALANT, - -

HYDRAULIC FLUID

RESISTANT

8 Remove

FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

Do not damage the

fastener holes on

the bracket or the

airplane structure.

9 Remove / Keep BRACKET - 1

Note shim thickness

if there is a shim. If

the shim is in good

condition, you may

want to reuse it.

10 Remove SHIM - -

FIGURE 1: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 1 ENGINE

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE

(SHEET 3 OF 5)

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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.

Step Task Name Identification Qty More Data

1 Disconnect UNION - 1 -

2 Remove / Keep BOLT - 3 -

WASHER, COUNTER- - 3 -

SUNK

Remove / Keep

Remove / Keep CLAMP - 3 -

FORWARD DRAIN - 1 -

TUBE ASSY

3 Remove / Keep

Do not damage the

fastener holes on

the support angle or

the airplane structure.

4 Remove / Keep ANGLE - 1

5 Remove BOLT - 2 -

WASHER, COUNTER- - 2 -

SUNK

Remove

Remove WASHER, FLAT - 2 -

NUT, SELF-LOCKING, - 2 -

HEX

Remove

CLAMP, UPPER - 1 -

BLOCK

Remove

CLAMP, LOWER - 1 -

BLOCK

Remove

After removing any

sealant present,

make sure the fastener holes on the

drain sump are not

damaged.

6 Remove BOLT - 4

Remove WASHER - 4 -

Remove COLLAR - 4 -

AFT DRAIN TUBE AS- - 1 -

SY

7 Remove

Used as a fay

sealant between the

drain sump and the

drain tube fitting.

FIREWALL SEALANT, - -

HYDRAULIC FLUID

RESISTANT

8 Remove

FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

Do not damage the

fastener holes on

the bracket or the

airplane structure.

9 Remove / Keep BRACKET - 1

Note shim thickness

if there is a shim. If

the shim is in good

condition, you may

want to reuse it.

10 Remove SHIM - -

FIGURE 2: AFT STRUT FAIRING DRAIN TUBE REMOVAL, NUMBER 2 ENGINE

(SHEET 5 OF 5)

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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)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 2 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 3 OF 10)

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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.

Step Task Name Identification Qty More Data

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 way

between the two existing fastener holes.

Maintain 0.38 inch

edge margin minimum. Install with

BMS 5-63 Type II

fay surface seal.

1 Install (New) FILLER - 1

If a shim was removed when the

bracket was disassembled, then reinstall a new laminated shim that has the

same thickness as

the original shim. Install with Class I (

0.190-0.194 inch diameter) holes. As an

option you may reinstall the original

shim if it is still in

good condition. Install with BMS 5-63

Type II fay surface

seal.

Install (New) SHIM, LAMINATED BACS40R007B020F 1

Install (Kept) BRACKET - 1

FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 4 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

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 the

short 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.

Install (New) RADIUS FILLER 313A2503-20 1

Locate the drain

tube assembly in

place. Temporarily

install drain tube to

bracket fasteners.

Use the sump fastener holes as a guide

to mark the hole locations in the drain

tube assembly.

2 Align DRAIN TUBE ASSY 313A2501-24 1

Remove DRAIN TUBE ASSY 313A2501-24 1 -

FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 5 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

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)

3 Drill DRAIN TUBE ASSY 313A2501-24 1

Fit the drain tube assembly to the sump

and hold firmly using

assembly pins or

temporary fasteners.

Align DRAIN TUBE ASSY 313A2501-24 1

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)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Ream

Remove DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN SUMP - 1 -

To the mating surface of the drain fitting and the drain

sump. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

4 Apply

Assemble drain tube

assembly to drain

sump. See fastener

code table below.(b)

(c)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Install (New)

Assemble drain tube

assembly to bracket.

See fastener code

table below.

5 Install (New) DRAIN TUBE ASSY 313A2501-24 1

FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 6 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

See fastener code

table below.

6 Install (Kept) ANGLE - 1

FORWARD DRAIN - 1 -

TUBE ASSY

7 Install (Kept)

Tighten loosely initially until all clamps are

in position, then

tighten fully.

Connect UNION - 1

See fastener code

table below.

8 Install (Kept) CLAMP - 3

Fillet seal the drain

fitting. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

9 Apply

(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)

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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.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K4X 4 0.2026-0.2036 (a)

HD

A

WASHER, PLAIN BACW10BP31NAPU 4 - (a)

COLLAR BACC30BH6S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX6K4Y 4 0.2182-0.2192 (a)

HD

WASHER, PLAIN BACW10BP32NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC6S 4 - (a)

OR - - - -

BOLT, PROTRUDING BACB30NX8K4X 4 0.2651-0.2661 (a)

HD

WASHER, PLAIN BACW10BP41NAPU 4 - (a)

COLLAR BACC30BH8S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX8K4Y 4 0.2807-0.2817 (a)

HD

WASHER, PLAIN BACW10BP42NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC8S 4 - (a)

B BOLT BACB30LM3U6 2 -

WASHER BACW10BP3ACU 2 - Install under the bolt head.

Install one washer under

the nut. (c)

WASHER NAS1149C0332R 2 -

NUT BACN11Z3C 2 - -

FIGURE 3: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 8 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

C BOLT BACB30NY6K4 2 - (b)

COLLAR BACC30BH6 2 - -

OR - - -

BOLT BACB30NY6K4X 2 - (b) (d)

COLLAR BACC30BH6 2 -

OR - - -

BOLT, 100 DEG HEX BACB30NY6K4Y 2 - (b)

DR

COLLAR BACC30AC6 2 -

Install all bolts loose initially to enable proper alignment of the drain tube.

Tighten bolts fully after

drain tube is properly

aligned.

BOLT, HEX HEAD, (KEPT) 3 -

LONG THREAD

D

WASHER, COUNTER- (KEPT) 3 - -

SUNK

E HI-LOK BACB30YM6K10 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10X 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10Y 2 - (e)

COLLAR, PRELOAD BACC30CP6CY 2 -

(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)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

(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)

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This Figure applies only to: Group 2.

FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 1 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 2 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 3 OF 10)

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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.

Step Task Name Identification Qty More Data

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 the

bracket was disassembled, then reinstall a new laminated shim that has the

same thickness as

the original shim. Install with Class I (

0.190-0.194 inch diameter) holes. As an

option you may reinstall the original

shim if it is still in

good condition. Install with BMS 5-63

Type II fay surface

seal.

1 Install (New) SHIM, LAMINATED BACS40R007B020F 1

Use existing fastener holes. Install with

BMS 5-63 Type II

fay surface seal.

Install (Kept) BRACKET - 1

Install with 0.190-

0.194 inch diameter

holes. Make sure the

short 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.

Install (New) RADIUS FILLER 313A2503-20 1

FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 4 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

Locate the drain

tube assembly in

place. Temporarily

install drain tube to

bracket fasteners.

Use the sump fastener holes as a guide

to mark the hole locations in the drain

tube assembly.

2 Align DRAIN TUBE ASSY 313A2501-24 1

Remove DRAIN TUBE ASSY 313A2501-24 1 -

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)

3 Drill DRAIN TUBE ASSY 313A2501-24 1

Fit the drain tube assembly to the sump

and hold firmly using

assembly pins or

temporary fasteners.

Align DRAIN TUBE ASSY 313A2501-24 1

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)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Ream

Remove DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN SUMP - 1 -

FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 5 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

To the mating surface of the drain fitting and the drain

sump. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

4 Apply

Assemble drain tube

assembly to drain

sump. See fastener

code table below.

(b)(c)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Install (New)

Assemble drain tube

assembly to bracket.

See fastener code

table below.

5 Install (New) DRAIN TUBE ASSY 313A2501-24 1

See fastener code

table below.

6 Install (Kept) ANGLE - 1

FORWARD DRAIN - 1 -

TUBE ASSY

7 Install (Kept)

Tighten loosely initially until all clamps are

in position, then

tighten fully.

Connect UNION - 1

See fastener code

table below.

8 Install (Kept) CLAMP - 3

Fillet seal the drain

fitting. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

9 Apply

(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)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 7 OF 10)

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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.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K4X 4 0.2026-0.2036 (a)

HD

A

WASHER, PLAIN BACW10BP31NAPU 4 - (a)

COLLAR BACC30BH6S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX6K4Y 4 0.2182-0.2192 (a)

HD

WASHER, PLAIN BACW10BP32NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC6S 4 - (a)

OR - - - -

BOLT, PROTRUDING BACB30NX8K4X 4 0.2651-0.2661 (a)

HD

WASHER, PLAIN BACW10BP41NAPU 4 - (a)

COLLAR BACC30BH8S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX8K4Y 4 0.2807-0.2817 (a)

HD

WASHER, PLAIN BACW10BP42NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC8S 4 - (a)

B BOLT BACB30LM3U6 2 -

WASHER BACW10BP3ACU 2 - Install under the bolt head.

Install one washer under

the nut.(c)

WASHER NAS1149C0332R 2 -

NUT BACN11Z3C 2 - -

FIGURE 4: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 1 ENGINE

(SHEET 8 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

C BOLT BACB30NY6K4 2 - (b)

COLLAR BACC30BH6 2 - -

OR - - -

BOLT BACB30NY6K4X 2 - (b) (d)

COLLAR BACC30BH6 2 -

OR - - -

BOLT, 100 DEG HEX BACB30NY6K4Y 2 - (b)

DR

COLLAR BACC30AC6 2 -

Install all bolts loose initially to enable proper alignment of the drain tube.

Tighten bolts fully after

drain tube is properly

aligned.

BOLT, HEX HEAD, (KEPT) 3 -

LONG THREAD

D

WASHER, COUNTER- (KEPT) 3 - -

SUNK

E HI-LOK BACB30YM6K10 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10X 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10Y 2 - (e)

COLLAR, PRELOAD BACC30CP6CY 2 -

(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)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

(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)

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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)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 2 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 3 OF 10)

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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.

Step Task Name Identification Qty More Data

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 way

between the two existing fastener holes.

Maintain 0.38 inch

edge margin minimum. Install with

BMS 5-63 Type II

fay surface seal.

1 Install (New) FILLER - 1

If a shim was removed when the

bracket was disassembled, then reinstall a new laminated shim that has the

same thickness as

the original shim. Install with Class I (

0.190-0.194 inch diameter) holes. As an

option you may reinstall the original

shim if it is still in

good condition. Install with BMS 5-63

Type II fay surface

seal.

Install (New) SHIM, LAMINATED BACS40R007B020F 1

Install (Kept) BRACKET - 1

FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 4 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

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 the

short 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.

Install (New) RADIUS FILLER 313A2503-20 1

Locate the drain

tube assembly in

place. Temporarily

install drain tube to

bracket fasteners.

Use the sump fastener holes as a guide

to mark the hole locations in the drain

tube assembly.

2 Align DRAIN TUBE ASSY 313A2501-24 1

Remove DRAIN TUBE ASSY 313A2501-24 1 -

FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 5 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

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)

3 Drill DRAIN TUBE ASSY 313A2501-24 1

Fit the drain tube assembly to the sump

and hold firmly using

assembly pins or

temporary fasteners.

Align DRAIN TUBE ASSY 313A2501-24 1

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)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Ream

Remove DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN SUMP - 1 -

To the mating surface of the drain fitting and the drain

sump. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

4 Apply

Assemble drain tube

assembly to drain

sump. See fastener

code table below.(b)(c)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Install (New)

Assemble drain tube

assembly to bracket.

See fastener code

table below.

5 Install (New) DRAIN TUBE ASSY 313A2501-24 1

FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 6 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Step Task Name Identification Qty More Data

See fastener code

table below.

6 Install (Kept) ANGLE - 1

FORWARD DRAIN - 1 -

TUBE ASSY

7 Install (Kept)

Tighten loosely initially until all clamps are

in position, then

tighten fully.

Connect UNION - 1

See fastener code

table below.

8 Install (Kept) CLAMP - 3

Fillet seal the drain

fitting. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

9 Apply

(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)

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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.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K4X 4 0.2026-0.2036 (a)

HD

A

WASHER, PLAIN BACW10BP31NAPU 4 - (a)

COLLAR BACC30BH6S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX6K4Y 4 0.2182-0.2192 (a)

HD

WASHER, PLAIN BACW10BP32NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC6S 4 - (a)

OR - - - -

BOLT, PROTRUDING BACB30NX8K4X 4 0.2651-0.2661 (a)

HD

WASHER, PLAIN BACW10BP41NAPU 4 - (a)

COLLAR BACC30BH8S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX8K4Y 4 0.2807-0.2817 (a)

HD

WASHER, PLAIN BACW10BP42NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC8S 4 - (a)

B BOLT BACB30LM3U6 2 -

WASHER BACW10BP3ACU 2 - Install under the bolt head.

Install one washer under

the nut.(c)

WASHER NAS1149C0332R 2 -

NUT BACN11Z3C 2 - -

FIGURE 5: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 8 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

C BOLT BACB30NY6K4 2 - (b)

COLLAR BACC30BH6 2 - -

OR - - -

BOLT BACB30NY6K4X 2 - (b) (d)

COLLAR BACC30BH6 2 -

OR - - -

BOLT, 100 DEG HEX BACB30NY6K4Y 2 - (b)

DR

COLLAR BACC30AC6 2 -

Install all bolts loose initially to enable proper alignment of the drain tube.

Tighten bolts fully after

drain tube is properly

aligned.

BOLT, HEX HEAD, (KEPT) 3 -

LONG THREAD

D

WASHER, COUNTER- (KEPT) 3 - -

SUNK

E HI-LOK BACB30YM6K10 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10X 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10Y 2 - (e)

COLLAR, PRELOAD BACC30CP6CY 2 -

(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)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

(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)

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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)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 2 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 3 OF 10)

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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.

Step Task Name Identification Qty More Data

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 the

bracket was disassembled, then reinstall a new laminated shim that has the

same thickness as

the original shim. Install with Class I (

0.190-0.194 inch diameter) holes. As an

option you may reinstall the original

shim if it is still in

good condition. Install with BMS 5-63

Type II fay surface

seal.

1 Install (New) SHIM, LAMINATED BACS40R007B020F 1

Use existing fastener holes. Install with

BMS 5-63 Type II

fay surface seal.

Install (Kept) BRACKET - 1

Install with 0.190-

0.194 inch diameter

holes. Make sure the

short 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.

Install (New) RADIUS FILLER 313A2503-20 1

FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 4 OF 10)

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Step Task Name Identification Qty More Data

Locate the drain

tube assembly in

place. Temporarily

install drain tube to

bracket fasteners.

Use the sump fastener holes as a guide

to mark the hole locations in the drain

tube assembly.

2 Align DRAIN TUBE ASSY 313A2501-24 1

Remove DRAIN TUBE ASSY 313A2501-24 1 -

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)

3 Drill DRAIN TUBE ASSY 313A2501-24 1

Fit the drain tube assembly to the sump

and hold firmly using

assembly pins or

temporary fasteners.

Align DRAIN TUBE ASSY 313A2501-24 1

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)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Ream

Remove DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN TUBE ASSY 313A2501-24 1 -

Deburr DRAIN SUMP - 1 -

FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 5 OF 10)

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Step Task Name Identification Qty More Data

To the mating surface of the drain fitting and the drain

sump. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

4 Apply

Assemble drain tube

assembly to drain

sump. See fastener

code table below.(b)(c)

DRAIN TUBE AS- - 1

SY/DRAIN SUMP

Install (New)

Assemble drain tube

assembly to bracket.

See fastener code

table below.

5 Install (New) DRAIN TUBE ASSY 313A2501-24 1

See fastener code

table below.

6 Install (Kept) ANGLE - 1

FORWARD DRAIN - 1 -

TUBE ASSY

7 Install (Kept)

Tighten loosely initially until all clamps are

in position, then

tighten fully.

Connect UNION - 1

See fastener code

table below.

8 Install (Kept) CLAMP - 3

Fillet seal the drain

fitting. Refer to

SOPM 20-50-19 as

an accepted procedure.

FIREWALL SEALANT, BMS 5-63, TYPE II -

HYDRAULIC FLUID

RESISTANT

9 Apply

(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)

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BOEING SERVICE BULLETIN 737-54-1043
FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 7 OF 10)

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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.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K4X 4 0.2026-0.2036 (a)

HD

A

WASHER, PLAIN BACW10BP31NAPU 4 - (a)

COLLAR BACC30BH6S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX6K4Y 4 0.2182-0.2192 (a)

HD

WASHER, PLAIN BACW10BP32NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC6S 4 - (a)

OR - - - -

BOLT, PROTRUDING BACB30NX8K4X 4 0.2651-0.2661 (a)

HD

WASHER, PLAIN BACW10BP41NAPU 4 - (a)

COLLAR BACC30BH8S 4 - (a)

OR - - -

BOLT, PROTRUDING BACB30NX8K4Y 4 0.2807-0.2817 (a)

HD

WASHER, PLAIN BACW10BP42NAPU 4 - (a)

COLLAR, PRELOAD BACC30AC8S 4 - (a)

B BOLT BACB30LM3U6 2 -

WASHER BACW10BP3ACU 2 - Install under the bolt head.

Install one washer under

the nut. (c)

WASHER NAS1149C0332R 2 -

NUT BACN11Z3C 2 - -

FIGURE 6: AFT STRUT FAIRING DRAIN TUBE INSTALLATION, NUMBER 2 ENGINE

(SHEET 8 OF 10)

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BOEING SERVICE BULLETIN 737-54-1043
Code Name Identification Qty Hole Dia More Data

C BOLT BACB30NY6K4 2 - (b)

COLLAR BACC30BH6 2 - -

OR - - -

BOLT BACB30NY6K4X 2 - (b) (d)

COLLAR BACC30BH6 2 -

OR - - -

BOLT, 100 DEG HEX BACB30NY6K4Y 2 - (b)

DR

COLLAR BACC30AC6 2 -

Install all bolts loose initially to enable proper alignment of the drain tube.

Tighten bolts fully after

drain tube is properly

aligned.

BOLT, HEX HEAD, (KEPT) 3 -

LONG THREAD

D

WASHER, COUNTER- (KEPT) 3 - -

SUNK

E HI-LOK BACB30YM6K10 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10X 2 - (e)

COLLAR, PRELOAD BACC30CP6C 2 -

OR - - -

BOLT, HEX DRIVE BACB30YM6K10Y 2 - (e)

COLLAR, PRELOAD BACC30CP6CY 2 -

(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)

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Code Name Identification Qty Hole Dia More Data

(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)

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BOEING SERVICE BULLETIN 737-54-1043