Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Number: 747-57-2332

Original Issue: November 09, 2010

ATA System: 5740

SUBJECT: WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage

Path Change

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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Copyright © 2010 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

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6.0
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BOEING SERVICE BULLETIN 747-57-2332

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 7

A. Effectivity ................................................ 7

1. Airplanes ............................................. 7

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 37

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 38

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION . . . . . . . . . 42

FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION . . . . . . . . 45

FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE . . . . . . . . . . . . . . . . 48

FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE . . . . . . . . . . . . . . . 50

FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE . . . . . . . . . . . . . . . . . . . . . . . 58

FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION . . . 60

FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION . . . 64

FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION [Group 1-6] . . . . 68

FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION [Group 1-6] . . . 71

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BOEING SERVICE BULLETIN 747-57-2332
APPENDIX A: MASTER FASTENER CODE TABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

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BOEING SERVICE BULLETIN 747-57-2332
Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Summary Number: 747-57-2332

Original Issue: November 09, 2010

ATA System: 5740

SUBJECT: WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage

Path Change

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area, forward of

the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating in the wing leading

edge may drain inboard and onto the engine exhaust nozzle, which could result in a fire.

Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the number

5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection with a fuel quantity

of over 2500 lbs. Subsequent investigation found that the leak occurred in an area of the front spar that does

not have a proper drain path. This led to the fuel draining onto the engine exhaust nozzle. The leak appears to

have been caused by a loose retaining nut of the slat track down stop and is the subject of Boeing Service Letter

737-SL-57-084.

Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid leakages

from the wing leading edge away from the engine exhaust area.

Boeing Service Related Problem (SRP) 747-SRP-57-0214 is related to this service bulletin.

ACTION (PRR 85901-96RS)

Get access to the leading edge of the wing by extending the variable camber flaps. Install the applicable fuel

dam assemblies, seal assemblies and drain assemblies. Repair the leading edge lower skin panel. Close access.

EFFECTIVITY

747-100, -100B, -100B SUD, -200B, -200F, -200C, -300, -400, -400D, -400F, 747SR and 747SP Airplanes.

Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

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COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Boeing recommends that the change given in this service bulletin be done within 60 months after the original

issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of November 15, 2007. Please refer to

Paragraph 2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

GROUP 1-6 94.50 55.00

GROUP 7-10 90.00 50.50

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 747-57-2332
Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Number: 747-57-2332

Original Issue: November 09, 2010

ATA System: 5740

SUBJECT: WINGS - Leading Edge And Leading Edge Devices - Leading Edge Fluid Drainage

Path Change

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

GROUP CONFIGURATION DESCRIPTION

1 - 747-100 Airplanes with line numbers 1-248.

747-100 Airplanes with line numbers 252-281 and 747SP Airplanes

with JT9D-7 Engines.

2 -

3 - 747SR Airplanes with line numbers 221-249.

4 - 747SR Airplane with line number 254.

747SR Airplanes with line numbers 346-572 and 747-100B Airplanes

with JT9D-7 Engines and 747-100B SUD Airplanes.

5 -

747-200B, 747-200C, 747-200F and 747-300 Airplanes with either

JT9D-7 or CF6-50 engines.

6 -

7 - 747-400, 747-400D and 747-400F Airplanes.

8 - 747SP Airplanes with RB211 series Engines.

9 - 747-100B Airplanes with RB211 series Engines.

747-200B, 747-200F and 747-300 Airplanes with either JT9D-70,

CF6-80 or RB211 series Engines.

10 -

Airplane Models:

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747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,

747-400D, 747-400F, 747SP, 747SR

Variable Number Group

RA001 - RA034 1

RA101 - RA115 1

RA161 - RA164 1

RA201 - RA203 1

RA216 - RA217 6

RA245 - RA246 6

RA251 - RA264 1

RA265 - RA266 2

RA301 - RA317 1

RA318 2

RA351 - RA360 1

RA369 - RA373 6

RA401 - RA418 1

RA501 - RA502 1

RA521 - RA527 1

RA528 2

RA532 - RA548 6

RA551 - RA552 1

RA559 - RA561 6

RA581 - RA582 1

RA585 6

RA601 - RA602 1

RA631 - RA635 1

RA651 - RA652 6

RA671 - RA677 6

RA701 - RA702 6

RA721 - RA731 6

RA741 - RA745 1

RA749 - RA750 6

RA761 - RA762 1

RA781 - RA784 6

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RA901 - RA916 1

RB001 - RB016 6

RB041 - RB044 1

RB071 - RB075 6

RB101 - RB102 1

RB411 - RB413 10

RB421 6

RB601 - RB606 3

RB607 4

RB681 - RB697 5

RB711 5

RB721 - RB723 5

RB741 - RB747 9

RD001 - RD004 6

RD021 - RD022 6

RD041 - RD059 6

RD071 - RD072 6

RD081 - RD083 6

RD091 - RD092 6

RD101 - RD104 6

RD121 - RD127 6

RD131 - RD144 10

RD166 - RD167 10

RD171 - RD172 6

RD181 - RD183 6

RD201 - RD204 6

RD221 - RD227 6

RD231 - RD235 6

RD241 - RD243 6

RD251 - RD262 6

RD271 - RD272 6

RD291 - RD292 6

RD301 - RD302 6

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RD311 10

RD351 - RD358 10

RD361 - RD366 6

RD381 - RD383 6

RD411 - RD414 6

RD421 - RD426 6

RD431 - RD435 6

RD441 - RD442 6

RD451 - RD456 6

RD461 6

RD471 - RD475 10

RD513 - RD516 6

RD517 - RD519 10

RD531 6

RD532 - RD533 10

RD551 6

RD561 10

RD571 6

RD581 - RD583 6

RD591 - RD592 10

RD593 6

RD601 - RD607 6

RD621 - RD623 6

RD641 - RD649 6

RD651 - RD659 6

RD661 6

RD671 6

RD681 - RD682 6

RD691 - RD692 6

RD701 - RD702 6

RD721 - RD722 6

RD741 - RD742 6

RD751 - RD755 6

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RD761 6

RD771 - RD775 6

RD781 - RD783 6

RD791 - RD792 6

RE001 6

RF001 - RF006 7

RG001 - RG009 2

RG091 2

RG095 2

RG101 - RG104 2

RG121 - RG126 2

RG141 - RG142 2

RG161 - RG164 2

RG171 - RG174 2

RG191 - RG193 2

RG211 - RG213 2

RG221 - RG222 2

RH101 - RH102 8

RH111 - RH112 8

RH121 - RH122 8

RJ131 - RJ133 6

RJ151 - RJ152 6

RJ301 - RJ303 6

RJ321 - RJ322 6

RJ331 - RJ333 6

RL401 - RL403 7

RL411 - RL436 7

RL451 - RL456 7

RL461 - RL462 7

RL471 - RL481 7

RL491 - RL492 7

RL501 - RL502 7

RL511 - RL516 7

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RL521 - RL522 7

RL531 - RL534 7

RL551 7

RL561 - RL568 7

RL571 - RL572 7

RL576 - RL577 7

RL579 7

RL581 - RL586 7

RL651 - RL655 7

RL671 - RL675 7

RL681 - RL684 7

RL751 - RL752 7

RM001 - RM007 7

RM010 - RM013 7

RM021 - RM024 7

RM026 - RM030 7

RM036 - RM045 7

RM051 - RM053 7

RM071 7

RM081 - RM084 7

RM091 7

RM096 - RM097 7

RM116 - RM117 7

RM126 - RM132 7

RM136 - RM147 7

RM156 - RM158 7

RM166 - RM177 7

RM191 - RM192 7

RM231 - RM233 7

RM241 - RM246 7

RM261 - RM264 7

RM316 - RM318 7

RM331 - RM333 7

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RM341 7

RM351 - RM355 7

RM366 - RM367 7

RM401 - RM403 7

RM426 7

RM431 7

RM441 - RM443 7

RM445 7

RM801 - RM803 7

RM811 - RM813 7

RM851 - RM859 7

RM861 - RM863 7

RM871 - RM899 7

RM901 - RM906 7

RM911 7

RR001 - RR005 6

RR021 - RR025 6

RR031 6

RR201 - RR206 6

RR221 - RR224 10

RR225 - RR226 6

RR261 - RR267 6

RR301 - RR310 6

RR331 - RR332 6

RR336 6

RR341 - RR345 6

RR361 - RR362 6

RR421 10

RR422 6

RR431 - RR432 6

RR441 - RR442 10

RR451 6

RR501 - RR504 6

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RR521 - RR522 6

RR526 10

RR531 10

RR551 - RR556 6

RR561 6

RR566 6

RR701 7

RR721 - RR724 7

RR746 - RR748 7

RR851 - RR856 7

RR861 - RR862 7

RR951 - RR952 7

RS001 - RS002 5

RS201 6

RS211 - RS212 6

RS221 - RS222 6

RS231 - RS241 6

RS251 - RS259 6

RS263 6

RS265 - RS268 6

RS271 - RS276 10

RS291 - RS292 6

RS301 - RS306 10

RS311 - RS320 10

RS331 - RS333 10

RS341 - RS342 10

RS699 6

RS701 - RS703 6

RS711 - RS713 6

RS721 - RS722 6

RS731 - RS732 6

RS741 - RS743 6

RS751 - RS752 6

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RS761 - RS762 6

RS771 6

RS781 - RS782 10

RS786 6

RT001 - RT014 7

RT021 - RT022 7

RT031 - RT035 7

RT041 - RT047 7

RT061 7

RT071 - RT075 7

RT101 - RT103 7

RT121 7

RT131 - RT137 7

RT151 - RT152 7

RT161 - RT168 7

RT401 - RT412 7

RT431 - RT447 7

RT451 - RT469 7

RT471 - RT499 7

RT501 - RT535 7

RT551 - RT568 7

RT571 - RT591 7

RT601 - RT657 7

RT671 - RT673 7

RT681 - RT682 7

RT691 - RT699 7

RT701 - RT704 7

RT711 - RT717 7

RT741 - RT757 7

RT776 - RT777 7

RT781 - RT784 7

RT801 - RT803 7

RT811 - RT814 7

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BOEING SERVICE BULLETIN 747-57-2332
Variable Number Group

RT831 - RT837 7

RT861 - RT864 7

RT876 - RT880 7

RT931 - RT932 7

RT945 - RT949 7

RT951 - RT955 7

RT966 - RT967 7

RU001 - RU006 7

RU016 - RU017 7

RU031 - RU032 7

RU051 - RU052 7

RU059 - RU062 7

RU081 - RU083 7

RU101 - RU102 7

RU121 - RU132 7

RU801 - RU809 7

RU831 - RU841 7

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to modify the fluid drain path in the wing leading edge area,

forward of the wing front spar. If this service bulletin is not incorporated, flammable fluids accumulating

in the wing leading edge may drain inboard and onto the engine exhaust nozzle, which could result in

a fire.

Boeing has received a report of leaking fuel from the wing leading edge area at the inboard end of the

number 5 leading edge slat of a 737 airplane. The leak was discovered during a post flight inspection

with a fuel quantity of over 2500 lbs. Subsequent investigation found that the leak occurred in an area

of the front spar that does not have a proper drain path. This led to the fuel draining onto the engine

exhaust nozzle. The leak appears to have been caused by a loose retaining nut of the slat track down

stop and is the subject of Boeing Service Letter 737-SL-57-084.

Accomplishment of this service bulletin will make sure that there is a drain path to safely direct all fluid

leakages from the wing leading edge away from the engine exhaust area.

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BOEING SERVICE BULLETIN 747-57-2332
Boeing Service Related Problem (SRP) 747-SRP-57-0214 is related to this service bulletin.

D. Description

Get access to the leading edge of the wing by extending the variable camber flaps. Install the applicable

fuel dam assemblies, seal assemblies and drain assemblies. Repair the leading edge lower skin panel.

Close access.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1:

Affected Maintenance Zones

Model Zone

747-100 521, 531, 621, 631

Group 2:

Affected Maintenance Zones

Model Zone

747-100, 747SP 521, 531, 621, 631

Group 3-4:

Affected Maintenance Zones

Model Zone

747SR 521, 531, 621, 631

Group 5:

Affected Maintenance Zones

Model Zone

747-100B, 747-100B SUD, 521, 531, 621, 631

747SR

Group 6:

Affected Maintenance Zones

Model Zone

747-200B, 747-200C, 747-200F, 521, 531, 621, 631

747-300

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BOEING SERVICE BULLETIN 747-57-2332
Group 7:

Affected Maintenance Zones

Model Zone

747-400, 747-400D, 747-400F 521, 531, 621, 631

Group 8:

Affected Maintenance Zones

Model Zone

747SP 521, 531, 621, 631

Group 9:

Affected Maintenance Zones

Model Zone

747-100B 521, 531, 621, 631

Group 10:

Affected Maintenance Zones

Model Zone

747-200B, 747-200F, 747-300 521, 531, 621, 631

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done within 60 months after the

original issue date of this service bulletin.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

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BOEING SERVICE BULLETIN 747-57-2332
G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1-6:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 2.25 2.25

Part 1: FIGURE 2 1 2.25 2.25

Part 2: FIGURE 3 1 1.00 1.00

Part 2: FIGURE 4 1 1.00 1.00

Part 3: FIGURE 5 2 5.50 2.75

Part 3: FIGURE 6 2 5.50 2.75

Part 3: FIGURE 7 1 1.75 1.75

Part 3: FIGURE 8 1 1.75 1.75

Part 3: FIGURE 9 2 34.00 17.00

Part 3: FIGURE 10 2 34.00 17.00

Part 4: FIGURE 11 1 2.25 2.25

Part 4: FIGURE 12 1 2.25 2.25

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 94.50 55.00

Group 7-10:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 2.25 2.25

Part 1: FIGURE 2 1 2.25 2.25

Part 2: FIGURE 3 1 1.00 1.00

Part 2: FIGURE 4 1 1.00 1.00

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BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

Task Number of Persons Task Hours Elapsed Hours

Part 3: FIGURE 5 2 5.50 2.75

Part 3: FIGURE 6 2 5.50 2.75

Part 3: FIGURE 7 1 1.75 1.75

Part 3: FIGURE 8 1 1.75 1.75

Part 3: FIGURE 9 2 34.00 17.00

Part 3: FIGURE 10 2 34.00 17.00

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 90.00 50.50

H. Weight and Balance Changes

Group 1-6:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All Airplanes + 11.8 + 18290.0

Group 7-10:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All Airplanes + 11.0 + 17292.0

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR 85901-96RS

b. Boeing Service Related Problem (SRP) 747-SRP-57-0214

c. Standard Overhaul Practices Manual (SOPM) 20-10-06, 20-30-03, 20-50-00, 20-50-10,

20-50-18, 20-50-19

d. 747-100/200/300 Aircraft Maintenance Manual (AMM) 27-81-00, 78-31-00

e. 747-100/200/300 Structural Repair Manual (SRM) 51-40-12, 51-40-14

f. 747-400 Aircraft Maintenance Manual (AMM) 27-81-00, 78-31-00

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BOEING SERVICE BULLETIN 747-57-2332
g. 747-400 Structural Repair Manual (SRM) 51-70-07, 51-70-17

h. 747-400F Structural Repair Manual (SRM) 51-70-07, 51-70-17

i. 747-400LCF Structural Repair Manual (SRM) 51-70-07, 51-70-17

j. 747-400SF Structural Repair Manual (SRM) 51-70-07, 51-70-17

k. 747-SP Structural Repair Manual (SRM) 51-40-14

2. Data supplied with this Service Bulletin

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

LEADING EDGE FLUID DAM ASSEMBLY 1 - -

- LOWER LEADING EDGE PANEL ASSEMBLY

624U0071

2 - -

3. Installation Drawings Used in the Preparation of this Service Bulletin

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Maintenance Manual 51-31

747 Illustrated Parts Catalog 57-31

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 747-57-2332
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BOEING SERVICE BULLETIN 747-57-2332

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown

below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.

More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the

date Boeing gets the purchase order.

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Original Issue: November 09, 2010

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BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

Unit Price thru

November 30,

2010

ROLT

(Calendar

Days)

Kit Number Name Date QTY

May 24, 25 420 $33,609.00

2010

TOP KIT - WING LEADING EDGE DRAINAGE015U1870-1

June 22, 25

2010

July 21, 13

2010

October 12

11, 2010

November 25

8, 2010

December 25

8, 2010

January 25

14, 2011

February 25

11, 2011

March 11, 25

2011

April 8, 25

2011

May 6, 25

2011

June 6, 25

2011

July 5, 15

2011

Group 7-10:

Unit Price thru

November 30,

2010

ROLT

(Calendar

Days)

Kit Number Name Date QTY

May 24, 10 420 $29,304.00

2010

TOP KIT - WING LEADING EDGE DRAINAGE015U1870-2

June 1, 4

2010

June 22, 10

2010

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Original Issue: November 09, 2010

747-57-2332

24 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

Unit Price thru

November 30,

2010

ROLT

(Calendar

Days)

Kit Number Name Date QTY

July 21,

2010

10

August 18, 10

2010

September 10

16, 2010

October 10

14, 2010

November 10

11, 2010

December 1

13, 2010

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.

Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are available for 747 airplanes in warranty as of November 15, 2007. For

task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be

supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service

bulletin number and reference the airplane variable numbers in your purchase order.

C. Parts Necessary For Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

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Original Issue: November 09, 2010

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BOEING SERVICE BULLETIN 747-57-2332
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 1 2 3 4 7 8

015U1870-1 1 1 1 1 1 1

015U1870-2 1 1 1 1 1 1

Figure Kit

Top Kit 9 10 11 12

015U1870-1 1 1 1 1

015U1870-2 1 1 - -

Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

KIT DETAIL -

SEAL

114U9202-10 1

KIT DETAIL -

DRAIN TUBE

114U9202-12

KIT - DRAIN FITTING ASSY114U9202-15 1

KIT - DRAIN FITTING ASSY114U9202-16 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-19

KIT DETAIL -

WEB, FLUID DAM

114U9202-20

KIT DETAIL -

DRAIN TUBE RETAINER

114U9202-24

KIT DETAIL -

BRACKET

114U9202-3 1 1

KIT DETAIL -

BRACKET

114U9202-4 1 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-5 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

26 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

KIT DETAIL -

WEB, FLUID DAM

114U9202-6 1

KIT DETAIL -

SEAL

114U9202-9 1

BACB30LH3-5 10 10 BOLT

BOLT-100 DEG

HEAD

BACB30NN3K3

BOLT, RADIUS

LEAD-IN

BACB30WQ5K13LY

BOLT, RADIUS

LEAD-IN

BACB30WQ5K14LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K12LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K14LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K15LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LY

BACB30WQ6K9LX BOLT, HEX DRIVE

BACB30WQ6K9LY BOLT

BOLT, RADIUS

LEAD-IN

BACB30WQ7K14L

BOLT, RADIUS

LEAD-IN

BACB30WQ7K15L

BACB30YN12K15X BOLT, HEX DRIVE

BACB30YN12K16X BOLT, HEX DRIVE

BACB30YN14K15 BOLT, HEX DRIVE

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

27 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

BACB30YN14K16 BOLT

BOLT, 100 DEG

HEX DR

BACB30YP6K4 2 2

BACC30BS6 2 2 COLLAR

BACN10HY5ACX NUT

SELF-LOCKING

NUT

BACN10HY6AC

BACN10HY6ACX NUT

SELF-LOCKING

NUT

BACN10HY7AC

SELF-LOCKING

NUT

BACN10YR6CD

BACN10YR7CD NUT

BACR15BA7AD10C RIVET, 100 DEG

BACR15BA7AD11C 3 3 RIVET, 100 DEG

BACR15BA7AD12C RIVET, 100 DEG

BACR15BA7AD13C RIVET, 100 DEG

BACR15BA7D10C RIVET, 100 DEG

BACR15BA7D12C RIVET, 100 DEG

BACR15BA7D9C RIVET, 100 DEG

RIVET, UNIVERSAL HDBACR15BB6D6C 6 6

BACR15GF7D7 RIVET, 100 DEG

BACW10AT26AS WASHER

BACW10AT27AS WASHER

BACW10AT36AS WASHER

BACW10AT37AS WASHER

BACW10P448CG WASHER, FLAT

BACW10P449CG WASHER

BACW10P454CG WASHER, FLAT

BACW10P455CG WASHER, FLAT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

28 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

NAS1149D0663J WASHER

NAS1149D0763J WASHER

NAS1399MW6A4 RIVET, BLIND

NAS1922-0050-3 CLAMP, HOSE

Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10 11 12

QTY

KIT DETAIL -

SEAL

114U9202-10

KIT DETAIL -

DRAIN TUBE

114U9202-12 1 1

KIT - DRAIN FITTING ASSY114U9202-15

KIT - DRAIN FITTING ASSY114U9202-16

KIT DETAIL -

WEB, FLUID DAM

114U9202-19 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-20 1

KIT DETAIL -

DRAIN TUBE RETAINER

114U9202-24 3 3

KIT DETAIL -

BRACKET

114U9202-3 1 1

KIT DETAIL -

BRACKET

114U9202-4 1 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-5

KIT DETAIL -

WEB, FLUID DAM

114U9202-6

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

29 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10 11 12

QTY

KIT DETAIL -

SEAL

114U9202-9

BACB30LH3-5 BOLT

BOLT-100 DEG

HEAD

BACB30NN3K3 105 105

BOLT, RADIUS

LEAD-IN

BACB30WQ5K13LY 2 2

BOLT, RADIUS

LEAD-IN

BACB30WQ5K14LY 2 2

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LX 6 6

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LY 6 6

BOLT, RADIUS

LEAD-IN

BACB30WQ6K12LY 1 1

BOLT, RADIUS

LEAD-IN

BACB30WQ6K14LX 1 1

BOLT, RADIUS

LEAD-IN

BACB30WQ6K15LX 8 8

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LX 1 1

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LY 1 1

BACB30WQ6K9LX 6 6 BOLT, HEX DRIVE

BACB30WQ6K9LY 6 6 BOLT

BOLT, RADIUS

LEAD-IN

BACB30WQ7K14L 10 10

BOLT, RADIUS

LEAD-IN

BACB30WQ7K15L 15 15

BACB30YN12K15X 6 6 BOLT, HEX DRIVE

BACB30YN12K16X 6 6 BOLT, HEX DRIVE

BACB30YN14K15 2 2 BOLT, HEX DRIVE

BACB30YN14K16 4 4 BOLT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

30 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10 11 12

QTY

BOLT, 100 DEG

HEX DR

BACB30YP6K4

BACC30BS6 COLLAR

BACN10HY5ACX 4 4 NUT

SELF-LOCKING

NUT

BACN10HY6AC 25 25

BACN10HY6ACX 15 15 NUT

SELF-LOCKING

NUT

BACN10HY7AC 25 25

SELF-LOCKING

NUT

BACN10YR6CD 15 15

BACN10YR7CD 6 6 NUT

BACR15BA7AD10C 15 15 RIVET, 100 DEG

BACR15BA7AD11C 52 51 RIVET, 100 DEG

BACR15BA7AD12C 38 37 2 2 RIVET, 100 DEG

BACR15BA7AD13C 30 30 RIVET, 100 DEG

BACR15BA7D10C 1 1 RIVET, 100 DEG

BACR15BA7D12C 1 1 RIVET, 100 DEG

BACR15BA7D9C 1 1 RIVET, 100 DEG

RIVET, UNIVERSAL HDBACR15BB6D6C 7 6

BACR15GF7D7 6 6 RIVET, 100 DEG

BACW10AT26AS 25 25 WASHER

BACW10AT27AS 25 25 WASHER

BACW10AT36AS 25 25 WASHER

BACW10AT37AS 25 25 WASHER

BACW10P448CG 4 4 WASHER, FLAT

BACW10P449CG 15 15 WASHER

BACW10P454CG 4 4 WASHER, FLAT

BACW10P455CG 15 15 WASHER, FLAT

NAS1149D0663J 25 25 WASHER

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

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31 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

KIT 015U1870-1

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10 11 12

QTY

NAS1149D0763J 15 15 WASHER

NAS1399MW6A4 2 2 RIVET, BLIND

NAS1922-0050-3 1 1 CLAMP, HOSE

Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

KIT DETAIL -

SEAL

114U9202-10 1

KIT DETAIL -

DRAIN TUBE

114U9202-12

KIT - DRAIN FITTING ASSY114U9202-15 1

KIT - DRAIN FITTING ASSY114U9202-16 1

KIT DETAIL -

DRAIN TUBE RETAINER

114U9202-24

KIT DETAIL -

BRACKET

114U9202-3 1 1

KIT DETAIL -

BRACKET

114U9202-4 1 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-5 1

KIT DETAIL -

WEB, FLUID DAM

114U9202-6 1

KIT DETAIL -

SEAL

114U9202-9 1

BACB30LH3-5 10 10 BOLT

BOLT-100 DEG

HEAD

BACB30NN3K3

BOEING PROPRIETARY -

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32 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

BOLT, RADIUS

LEAD-IN

BACB30WQ5K13LY

BOLT, RADIUS

LEAD-IN

BACB30WQ5K14LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K12LY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K14LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K15LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LX

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LY

BACB30WQ6K9LX BOLT, HEX DRIVE

BACB30WQ6K9LY BOLT

BOLT, RADIUS

LEAD-IN

BACB30WQ7K14L

BOLT, RADIUS

LEAD-IN

BACB30WQ7K15L

BACB30YN12K15X BOLT, HEX DRIVE

BACB30YN12K16X BOLT, HEX DRIVE

BACB30YN14K15 BOLT, HEX DRIVE

BACB30YN14K16 BOLT

BOLT, 100 DEG

HEX DR

BACB30YP6K4 2 2

BACC30BS6 2 2 COLLAR

BACN10HY5ACX NUT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

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33 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 7 8

QTY

SELF-LOCKING

NUT

BACN10HY6AC

BACN10HY6ACX NUT

SELF-LOCKING

NUT

BACN10HY7AC

SELF-LOCKING

NUT

BACN10YR6CD

BACN10YR7CD NUT

BACR15BA7AD10C RIVET, 100 DEG

BACR15BA7AD11C 3 3 RIVET, 100 DEG

BACR15BA7AD12C RIVET, 100 DEG

BACR15BA7AD13C RIVET, 100 DEG

BACR15BA7D10C RIVET, 100 DEG

BACR15BA7D12C RIVET, 100 DEG

BACR15BA7D9C RIVET, 100 DEG

RIVET, UNIVERSAL HDBACR15BB6D6C 6 6

BACR15GF7D7 RIVET, 100 DEG

BACW10AT26AS WASHER

BACW10AT27AS WASHER

BACW10AT36AS WASHER

BACW10AT37AS WASHER

BACW10P448CG WASHER, FLAT

BACW10P449CG WASHER

BACW10P454CG WASHER, FLAT

BACW10P455CG WASHER, FLAT

NAS1149D0663J WASHER

NAS1149D0763J WASHER

NAS1399MW6A4 RIVET, BLIND

NAS1922-0050-3 CLAMP, HOSE

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

34 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10

QTY

KIT DETAIL -

SEAL

114U9202-10

KIT DETAIL -

DRAIN TUBE

114U9202-12 1 1

KIT - DRAIN FITTING ASSY114U9202-15

KIT - DRAIN FITTING ASSY114U9202-16

KIT DETAIL -

DRAIN TUBE RETAINER

114U9202-24 3 3

KIT DETAIL -

BRACKET

114U9202-3

KIT DETAIL -

BRACKET

114U9202-4

KIT DETAIL -

WEB, FLUID DAM

114U9202-5

KIT DETAIL -

WEB, FLUID DAM

114U9202-6

KIT DETAIL -

SEAL

114U9202-9

BACB30LH3-5 BOLT

BOLT-100 DEG

HEAD

BACB30NN3K3 105 105

BOLT, RADIUS

LEAD-IN

BACB30WQ5K13LY 2 2

BOLT, RADIUS

LEAD-IN

BACB30WQ5K14LY 2 2

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LX 6 6

BOLT, RADIUS

LEAD-IN

BACB30WQ6K10LY 6 6

BOLT, RADIUS

LEAD-IN

BACB30WQ6K12LY 1 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

35 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10

QTY

BOLT, RADIUS

LEAD-IN

BACB30WQ6K14LX 1 1

BOLT, RADIUS

LEAD-IN

BACB30WQ6K15LX 8 8

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LX 1 1

BOLT, RADIUS

LEAD-IN

BACB30WQ6K8LY 1 1

BACB30WQ6K9LX 6 6 BOLT, HEX DRIVE

BACB30WQ6K9LY 6 6 BOLT

BOLT, RADIUS

LEAD-IN

BACB30WQ7K14L 10 10

BOLT, RADIUS

LEAD-IN

BACB30WQ7K15L 15 15

BACB30YN12K15X 6 6 BOLT, HEX DRIVE

BACB30YN12K16X 6 6 BOLT, HEX DRIVE

BACB30YN14K15 2 2 BOLT, HEX DRIVE

BACB30YN14K16 4 4 BOLT

BOLT, 100 DEG

HEX DR

BACB30YP6K4

BACC30BS6 COLLAR

BACN10HY5ACX 4 4 NUT

SELF-LOCKING

NUT

BACN10HY6AC 25 25

BACN10HY6ACX 15 15 NUT

SELF-LOCKING

NUT

BACN10HY7AC 25 25

SELF-LOCKING

NUT

BACN10YR6CD 15 15

BACN10YR7CD 6 6 NUT

BACR15BA7AD10C 15 15 RIVET, 100 DEG

BACR15BA7AD11C 52 51 RIVET, 100 DEG

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: November 09, 2010

747-57-2332

36 of 85

BOEING SERVICE BULLETIN 747-57-2332
Group 7-10:

KIT 015U1870-2

NOTES

Existing Part

Name Number

Figure

New Part Number

9 10

QTY

BACR15BA7AD12C 38 37 RIVET, 100 DEG

BACR15BA7AD13C 30 30 RIVET, 100 DEG

BACR15BA7D10C 1 1 RIVET, 100 DEG

BACR15BA7D12C 1 1 RIVET, 100 DEG

BACR15BA7D9C 1 1 RIVET, 100 DEG

RIVET, UNIVERSAL HDBACR15BB6D6C

BACR15GF7D7 6 6 RIVET, 100 DEG

BACW10AT26AS 25 25 WASHER

BACW10AT27AS 25 25 WASHER

BACW10AT36AS 25 25 WASHER

BACW10AT37AS 25 25 WASHER

BACW10P448CG 4 4 WASHER, FLAT

BACW10P449CG 15 15 WASHER

BACW10P454CG 4 4 WASHER, FLAT

BACW10P455CG 15 15 WASHER, FLAT

NAS1149D0663J 25 25 WASHER

NAS1149D0763J 15 15 WASHER

NAS1399MW6A4 2 2 RIVET, BLIND

NAS1922-0050-3 1 1 CLAMP, HOSE

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

BMS5-95 3 Qt Sealant (a)

BMS10-21, TYPE 3 Oz Anti-Static Coating (a)

III

BMS5-16 6 Oz Two Part Hole Filling Compound (a)

BMS8-79, CLASS 2 ft Glass Fabric (a)

III, STYLE 1581

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BOEING SERVICE BULLETIN 747-57-2332
Part Number / QTY Name Notes

Specification

BMS9-3, TYPE H- 2 ft Glass Fabric Reinforcement (a)

2

Two Part Resin for Composite Re- (b)

pairs

RESIN MIX 3 8 Oz

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for

supplier data.

(b) Refer to 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400

SRM 51-70-07 or 747-400 SRM 51-70-17, as applicable, for material specification and

supplier information.

3. Parts Modified and Reidentified

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane.

Existing Part QTY Name New Part Number Notes

Number

Skin Panel Assembly, 65B10873 (a) (b) (c) (d)

Leading Edge Wing

65B10873 2

SB 747-57-2332

(a) Make the change in accordance with this service bulletin.

(b) There is no equivalent Boeing part number for the changed part. Identify on the part that

the change done in accordance with this service bulletin was made.

(c) This is the part number after the change is done in accordance with this service bulletin.

(d) This part is not used in production.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 747-57-2332
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are in 747 SRM, Chapter 51

– Torque limits to tighten nuts and bolts are in 747 SRM, Chapter 51

5. Use the approved fastener and process material substitutions in accordance with

747 SRM, Chapter 51. Alternate fasteners are listed in 747 SRM Chapter 51 and

Boeing Drawing 012W6100.

6. If the length of any fastener specified in this service bulletin does not meet the

installation standards in SRM Chapter 51, then a fastener of the same specification,

or an approved substitute, with a length which meets the installation standards in

SRM Chapter 51 may be used.

7. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

8. Refer to APPENDIX A for Master Fastener Code Table.

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BOEING SERVICE BULLETIN 747-57-2332
B. WORK INSTRUCTIONS

ACCESS

1. Deactivate the thrust reverser for ground maintenance. Refer to 747-100/200/300 AMM 78-31-00

or 747-400 AMM 78-31-00 as an accepted procedure, as applicable.

2. Extend the variable camber leading edge flaps to the fully extended position and deactivate. Refer

to 747-100/200/300 AMM 27-81-00 or 747-400 AMM 27-81-00 as an accepted procedure, as

applicable.

Part 1 - Outboard Leading Edge Fluid Dam Installation

1. At Outboard Leading Edge Station (OLES) 1250, install fluid dam assemblies in accordance with

the figures below:

Left Wing Right Wing

FIGURE 1 FIGURE 2

Part 2 - Outboard Leading Edge Seal Change

1. At OLES 1185, install seal assemblies in accordance with the figures below:

Left Wing Right Wing

FIGURE 3 FIGURE 4

Part 3 - Inboard Leading Edge Drain Tube Installation

1. Between Inboard Leading Edge Station (ILES) 1116 and ILES 994, remove the lower leading edge

panel in accordance with the figures below:

Left Wing Right Wing

FIGURE 5 FIGURE 6

2. Change the lower leading edge panel in accordance with the figures below:

Left Wing Right Wing

FIGURE 7 FIGURE 8

3. Install the lower leading edge panel and drain tube assembly in accordance with the figures below:

Left Wing Right Wing

FIGURE 9 FIGURE 10

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BOEING SERVICE BULLETIN 747-57-2332
Group 1-6:

Part 4 - Inboard Leading Edge Fluid Dam Installation

1. At ILES 770, install fluid dam assemblies in accordance with the figures below:

Left Wing Right Wing

FIGURE 11 FIGURE 12

Close Access

1. Retract the variable camber leading edge flaps to the fully up position and activate. Refer to

747-100/200/300 AMM 27-81-00 or 747-400 AMM 27-81-00 as an accepted procedure, as

applicable.

2. Activate the thrust reversers. Refer to 747-100/200/300 AMM 78-31-00 or 747-400 AMM 78-31-00

as an accepted procedure, as applicable.

3. Put the airplane back to serviceable condition.

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 2

KIT DETAIL - BRACK- 114U9202-3 1 as shown.

ET

2 Locate

KIT DETAIL - BRACK- 114U9202-4 1 as shown.

ET

Locate

KIT DETAIL - WEB, 114U9202-5 1 as shown.

FLUID DAM

Locate

3 Drill Hole - 8

Clean Hole - 8 and deburr.

KIT DETAIL - BRACK- 114U9202-3 1

ET

4 Install (New)

Fay surface seal between mating surface of bracket to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - BRACK- 114U9202-4 1

ET

Install (New)

Fay surface seal between mating surface of fluid dam to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - WEB, 114U9202-5 1

FLUID DAM

Install (New)

5 Install (New) Fastener - 8

as required to apply

fillet seal to both

sides of fluid dam.

Refer to SOPM 20-

50-19 as an accepted procedure. Make

sure drainage hole

is clear of sealant.

6 Apply Sealant BMS5-95 -

FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply bead of

sealant extending

from fluid dam to

forward edge of

beam panel support.

Make sure sealant is

flush with top of fluid

dam.

7 Apply Sealant BMS5-95 -

The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

RIVET, UNIVERSAL BACR15BB6D6C 6

HD

RIVET, 100 DEG BACR15BA7AD11C 3 (a)

(a) Quantity may be in excess of requirements.

FIGURE 1: OUTBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 2

KIT DETAIL - BRACK- 114U9202-3 1 as shown.

ET

2 Locate

KIT DETAIL - BRACK- 114U9202-4 1 as shown.

ET

Locate

KIT DETAIL - WEB, 114U9202-6 1 as shown.

FLUID DAM

Locate

3 Drill Hole - 8

Clean Hole - 8 and deburr.

KIT DETAIL - BRACK- 114U9202-3 1

ET

4 Install (New)

Fay surface seal between mating surface of bracket to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - BRACK- 114U9202-4 1

ET

Install (New)

Fay surface seal between mating surface of fluid dam to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - WEB, 114U9202-6 1

FLUID DAM

Install (New)

5 Install (New) Fastener - 8

as required to apply

fillet seal to both

sides of fluid dam.

Refer to SOPM 20-

50-19 as an accepted procedure. Make

sure drainage hole

is clear of sealant.

6 Apply Sealant BMS5-95 -

FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply bead of

sealant extending

from fluid dam to

forward edge of

beam panel support.

Make sure sealant is

flush with top of fluid

dam.

7 Apply Sealant BMS5-95 -

The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

RIVET, UNIVERSAL BACR15BB6D6C 6

HD

RIVET, 100 DEG BACR15BA7AD11C 3 (a)

(a) Quantity may be in excess of requirements.

FIGURE 2: OUTBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 9

2 Remove / Keep Retainer - 1

4.20 inches from

edge of retainer.

3 Cut Bulb Seal - 1

with BMS5-16 - Hole

Filling Compound.

Refer to SOPM 20-

50-19 as an accepted procedure.

4 Fill Drainage Hole - 1

in contact with the

end of the existing

bulb seal and

aligned with the forward edge of the retainer.

5 Locate KIT DETAIL - SEAL 114U9202-9 1

Locate Retainer - 1 as shown.

Mark hole locations

on seal.

6 Locate Hole - 2

7 Remove / Keep Retainer - 1

Remove / Keep KIT DETAIL - SEAL 114U9202-9 1

Diameter of holes is

0.35 inches.

8 Drill Hole - 2

9 Install (New) KIT DETAIL - SEAL 114U9202-9 1

Install (Kept) Retainer - 1

Install (New) BOLT BACB30LH3-5 9

The parts shown in the table below are provided as extra parts for this figure.

NAME IDENTIFICATION QTY MORE DATA

BOLT BACB30LH3-5 1

FIGURE 3: OUTBOARD LEADING EDGE LEFT WING SEAL CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 9

2 Remove / Keep Retainer - 1

4.20 inches from

edge of retainer.

3 Cut Bulb Seal - 1

with BMS5-16 - Hole

Filling Compound.

Refer to SOPM 20-

50-19 as an accepted procedure.

4 Fill Drainage Hole - 1

in contact with the

end of the existing

bulb seal and

aligned with the forward edge of the retainer.

5 Locate KIT DETAIL - SEAL 114U9202-10 1

Locate Retainer - 1 as shown.

Mark hole locations

on seal.

6 Locate Hole - 2

7 Remove / Keep Retainer - 1

Remove / Keep KIT DETAIL - SEAL 114U9202-10 1

Diameter of holes is

0.35 inches.

8 Drill Hole - 2

9 Install (New) KIT DETAIL - SEAL 114U9202-10 1

Install (Kept) Retainer - 1

Install (New) BOLT BACB30LH3-5 9

The parts shown in the table below are provided as extra parts for this figure.

NAME IDENTIFICATION QTY MORE DATA

BOLT BACB30LH3-5 1

FIGURE 4: OUTBOARD LEADING EDGE RIGHT WING SEAL CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Recommend noting

fastener type removed from each

hole for future reference.

1 Remove Fastener - -

Skin Panel Assy, Lead- 65B10873-7, -27 1

ing Edge Wing

2 Remove / Keep

FIGURE 5: LEFT WING LOWER SKIN PANEL REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Recommend noting

fastener type removed from each

hole for future reference.

1 Remove Fastener - -

Skin Panel Assy, Lead- 65B10873-8, -28 1

ing Edge Wing

2 Remove / Keep

FIGURE 6: RIGHT WING LOWER SKIN PANEL REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

as shown above.

Remove existing

plies, cut core and

install new plies in

accordance with (a).

Replace the two existing plies and add

two extra repair

plies.

Skin Panel Assy, Lead- 65B10873-7, -27 1

ing Edge Wing

1 Change

Drainage hole diameter is 0.375 in.2 Drill Hole - 1

KIT - DRAIN FITTING 114U9202-15 1

ASSY

3 Put / Hold

Hole diameter: 0.190

- 0.193 in.

4 Drill Hole - 2

5 Clean Hole - 3 and deburr.

KIT - DRAIN FITTING 114U9202-15 1

ASSY

6 Install (New)

Refer to SOPM 20-

50-18 as an accepted procedure.

BOLT, 100 DEG HEX BACB30YP6K4 2

DR

7 Install (New)

Install (New) COLLAR BACC30BS6 2

Rubber stamp part

number on the part.

Refer to SOPM 20-

50-10 as an accepted procedure.

8 Apply Part Number SB 747-57-2332 1

(a) 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400 SRM 51-70-07, 747-400

SRM 51-70-17, 747-400F SRM 51-70-07, 747-400F SRM 51-70-17, 747-400LCF SRM 51-70-07, 747-

400LCF SRM 51-70-17, 747-400SF SRM 51-70-07, 747-400SF SRM 51-70-17 or 747-SP SRM 51-40-

14, as applicable.

FIGURE 7: LEFT WING LOWER SKIN PANEL CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

as shown above.

Remove existing

plies, cut core and

install new plies in

accordance with (a).

Replace the two existing plies and add

two extra repair

plies.

Skin Panel Assy, Lead- 65B10873-8, -28 1

ing Edge Wing

1 Change

Drainage hole diameter is 0.375 in.2 Drill Hole - 1

KIT - DRAIN FITTING 114U9202-16 1

ASSY

3 Put / Hold

Hole diameter: 0.190

- 0.193 in.

4 Drill Hole - 2

5 Clean Hole - 3 and deburr.

KIT - DRAIN FITTING 114U9202-16 1

ASSY

6 Install (New)

Refer to SOPM 20-

50-18 as an accepted procedure.

BOLT, 100 DEG HEX BACB30YP6K4 2

DR

7 Install (New)

Install (New) COLLAR BACC30BS6 2

Rubber stamp part

number on the part.

Refer to SOPM 20-

50-10 as an accepted procedure.

8 Apply Part Number SB 747-57-2332 1

(a) 747-100/200/300 SRM 51-40-12, 747-100/200/300 SRM 51-40-14, 747-400 SRM 51-70-07, 747-400

SRM 51-70-17, 747-400F SRM 51-70-07, 747-400F SRM 51-70-17, 747-400LCF SRM 51-70-07, 747-

400LCF SRM 51-70-17, 747-400SF SRM 51-70-07, 747-400SF SRM 51-70-17 or 747-SP SRM 51-40-

14, as applicable.

FIGURE 8: RIGHT WING LOWER SKIN PANEL CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Skin Panel Assy, Lead- 65B10873-7, -27 1

ing Edge Wing

1 Put / Hold

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

2 Locate

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

Put / Hold

3 Drill / Ream Hole - 107

4 Clean Hole - 107 and deburr.

as necessary. Refer

to SOPM 20-10-06

as an accepted procedure.

5 Apply Anti-Static Coating BMS10-21, TYPE III -

Fay surface seal between mating surface of aft edge of

panel to lower wing

skin with BMS5-95.

Skin Panel Assy, Lead- 65B10873-7, -27 1

ing Edge Wing

6 Install (Kept)

into clips of the drain

tube retainers. Ensure that the outboard end of the

drain tube extends

past the outboard

edge of the rib. Remove sealant as

necessary.

KIT DETAIL - DRAIN 114U9202-12 1

TUBE

7 Install (New)

FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 1 OF 4)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

to connect the drain

tube to the drain fitting assembly. Refer

to SOPM 20-50-00

as an accepted procedure.

8 Install (New) CLAMP, HOSE NAS1922-0050-3 1

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

9 Install (New)

For codes with optional bolts, measure

the height of the

stackup and diameter of the pre-existing hole. Use the

bolt compatible for

the measured stackup and the corresponding smallest

diameter attainable

from the measured

hole.

10 Install (New) Fastener - 202

to apply fillet seal.

Ensure absolute

seal around outer diameter of drain tube

filing entire gap between adjacent

structures. Ensure

drain tube is clear of

sealant.

11 Apply Sealant BMS5-95 -

FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

BOLT, HEX DRIVE BACB30YN12K15X 6 (a)

BOLT, HEX DRIVE BACB30YN12K16X 6 (a)

WASHER NAS1149D0663J 25 (a)

SELF-LOCKING NUT BACN10YR6CD 15 (a)

BOLT, HEX DRIVE BACB30YN14K15 2 (a)

BOLT BACB30YN14K16 4 (a)

WASHER NAS1149D0763J 15 (a)

NUT BACN10YR7CD 6 (a)

BOLT, RADIUS LEAD- BACB30WQ7K14L 10 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ7K15L 15 (a)

IN

SELF-LOCKING NUT BACN10HY7AC 25 (a)

BOLT, RADIUS LEAD- BACB30WQ6K15LX 8 (a)

IN

WASHER BACW10AT26AS 25 (a)

WASHER BACW10AT36AS 25 (a)

SELF-LOCKING NUT BACN10HY6AC 25 (a)

WASHER BACW10AT37AS 25 (a)

WASHER BACW10AT27AS 25 (a)

BOLT, RADIUS LEAD- BACB30WQ5K13LY 2 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ5K14LY 2 (a)

IN

WASHER, FLAT BACW10P448CG 4 (a)

WASHER, FLAT BACW10P454CG 4 (a)

NUT BACN10HY5ACX 4 (a)

BOLT, RADIUS LEAD- BACB30WQ6K8LX 1 (a)

IN

BOLT, HEX DRIVE BACB30WQ6K9LX 6 (a)

BOLT, RADIUS LEAD- BACB30WQ6K10LX 6 (a)

IN

FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
NAME IDENTIFICATION QTY MORE DATA

BOLT, RADIUS LEAD- BACB30WQ6K8LY 1 (a)

IN

BOLT BACB30WQ6K9LY 6 (a)

BOLT, RADIUS LEAD- BACB30WQ6K10LY 6 (a)

IN

WASHER BACW10P449CG 15 (a)

WASHER, FLAT BACW10P455CG 15 (a)

NUT BACN10HY6ACX 15 (a)

BOLT, RADIUS LEAD- BACB30WQ6K12LY 1 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ6K14LX 1 (a)

IN

RIVET, BLIND NAS1399MW6A4 2 (a)

RIVET, 100 DEG BACR15BA7D9C 1 (a)

RIVET, 100 DEG BACR15BA7D10C 1 (a)

RIVET, 100 DEG BACR15BA7D12C 1 (a)

BOLT-100 DEG HEAD BACB30NN3K3 105 (a)

RIVET, 100 DEG BACR15GF7D7 6 (a)

RIVET, 100 DEG BACR15BA7AD10C 15 (a)

RIVET, 100 DEG BACR15BA7AD11C 52 (a)

RIVET, 100 DEG BACR15BA7AD12C 38 (a)

RIVET, 100 DEG BACR15BA7AD13C 30 (a)

(a) Quantity may be in excess of requirements.

FIGURE 9: LEFT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Skin Panel Assy, Lead- 65B10873-8, -28 1

ing Edge Wing

1 Put / Hold

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

2 Locate

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

Put / Hold

3 Drill / Ream Hole - 107

4 Clean Hole - 107 and deburr.

as necessary. Refer

to SOPM 20-10-06

as an accepted procedure.

5 Apply Anti-Static Coating BMS10-21, TYPE III -

Fay surface seal between mating surface of aft edge of

panel to lower wing

skin with BMS5-95.

Skin Panel Assy, Lead- 65B10873-8, -28 1

ing Edge Wing

6 Install (Kept)

into clips of the drain

tube retainers. Ensure that the outboard end of the

drain tube extends

past the outboard

edge of the rib. Remove sealant as

necessary.

KIT DETAIL - DRAIN 114U9202-12 1

TUBE

7 Install (New)

FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

to connect the drain

tube to the drain fitting assembly. Refer

to SOPM 20-50-00

as an accepted procedure.

8 Install (New) CLAMP, HOSE NAS1922-0050-3 1

KIT DETAIL - DRAIN 114U9202-24 3

TUBE RETAINER

9 Install (New)

For codes with optional bolts, measure

the height of the

stackup and diameter of the pre-existing hole. Use the

bolt compatible for

the measured stackup and the corresponding smallest

diameter attainable

from the measured

hole.

10 Install (New) Fastener - 202

as required to apply

fillet seal. Ensure

absolute seal around

outer diameter of

drain tube filing entire gap between adjacent structures.

Ensure drain tube is

clear of sealant.

11 Apply Sealant BMS5-95 -

FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 2 OF 4)

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65 of 85

BOEING SERVICE BULLETIN 747-57-2332
The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

BOLT, HEX DRIVE BACB30YN12K15X 6 (a)

BOLT, HEX DRIVE BACB30YN12K16X 6 (a)

WASHER NAS1149D0663J 25 (a)

SELF-LOCKING NUT BACN10YR6CD 15 (a)

BOLT, HEX DRIVE BACB30YN14K15 2 (a)

BOLT BACB30YN14K16 4 (a)

WASHER NAS1149D0763J 15 (a)

NUT BACN10YR7CD 6 (a)

BOLT, RADIUS LEAD- BACB30WQ7K14L 10 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ7K15L 15 (a)

IN

SELF-LOCKING NUT BACN10HY7AC 25 (a)

BOLT, RADIUS LEAD- BACB30WQ6K15LX 8 (a)

IN

WASHER BACW10AT26AS 25 (a)

WASHER BACW10AT36AS 25 (a)

SELF-LOCKING NUT BACN10HY6AC 25 (a)

WASHER BACW10AT37AS 25 (a)

WASHER BACW10AT27AS 25 (a)

BOLT, RADIUS LEAD- BACB30WQ5K13LY 2 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ5K14LY 2 (a)

IN

WASHER, FLAT BACW10P448CG 4 (a)

WASHER, FLAT BACW10P454CG 4 (a)

NUT BACN10HY5ACX 4 (a)

BOLT, RADIUS LEAD- BACB30WQ6K8LX 1 (a)

IN

BOLT, HEX DRIVE BACB30WQ6K9LX 6 (a)

BOLT, RADIUS LEAD- BACB30WQ6K10LX 6 (a)

IN

FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
NAME IDENTIFICATION QTY MORE DATA

BOLT, RADIUS LEAD- BACB30WQ6K8LY 1 (a)

IN

BOLT BACB30WQ6K9LY 6 (a)

BOLT, RADIUS LEAD- BACB30WQ6K10LY 6 (a)

IN

WASHER BACW10P449CG 15 (a)

WASHER, FLAT BACW10P455CG 15 (a)

NUT BACN10HY6ACX 15 (a)

BOLT, RADIUS LEAD- BACB30WQ6K12LY 1 (a)

IN

BOLT, RADIUS LEAD- BACB30WQ6K14LX 1 (a)

IN

RIVET, BLIND NAS1399MW6A4 2 (a)

RIVET, 100 DEG BACR15BA7D9C 1 (a)

RIVET, 100 DEG BACR15BA7D10C 1 (a)

RIVET, 100 DEG BACR15BA7D12C 1 (a)

BOLT-100 DEG HEAD BACB30NN3K3 105 (a)

RIVET, 100 DEG BACR15GF7D7 6 (a)

RIVET, 100 DEG BACR15BA7AD10C 15 (a)

RIVET, 100 DEG BACR15BA7AD11C 51 (a)

RIVET, 100 DEG BACR15BA7AD12C 37 (a)

RIVET, 100 DEG BACR15BA7AD13C 30 (a)

(a) Quantity may be in excess of requirements.

FIGURE 10: RIGHT WING LOWER LEADING EDGE PANEL AND DRAIN TUBE INSTALLATION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 747-57-2332
This Figure applies only to: Group 1-6.

FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 2

KIT DETAIL - BRACK- 114U9202-3 1 as shown.

ET

2 Locate

KIT DETAIL - BRACK- 114U9202-4 1 as shown.

ET

Locate

KIT DETAIL - WEB, 114U9202-19 1 as shown.

FLUID DAM

Locate

3 Drill Hole - 8

Clean Hole - 8 and deburr.

KIT DETAIL - BRACK- 114U9202-3 1

ET

4 Install (New)

Fay surface seal between mating surface of bracket to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - BRACK- 114U9202-4 1

ET

Install (New)

Fay surface seal between mating surface of fluid dam to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - WEB, 114U9202-19 1

FLUID DAM

Install (New)

5 Install (New) Fastener - 8

as required to apply

fillet seal on both

sides of fluid dam.

Refer to SOPM 20-

50-19 as an accepted procedure. Make

sure drainage hole

is clear of sealant.

6 Apply Sealant BMS5-95 -

FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

RIVET, UNIVERSAL BACR15BB6D6C 7

HD

RIVET, 100 DEG BACR15BA7AD12C 2

FIGURE 11: INBOARD LEFT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 3 OF 3)

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70 of 85

BOEING SERVICE BULLETIN 747-57-2332
This Figure applies only to: Group 1-6.

FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 1 OF 3)

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71 of 85

BOEING SERVICE BULLETIN 747-57-2332
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Fastener - 2

KIT DETAIL - BRACK- 114U9202-3 1 as shown.

ET

2 Locate

KIT DETAIL - BRACK- 114U9202-4 1 as shown.

ET

Locate

KIT DETAIL - WEB, 114U9202-20 1 as shown.

FLUID DAM

Locate

3 Drill Hole - 8

Clean Hole - 8 and deburr.

KIT DETAIL - BRACK- 114U9202-3 1

ET

4 Install (New)

Fay surface seal between mating surface of bracket to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - BRACK- 114U9202-4 1

ET

Install (New)

Fay surface seal between mating surface of fluid dam to

lower wing skin with

BMS5-95. Refer to

SOPM 20-50-19 as

an accepted procedure. Make sure

drainage hole is

clear of sealant.

KIT DETAIL - WEB, 114U9202-20 1

FLUID DAM

Install (New)

5 Install (New) Fastener - 8

as required to apply

fillet seal on both

sides of fluid dam.

Refer to SOPM 20-

50-19 as an accepted procedure. Make

sure drainage hole

is clear of sealant.

6 Apply Sealant BMS5-95 -

FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
The parts listed below are used in this figure. Refer to APPENDIX A for fastener codes.

NAME IDENTIFICATION QTY MORE DATA

RIVET, UNIVERSAL BACR15BB6D6C 6

HD

RIVET, 100 DEG BACR15BA7AD12C 2

FIGURE 12: INBOARD RIGHT WING LEADING EDGE FLUID DAM INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

RIVET, UNIVERSAL BACR15BB6D6C 0.191 - 0.202

HD

A

B RIVET, 100 DEG BACR15BA7AD11C 0.223 - 0.233

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 1 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

C GROUP 1-5, 8, 9:

Determine grip length

from hole before installation. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K14L

IN

Determine grip length

from hole before installation. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K15L

IN

WASHER BACW10AT27AS - Install under the nut.

WASHER BACW10AT37AS - Install under the nut.

Torque to 330 - 340 inlbs.SELF-LOCKING NUT BACN10HY7AC -

GROUP 6, 10:

If removed fastener was

a straight shank bolt.

Determine grip length

from hole before installation. (a)

0.3866 -

0.3886

BOLT, HEX DRIVE BACB30YN12K15X

If removed fastener was

a straight shank bolt.

Determine grip length

from hole before installation. (a)

0.3866 -

0.3886

BOLT, HEX DRIVE BACB30YN12K16X

If removed fastener was

a straight shank bolt. Install 2 washers under the

nut.

WASHER NAS1149D0663J -

If removed fastener was

a straight shank bolt.

Torque to 213 - 227 inlbs.

SELF-LOCKING NUT BACN10YR6CD -

If removed fastener was

a taper shank bolt. Determine grip length from

hole before installation.

(a)

0.4335 -

0.4355

BOLT, HEX DRIVE BACB30YN14K15

If removed fastener was

a taper shank bolt. Determine grip length from

hole before installation.

(a)

0.4335 -

0.4355

BOLT BACB30YN14K16

WASHER NAS1149D0763J -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 2 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

If removed fastener was

a taper shank bolt. Install

2 washers under the nut.

If removed fastener was

a taper shank bolt.

Torque to 291 - 309 inlbs.

NUT BACN10YR7CD -

GROUP 7:

Determine grip length

from hole before installation. (a)

0.3866 -

0.3886

BOLT, HEX DRIVE BACB30YN12K15X

Determine grip length

from hole before installation. (a)

0.3866 -

0.3886

BOLT, HEX DRIVE BACB30YN12K16X

Install 2 washers under

the nut.

WASHER NAS1149D0663J -

Torque to 213 - 227 inlbs.SELF-LOCKING NUT BACN10YR6CD -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 3 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

D GROUP 1-5, 8, 9:

Determine grip length

from hole before installation. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K14L

IN

Determine grip length

from hole before installation. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K15L

IN

WASHER BACW10AT27AS - Install under the nut.

WASHER BACW10AT37AS - Install under the nut.

Torque to 330 - 340 inlbs.SELF-LOCKING NUT BACN10HY7AC -

GROUP 6, 10:

If removed fastener was

a straight shank bolt. (a)

0.3856 -

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K15LX

IN

If removed fastener was

a straight shank bolt. Install under the nut.

WASHER BACW10AT26AS -

If removed fastener was

a straight shank bolt. Install under the nut.

WASHER BACW10AT36AS -

If removed fastener was

a straight shank bolt.

Torque to 235 - 245 inlbs.

SELF-LOCKING NUT BACN10HY6AC -

If removed fastener was

a taper shank bolt. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K15L

IN

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10AT27AS -

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10AT37AS -

If removed fastener was

a taper shank bolt.

Torque to 330 - 340 inlbs.

SELF-LOCKING NUT BACN10HY7AC -

GROUP 7:

0.3856 - (a)

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K15LX

IN

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 4 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

WASHER Install under the nut. BACW10AT26AS -

WASHER BACW10AT36AS - Install under the nut.

Torque to 235 - 245 inlbs.SELF-LOCKING NUT BACN10HY6AC -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 5 OF 12)

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78 of 85

BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

E GROUP 1-4, 8:

Determine grip length

from hole before installation. (a)

0.3387 -

0.3408

BOLT, RADIUS LEAD- BACB30WQ5K13LY

IN

Determine grip length

from hole before installation. (a)

0.3387 -

0.3408

BOLT, RADIUS LEAD- BACB30WQ5K14LY

IN

WASHER, FLAT BACW10P448CG - Install under the nut.

WASHER, FLAT BACW10P454CG - Install under the nut.

Torque to 150 - 155 inlbs.NUT BACN10HY5ACX -

GROUP 5, 9:

0.4385 - (a)

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K15L

IN

WASHER BACW10AT27AS - Install under the nut.

WASHER BACW10AT37AS - Install under the nut.

Torque to 330 - 340 inlbs.SELF-LOCKING NUT BACN10HY7AC -

GROUP 6, 10:

If removed fastener was

a straight shank bolt. (a)

0.3856 -

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K15LX

IN

If removed fastener was

a straight shank bolt. Install under the nut.

WASHER BACW10AT26AS -

If removed fastener was

a straight shank bolt. Install under the nut.

WASHER BACW10AT36AS -

If removed fastener was

a straight shank bolt.

Torque to 235 - 245 inlbs.

SELF-LOCKING NUT BACN10HY6AC -

If removed fastener was

a taper shank bolt. (a)

0.4385 -

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K15L

IN

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10AT27AS -

WASHER BACW10AT37AS -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 6 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

If removed fastener was

a taper shank bolt. Install

under the nut.

If removed fastener was

a taper shank bolt.

Torque to 330 - 340 inlbs.

SELF-LOCKING NUT BACN10HY7AC -

GROUP 7:

0.3856 - (a)

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K15LX

IN

WASHER BACW10AT26AS - Install under the nut.

WASHER BACW10AT36AS - Install under the nut.

Torque to 235 - 245 inlbs.SELF-LOCKING NUT BACN10HY6AC -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 7 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

F GROUP 1, 2, 8:

If removed fastener was

a radius lead-in bolt. (a)

0.3856 -

0.3877

BOLT, HEX DRIVE BACB30WQ6K9LX

If removed fastener was

a radius lead-in bolt. Install under the nut.

WASHER BACW10AT26AS -

If removed fastener was

a radius lead-in bolt. Install under the nut.

WASHER BACW10AT36AS -

If removed fastener was

a radius lead-in bolt.

Torque to 235 - 245 inlbs.

SELF-LOCKING NUT BACN10HY6AC -

If removed fastener was

a taper shank bolt. (a)

0.4012 -

0.4033

BOLT BACB30WQ6K9LY

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10P449CG -

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER, FLAT BACW10P455CG -

If removed fastener was

a taper shank bolt.

Torque to 235 - 245 inlbs.

NUT BACN10HY6ACX -

GROUP 3- 6, 9, 10:

If removed fastener was

a radius lead-in bolt. Determine grip length from

hole before installation.

(a)

0.3856 -

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K8LX

IN

If removed fastener was

a radius lead-in bolt. Determine grip length from

hole before installation.

(a)

0.3856 -

0.3877

BOLT, HEX DRIVE BACB30WQ6K9LX

If removed fastener was

a radius lead-in bolt. Determine grip length from

hole before installation.

(a)

0.3856 -

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K10LX

IN

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 8 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

WASHER If removed fastener was

a radius lead-in bolt. Install under the nut.

BACW10AT26AS -

If removed fastener was

a radius lead-in bolt. Install under the nut.

WASHER BACW10AT36AS -

If removed fastener was

a radius lead-in bolt.

Torque to 235 - 245 inlbs.

SELF-LOCKING NUT BACN10HY6AC -

If removed fastener was

a taper shank bolt. Determine grip length from

hole before installation.

(a)

0.4012 -

0.4033

BOLT, RADIUS LEAD- BACB30WQ6K8LY

IN

If removed fastener was

a taper shank bolt. Determine grip length from

hole before installation.

(a)

0.4012 -

0.4033

BOLT BACB30WQ6K9LY

If removed fastener was

a taper shank bolt. Determine grip length from

hole before installation.

(a)

0.4012 -

0.4033

BOLT, RADIUS LEAD- BACB30WQ6K10LY

IN

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10P449CG -

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER, FLAT BACW10P455CG -

If removed fastener was

a taper shank bolt.

Torque to 235 - 245 inlbs.

NUT BACN10HY6ACX -

GROUP 7:

If removed fastener was

a radius lead-in bolt. (a)

0.3856 -

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K10LX

IN

If removed fastener was

a radius lead-in bolt. Install under the nut.

WASHER BACW10AT26AS -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 9 OF 12)

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CODE NAME IDENTIFICATION HOLE DIA MORE DATA

WASHER If removed fastener was

a radius lead-in bolt. Install under the nut.

BACW10AT36AS -

If removed fastener was

a radius lead-in bolt.

Torque to 235 - 245 inlbs.

SELF-LOCKING NUT BACN10HY6AC -

If removed fastener was

a taper shank bolt. (a)

0.4012 -

0.4033

BOLT, RADIUS LEAD- BACB30WQ6K10LY

IN

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER BACW10P449CG -

If removed fastener was

a taper shank bolt. Install

under the nut.

WASHER, FLAT BACW10P455CG -

If removed fastener was

a taper shank bolt.

Torque to 235 - 245 inlbs.

NUT BACN10HY6ACX -

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 10 OF 12)

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CODE NAME IDENTIFICATION HOLE DIA MORE DATA

G GROUP 1, 3:

0.4012 - (a)

0.4033

BOLT, RADIUS LEAD- BACB30WQ6K12LY

IN

WASHER BACW10P449CG - Install under the nut.

WASHER, FLAT BACW10P455CG - Install under the nut.

Torque to 235 - 245 inlbs.NUT BACN10HY6ACX -

GROUP 2, 4-6, 8-10:

0.4385 - (a)

0.4406

BOLT, RADIUS LEAD- BACB30WQ7K14L

IN

WASHER BACW10AT27AS - Install under the nut.

WASHER BACW10AT37AS - Install under the nut.

Torque to 330 - 340 inlbs.SELF-LOCKING NUT BACN10HY7AC -

GROUP 7:

0.3856 - (a)

0.3877

BOLT, RADIUS LEAD- BACB30WQ6K14LX

IN

WASHER BACW10AT26AS - Install under the nut.

WASHER BACW10AT36AS - Install under the nut.

Torque to 235 - 245 inlbs.SELF-LOCKING NUT BACN10HY6AC -

Clean underside of fastener head prior to installation. Refer SOPM 20-

30-03, Solvent Cleaning

Method 3 as an accepted procedure. (b)

H RIVET, BLIND NAS1399MW6A4 0.192 - 0.196

I RIVET, 100 DEG BACR15BA7D9C 0.223 - 0.233 (b)

RIVET, 100 DEG BACR15BA7D10C 0.223 - 0.233 (b)

RIVET, 100 DEG BACR15BA7D12C 0.223 - 0.233 (b)

J BOLT-100 DEG HEAD BACB30NN3K3 0.190 - 0.194 (b)

K RIVET, 100 DEG BACR15GF7D7 0.223 - 0.229 (b)

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 11 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332
CODE NAME IDENTIFICATION HOLE DIA MORE DATA

Determine grip length

from hole before installation. (b)

L RIVET, 100 DEG BACR15BA7AD10C 0.223 - 0.233

Determine grip length

from hole before installation. (b)

RIVET, 100 DEG BACR15BA7AD11C 0.223 - 0.233

Determine grip length

from hole before installation. (b)

RIVET, 100 DEG BACR15BA7AD12C 0.223 - 0.233

Determine grip length

from hole before installation. (b)

RIVET, 100 DEG BACR15BA7AD13C 0.223 - 0.233

M RIVET, 100 DEG BACR15BA7AD12C 0.223 - 0.233

(a) Install with BMS5-95 wet sealant. Refer to SOPM 20-50-19, Method 2 as an accepted procedure.

(b) Refer to SOPM 20-50-18 as an accepted procedure for installation.

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 12 OF 12)

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BOEING SERVICE BULLETIN 747-57-2332