Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0070

Original Issue: January 27, 2010

ATA System: 5741

SUBJECT: WINGS - Leading Edge Lower Panel Assemblies - 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Unpublished Work - All Rights Reserved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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Table of Contents

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

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 15

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 18

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

FIGURE 1: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO.

4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 2: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND

ADJACENT RIBS - SLAT NO. 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 3: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND

ADJACENT RIBS - SLAT NO. 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

FIGURE 4: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO.

7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 5: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND

ADJACENT RIBS - SLAT NO. 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 6: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND

ADJACENT RIBS - SLAT NO. 7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

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Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Summary Number: 757-57-0070

Original Issue: January 27, 2010

ATA System: 5741

SUBJECT: WINGS - Leading Edge Lower Panel Assemblies - Drainage Path Change.

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

757 airplanes in service have drain holes and unsealed panel assemblies in the fixed leading edge (LE) adjacent

to the inboard end of slats 4 and 7 that are too close to the hot portion of the engines. A design change adds a

new drain hole at outboard slat station (OSS) 344.500 and seals ribs adjacent to the new drain hole. Doing this

change will create new drain paths to direct fluid drainage from the adjacent track housings safely away from

the hot portion of the engines. If not corrected, drainage path too close to the hot portion of the engines could

possibly result in fire in case of fuel leakage from the slat track housings.

ACTION (PRR 54530-289RS)

This service bulletin provides instructions to makes changes to the lower fixed leading edge (LE) panel assemblies,

immediately outboard of the nacelles, as follows:

1. Makes new reinforced drain hole at outboard slat station (OSS) 344.50.

2. Seals the ribs adjacent to the new drain hole.

EFFECTIVITY

All 757 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

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.

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INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the changes given in this service bulletin.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

757 8.50 8.50

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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Commercial 

Airplanes 757

Service Bulletin

SPECIAL ATTENTION

Number: 757-57-0070

Original Issue: January 27, 2010

ATA System: 5741

SUBJECT: WINGS - Leading Edge Lower Panel Assemblies - Drainage Path Change.

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. Refer to PRR 54530-289RS for data about

this change.

Refer to Service Bulletin Index Document D624N001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - Drain Path Change - Inboard end of slat No. 4 and slat No. 7.

Airplane Models:

757-200, 757-200CB, 757-200PF, 757-300

Variable Number Group

NA001 - NA028 1

NA191 - NA199 1

NA201 - NA239 1

NA301 - NA305 1

NA341 - NA352 1

NA391 - NA399 1

NA401 - NA408 1

NA441 - NA447 1

NA501 - NA586 1

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Variable Number Group

NB001 - NB004 1

NB021 - NB023 1

NB036 - NB041 1

NB051 - NB053 1

NB061 - NB073 1

NB079 1

NB131 - NB148 1

NB161 - NB162 1

NB166 - NB168 1

NB201 - NB204 1

NB221 - NB228 1

NB230 1

NB236 1

NB239 1

NB261 - NB267 1

NB291 - NB299 1

NB301 - NB302 1

NB311 - NB312 1

NB321 - NB331 1

NB421 - NB438 1

NB446 1

NB451 - NB454 1

NB501 - NB523 1

NB561 1

NB571 1

NB581 - NB583 1

NC001 - NC033 1

NC041 - NC042 1

NC051 - NC052 1

NC056 - NC062 1

NC066 - NC084 1

NC091 - NC094 1

NC151 1

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BOEING SERVICE BULLETIN 757-57-0070
Variable Number Group

NC161 1

NC901 - NC951 1

NC971 - NC974 1

ND001 - ND007 1

ND011 - ND059 1

ND111 - ND113 1

ND161 - ND199 1

ND201 - ND203 1

ND221 - ND225 1

ND241 - ND248 1

ND301 - ND322 1

ND401 1

ND891 1

ND895 1

NE001 - NE008 1

NE011 - NE088 1

NE091 - NE094 1

NE141 - NE150 1

NE161 - NE177 1

NE201 - NE204 1

NE301 - NE302 1

NE311 - NE325 1

NJ001 - NJ004 1

NJ031 - NJ032 1

NJ551 - NJ555 1

NL001 - NL002 1

NL006 - NL017 1

NL101 - NL109 1

NL141 1

NL601 - NL616 1

NN001 - NN002 1

NN051 - NN052 1

NP901 - NP904 1

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Variable Number Group

NS601 - NS616 1

NT001 - NT009 1

NT201 - NT202 1

NT231 - NT234 1

NT237 - NT240 1

NT242 1

NT245 - NT248 1

NT281 - NT289 1

NT341 - NT347 1

NT351 - NT360 1

NT371 - NT373 1

NT375 - NT379 1

NT381 - NT386 1

NT401 - NT409 1

NT411 - NT412 1

NT426 - NT427 1

NT431 - NT432 1

NT436 - NT438 1

NT441 - NT442 1

NT446 1

NT701 - NT769 1

NT791 - NT796 1

NT861 - NT862 1

NT881 - NT885 1

NT901 - NT916 1

NT971 - NT985 1

NU031 - NU038 1

NU701 - NU705 1

NU721 - NU728 1

NU731 - NU732 1

2. Spares Affected

None.

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BOEING SERVICE BULLETIN 757-57-0070
B. Concurrent Requirements

None.

C. Reason

757 airplanes in service have drain holes and unsealed panel assemblies in the fixed leading edge

(LE) adjacent to the inboard end of slats 4 and 7 that are too close to the hot portion of the engines. A

design change adds a new drain hole at outboard slat station (OSS) 344.500 and seals ribs adjacent

to the new drain hole. Doing this change will create new drain paths to direct fluid drainage from the

adjacent track housings safely away from the hot portion of the engines. If not corrected, drainage path

too close to the hot portion of the engines could possibly result in fire in case of fuel leakage from the

slat track housings.

D. Description

This service bulletin provides instructions to makes changes to the lower fixed leading edge (LE) panel

assemblies, immediately outboard of the nacelles at slat 4 and slat 7, as follows:

1. Makes new reinforced drain hole at outboard slat station (OSS) 344.50.

2. Seals the ribs adjacent to the new drain hole.

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

Affected Maintenance Zones

Model Zone

757-200, 757-200CB, 757- 522, 622

200PF, 757-300

E. Compliance

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

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

service bulletin mandatory.

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

original issue date of this service bulletin.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

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BOEING SERVICE BULLETIN 757-57-0070
G. Manpower

The tables 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.

Work Package 1 - Left Wing - Slat No. 4

Task Number of Persons Task Hours Elapsed Hours

Remove panel as- 1 0.75 0.75

sembly

Figure 1 1 0.75 0.75

Clean Panel 1 0.25 0.25

Figure 2 1 1.00 1.00

Figure 3 1 0.75 0.75

Install panel assem- 1 0.75 0.75

bly

TOTAL FOR EACH AIRPLANE 4.25 4.25

Work Package 2 - Right Wing - Slat No. 7

Task Number of Persons Task Hours Elapsed Hours

Remove panel as- 1 0.75 0.75

sembly

Figure 4 1 0.75 0.75

Clean Panel 1 0.25 0.25

Figure 5 1 1.00 1.00

Figure 6 1 0.75 0.75

Install panel assem- 1 0.75 0.75

bly

TOTAL FOR EACH AIRPLANE 4.25 4.25

H. Weight and Balance Changes

None.

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BOEING SERVICE BULLETIN 757-57-0070
I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR 54530-289RS.

b. Standard Overhaul Practices Manual (SOPM) 20-50-10, 20-50-19.

c. 757 Aircraft Maintenance Manual (AMM) 06-44-00, 57-41-01.

d. Service Bulletin Index Document D624N001 Part 3.

2. Data supplied with this Service Bulletin

None.

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

Drawing Number Title

114N2202 Panel Assembly - Lower

OSS 333.00 - OSS 365.0 Outboard Wing Leading Edge.

110N3456 Sealant Installation - Leading Edge, Wing

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

757 Maintenance Manual 57-41

757 Illustrated Parts Catalog 57-41

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated 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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BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

Part Number/ Specification QTY Name Notes

BMS5-95 TYPE 1, CLASS B 1 Pt SEALANT (a) or (d)

(PRO-SEAL 870 B-1/2 OR B-2

optional)

NAS11490632J 2 WASHER

PRIMER, CORROSION RESIS- (b) or (d)

TANT

BMS10-79 TYPE 3, CLASS A, 1 Pt

GRADE A

BMS10-60 TYPE 1, CLASS A, 1 Pt PAINT, PROTECTIVE ENAMEL (b) or (d)

GRADE A

BMS5-45 CLASS B (PR-1776M 1 Pt SEALANT (a) or (d)

B-1/2 OR B-2 optional)

FREKOTE 710-NC 1 Pt PARTING AGENT (c) or (d)

(a) Can be purchased from: PRC-Desoto International, Incorporated CAGE:

Application Support Center - Los Angeles 83574

24811 Avenue Rockefeller

Valencia, CA. 91355-3468

(b) Can be purchased from: PRC-Desoto International, Incorporated. 85570

11601 United Street

Mojave, CA 93501

(c) Can be purchased from: The Dexter Corporation 1JB33

HYSOL Division

1 Dexter Drive,

Seabrook, New Hamshire 03874

(d) See the Qualified Product Lists at the end of the Boeing Material Specification (BMS) for

supplier data.

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BOEING SERVICE BULLETIN 757-57-0070
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

114N2202-XX 1 PANEL ASSEMBLY, LOWER 114N2202-27

114N2202-YY 1 PANEL ASSEMBLY, LOWER 114N2202-28

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 757-57-0070
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. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

5. 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 757 SRM, Chapter 51

– Torque limits to tighten nuts and bolts are in 757 SRM, Chapter 51

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

757 SRM, Chapter 51. Alternate fasteners are listed in 757 SRM Chapter 51 and

Boeing Drawing 65-88700.

7. 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.

8. 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.

9. The dashed letters "-XX" or "-YY" after a part number means any existing dashed

numbered part as removed from the airplane.

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BOEING SERVICE BULLETIN 757-57-0070
B. WORK INSTRUCTIONS

Work Package 1 - Left Wing - Slat Number 4 - Lower Fixed Leading Edge Panel Assembly Change

1. Remove and keep the lower fixed leading edge panel assembly 114N2202-XX. Refer to 757 AMM

57-41-01 as an accepted procedure.

2. Drill new drain hole and bond washer in accordance with FIGURE 1.

3. Clean lower fixed leading edge panel assembly 114N2202-27 and Ribs at OSS 343.2 and 345.8

and prepare for sealing. Refer to SOPM 20-50-19 as an accepted procedure.

4. Apply sealant to rib areas at OSS 343.2 and 345.8 as given in FIGURE 2. Refer to SOPM 20-50-19

as an accepted procedure.

5. Install the changed lower fixed leading edge panel assembly 114N2202-27. Refer to 757 AMM

57-41-01 as an accepted procedure.

NOTE: Make sure the sealant applied in FIGURE 2 is cured before installing the panel assembly.

6. Apply sealant to areas common to the lower fixed leading edge panel assembly and adjacent ribs

at OSS 343.2 in accordance with FIGURE 3. Refer to SOPM 20-50-19 as an accepted procedure.

a. Do not cover drain hole with sealant.

b. Do not cover drain path under rib at OSS 345.80 with sealant

7. Put the airplane back to a serviceable condition.

Work Package 2 - Right Wing - Slat Number 7 - Lower Fixed Leading Edge Panel Assembly

Change

1. Remove and keep the lower fixed leading edge panel assembly 114N2202-YY. Refer to 757 AMM

57-41-01 as an accepted procedure.

2. Drill new drain hole and bond washer in accordance with FIGURE 4.

3. Clean lower fixed leading edge panel assembly 114N2202-28 and Ribs at OSS 343.2 and 345.8

and prepare for sealing. Refer to SOPM 20-50-19 as an accepted procedure.

4. Apply sealant to rib areas at OSS 343.2 and 345.8 as given in FIGURE 5. Refer to SOPM 20-50-19

as an accepted procedure.

5. Install the changed lower fixed leading edge panel assembly 114N2202-28. Refer to 757 AMM

57-41-01 as an accepted procedure.

NOTE: Make sure the sealant applied in FIGURE 5 is cured before installing the panel assembly.

6. Apply sealant to areas common to the lower fixed leading edge panel assembly and adjacent ribs

at OSS 343.2 in accordance with FIGURE 6. Refer to SOPM 20-50-19 as an accepted procedure.

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BOEING SERVICE BULLETIN 757-57-0070
a. Do not cover drain hole with sealant.

b. Do not cover drain path under rib at OSS 345.80 with sealant

7. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 1: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO. 4

(SHEET 1 OF 2)

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22 of 35

BOEING SERVICE BULLETIN 757-57-0070
The step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

-XX is any dash part

number.

PANEL ASSEMBLY, 114N2202-XX 1

LOWER

1 Drill

Apply sealant on

faying surfaces between panel assembly and washer. (a)

BMS5-95 TYPE 1, -

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

2 Apply SEALANT

Bond washer to

panel assembly using BMS-95 Type 1,

class B.

3 Install (New) WASHER NAS11490632J 1

Fillet seal edges of

washer. (a)

BMS5-95 TYPE 1, -

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

4 Apply SEALANT

Touch up as required. Refer to

SOPM 20-44-04 as

an accepted procedure.

BMS10-79 TYPE 3, -

CLASS A, GRADE A

PRIMER, CORROSION

RESISTANT

5 Apply

Touch up as required. Refer to

SOPM 20-44-04 as

an accepted procedure.

BMS10-60 TYPE 1, -

CLASS A, GRADE A

PAINT, PROTECTIVE

ENAMEL

Apply

Part mark panel assembly as

114N2202-27. Refer

to SOPM 20-50-10

as an accepted procedure. (b)

PANEL ASSEMBLY, 114N2202-27 1

LOWER

6 Identify

Apply parting agent

to the lower fixed

L.E. panel assembly

at areas that require

fillet seal common to

the slat rib.

7 Apply PARTING AGENT FREKOTE 710-NC -

(a) Use as required.

(b) Location of part mark is optional, make sure you can see the part number after the panel assembly is installed.

FIGURE 1: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO. 4

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 2: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 4

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 2: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 4

(SHEET 2 OF 3)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: January 27, 2010

757-57-0070

25 of 35

BOEING SERVICE BULLETIN 757-57-0070
The step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

BMS5-95 TYPE 1, - (a) (c)

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

1 Apply SEALANT

Fillet seal in areas

as shown.

BMS5-45 CLASS B -

(PR-1776M B-1/2 OR

B-2 optional)

2 Apply SEALANT

BMS5-45 CLASS B - (b) (c)

(PR-1776M B-1/2 OR

B-2 optional)

3 Apply SEALANT

4 Make DRAIN PATH - - (d)

(a) Inject sealant into cavity from one side until sealant extrudes at the other end(s) of the cavity.

(b) Formed-in-place sealant-fill pocket with BMS 5-45 to form pool approximately as shown. Fill to 0.6 plus

0.4 minus 0.1 inch depth at lowest point, extend pool outboard and forward as shown. Fair and shape

surface to channel fluids toward drain. Smooth fillet edges of pool to structure.

(c) Make sure the sealant is flush in areas that mate with the removeable panel assembly and the sealant

will not interfere with the installation of the panel assembly.

(d) Make a drain path under the fixed leading edge rib at OSS 345.80 by making sure there is no sealant in

the space between rib and splice strap.

FIGURE 2: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 4

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 3: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 4

(SHEET 1 OF 2)

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757-57-0070

27 of 35

BOEING SERVICE BULLETIN 757-57-0070
he step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY numbers

shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Not shown in figure.

Remove and keep

522DB access cover. Refer to 757

AMM 06-44-00 as

an accepted procedure.

1 Remove / Keep ACCESS COVER 114N4078-24 1

Make sure parting

agent has been applied to the panel

assembly in areas

common to the ribs

for fillet seal.

2 Inspect PARTING AGENT FREKOTE 710-NC -

Fillet seal in areas

as shown.

BMS5-45 CLASS B -

(PR-1776M B-1/2 OR

B-2 optional)

3 Apply SEALANT

Not shown in figure.

Install kept 522DB

access cover. Refer

to 757 AMM 06-44-

00 as an accepted

procedure.

4 Install (Kept) ACCESS COVER 114N4078-24 1

FIGURE 3: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 4

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 4: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO. 7

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: January 27, 2010

757-57-0070

29 of 35

BOEING SERVICE BULLETIN 757-57-0070
The step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

-YY is any dash part

number.

PANEL ASSEMBLY, 114N2202-YY 1

LOWER

1 Drill

Apply sealant on

faying surfaces between panel assembly and washer. (a)

BMS5-95 TYPE 1, -

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

2 Apply SEALANT

Bond washer to

panel assembly using BMS-95 Type 1,

class B.

3 Install (New) WASHER NAS11490632J 1

Fillet seal edges of

washer. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS5-95 TYPE 1, -

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

4 Apply SEALANT

Touch up as required. Refer to

SOPM 20-44-04 as

an accepted procedure.

BMS10-79 TYPE 3, -

CLASS A, GRADE A

PRIMER, CORROSION

RESISTANT

5 Apply

Touch up as required. Refer to

SOPM 20-44-04 as

an accepted procedure.

BMS10-60 TYPE 1, -

CLASS A, GRADE A

PAINT, PROTECTIVE

ENAMEL

Apply

Mark panel assembly as 114N2202-28.

Refer to SOPM 20-

50-10 as an accepted procedure. (b)

PANEL ASSEMBLY, 114N2202-28 1

LOWER

6 Identify

Apply parting agent

to the lower fixed

L.E. panel assembly

at areas that require

fillet seal common to

the slat rib.

7 Apply PARTING AGENT FREKOTE 710-NC -

(a) Use as required.

(b) Location of part mark is optional, make sure you can see the part number after the panel assembly is installed.

FIGURE 4: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO. 7

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 5: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 7

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 5: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 7

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: January 27, 2010

757-57-0070

32 of 35

BOEING SERVICE BULLETIN 757-57-0070
The step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

BMS5-95 TYPE 1, - (a) (c)

CLASS B (PRO-SEAL

870 B-1/2 OR B-2 optional)

1 Apply SEALANT

Fillet seal in areas

as shown.

BMS5-45 CLASS B -

(PR-1776M B-1/2 OR

B-2 optional)

2 Apply SEALANT

BMS5-45 CLASS B - (b) (c)

(PR-1776M B-1/2 OR

B-2 optional)

3 Apply SEALANT

4 Make DRAIN PATH - - (d)

(a) Inject sealant into cavity from one side until sealant extrudes at the other end(s) of the cavity.

(b) Formed-in-place sealant-fill pocket with BMS5-45 to form pool approximately as shown. Fill to 0.6 plus

0.4 minus 0.1 inch depth at lowest point, extend pool outboard and forward as shown. Fair and shape

surface to channel fluids toward drain. Smooth fillet edges of pool to structure.

(c) Make sure the sealant is flush in areas that mate with the removeable panel assembly and the sealant

will not interfere with the installation of the panel assembly.

(d) Make a drain path under the fixed leading edge rib at OSS 345.80 by making sure there is no sealant in

the space between rib and splice strap.

FIGURE 5: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 7

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 757-57-0070
FIGURE 6: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 7

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: January 27, 2010

757-57-0070

34 of 35

BOEING SERVICE BULLETIN 757-57-0070
The step numbers shown below agree with the numbers show in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one side of the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Not shown in figure.

Remove and keep

622DB access cover. Refer to 757

AMM 06-44-00 as

an accepted procedure.

1 Remove / Keep ACCESS COVER 114N4078-24 1

Make sure parting

agent has been applied to the panel

assembly in areas

common to the ribs

for fillet seal.

2 Inspect PARTING AGENT FREKOTE 710-NC -

Fillet seal in areas

as shown.

BMS5-45 CLASS B -

(PR-1776M B-1/2 OR

B-2 optional)

3 Apply SEALANT

Not shown in figure.

Install kept 622DB

access cover. Refer

to 757 AMM 06-44-

00 as an accepted

procedure.

4 Install (Kept) ACCESS COVER 114N4078-24 1

FIGURE 6: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT

RIBS - SLAT NO. 7

(SHEET 2 OF 2)

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35 of 35

BOEING SERVICE BULLETIN 757-57-0070