### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 1 of 35 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 2 of 35 **BOEING SERVICE BULLETIN 757-57-0070**

BLANK PAGE**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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 3 of 35 **BOEING SERVICE BULLETIN 757-57-0070**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 4 of 35 **BOEING SERVICE BULLETIN 757-57-0070**

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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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 5 of 35**INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the changes given in this service bulletin. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  8.50 8.50 757
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 6 of 35 **BOEING SERVICE BULLETIN 757-57-0070**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 7 of 35 **BOEING SERVICE BULLETIN 757-57-0070**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 8 of 35 **BOEING SERVICE BULLETIN 757-57-0070**

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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.
**DESCRIPTION CONFIGURATION**  **GROUP** Drain Path Change - Inboard end of slat No. 4 and slat No. 7.

- 1

Airplane Models: 757-200, 757-200CB, 757-200PF, 757-300 **Group Variable Number**  1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 9 of 35**Group Variable Number**  1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 10 of 35 **BOEING SERVICE BULLETIN 757-57-0070 Group**  **Variable Number** 1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 11 of 35 **BOEING SERVICE BULLETIN 757-57-0070 Group**  **Variable Number** 1 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 2. Spares Affected None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 12 of 35 **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 Zone**  **Model** 522, 622 757-200, 757-200CB, 757- 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 13 of 35 **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 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.75 0.75 1 Remove panel as- sembly 0.75 0.75 1 Figure 1 0.25 0.25 1 Clean Panel 1.00 1.00 1 Figure 2 0.75 0.75 1 Figure 3 0.75 0.75 1 Install panel assem- bly 4.25 4.25 TOTAL FOR EACH AIRPLANE **Work Package 2 - Right Wing - Slat No. 7 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.75 0.75 1 Remove panel as- sembly 0.75 0.75 1 Figure 4 0.25 0.25 1 Clean Panel 1.00 1.00 1 Figure 5 0.75 0.75 1 Figure 6 0.75 0.75 1 Install panel assem- bly 4.25 4.25 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 14 of 35 **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
**Title Drawing Number**  Panel Assembly - Lower 114N2202 OSS 333.00 - OSS 365.0 Outboard Wing Leading Edge. Sealant Installation - Leading Edge, Wing 110N3456 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: **Chapter-Section Publication**  57-41 757 Maintenance Manual 57-41 757 Illustrated Parts Catalog 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 15 of 35 **BOEING SERVICE BULLETIN 757-57-0070**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 16 of 35 **BOEING SERVICE BULLETIN 757-57-0070**

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
**Notes Name**  **QTY Part Number/ Specification**  (a) or (d) SEALANT 1 Pt BMS5-95 TYPE 1, CLASS B (PRO-SEAL 870 B-1/2 OR B-2 optional) WASHER 2 NAS11490632J (b) or (d) PRIMER, CORROSION RESIS- TANT 1 Pt BMS10-79 TYPE 3, CLASS A, GRADE A (b) or (d) PAINT, PROTECTIVE ENAMEL 1 Pt BMS10-60 TYPE 1, CLASS A, GRADE A (a) or (d) SEALANT 1 Pt BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) (c) or (d) PARTING AGENT 1 Pt FREKOTE 710-NC
CAGE: PRC-Desoto International, Incorporated Can be purchased from: (a) 83574 Application Support Center - Los Angeles 24811 Avenue Rockefeller Valencia, CA. 91355-3468 85570 PRC-Desoto International, Incorporated. Can be purchased from: (b) 11601 United Street Mojave, CA 93501 1JB33 The Dexter Corporation Can be purchased from: (c) 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 17 of 35 **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.
**Notes New Part Number**  **Name QTY**  **Existing Part Number**  114N2202-27 PANEL ASSEMBLY, LOWER 1 114N2202-XX 114N2202-28 PANEL ASSEMBLY, LOWER 1 114N2202-YY

4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 18 of 35 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 19 of 35 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 20 of 35 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 21 of 35 **BOEING SERVICE BULLETIN 757-57-0070 FIGURE 1: BENCH WORK - LOWER FIXED LEADING EDGE PANEL ASSEMBLY CHANGE - SLAT NO. 4**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  -XX is any dash part number. 1 114N2202-XX PANEL ASSEMBLY, LOWER Drill 1 Apply sealant onfaying surfaces between panel assembly and washer. (a) - BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 2

Bond washer topanel assembly using BMS-95 Type 1, class B. 1 NAS11490632J WASHER Install (New) 3

Fillet seal edges of washer. (a) - BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 4

Touch up as required. Refer to SOPM 20-44-04 asan accepted procedure. - BMS10-79 TYPE 3, CLASS A, GRADE A PRIMER, CORROSION RESISTANT Apply 5

Touch up as required. Refer to SOPM 20-44-04 asan accepted procedure. - BMS10-60 TYPE 1, CLASS A, GRADE A PAINT, PROTECTIVE ENAMEL Apply

Part mark panel assembly as 114N2202-27. Refer to SOPM 20-50-10as an accepted procedure. (b) 1 114N2202-27 PANEL ASSEMBLY, LOWER Identify 6

Apply parting agent to the lower fixed L.E. panel assembly at areas that require fillet seal common to the slat rib. - FREKOTE 710-NC PARTING AGENT Apply 7

(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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 23 of 35 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 24 of 35 **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)** 

BOEING PROPRIETARY - 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (c)

- BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 1

Fillet seal in areas as shown. - BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 2

(b) (c)

- BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 3

(d)

- - DRAIN PATH Make 4 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 26 of 35 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Not shown in figure. Remove and keep522DB access cover. Refer to 757 AMM 06-44-00 asan accepted procedure. 1 114N4078-24 ACCESS COVER Remove / Keep 1

Make sure partingagent has been applied to the panel assembly in areas common to the ribs for fillet seal. - FREKOTE 710-NC PARTING AGENT Inspect 2

Fillet seal in areas as shown. - BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 3

Not shown in figure. Install kept 522DB access cover. Refer to 757 AMM 06-44- 00 as an accepted procedure. 1 114N4078-24 ACCESS COVER Install (Kept) 4

**FIGURE 3: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT RIBS - SLAT NO. 4**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 28 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  -YY is any dash part number. 1 114N2202-YY PANEL ASSEMBLY, LOWER Drill 1 Apply sealant onfaying surfaces between panel assembly and washer. (a) - BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 2

Bond washer topanel assembly using BMS-95 Type 1, class B. 1 NAS11490632J WASHER Install (New) 3

Fillet seal edges of washer. Refer to SOPM 20-50-19 asan accepted procedure. - BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 4

Touch up as required. Refer to SOPM 20-44-04 asan accepted procedure. - BMS10-79 TYPE 3, CLASS A, GRADE A PRIMER, CORROSION RESISTANT Apply 5

Touch up as required. Refer to SOPM 20-44-04 asan 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) 1 114N2202-28 PANEL ASSEMBLY, LOWER Identify 6

Apply parting agent to the lower fixed L.E. panel assembly at areas that require fillet seal common to the slat rib. - FREKOTE 710-NC PARTING AGENT Apply 7

(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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 30 of 35 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 31 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (c)

- BMS5-95 TYPE 1, CLASS B (PRO-SEAL870 B-1/2 OR B-2 optional) SEALANT Apply 1

Fillet seal in areas as shown. - BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 2

(b) (c)

- BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 3

(d)

- - DRAIN PATH Make 4 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 33 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Not shown in figure. Remove and keep622DB access cover. Refer to 757 AMM 06-44-00 asan accepted procedure. 1 114N4078-24 ACCESS COVER Remove / Keep 1

Make sure partingagent has been applied to the panel assembly in areas common to the ribs for fillet seal. - FREKOTE 710-NC PARTING AGENT Inspect 2

Fillet seal in areas as shown. - BMS5-45 CLASS B (PR-1776M B-1/2 OR B-2 optional) SEALANT Apply 3

Not shown in figure. Install kept 622DB access cover. Refer to 757 AMM 06-44- 00 as an accepted procedure. 1 114N4078-24 ACCESS COVER Install (Kept) 4

**FIGURE 6: SEALANT INSTALLATION - LOWER FIXED LEADING EDGE PANEL ASSEMBLY AND ADJACENT RIBS - SLAT NO. 7**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 27, 2010 757-57-0070 35 of 35 **BOEING SERVICE BULLETIN 757-57-0070**