May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 38 

### Commercial **Airplane Group**  

# 757 Service Bulletin

**Number: 757-54-0036** Date: May 14, 1998 Revision 1: July 31, 2006 ATA System: 5451 5741 **SUBJECT:** NACELLES/PYLONS - NACELLE STRUT - UPPER LINK REPLACEMENT - STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY POWERED AIRPLANES 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 1998 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise.**BLANK PAGE** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

BLANK PAGE**Table of Contents** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**Table of Contents** Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 16 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 16 4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 16 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: . . . . . . . . . . . . . . . . . . . . . . 18 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 19 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 FIGURE 1: ACCESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 FIGURE 2: DISCONNECT WIRE BUNDLES (ENGINE NO. 1 SIDE ONLY). . . . . . . . . . . . . . 25 FIGURE 3: REMOVAL AND MODIFICATION OF THE BRACKET ASSEMBLY. . . . . . . . . . . . 27 FIGURE 4: INSTALL THE BRACKET ASSEMBLY. . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY . . . . . . . . . . . . . . . . . . 31 FIGURE 6: REPLACE THE ELECTRICAL BRACKET (ENGINE NO. 1 SIDE ONLY) . . . . . . . . . 35 FIGURE 7: CUT THE GAP COVER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . 36 APPENDIX A: EXISTING PARTS ACCOUNTABILITY . . . . . . . . . . . . . . . . . . . . . . . . . 37**Table of Contents** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

BLANK PAGEMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 38 

### Commercial **Airplane Group**  

# 757 Service Bulletin

**Number: 757-54-0036** 

### Revision Transmittal Sheet Date: May 14, 1998 Revision 1: July 31, 2006 ATA System: 5451 5741 **SUBJECT:** NACELLES/PYLONS - NACELLE STRUT - UPPER LINK REPLACEMENT - STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY POWERED AIRPLANES
This Revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Airworthiness Directive 2003-18-05 is related to this service bulletin. No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. **REASON FOR REVISION** This revision is sent to do the following: — Add airplane NA001 to the effectivity — In Figure 5, correct the number of rivets installed in the circle note table — In Figure 5, clarify which hole to measure from to locate the coverplate Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** Original Issue: May 14, 1998 Revision 1: July 31, 2006May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

BLANK PAGEMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 38 

### Commercial **Airplane Group**  

# 757 Service Bulletin

**Number: 757-54-0036** 

### Summary Date: May 14, 1998 Revision 1: July 31, 2006 ATA System: 5451 5741 **SUBJECT:** NACELLES/PYLONS - NACELLE STRUT - UPPER LINK REPLACEMENT - STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY POWERED AIRPLANES

**CONCURRENT REQUIREMENTS**
None **BACKGROUND** The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires incorporation of this service bulletin. The structural changes given in this service bulletin will increase the strength and durability of the upper link installation. The increase in the strength and durability will give the structural component the damage tolerance rating necessary for continued operations without special inspections and/or scheduled component replacement. A structural reassessment and a review of the structural inspection planning data (SIPD) document were completed for the 757 airplane. Data from flight tests, fatigue tests, and in-service experience were used to complete the reassessment and review. The flight test data included the results from tests on the 747, 757, and 767 airplanes and found the operational loads of the nacelle were higher than those used during the initial design. With consideration given to the higher loads, analysis of the fatigue test data shows that fatigue cracks can occur before the structure gets to the design life goal for the 757 airplane. Also, the higher loads can cause the length of a crack to increase at a much faster rate than initially shown for the strut structure. The structural integrity of the upper link is an important component in the damage tolerance criteria for the wing to strut. Boeing has no reports of cracks at this time. As a result of the structural reassessment and review of the SIPD document, components of the strut and wing were identified for design changes. As part of a service bulletin validation program, this change was completed on airplane NC024 before the release of Revision 00. (Airplane NC024 has the configuration of a Group 1 airplane.) **NOTE:** The related service bulletin is 757-54-0034. **ACTION** (PRR 54687-1R) Hold the engine and strut. Remove access panels. Disconnect the duct leak detector in the leading edge. Disconnect wire bundles for Engine Number 1. Remove the wire support bracket attached to the Upper Link. Remove and discard the Upper Link.May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

Make a change to the wire support bracket attached to the Upper Link. Make a change to the leading edge of the gap cover installation and replace an electrical bracket on the gap cover installation. Replace the Upper Link. Install the wire support brackets, and the access panels. Remove the support from the engine and strut. Do the test of the duct leak detector. Put the airplane back in a serviceable condition. **EFFECTIVITY** See Paragraph 1.A., Effectivity **COMPLIANCE** Boeing recommends Group 1 (passenger) airplanes do the change no later than 27,000 flight cycles and Group 2 (freighter) airplanes do the change no later than 29,000 flight cycles **INDUSTRY SUPPORT INFORMATION** Boeing Industry Support information is provided in Program Letter 6-1151-757/767PGM-120 to be released May 30, 1998. Additional copies of program letters are available from Boeing Product Assurance Contracts. **MANPOWER** Total Man-hours - 45 for each engine Elapsed Time - 22.5 Hours **MATERIAL INFORMATION** Boeing Supplied Kits Refer to Paragraph 2.A., Material - Price and Availability.May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

FWD THE GAP COVER DOUBLER ON INSTALL A

THE BRACKETS MODIFICATIONS TO UPPER LINK. MAKE REMOVE AND REPLACER91110May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

BLANK PAGEMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 38 

### Commercial **Airplane Group**  

# 757 Service Bulletin

**Number: 757-54-0036** Date: May 14, 1998 Revision 1: July 31, 2006 ATA System: 5451 5741 **SUBJECT:** NACELLES/PYLONS - NACELLE STRUT - UPPER LINK REPLACEMENT - STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY POWERED AIRPLANES

**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624N001, Part 3 for Airplane Variable Number, Line Number, and Serial Number data.. This service bulletin is for the airplanes shown below. Refer to PRR54687-1R for data about this change

Airplane models: 757-200 757-200PF IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AEROMEXICO (AMX) 1 NC068 NC070–NC071 NE301 AIR ITALY (RIT) 1 NE162–NE164 AMERICAN AIRLINES (AAL) 1 NC075–NC076 ASTRAEUS, LTD. (AUA) 1 NC052 NC067 BOEING (TBC) 1 NA001 **GROUP CONFIGURATION DESCRIPTION** 1 - 757 Passenger Airplanes 2 - 757 Freighter AirplanesMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

CONDOR (CDF) 1 NE166 DELTA AIR LINES (DAL) 1 NA501–NA586 NB001–NB004 EOS AIRLINES, INC. (EPX) 1 NC056 NC072–NC073 ETHIOPIAN AIRLINES (ETH) 1 NE201–NE204 2 NC951 FAR EASTERN AIR TRANSPORT (FAT) 1 NC051 NE302 FISCHER AIR POLAND (FSP) 1 NB167 NC057 MEXICANA (CMA) 1 NE161 NORTHWEST AIRLINES (NWA) 1 NC001–NC033 NE311–NE325 ROYAL AIR MAROC (RAM) 1 NC041–NC042 SAUDI ROYAL FLIGHT (SRF) 1 NB168 SHANGHAI AIRLINES (SHA) 1 NE001–NE007 SUNEXPRESS (SNS) 1 NC066 NC069 TACV-CABO VERDE AIRLINES (TCV) 1 NC074 UNITED AIRLINES (UAL) 1 NE011–NE088 NE092–NE094 NE141–NE150 UPS (UPS) 2 NC901–NC935 UZBEKISTAN AIRWAYS (UZB) 1 NC151 VIM AVIA (VIM) 1 NE165 NE167–NE177May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

IDENTIFICATION BY VARIABLE NUMBER

2. Spares Affected Examine your spares supply for the parts or components identified in Appendix A, Existing Parts Accountability. If any parts or components are found, refer to Appendix A, Existing Parts Accountability. **B. Concurrent Requirements**
None **C. Reason** The Federal Aviation Administration (FAA) has issued an Airworthiness Directive (AD) which requires incorporation of this service bulletin. The structural changes given in this service bulletin will increase the strength and durability of the upper link installation. The increase in the strength and durability will give the structural component the damage tolerance rating necessary for continued operations without special inspections and/or scheduled component replacement. **Variable Group** NA001 1 NA501–NA586 1 NB001–NB004 1 NB166–NB168 1 NC001–NC033 1 NC041–NC042 1 NC051–NC052 1 NC056–NC057 1 NC066–NC076 1 NC151 1 NC901–NC935 2 NC951 2 NE001–NE007 1 NE011–NE088 1 NE091–NE094 1 NE141–NE150 1 NE161–NE177 1 NE201–NE204 1 NE301–NE302 1 NE311–NE325 1May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

A structural reassessment and a review of the structural inspection planning data (SIPD) document were completed for the 757 airplane. Data from flight tests, fatigue tests, and in-service experience were used to complete the reassessment and review. The flight test data included the results from tests on the 747, 757, and 767 airplanes and found the operational loads of the nacelle were higher than those used during the initial design. With consideration given to the higher loads, analysis of the fatigue test data shows that fatigue cracks can occur before the structure gets to the design life goal for the 757 airplane. Also, the higher loads can cause the length of a crack to increase at a much faster rate than initially shown for the strut structure. The structural integrity of the upper link is an important component in the damage tolerance criteria for the wing to strut. Boeing has no reports of cracks at this time. As a result of the structural reassessment and review of the SIPD document, components of the strut and wing were identified for design changes. As part of a service bulletin validation program, this change was completed on airplane NC024 before the release of Revision 00. (Airplane NC024 has the configuration of a Group 1 airplane.) **NOTE:** 1. The related Service Bulletin is 757-54-0034. 2. Because of common access, this is a convinient time to do the modifications in the area of the upper link shown in service bulletins 757-54-0026 and 757-54-0027. This revision is sent to do the following: — Add airplane NA001 to the effectivity — In Figure 5, correct the number of rivets installed in the circle note table — In Figure 5, clarify which hole to measure from to locate the coverplate **D. Description** The airplane effectivity is divided in 2 groups. Group 1 are passenger airplanes, Group 2 are Package Freighter airplanes. Hold the engine and strut. Remove access panels. Disconnect the duct leak detector in the leading edge. Disconnect wire bundles for Engine Number 1. Remove the wire support bracket attached to the Upper Link. Remove and discard the Upper Link. Make a change to the wire support bracket attached to the Upper Link. Make a change to the leading edge of the gap cover installation and replace an electrical bracket on the gap cover installation. Replace the Upper Link. Install the wire support brackets, and the access panels. Remove the support from the engine and strut. Do the test of the duct leak detector. Put the airplane back in a serviceable condition. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. **E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive 2003-18-05 is related to this service bulletin.May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

Boeing recommends Group 1 airplanes incorporate the change no later than 27,000 flight cycles, and Group 2 airplanes incorporate the change no later than 29,000 flight cycles. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable Federal Aviation Regulations (FAR) and are FAA approved. This service bulletin and the FAA approval were based on the airplane in its original Boeing delivery configuration or as modified by other FAA approved Boeing changes. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the modification defined in this service bulletin as an alternative method of compliance to the modification requirements of paragraph (b), (d), and (g) of AD 2003-18- 05 for Boeing Service Bulletin 757-54-0036 only. All provisions of AD 2003-18-05 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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. **G. Manpower** Approximately 90 man-hours and 4 persons are 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 man-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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. **H. Weight and Balance Changes**

**I. Electrical Load Data** Not changed **J. References** 1. Existing Data: a. Engineering Change Memo PRR 54687-1R b. Boeing Program Letter 6-1151-757/767-120 **Airplane Change in Weight (Pounds) Change in Moment (Pound-Inches)** Group 1 (Passenger) +53.1 +51,507 Group 2 (Package Freighter) +39.9 +38,703May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

c. 757 Maintenance Manual (AMM) Subject 26-18-01/400, 54-51-02/400, 71-00-00/200 d. 757 Structural Repair Manual (SRM) Subject 51-70-16 e. Boeing Standard Wiring Practices Manual (BSWPM) 20-10-11, 20-10-12 f. Boeing Standard Overhaul Practices Manual (BSOPM) 20-50-11 g. Boeing Service Bulletin 757-54-0026, "Nacelles/Pylons - Strut - Mid Spar Bushing, Strut Fitting Bushing, and Wing Fitting Bushing Inspection and Replacement." h. Boeing Service Bulletin 757-54-0027, "Nacelles/Pylons - Pylon Attach Pins/Bolts - Diagonal Brace Fuse Pins and Upper link Fuse Pins - Inspection and Replacement". i. Boeing Service Bulletin 757-54-0034, "Nacelles/Pylons - Pratt and Whitney PW2000 Powered Airplanes - Nacelle Strut and Wing Structure Improvement". j. FAA Airworthiness Directive 2003-18-05. 2. Data supplied with this Service Bulletin:
None 3. Installation Drawings Used in the Preparation of this Service Bulletin:

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.
4. Process Data: None **K. Publications Affected**

**L. Interchangeability and Intermixability of Parts** Refer to Appendix A, Existing Parts Accountability, for interchangeability and intermixability information. **Drawing Number Title** 114N1801 Gap Cover Installation, Wing, Leading Edge 311N3050 Strut Installation - PW2000 Engines 313N3004 Fairing Underwing Installation - Strut, PW2000 316N3190 Bracket Installation - System Support Strut to Wing

**Publication Chapter-Section** 757 Structural Repair Manual 54-51 757 Illustrated Parts Catalog 54-51, 54-52, 57-41 Component Maintenance Manual 54-50May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing supplies the kits, at no charge, shown in Paragraph 2.C., Parts Necessary For Each Airplane. See Boeing Program Letter 6-1151-757/767PGM-120. Supply data can be given if requested. Send purchase orders and letters about the supply data to the Director of Spares and refer to this service bulletin number. **B. Industry Support Information** Boeing Industry Support information is provided in Program Letter (6-1151-757/767PGM-120). Additional copies of program letters are available from Boeing Product Assurance Contracts. **C. Parts Necessary For Each Airplane** 1. Kits/Parts: To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.A.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.
**012N8042- TOP KIT - 757 STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY -64 -63 -62 -61 -45 -44**  **Quantity Part Number/**  **Specification Name**  . . . . . - 012N8042-44 Top Kit, Upper Link - Passenger . . . . - . 012N8042-45 Top Kit, Upper Link - Package Freighter . . . - . 1 012N8042-61 Subkit, Upper Link . . - . . 1 012N8042-62 Subkit, Upper Link . - . . 1 . 012N8042-63 Subkit, Upper Link - . . . 1 . 012N8042-64 Subkit, Upper Link . . 1 1 . . 311N3710-11 Upper Link 1 1 . . . . 311N3710-9 Upper Link . 1 . 1 . . 313N3210-33 Cover Panel 1 . 1 . . . 313N3210-34 Cover Panel . 1 . 1 . . 313N3210-35 Doubler 1 . 1 . . . 313N3210-36 Doubler . . 4 4 . . 316N3191-31 Pad 4 4 . . . . 316N3191-32 Pad 51 51 51 51 . . BACR15BA5D6 Rivet . 3 . 3 . . BACR15FT6D3 Rivet - Blind . 3 . 3 . . BACR15FT7D4 Rivet - Blind 4 . . . . . NAS1802-3-8 ScrewMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

2. Parts and Materials Supplied by the Operator:

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified: Refer to Appendix A, Existing Parts Accountability. 4. Parts Removed and Not Replaced: Refer to Appendix A, Existing Parts Accountability. **D. Parts Necessary to Change Spares**
None . 2 . . . . NAS1802-3-9 Screw . 1 . 1 . . 312N5855U8 Bracket (a) The kit has more parts than are necessary for installation. Discard parts that are not used or keep the parts for spares.

**Quantity Part Number (Specification) Name** As necessary - Alodine As necessary BMS 10-11, Type I Primer As necessary BMS 5-95 Sealant As necessary RTV 174 (a), (b) Adhesives (a) Optional: RTV 102 RTV 108 RTV 157 General Electric Company (V 01139) - Silicon Products Business Dept. Hudson River Road Waterford, New York 12188 (b) Optional: DC Q3-7063 DC 1200 RTV Prime Coat Red or Clear Dow Corning (V 71984) 3901 S. Saginaw Road Midland, Michigan 48641-2721 **012N8042- TOP KIT - 757 STRUT IMPROVEMENT PROGRAM - PRATT AND WHITNEY -64 -63 -62 -61 -45 -44**  **Quantity Part Number/**  **Specification Name** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**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.May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

BLANK PAGEMay 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch — Angular tolerance is plus or minus 2 degrees — Hole dimensions for standard solid rivets are given in 757 Structural Repair Manual, Chapter 51 — Torque limits to tighten nuts and bolts are given in 757 Structural Repair Manual, Chapter 51. 4. For approved fastener and process material substitutions, refer to 757 Structural Repair Manual, Chapter 51, Alternate fasteners are given in 757 Structural Repair Manual Chapter 51 and Boeing Drawing 65-88700. 5. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the wire installation procedures. 6. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. **B. WORK INSTRUCTIONS** 1. Get access to the Upper Link. Do the "Prepare to Remove the Fuse Pins" up to removal of the underwing fairings shown in 757 AMM 54-51-02/400 or operators equivalent procedure. 2. Remove the gap cover installation and disconnect wires as shown in Figure 1. 3. Continue to do the "Prepare to Remove the Fuse Pins" shown in 757 AMM 54-51-02/400 or operators equivalent procedure. 4. Engine No. 1 side only: Detach wire bundles as shown in Figure 2. 5. Remove and make a change to the Bracket Assembly on the Upper Link as shown in Figure 3.May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

6. Remove and keep the Fuse Pins, bolts and related parts for the Upper Link as shown in 757 AMM 54-51-02/400. 7. Remove and discard the Upper Link. 8. Group 1: Install the new Upper Link, 311N3710-11. Install the kept Fuse Pins, bolts and related parts as shown in 757 AMM 54-51-02/400 or operators equivalent procedure, or Service Bulletin 757-54-0027. 9. Group 2: Install the new Upper Link, 311N3710-9. Install the kept Fuse Pins, bolts and related parts as shown in 757 AMM 54-51-02/400 or operators equivalent procedure, or Service Bulletin 757-54-0027. 10. Install the Bracket Assembly as shown in Figure 4. 11. Engine No. 1 side only: Install the wire bundles on the Bracket Assemblies in the same locations they were removed from. Use clamps and fasteners removed previous. Refer to Figure 2. 12. Make a change to the strut panel assembly as shown in Figure 5. 13. Engine No. 1 side only: Replace an electrical bracket on the gap cover installation as shown in Figure 6. 14. Cut the leading edge of the gap cover installation to match the strut cover plate as shown in Figure 7. 15. Close access as shown in 757 AMM 54-51-02/400 or operators equivalent procedure. Do the steps in "Put the Airplane Back To It's Usual Condition" up to "Install the applicable access panel, 511KT or, 611KT. 16. Install the gap cover installation and wires removed in Figure 1. 17. Continue to do the "Put the Airplane Back To It's Usual Condition" shown in 757 AMM 54-51-02/ 400 or operators equivalent procedure. 18. Do an operational check of Engine No. 1. Refer to 757 AMM 71-00-00/200 or operators equivalent procedure. 19. Do the test of Detector Installation as shown in 757 AMM 26-18-01/400 or operators equivalent procedure. 20. Restore the airplane to a servicable condition.**FIGURE 1: ACCESS** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 1: ACCESS**

A

A

FWD 2 WIRE BUNDLE

DETECTOR DUCT LEAK 1 1 DETECTOR DUCT LEAK (TYPICAL) GAP COVER INSTALLATION 3

MOUNTING CLAMP (TYPICAL) 

### A-A LOOP DUCT LEAK DETECTOR DETECTOR



### LEFT SIDE SHOWN RIGHT SIDE OPPOSITER91713

**(SHEET 1 OF 2) FIGURE 1: ACCESS**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**STEP TASK NAME QTY NOTES** 1 Disconnect Duct Leak Detector 2 Refer to AMM 26-18-01/400. Disconnect the Duct Leak Detector. Minimum bend radius is 1 inch. 2 Remove/ Keep Fastener Engine No. 1 side: Quantity 4 Engine No. 2 side: Quantity 3 Detach Wire Bundle 1 Detach wire bundle from clamps 3 Remove/ Keep Gap Cover Installation 1 Fastener -

**(SHEET 2 OF 2) FIGURE 2: DISCONNECT WIRE BUNDLES (ENGINE NO. 1 SIDE ONLY)**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 2: DISCONNECT WIRE BUNDLES (ENGINE NO. 1 SIDE ONLY)** 

FWD 5 2 CLAMP (12 LOCATIONS)

CLAMP 1 TYPICAL

3 4 WIRE BUNDLE

5 WIRE BUNDLE



### LEFT SIDE ONLYR92286

**(SHEET 1 OF 2) FIGURE 2: DISCONNECT WIRE**  **BUNDLES (ENGINE NO. 1 SIDE ONLY)** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**STEP TASK NAME QTY NOTES** 1 Record Location - Record the locations of the wire bundles and clamps 2 Remove/ Keep Fastener 12 Disconnect Clamp 12 3 Remove/ Keep Clamp - Remove as necessary 4 Move Wire Bundle 2 Move the Wire Bundles to the inboard side of the Upper Link. 5 Disconnect Wire Bundle 2 Put Cap 7 Put caps on the connectors

**(SHEET 2 OF 2) FIGURE 3: REMOVAL AND MODIFICATION OF THE BRACKET ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 3: REMOVAL AND MODIFICATION OF THE BRACKET ASSEMBLY**

UPPER LINK

DO NOT REMOVE CLARITY) (EXPLODED FOR PAD BRACKET ASSEMBLY (2 LOCATIONS) SPACER (2 LOCATIONS) CLAMP

(2 LOCATIONS) SCREW

PAD UPPER LINK



### LEFT SIDE 1 2

1 2 SPACER

BRACKET ASSEMBLY SCREW (2 LOCATIONS)

SCREW (2 LOCATIONS) 

### RIGHT SIDER92685

**(SHEET 1 OF 2) FIGURE 3: REMOVAL AND MODIFICATION OF THE BRACKET ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**STEP TASK NAME QTY NOTES** 1 Remove/ Keep Bracket Assembly 2 Make a note of the location of the bracket on the Upper Link (a) Screw - 2 Remove/ Discard Spacer 4 Group 2 only (a) Group 1: Remove/Keep Group 2: Remove/Discard

**(SHEET 2 OF 2) FIGURE 4: INSTALL THE BRACKET ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 4: INSTALL THE BRACKET ASSEMBLY**

UPPER LINK

(4 LOCATIONS) PAD B

B

A SCREW (2 LOCATIONS) 1

1 (4 LOCATIONS) PAD ASSEMBLY BRACKET 2 UPPER LINK 2



### LEFT SIDE CLAMP (2 LOCATIONS)

(2 LOCATIONS) SCREW (2 LOCATIONS) SCREW

ASSEMBLY BRACKET

EXPLODED FOR CLARITY



### RIGHT SIDER94275

**(SHEET 1 OF 2) FIGURE 4: INSTALL THE BRACKET ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener.

**STEP TASK NAME PART NUMBER QTY NOTES** 1 Apply Adhesive RTV 174 - (a) Install Pad Group 1: 316N3191-31 8 Group 2: 316N3191-32 8 2 Install Bracket (kept) 2 Install the bracket in the same location on the new Upper Link as the old bracket was to the old Upper Link. (a) Optional: RTV 102, RTV 108, RTV 157, DC Q3-7063, or DC 1200 RTV Prime Coat Red or Clear

**CODE NAME PART NUMBER NOTES** A Screw NAS1802-3-9 Engine No. 1 side B Screw NAS1802-3-8 Engine No. 2 side

**(SHEET 2 OF 2) FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY**

(ONE LOCATION) FASTENER HOLE EXISTING 8/64TH

1

1 12.75 13.25

PANEL ASSEMBLY FWD 

### LEFT SIDE SHOWN RIGHT SIDE OPPOSITE

PANEL ASSEMBLY 1.96 3 COVER PLATE 2

3R92956

**(SHEET 1 OF 4) FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

PANEL 3 PANEL 2 6 5

PANEL ASSEMBLY 8 9 DOUBLER 7 9 TRIM AREA



### PANEL ASSEMBLY ROTATED 180 DEGREES (UPSIDE DOWN ON BENCH) PANEL ASSEMBLY

(UPSIDE DOWN ON BENCH) 

### PANEL ASSEMBLY ROTATED 180 DEGREES 48 LOCATIONS COVER PLATE DOUBLER 4R93047

**(SHEET 2 OF 4) FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

STRUT PANEL ASSEMBLY A A

10 10 10 10

DOUBLER SEALANT 12

COVER PLATE

DOUBLER PANEL ASSEMBLY SEALANT

(46 LOCATIONS) RIVET PANEL ASSEMBLY

COVER PLATE



### A-A DOUBLER

SEALANT 11

SEALANT 11 PANEL ASSEMBLYR94478

**(SHEET 3 OF 4) FIGURE 5: MODIFICATION OF THE STRUT PANEL ASSEMBLY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **STEP TASK NAME PART NUMBER QTY NOTES** Panel 1: 1 Mark Middle Point 1 Measure the distance from the center of the first fastener hole to the middle point between the specified fasteners. 2 Put Cover Plate 313N3210-33,-34 opposite 1 Put the doubler on the panel assembly. 3 Drill Hole - 2 0.159 to 0.171 inch diameter. Keep a minimum 2D edge margin for the fasteners. Panel 2: 4 Put Doubler 313N3210-35, -36 opposite 1 Put the doubler on the panel assembly. 5 Drill Hole - 46 0.159 to 0.171 inch diameter. Keep a minimum 2D edge margin, and a 4D to 6D distance between fasteners. Countersi nk Hole - 46 100 degree countersink the cover plate 6 Remove Cover Plate - 1 Deburr Hole - 46 Panel 3: 7 Mark Panel Assembly - - Mark to match the hole in the doubler. 8 Remove Doubler - 1 Deburr Hole - 46 9 Cut Panel Assembly - 1 Cut the panel assembly to match the hole in the doubler. Refer to 757 SRM 51-70-16. Panel 4: 10 Apply Sealant BMS 5-95 - Install Cover Plate 313N3210-33, -34 opposite 1 Refer to 757 SRM 51-70-16. Doubler 313N3210-35, -36 opposite 1
Rivet BACR15BA5D6 46 11 Apply Sealant BMS 5-95 - Fillet Seal 12 Apply Sealant BMS 5-95 - Aerosmooth as shown in BSOPM 20-50-11. Apply to the inboard, outboard and forward sides of the cover plate.

**(SHEET 4 OF 4) FIGURE 6: REPLACE THE ELECTRICAL BRACKET (ENGINE NO. 1 SIDE ONLY)**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**FIGURE 6: REPLACE THE ELECTRICAL BRACKET (ENGINE NO. 1 SIDE ONLY)**

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**STEP TASK NAME PART NUMBER QTY NOTES** 1 Remove/ Keep Clamp - 1
2 Remove Bracket - 1 3 Drill Bracket 312N5855U8 3 Drill to match old bracket. Align the top of the old and new brackets. 4 Apply Sealant BMS 5-95 - Install Bracket - 1 Fastener (a) 3 5 Install Clamp (kept) - 1 (a) Install BACR15FT6D3 or BACR15FT7D4 as necessary to fit existing hole. 2 GAP COVER INSTALLATION

BRACKET 2 3 4 2 4 FASTENER

1 5 CLAMPR93146

**(SHEET 1 OF 1) FIGURE 7: CUT THE GAP COVER INSTALLATION**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

**FIGURE 7: CUT THE GAP COVER INSTALLATION**

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

**STEP TASK NAME PART NUMBER QTY NOTES** 1 Put Gap Cover - 1 Put the Gap Cover in position on the strut panel assembly 2 Mark Gap Cover - 1 3 Mark Gap Cover - 2 4 Cut Gap Cover - 1 5 Apply Alodine - - Primer BMS 10-11 Type I - 2 layers A A

5.50 5.50
PLATE COVER

2 0.20 0.30 (TYPICAL) 0.50 R MIN



### A-A STRUT 1 GAP COVER

0.20 2 5 4

2 LOCATIONS 3 ASSEMBLY GAP COVERR93185

**(SHEET 1 OF 1) APPENDIX A: EXISTING PARTS ACCOUNTABILITY**  May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 38 

### BOEING SERVICE BU **LLETIN 757-54-0036**

**APPENDIX A: EXISTING PARTS ACCOUNTABILITY** The parts shown below are changed as shown in this service bulletin. The Quantity is the number of parts changed on each airplane. Components or subassembly parts are indented. The Quantity of the indented part is the number of parts used on the next higher assembly. **Existing Part Number RUC Name QTY New Part Number PNC RC** 311N3710-( ) (a) DIS Upper Link Assembly 2 311N3710-11 R,S A 311N3710-3 (b) DIS Upper Link Assembly 2 311N3710-9 R,S A 114N1804 -( ) RWK Nose Panel 1 114N1804-39, -40 Opposite N,S A 313N3004-( ) RWK Fairing Underwing 1 313N3004-141A, - 142A Opposite S A .313N3210-( ) RWK Panel Assembly 1 313N3210-31, -32 Opposite S A 316N3190-1 (a) RWK Bracket Installation 1 316N3190-5 S A .316N3191-18 RWK Bracket 1 316N3191-23 R,S A ..316N3191-7 DIS Pad 2 316N3191-31 R,S A .316N3191-20 RWK Bracket 2 316N3191-25 R,S A ..316N3191-7 DIS Pad 1 316N3191-31 R,S A 316N3190-2 (a) RWK Bracket Installation 1 316N3190-6 S A .316N3191-8 RWK Bracket 1 316N3191-24 R,S A ..316N3191-7 DIS Pad 2 316N3191-31 R,S A .316N3191-9 RWK Bracket 2 316N3191-26 R,S A ..316N3191-7 DIS Pad 1 316N3191-31 R,S A 316N3190-3 (b) RWK Bracket Installation 1 316N3190-7 S A .316N3191-18 RWK Bracket 1 316N3191-27 R,S A ..316N3191-7 DIS Pad 2 316N3191-32 R,S A .316N3191-20 RWK Bracket 2 316N3191-29 R,S A ..316N3191-7 DIS Pad 1 316N3191-32 R,S A .316N3191-21 DIS Spacer 2 - - B .NAS1802-3-15 DIS Screw 2 NAS1802-3-9 R,S A 316N3190-4 (b) RWK Bracket Installation 1 316N3190-8 S A .316N3191-8 RWK Bracket 1 316N3191-28 R,S A ..316N3191-7 DIS Pad 2 316N3191-32 R,S A .316N3191-9 RWK Bracket 2 316N3191-30 R,S A ..316N3191-7 DIS Pad 1 316N3191-32 R,S A .316N3191-22 DIS Spacer 2 - - B .NAS1802-3-14 DIS Screw 2 NAS1802-3-8 R,S A BACR15BA5D5 (a,b) DIS Rivet 48 BACR15BA5D6 R,S A (a) Group 1 (b) Group 2**APPENDIX A: EXISTING PARTS ACCOUNTABILITY** May 14, 1998 Revision 1: July 31, 2006 757-54-0036 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 38 

### BOEING SERVICE BULLETIN 757-54-0036

**RUC Recommended Use Code** DIS - Discard the part. - Keep the part if there are other uses for it. RWK - Make the change given in this service bulletin.
**PNC Part Number Code** N - There is no equivalent Boeing part number for the changed part. Identify on the part that the change given in this service bulletin was made. R - This is the part number after the change given in this service bulletin. S - This is the part number for the new equivalent or replacement part. - To get a new part, use this part number in your order. - This is the part number after the change given in this service bulletin. - This part is used in production. **RC Replacement Code** A - Do not use the existing part to replace the new or changed part. B - This part is removed from the airplane. This part has no replacement.