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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 38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Unpublished Work - All Rights Reserved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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 38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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 38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 BULLETIN 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 PAGE
May 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, 2006
 

May 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 PAGE
May 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 BULLETIN 757-54-0036

FWD

THE GAP COVER

DOUBLER ON

INSTALL A

THE BRACKETS

MODIFICATIONS TO

UPPER LINK. MAKE

REMOVE AND REPLACE

R91110
 

May 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 PAGE
May 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 Airplanes
 

May 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–NE177
 

May 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 BULLETIN 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 1
 

May 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 BULLETIN 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 +38,703
 

May 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 54-50
 

May 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 BULLETIN 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 Screw
 

May 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 BULLETIN 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 PAGE
 

May 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 BULLETIN 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 BULLETIN 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 OPPOSITE

R91713

(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 BULLETIN 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 ONLY

R92286

(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 BULLETIN 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 SIDE

R92685

(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 BULLETIN 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 SIDE

R94275

(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 BULLETIN 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

2 COVER PLATE

3

R92956

(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

5 6

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

4 DOUBLER

R93047

(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 BULLETIN 757-54-0036

STRUT PANEL ASSEMBLY

A

A

10

10

10

10

DOUBLER

12 SEALANT

COVER PLATE

DOUBLER

PANEL ASSEMBLY

SEALANT

(46 LOCATIONS)

RIVET

PANEL ASSEMBLY

COVER PLATE

A-A

DOUBLER

11 SEALANT

11 SEALANT

PANEL ASSEMBLY

R94478

(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 BULLETIN 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 CLAMP

R93146

(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

2 0.20

4 5

2 LOCATIONS

3

ASSEMBLY

GAP COVER

R93185

(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 BULLETIN 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.