July 23, 1998

Revision 4 July 07, 2005 767-31-0091

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 51

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-31-0091

Date: July 23, 1998

Revision 4 July 07, 2005

ATA System: 3141

SUBJECT: INDICATING/RECORDING SYSTEMS - Central Computers - Engine Indication And 

Crew Alerting System - EICAS Computer Replacement And Wire Change - GE FADEC 

Engines

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Unpublished Work - All Rights Reserved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, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, DC-8, DC-9, 

DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue 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.
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 Table of Contents

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BOEING SERVICE BULLETIN 767-31-0091

Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

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

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

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

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

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

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

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

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

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: . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 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: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

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: EICAS COMPUTER REMOVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE . . . . . . . . . . . . . . . . . . . 30

FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES . . . . . . . . . . . . . . . . . . . . 34

FIGURE 4: GROUP 1, 3 AIRPLANES - W1037 WIRE CHANGES. . . . . . . . . . . . . . . . . . . 38

FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES . . . . . . . . . . . . . . . . . . . . 41

FIGURE 6: AIRPLANES VF251, VL895-VL900, VR201, VW701-VW721 - W2000 WIRE CHANGES . 45

FIGURE 7: EICAS COMPUTER S242N701-1001 CONNECTOR KEYING CHANGE . . . . . . . . . 46

FIGURE 8: EICAS COMPUTER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

APPENDIX A: OPC PART NUMBER BY CUSTOMER EFFECTIVITY . . . . . . . . . . . . . . . . 48

APPENDIX B: SERVICE BULLETIN GROUP TO PROGRAM PINS - LEFT EICAS COMPUTER . . 50

APPENDIX C: SERVICE BULLETIN GROUP TO PROGRAM PINS - RIGHT EICAS COMPUTER. . 51
 Table of Contents

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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-31-0091 Revision Transmittal Sheet

Date: July 23, 1998

Revision 4 July 07, 2005

ATA System: 3141

SUBJECT: INDICATING/RECORDING SYSTEMS - Central Computers - Engine Indication And 

Crew Alerting System - EICAS Computer Replacement And Wire Change - GE FADEC 

Engines

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive (AD) 96-07-09, paragraph (d)(2) is related to this 

service bulletin.

No more work is necessary on airplanes changed as shown in the initial release or in Revision 2-3 of this service 

bulletin. This revision adds a new Group 3 effectivity (Airplanes VF181-VF184) in the service bulletin.

REASON FOR REVISION

This revision is sent to add a new Group 3 effectivity (Airplanes VF181-VF184) in the service bulletin.

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 Release: July 23, 1998

Revision 1: February 4, 1999

Revision 2: February 24, 2000

Revision 3: April 27, 2000

Revision 4: July 7, 2005
 

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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-31-0091 Summary

Date: July 23, 1998

Revision 4 July 07, 2005

ATA System: 3141

SUBJECT: INDICATING/RECORDING SYSTEMS - Central Computers - Engine Indication And 

Crew Alerting System - EICAS Computer Replacement And Wire Change - GE FADEC 

Engines

CONCURRENT REQUIREMENTS

None

BACKGROUND

This service bulletin gives instructions to replace the two Engine Indication and Crew Alerting System (EICAS) 

computers. The new computers allow loadable Operational Program Software (OPS) and Operational Program 

Configuration (OPC) software installation via a portable data loader (PDL) or an airborne data loader (ADL).

The new EICAS computers allow the use of OPC software to change the configuration of options selected by 

the customer. Loadable OPC software eliminates the requirement to change program pin wiring to make 

customer options.

The new EICAS computers have increased capacity, support optional Future Air Navigation System (FANS) 

features, comply with Amendment No. 121-266 [Docket No. 28109], "Revisions to Digital Flight Data Recorder 

Rules", and in combination with the appropriate Airplane Flight Manual (AFM) revision to Section 3.2, in 

accordance with Airworthiness Directive (AD) 96-07-09 paragraph (d)(2), will provide terminating action for the 

fuel filter bypass AD 96-07-09.

The related Rockwell/Collins Service Bulletins are EAP-701E-31-AT or EAP-701G-31-AV.

Boeing Service Letter 767-SL-31-036A is related to this service bulletin. 

ACTION (PRR B12710, PRR B13451-R)

In the E8 rack, replace the left and right EICAS computers. Make wire changes in the E8 shelf. Change left 

and right EICAS computer connector keying on the E-8 shelf. Load OPC software into both left and right EICAS 

computers. Do an operational test of the EICAS computers.

EFFECTIVITY

All 767 airplanes line positions 165-686, 688, 691, 693, 694 with General Electric (GE) CF6-80C2 Full Authority 

Digital Electronic Engine Control (FADEC) engines.

The effectivity is broken up into three major groups for convenience of wire changes.
 

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BOEING SERVICE BULLETIN 767-31-0091

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive 96-07-09, Amendment 39-9558, is related to this 

service bulletin.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Total Man-hours - 13.0 for each airplane

Elapsed Time - 6.5 Hours

The change to the EICAS computers as given in the Rockwell/Collins service bulletins are not included.

MATERIAL INFORMATION

Operator Supplied Parts

REPLACE LEFT AND RIGHT

EICAS COMPUTERS IN E8 RACK

MAIN EQUIPMENT CENTER

EICAS SHELF WIRES

MAKE CHANGES TO

FWD

S34301
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Commercial

Airplane

Group 767

Service Bulletin

Number: 767-31-0091

Date: July 23, 1998

Revision 4 July 07, 2005

ATA System: 3141

SUBJECT: INDICATING/RECORDING SYSTEMS - Central Computers - Engine Indication And 

Crew Alerting System - EICAS Computer Replacement And Wire Change - GE FADEC 

Engines

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent 

production airplanes. Refer to PRR B12710 and PRR B13451-R for data about this change.

Airplane models:

767-200 767-300 767-300F

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AIR ALGERIE (ALG)

1 VK131–VK133

AIR CANADA (ACN)

1 VN057–VN062 VN751–VN752 VN811–VN812

AIR EUROPA (ARE)

1 VN421

AIR FRANCE (AFA)

1 VN634

AIR HORIZONS (AHZ)

1 VK142

GROUP CONFIGURATION DESCRIPTION

1 - Wiring changes are different from other groups.

2 - Wiring changes are different from other groups.

3 - Wiring changes are different from other groups.
 

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AIR MADAGASCAR (MAD)

1 VN731

AIR NEW ZEALAND (ANZ)

1 VN657–VN658

AIR SEYCHELLES (ASY)

1 VL941

ALITALIA (ALI)

1 VL701–VL702 VN422–VN427 VN732 VN813

ALL NIPPON AIRWAYS (ANA)

1 VK090–VK113 VN193–VN198 VR401

ASIANA AIRLINES (AAR)

1 VK141 VK143–VK148 VN636 VR426

2 VW851

BLUE PANORAMA AIRLINES (BPA)

1 VL911

BRITANNIA AIRWAYS (BRI)

1 VB331–VB332 VL912–VL914 VS051

DELTA AIR LINES (DAL)

1 VL753

EVA AIR (EVA)

1 VB441–VB444 VN471–VN472 VN791–VN792

FIRST CHOICE AIRWAYS (ATZ)

1 VL751 VN921

ITOCHU CORPORATION (CIT)

3 VF181–VF184

JAL INTERNATIONAL (JAL)

1 VK012–VK016 VK181 VK186 VR461

KENYA AIRWAYS (KEN)

1 VN546–VN547

KLM - ROYAL DUTCH AIRLINES (KLM)

1 VL891–VL900

LAN AIRLINES (LAN)

1 VL703 VN063–VN064 VN753 VN968–VN970

VS111

MALEV HUNGARIAN AIRLINES (HGA)

1 VF171–VF172
 

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MID EAST JET (SKL)

1 VF251

MYTRAVEL AIRWAYS (GUE)

1 VN951–VN953

NORTH AMERICAN AIRLINES (NNA)

1 VL755 VN922

PLUNA (PLU)

1 VN436

ROYAL BRUNEI AIRLINES (RBA)

1 VN637–VN638

THE SULTAN'S FLIGHT (BWN)

1 VF180

TUI AIRLINES BELGIUM (TLB)

1 VN234

UPS (UPS)

2 VR201 VW701–VW721

VARIG AIRLINES (VAR)

1 VN055–VN056 VN231–VN233

VIETNAM AIRLINES (VIE)

1 VL752 VL754

ZOOM AIRLINES (YFM)

1 VN635

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

VB331–VB332 1

VB441–VB444 1

VF171–VF172 1

VF180 1

VF181–VF184 3

VF251 1

VK012–VK016 1

VK090–VK113 1

VK131–VK133 1

VK141–VK148 1

VK181 1

VK186 1
 

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2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts 

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for 

the recommended use.

B. Concurrent Requirements

None

VL701–VL703 1

VL751–VL755 1

VL891–VL900 1

VL911–VL914 1

VL941 1

VN055–VN064 1

VN193–VN198 1

VN231–VN234 1

VN421–VN427 1

VN436 1

VN471–VN472 1

VN546–VN547 1

VN634–VN638 1

VN657–VN658 1

VN731–VN732 1

VN751–VN753 1

VN791–VN792 1

VN811–VN813 1

VN921–VN922 1

VN951–VN953 1

VN968–VN970 1

VR201 2

VR401 1

VR426 1

VR461 1

VS051 1

VS111 1

VW701–VW721 2

VW851 2

Variable Group
 

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C. Reason

This service bulletin gives instructions to replace the two Engine Indication and Crew Alerting System 

(EICAS) computers. The new computers allow loadable Operational Program Software (OPS) and 

Operational Program Configuration (OPC) software installation via a portable data loader (PDL) or an 

airborne data loader (ADL).

The new EICAS computers allow the use of OPC software to change the configuration of options 

selected by the customer. Loadable OPC software eliminates the requirement to change program pin 

wiring to make customer options.

The new EICAS computers have increased capacity, support optional Future Air Navigation System 

(FANS) features, comply with Amendment No. 121-266 [Docket No. 28109], "Revisions to Digital 

Flight Data Recorder Rules", and in combination with the appropriate Airplane Flight Manual (AFM) 

revision to Section 3.2, in accordance with Airworthiness Directive (AD) 96-07-09 paragraph (d)(2), 

will provide terminating action for the fuel filter bypass AD 96-07-09.

The related Rockwell/Collins Service Bulletins are EAP-701E-31-AT or EAP-701G-31-AV.

Boeing Service Letter 767-SL-31-036A is related to this service bulletin.

Revision 1 is sent to make changes to the EICAS functional test and the Parts Necessary for Each 

Airplane section 2.C.

Revision 2 is sent to make changes to the OPC software part numbers and diskette set part numbers 

in Appendix A for operators AFA, HGA and SKL only.

Revision 3 is sent to make changes to the OPC software part number and diskette set part number in 

Appendix A for only one airplane (VN198) owned by operator ANA. A production master change was 

accepted by ANA and resulted in an out of date data for VN198 in Appendix A of this service bulletin.

Revision 4 is sent to add a new Group 3 effectivity (Airplanes VF181-VF184) in the service bulletin.

D. Description

In the E8 rack, replace the left and right EICAS computers. Make wire changes in the E8 shelf. 

Change left and right EICAS computer connector keying on the E-8 shelf. Load OPC software into 

both left and right EICAS computers. Do an operational test of the EICAS computers.

Note: Some service bulletins with EICAS program pin changes are not usable after this change is 

done. Operators must contact Boeing for the OPC diskette that accomplishes the equivalent 

of those program pin changes.

Revision 1 - More work is necessary on airplanes changed as shown in the initial release of this 

service bulletin. The EICAS functional test was changed with the addition of two new steps on page 

14 and to show the correct circuit breaker name, location and numbers on pages 12, 13 and 14.

Revision 2 - No more work is necessary on all airplanes except AFA airplanes VN634-VN635, HGA 

airplanes VF171-VF172 and SKL airplane VF251 changed as shown in the initial release or in 

Revision 1 of this service bulletin. OPC software part numbers and diskette set part numbers for AFA 

and HGA airplanes were changed in Appendix A . OPC software part number and diskette set part 

numbers were added in Appendix A for SKL airplane VF251. 
 

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Revision 3 - No more work is necessary on airplanes changed as shown in the initial release or in 

Revision 2 of this service bulletin. OPC software part number and diskette set part number were 

changed in Appendix A for one ANA owned airplane. A production master change was accepted by 

ANA and resulted in an out of date data for VN198 in Appendix A of this service bulletin.

Revision 4 - No more work is necessary on airplanes changed as shown in the initial release or in 

Revision 2-3 of this service bulletin. This revision adds a new Group 3 effectivity (Airplanes VF181-

VF184) in the service bulletin.

The changes in this service bulletin will change the Engine Indication and Crew Alerting System 

(EICAS). 

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive 96-07-09, Amendment 39-9558, is 

related to 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.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle 

Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service 

bulletin as an alternative method of compliance to the requirements of paragraph (d), (1) of AD 96-07-

09. All provisions of AD 96-07-09 that are not specifically referenced in the above statement remain 

fully applicable and must be complied with.

G. Manpower

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

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

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

lost time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts
 

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— Time to find the tools.

The change to the EICAS computers as given in Collins Service Bulletins EAP-701E-31-AT and EAP701G-31-AV are not included.

H. Weight and Balance Changes

None

I. Electrical Load Data

Not changed

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12710, PRR B13451-R

b. 767 Maintenance Manual (AMM) Subjects 20-41-01, 24-22-00, 31-41-02, 31-41-02/201

c. 767 Wiring Diagrams 31-41-15, 31-41-18, 31-51-33

d. Boeing Standard Wiring Practices Manual (BSWPM) 20-10-11, 20-10-12, 20-10-14, 20-10-

19, 20-30-11, 20-71-14, 20-90-11

e. Collins Service Bulletins EAP-701E-31-AT, EAP-701G-31-AV*

f. Boeing Service Letter 767-SL-31-036A, dated August 21, 1998.

g. FAA Airworthiness Directive 96-07-09, Amendment 39-9558

h. Amendment No. 121-266 [Docket No. 28109], Revisions to Digital Flight Data Recorder 

Rules

* The supplier was told to send copies of the service bulletin to each operator.

2. Data supplied with this Service Bulletin:

None.

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 1.5 0.75

Change 2 7.0 3.5

Close Access 2 1.5 0.75

Test 2 3.0 1.5

TOTAL FOR EACH AIRPLANE 13.0 6.5
 

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

None.

K. Publications Affected

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.E., Existing Parts Accountability, for interchangeability and intermixability 

information.

Publication Chapter-Section

767 FAA Approved Airplane Flight Manual *

767 Operations Manual Chapter 21

767 Maintenance Manual 23-21, 23-42, 23-43, 23-46, 31-41, 32-09, 

and 32-61

767 Wiring Diagram Manual Equipment List

767 Fault Reporting Manual 32-09

767 Illustrated Parts Catalog 31-41

767 Ramp Maintenance Manual 31-03, 31-04 and 31-05

* This change affects Section 3.2 of the FAA Approved Airplane Flight Manual. Operators will 

receive applicable data.
 

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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 and Paragraph 2.D., Parts Necessary to Change Spares. As an alternative, operators can 

purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and 

supply data. 

Refer to Collins Service Bulletins EAP-701E-31-AT or EAP-701G-31-AV. The OPC diskette can be 

ordered through Boeing Spares.

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.
 

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2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

Part Number / 

Specification QTY Name Existing Part Number Notes

S242N701-1001 2 EICAS computer S242N701-70X (Collins part 

number 622-9152-10X)

(a) (g) (i) (j)

S242N701-901 (Collins part 

number 822-0801-100)

(a) (h) (i) (j)

BMS 13-54, Type 3, 

Class 1

30 

Feet

Lacing Tape, White (b) (c)

RT876 (k) 10 

feet

Heat Shrink Sleeve, 1/8 

inch diameter

(d) (k)

M39029/11-145 6 Terminal Block Contact (b)

BMS 13-48, Type 10, 

Class 1, AWG 22

5 feet Wire (b)

242T7001-2XXX 1 OPC diskette (e)

831-4565-100 1 OPS diskette (f)

(a) Get EICAS computers S242N701-1001 from S242N701-70X (Collins Part Number 622-9152-

10X) or S242N701-901 (Collins Part Number 822-0801-100). See Collins Service Bulletins EAP701E-31-AT or EAP-701G-31-AV to get the new EICAS computers or contact Collins at the address 

given below.

Rockwell Collins Incorporated (V4V792)

Air Transport Division

400 Collins Road N.E

Cedar Rapids, Iowa 52498

Phone (319) 295-5000

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

data.

(c) . Gudebrod Incorporated (V82110)

Griffith Towers PO Box 357

Pottstown, PA 19464-5568

(d) .Raychem Corporation (V06090)

300 Constitution Drive

Menlo Park, CA 94025-1111

(e) Refer to Appendix A in this service bulletin for the applicable part number of the OPC diskette. 

(f) Refer to (a) above for manufacturer and address.

(g) Make the change given in Collins Service Bulletin EAP-701E-31-AT.

(h) Make the change given in Collins Service Bulletin EAP-701G-31-AV.

(i) This is the part number for the new equivalent or replacement part.

To get a new part, use this part number in your order.

(j) Do not use the existing part to replace the new or changed part.

(k) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01 are 

acceptable.
 

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See Paragraph 2.C.2., Parts and Materials Supplied by the Operator.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

See the Collins Service Bulletins EAP-701E-31-AT or EAP-701G-31-AV to change spare EICAS 

computers. Get OPC software from Boeing Spares organization.

E. Special Tooling - Price and Availability

None

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BLANK PAGE
 

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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: ELECTRICAL SHOCK HAZARD. THE CONNECTION AND REMOVAL OF THE

PORTABLE DATA LOADER (PDL) INTERFACE CABLE CAN CAUSE AN

ELECTRICAL SHOCK. DAMAGE TO PEOPLE AND EQUIPMENT CAN OCCUR.

MAKE SURE THAT THE EICAS COMPUTER CIRCUIT BREAKERS SPECIFIED IN

STEPS 2, 12, AND 22 ARE OPEN BEFORE THE PDL INTERFACE CABLE IS

CONNECTED OR REMOVED.

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. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the 

wire installation procedures and 20-10-19 for wire separation.

4. Some service bulletins with EICAS program pin changes are not usable after this change 

is done. Operators must contact Boeing for the OPC diskette that accomplishes the 

equivalent of those program pin changes.

5. The Accomplishment Instructions are divided into two parts as follows:

— Part I - Instructions to compare the EICAS readouts to those given in Appendix A are 

given. These instructions will make sure the applicable software is used for this 

change.

— Part II - Instructions to replace the EICAS computers, make wire changes and load 

the new software are given.

B. WORK INSTRUCTIONS

Group 1-2: PART I - EICAS READOUT COMPARISON

1. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "L".

2. On the P61 panel, press the EICAS MAINT Panel "CONF/MCDP" button.

3. Compare the "PROG PINS" and "SUPL PINS" readouts displayed on the lower EICAS display 

with the LEFT PROG PINS and SUPL PINS information in Appendix A for the applicable 

effectivity. If the EICAS readouts do not agree with those given in Appendix A, supply the PROG 

PINS and SUPL PINS data to the Boeing Company to get the correct OPC software part number.
 

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4. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "AUTO".

PART II - SOFTWARE LOADABLE EICAS COMPUTER CHANGE

1. Remove the electrical power from the airplane circuits as given in 767 AMM Subject 24-22-00. 

Attach DO-NOT-CLOSE tags to opened circuit breakers and DO-NOT-OPERATE tags to 

applicable switches. Use an independent power source for lighting.

2. Gain access to the E8 shelf in the main equipment center.

3. Remove the left and right EICAS computers as shown in Figure 1.

4. Group 1, 3: Make W1035 wire changes as shown in Figure 2.

5. Group 2: Make W1035 wire changes as shown in Figure 3.

6. Group 1, 3: Make W1037 wire changes as shown in Figure 4.

7. Group 2: Make W1037 wire changes as shown in Figure 5.

8. On airplanes VF251, VL895-VL900, VR201 and VW701-VW721, make W2000 wire changes as 

shown in Figure 6.

9. On the E8 shelf, make changes to the left and right EICAS computer connector keying as shown 

in Figure 7.

10. Install the new left and right EICAS computers as shown in Figure 8.

11. Remove DO-NOT-CLOSE tags from circuit breakers and DO-NOT-OPERATE tags from 

switches installed in Step A. Supply the electrical power to the airplane circuits as given in 767 

AMM 24-22-00.

12. Install the OPC software for the left and right EICAS computers. Refer to Appendix A in this 

service bulletin and the instructions below. Load the left EICAS computer first. Load the right 

EICAS computer second.

a. Make sure that the PDL ON/OFF switch is in the OFF position. 

b. Open the circuit breakers shown below:

c. Set the airplane parking brake. 

d. Connect the Portable Data Loader (PDL) interface cable to the ARINC 615 connector on the 

front face of the left EICAS computer (M10181).

Circuit Breaker Name Panel Location

C4078 EICAS CMPTR L P11-2 J02

C4079 EICAS CMPTR R P11-5 J29
 

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e. Close the circuit breakers shown below:

f. Obtain the applicable EICAS OPC software part number diskette for the airplane effectivity. 

Refer to Appendix A. 

g. Close the circuit breaker shown below:

h. Put the PDL ON/OFF switch in the ON position. Make sure that the PDL is powered.

i. Install the OPC diskette into the PDL and follow the normal data load procedures given by 

the PDL supplier.

j. Make sure that the data loader indicates that the load is in progress.

Note: The load process can take one to two minutes to begin.

k. After three to four minutes, make sure that the Data Loader indicates that the load is 

complete. Put the ON/OFF switch on the PDL in the OFF position.

l. Open the circuit breaker shown below:

m. Remove the PDL interface cable from the left EICAS computer

Install the connector dust cover to the front face of the left EICAS computer.

n. Connect the PDL interface cable to the ARINC 615 connector on the front face of the right 

EICAS computer (M10182). 

o. Make sure that the circuit breakers shown below are closed:

Circuit Breaker Name Panel Location

C1170 LANDING GEAR AIR/GND SYS 2 P11-6 U23 or U24

C1175 LDG GEAR POS SYS 1 P11-4 C30

C1179 PARKING BRAKE VLV P6-1 F4

C1182 LANDING GEAR AIR/GND SYS 1 P11-3 U15

Circuit Breaker Name Panel Location

C4078 EICAS CMPTR L P11-2 J02

Circuit Breaker Name Panel Location

C4078 EICAS CMPTR L P11-2 J02

Circuit Breaker Name Panel Location

C1170 LANDING GEAR AIR/GND SYS 2 P11-6 U23 or U24

C1175 LDG GEAR POS SYS 1 P11-4 C30

C1179 PARKING BRAKE VLV P6-1 F4

C1182 LANDING GEAR AIR/GND SYS 1 P11-3 U15
 

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p. Make sure that the airplane parking brake is set.

q. Close the circuit breaker shown below:

r. Put the PDL ON/OFF switch in the ON position. Make sure that the PDL is powered.

s. Install the OPC diskette into the PDL and follow the normal data load procedures given by 

the PDL supplier.

t. Make sure that the data loader indicates that the load is in progress.

Note: The load process can take one to two minutes to begin.

u. After three to four minutes, make sure that the Data Loader indicates that the load is 

complete. Put the ON/OFF switch on the PDL in the OFF position.

v. Open the circuit breaker shown below:

w. Remove the PDL interface cable from the right EICAS computer. Install the connector dust 

cover to the front face of the right EICAS computer.

13. Do this test:

a. Make sure that the circuit breakers shown below are closed:

Circuit Breaker Name Panel Location

C4079 EICAS CMPTR R P11-5 J29

Circuit Breaker Name Panel Location

C4079 EICAS CMPTR R P11-5 J29

Circuit Breaker Name Panel Location

C1182 LANDING GEAR AIR/GND SYS 1 P11-3 U15

C1170 LANDING GEAR AIR/GND SYS 2 P11-6 U23 OR 

U24

C1175 LDG GEAR POS SYS 1 P11-4 C30

C4078 EICAS COMPTR-L P11-2 J2

C4079 EICAS COMPTR-R P11-5 J29

C4081 EICAS UPPER DSPL P11-2 J3

C4082 EICAS LOWER DSPL P11-5 J30

C4094 EICAS DSPL SELECT P11-5 J32

C4189 EICAS DSPL SW P11-5 J31

C0565 WARN ELEX-A P11-5 J34

C0566 WARN ELEX-B P11-1 B18

C0567 AURAL WARN SPKR L P11-1 B16

C0568 AURAL WARN SPKR R P11-5 H35

C1179 PARKING BRAKE VLV P6-1 F4
 

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b. Make sure that the airplane parking brake is set and that the L and R EEC's are powered.

c. On the P61 panel, turn the left and right EEC ground test switches to "ON".

d. Make sure that the STANDBY ENGINE INDICATOR is powered and the front panel switch 

is in "AUTO".

e. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "L".

f. On the P61 panel, press the EICAS MAINT Panel "TEST" button.

g. Make sure that each event shown below occurs:

(1) On the P7 panel, the Master CAUTION lighted switches illuminate.

(2) An "OWL" aural and "SIREN" aural occur at the same time.

(3) On the P1 panel, the standby engine indicator displays for L and R EGT are not 

blanked.

(4) The test format is displayed on each EICAS display unit with "LEFT EICAS 

COMPUTER" at the top of the screen.

(5) "TEST IN PROGRESS" is displayed for approximately 5 seconds. The message is 

then replaced by the message "SELF TEST COMPLETE".

(6) Make sure "NO INTERFACE FAULTS" is displayed at the upper left corner of test 

page.

(7) Make sure "NO INTERNAL FAULTS" is displayed at the upper left corner of test page.

Note: If "Program Pin Error" is displayed, compare the program pin codes displayed 

on the test page to those given in Appendix B. If the PROG PINS code display 

is not the same, it is necessary to examine the wiring. The changes made on 

the airplane must be the same as given in the applicable wiring changes shown.

h. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "R".

i. Make sure that each item given below is displayed on the EICAS upper and lower displays.

(1) The test format is displayed on each EICAS display unit with "RIGHT EICAS 

COMPUTER" at the top of the screen. 

(2) The message "SELF TEST COMPLETE" is displayed at the upper left corner of the test 

page.

(3) "NO INTERFACE FAULTS" is displayed at the upper left corner of the test page.

(4) "NO INTERNAL FAULTS" is displayed at the upper left corner of the test page.

Note: If "Program Pin Error" is displayed, compare the program pin codes displayed 

on the test page to those given in Appendix C. If the PROG PINS code display 

is not the same, it is necessary to examine the wiring. The changes made on 
 

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the airplane must be the same as given in the applicable wiring changes shown. 

j. PRESS either Master CAUTION/WARNING lighted switch on the P7 panel.

k. Make sure that both Master CAUTION lights on the P7 panel are off.

l. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "L".

m. On the P61 panel, press and release the EICAS MAINT Panel "TEST" button.

n. Make sure that the PRIMARY engine format is displayed on the Upper display and 

SECONDARY engine format is displayed on the Lower display.

o. On the P61 panel, press the EICAS MAINT Panel "CONF/MCDP" button.

p. Make sure that the EICAS CONFIGURATION on the CONF/MCDP maintenance page 

reads as follows:

(1) H/W P/N S242N701-1001

(2) OPS P/N 3172-COL-DE0-01 

Note: If the OPS part number readout is not the same as this part number, it is 

necessary to load the OPS software again. Refer to 767 AMM 31-41-02 or your 

own procedure. The OPS diskette is available, if necessary, from Rockwell 

Collins. 

(3) OPC P/N (31XX-BCG-006-XX)

Note: See Appendix A for the applicable OPC P/N. If the OPC part number display is 

not the same as the part number given in Appendix A, it is necessary to load the 

EICAS computer with the correct software. The procedure is given in these 

Accomplishment Instructions.

(4) PROG PINS (XXXX)

Note: See Appendix B for the applicable PROG PINS. If the PROG PINS code display 

is not the same as the code given in Appendix B, it is necessary to examine the 

wiring. The changes made on the airplane must be the same as given in the 

applicable wiring changes. 

q. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "R".

r. Make sure that the EICAS CONFIGURATION is as follows:

(1) H/W P/N S242N701-1001

(2) OPS P/N 3172-COL-DE0-01 

Note: If the OPS part number readout is not the same as this part number, it is 

necessary to load the OPS software again. Refer to 767 AMM 31-41-02 or your 

own procedure. The OPS diskette is available, if necessary, from Rockwell 

Collins. 
 

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(3) OPC P/N (31XX-BCG-006-XX)

Note: See Appendix A for the applicable OPC P/N. If the OPC part number display is 

not the same as the part number given in Appendix A, it is necessary to load the 

EICAS computer with the correct software. The procedure is given in these 

Accomplishment Instructions. 

(4) PROG PINS (XXXX) 

Note:See Appendix C for the applicable PROG PINS. If the PROG PINS code 

display is not the same as the code given in Appendix C, it is necessary to examine 

the wiring. The changes made on the airplane must be the same as given in the 

applicable wiring changes shown. 

s. On the P9 panel, press the EICAS DSP "ENGINE" button.

t. Make sure that the EICAS ALERT messages shown below are NOT displayed on the upper 

EICAS display:

— EICAS DISPLAY

— EICAS CONT PNL

u. On the P9 panel, press the EICAS DSP "STATUS" button.

v. Make sure that the EICAS status messages shown below are NOT displayed on the lower 

EICAS display:

— L EICAS CMPTR

— R EICAS CMPTR

— EICAS DISAGREE

— EICAS SOFTWARE

Note: If an "EICAS SOFTWARE" message is displayed, there is a disagree between the left 

and the right EICAS software versions. Check the OPC and OPS software part 

numbers for the left and right EICAS computers on the CONF/MCDP page and reload 

the software accordingly.

w. On the P61 panel, press the EICAS MAINT Panel "ECS/MSG" button.

x. Make sure that the message "EICAS BITE" is NOT displayed on the lower EICAS indicator.

y. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "L".

z. Make sure that the EICAS ALERT messages shown below are NOT displayed on the upper 

EICAS display:

— EICAS DISPLAY

— EICAS CONT PNL

aa. On the P9 panel, press the EICAS DSP "STATUS" button.

ab. Make sure that the EICAS status messages shown below are NOT displayed on the lower 

EICAS display:

— L EICAS CMPTR

— R EICAS CMPTR

— EICAS DISAGREE
 

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— EICAS SOFTWARE

Note: If an "EICAS SOFTWARE" message is displayed, there is a disagree between the left 

and the right EICAS software versions. Check the OPC and OPS software part 

numbers for the left and right EICAS computers on the CONF/MCDP page and reload 

the software accordingly.

ac. On the P61 panel, press the EICAS MAINT Panel "ECS/MSG" button.

ad. Make sure that the message "EICAS BITE" is NOT displayed on the lower EICAS display.

ae. On the P9 panel, move the EICAS DSP "COMPUTER" switch to "AUTO".

14. Put the airplane back into serviceable condition.
 FIGURE 1: EICAS COMPUTER REMOVAL

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FIGURE 1: EICAS COMPUTER REMOVAL

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE ON THE EICAS COMPUTERS

AS GIVEN IN 767 AMM 20-41-01. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO

THE EICAS COMPUTERS.

The step number shown below agrees with the number shown in the circle symbol in the figure.

STEP TASK NAME PART NUMBER QTY NOTES

1 Remove EICAS Computer S242N701-70x or 

S242N701-901

2 767 AMM 31-41-02

MAIN EQUIPMENT CENTER

FWD 1

S34302

(SHEET 1 OF 1)
 FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE

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FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE

TB239

TB239

W1035-043-24

W1035-081-22

W1035-071-22

W1035-089-22

W1035-092-22

W1035-073-22

W1035-074-22

W1035-083-22

Z8

Z7

W1035-059-22

W1035-058-22

W1035-068-22

W1035-082-22

W1035-076-22

W1035-069-22

W1035-086-22

W1035-084-22 Z9

W1035-070-22

COMPUTER

L EICAS

M10181

XC13

XC14

XB18

K9

K6

E13

W1035-041-24

W1035-042-24

W1035-036-24

D881B

D881E

W1035-037-24

W1035-046-24

W1035-045-24

G1

J8

K1

XB19

XC17

XC18

XC12

XC11

W1035-040-24

W1035-039-24

D881A

K9

K1

XC15

XC16

XB20

K12

J12

D881D

W1035-044-24

W1035-038-24

D881F

W1035-047-24 XC19

W1035-035-24 XB17

J5

XB16

XB15

XB14

W1035-034-24

W1035-033-24

W1035-032-24

D881B

B6

D11

D3

C6

2 1

D8

S34345

(SHEET 1 OF 4)
 FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE

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W1035-100-22

W1035-085-22

REFERENCE: 767 WIRING DIAGRAM 31-41-15 COMPUTER

L EICAS

M10181

TB239

Z7

TB239

W1035-050-24 W1035-079-22

D881E

J1 XD12

D881F

D8 W1035-030-24 XB12 W1035-072-22 Z9

W1035-057-22

D881B

XB13

XA20

XA19

W1035-031-24

W1035-028-24

W1035-027-24

C9

F6

F10

3

4 4

2

S34342

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 2 OF 4)
 FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE

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The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for the left EICAS computer on one airplane.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

1 - - - Wires become spare. No action necessary.

2 Wire - - Delete, if installed at indicated locations or 

other locations not shown in this figure.

3 Wire BMS 13-48, 1 Install or connect wire if not installed. Cut 

and code new wire, if necessary, as given in 

your own procedures. Identify the new wire 

as given in .SWPM 20-10-11

Type 10, Class 1, 

AWG 22

4 Terminal Block 

Contact

M39029/11-145 2 SWPM 20-90-11

REFERENCE: 767 WIRING DIAGRAM 31-41-18

D881B

L EICAS COMPUTER

M10181

G12 W1035-113-24

K3 W1035-114-24

K12 W1035-110-24

W1035-109-24

TB239

W1035-096-24

W1035-108-24

W1035-106-24

D881A

Z10

Z38

H7

D881F

H7

G6

D881D

K7

5

S43447

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 3 OF 4)
 FIGURE 2: GROUP 1, 3 AIRPLANES - W1035 WIRE CHANGE

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5 Heat Shrink Sleeve RT876, 1/8 inch 

diameter, 3 inches

- Tape and stow wire, if installed near TB239. 

Refer to BSWPM 20-30-11 and 20-10-14. (a)

Lacing Tape BMS 13-54, Type 3, 

Class 1

- Color White - Refer to BSWPM 20-10-11.

 (a) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01 are acceptable.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

(SHEET 4 OF 4)
 FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES

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FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES

TB239

TB239

W1035-043-24

COMPUTER

W1035-081-22

W1035-071-22

W1035-089-22

W1035-092-22

W1035-073-22

W1035-074-22

W1035-083-22

Z8

Z7

W1035-059-22

W1035-058-22

W1035-068-22

W1035-082-22

W1035-076-22

W1035-069-22

W1035-086-22

W1035-084-22 Z9

W1035-070-22

L EICAS

M10181

XC13

XC14

XB18

K9

K6

E13

W1035-041-24

W1035-042-24

W1035-036-24

D881B

D881E

W1035-037-24

W1035-046-24

W1035-045-24

G1

J8

K1

XB19

XC17

XC18

XC12

XC11

W1035-040-24

W1035-039-24

D881A

K9

K1

XC15

XC16

XB20

K12

J12

D8

D881D

W1035-044-24

W1035-038-24

D881F

W1035-047-24 XC19

W1035-035-24 XB17

J5

XB16

XB15

XB14

W1035-034-24

W1035-033-24

W1035-032-24

D881B

B6

D11

D3

C6

2 1

S34349

(SHEET 1 OF 4)
 FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES

July 23, 1998

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REFERENCE: 767 WIRING DIAGRAM 31-41-15

W1035-079-22

D881F

TB239

Z7

Z9

TB239

W1035-050-24

COMPUTER

L EICAS

M10181

D881E

W1035-072-22

XD12

W1035-049-24 XD11

J1

J4

D8 W1035-030-24 XB12

W1035-057-22

D881B

W1035-085-22

W1035-100-22

XB13

XA20

XA19

W1035-031-24

W1035-028-24

W1035-027-24

C9

F6

F10

2

2

3

4

3

S34348

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 2 OF 4)
 FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES

July 23, 1998

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The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY 

numbers shown below are the numbers of parts necessary for the left EICAS computer on one airplane. 

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

1 - - - Wires become spare. No action necessary.

2 Wire - - Delete, if installed at indicated locations or 

other locations not shown in this figure.

3 Terminal Block 

Contact

M39029/11-145 2 SWPM 20-90-11

4 Wire BMS 13-48, 1 Install or connect wire if not installed. Cut 

and code new wire, if necessary, as given in 

your own procedures. Identify the new wire 

as given in SWPM 20-10-11.

Type 10, Class 1, 

AWG 22

REFERENCE: 767 WIRING DIAGRAM 31-41-18

D881B

L EICAS COMPUTER

M10181

G12 W1035-113-24

K3 W1035-114-24

K12 W1035-110-24

W1035-109-24

TB239

W1035-096-24

W1035-108-24

W1035-106-24

D881A

Z10

Z38

H7

D881F

H7

G6

D881D

K7

5

S43449

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 3 OF 4)
 FIGURE 3: GROUP 2 AIRPLANES - W1035 WIRE CHANGES

July 23, 1998

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5 Heat Shrink Sleeve RT876, 1/8 inch 

diameter, 3 inches

- Tape and stow wire, if installed near TB239. 

Refer to BSWPM 20-30-11 and 20-10-14. (a)

Lacing Tape BMS 13-54, Type 3, 

Class 1

- Color White - Refer to BSWPM 20-10-11.

 (a) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01 are acceptable.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

(SHEET 4 OF 4)
 FIGURE 4: GROUP 1, 3 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

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FIGURE 4: GROUP 1, 3 AIRPLANES - W1037 WIRE CHANGES

REFERENCE: 767 WIRING DIAGRAM 31-41-15

M10182

TB239

TB239

W1037-092-22

W1037-069-22

W1037-049-22

W1037-055-22

W1037-068-22

W1037-062-22

W1037-073-22

W1037-081-22

W1037-056-22 Z37

W1037-061-22 Z33

W1037-028-24 XB29

W1037-036-24 XC27

W1037-037-24 XC28

G1

K1

J8

D883E

XC25

XC26

XB30

W1037-034-24

W1037-035-24

W1037-029-24

J5 W1037-038-24 XC29

D883F

D883D

K12

J12

W1037-030-24 XC21

D8

D883A

Z31

W1037-060-22

W1037-031-24 XC22

W1037-032-24 XC23

W1037-026-24 XB27

K1

K9

D883B

K9

B6

K6 W1037-033-24 XC24 W1037-058-22

E13 W1037-027-24 XB28 W1037-076-22

C6 W1037-023-24 XB24 W1037-057-22

D11 W1037-025-24 XB26 W1037-048-22

D3 W1037-024-24 XB25 W1037-070-22

COMPUTER

R EICAS

1 2

S34441

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 1 OF 3)
 FIGURE 4: GROUP 1, 3 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

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W1037-079-22

W1037-072-22

TB239

Z37

Z31

R EICAS

M10182

COMPUTER

TB239

J1 W1037-041-24 XD22 W1037-050-22

D883E

D883F

D8 W1037-021-24 XB22 W1037-059-22

XB23 W1037-047-22

XA30

XA29

W1037-022-24

W1037-019-24

W1037-018-24

D883B

C9

F6

F10

2

S34371

(SHEET 2 OF 3)
 FIGURE 4: GROUP 1, 3 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

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The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY 

numbers shown below are the numbers of parts necessary for the right EICAS computer on one airplane.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

1 - - - Wire becomes spare. No action necessary.

2 Wire - - Delete, if installed at indicated locations or 

other locations not shown in this figure.

3 Heat Shronk Sleeve RT876, 1/8 inch 

diameter, 3 inches

- Tape and stow wire, if installed near TB239. 

Refer to SWPM 20-30-11 and SWPM 20-10-

14. (a)

Lacing Tape BMS 13-54, Type 3, 

Class 1

- Color White - Refer to SWPM 20-10-11.

 (a) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01 are acceptable.

Z37

Z39

W1037-113-24

W1037-114-24

W1037-110-24

W1037-109-24

W1037-096-24

W1037-108-24

W1037-085-24

R EICAS COMPUTER

M10182

D883B

D883A

D883F

D883D

G12

K3

K12

TB239

H7

H7

G6

K7

REFERENCE: 767 WIRING DIAGRAM 31-41-18

3

S43457

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 3 OF 3)
 FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

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FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES

M10182

TB239

TB239

W1037-092-22

W1037-069-22

W1037-049-22

W1037-055-22

W1037-068-22

W1037-062-22

W1037-073-22

W1037-081-22

W1037-056-22 Z37

W1037-061-22 Z33

W1037-028-24 XB29

W1037-036-24 XC27

W1037-037-24 XC28

G1

K1

J8

D883E

XC25

XC26

W1037-034-24

W1037-035-24

W1037-029-24

J5 W1037-038-24 XC29

D883F

D883D

K12

J12

W1037-030-24 XC21

D8

D883A

Z31

W1037-060-22

W1037-031-24 XC22

W1037-032-24 XC23

W1037-026-24 XB27

K1

K9

D883B

K9

B6

K6 W1037-033-24 XC24 W1037-058-22

E13 W1037-027-24 XB28 W1037-076-22

C6 W1037-023-24 XB24 W1037-057-22

D11 W1037-025-24 XB26 W1037-048-22

D3 W1037-024-24 XB25 W1037-070-22

COMPUTER

R EICAS

XB30

1 2

S34445

(SHEET 1 OF 4)
 FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

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Z37

TB239

Z31

W1037-050-22

W1037-059-22

REFERENCE: 767 WIRING DIAGRAM 31-41-15

R EICAS

M10182

COMPUTER

J1

TB239

W1037-041-24 XD22

D883E

D883F

W1037-021-24 XB22

W1037-047-22

W1037-072-22

W1037-079-22

XB23

XA30

XA29

W1037-022-24

W1037-019-24

W1037-018-24

D883B

D8

C9

F6

F10

3 3

3

4

3

2

4

S34443

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 2 OF 4)
 FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

Revision 4 July 07, 2005 767-31-0091

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BOEING SERVICE BULLETIN 767-31-0091

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The QTY 

numbers shown below are the numbers of parts necessary for the right EICAS computer on one airplane.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

1 - - - Wires become spare. No action necessary.

2 Wire - - Delete, if installed at indicated locations or 

other locations not shown in this figure.

3 Terminal Block 

Contact

M39029/11-145 4 SWPM 20-90-11

4 Wire BMS 13-48, 2 Install or connect wire if not installed. Cut 

and code new wire, if necessary, as given in 

your own procedures. Identify the new wire 

as given in SWPM 20-10-11.

Type 10, Class 1, 

AWG 22

Z37

Z39

W1037-113-24

W1037-114-24

W1037-110-24

W1037-109-24

W1037-096-24

W1037-108-24

W1037-085-24

R EICAS COMPUTER

M10182

D883B

D883A

D883F

D883D

G12

K3

K12

TB239

H7

H7

G6

K7

REFERENCE: 767 WIRING DIAGRAM 31-41-18

5

S43461

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 3 OF 4)
 FIGURE 5: GROUP 2 AIRPLANES - W1037 WIRE CHANGES

July 23, 1998

Revision 4 July 07, 2005 767-31-0091

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BOEING SERVICE BULLETIN 767-31-0091

5 Heat Shrink Sleeve RT876, 1/8 inch 

diameter, 3 inches

- Tape and stow wire, if installed near TB239. 

Refer to BSWPM 20-30-11 and 20-10-14. (a)

Lacing Tape BMS 13-54, Type 3, 

Class 1

- Color White - Refer to SWPM 20-10-11.

 (a) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01 are acceptable.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

(SHEET 4 OF 4)
 FIGURE 6: AIRPLANES VF251, VL895-VL900, VR201, VW701-VW721 - W2000 WIRE CHANGES

July 23, 1998

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FIGURE 6: AIRPLANES VF251, VL895-VL900, VR201, VW701-VW721 - W2000 WIRE CHANGES

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FLAG

NOTE

NAME PART NUMBER 

QTY

NOTES

1 Heat Shrink Sleeve RT876, 1/8 inch 

diameter, 3 inches

- Tape and stow wire, if installed near EICAS 

connector. Refer to SWPM 20-30-11 and 

SWPM 20-10-14. (a)

Lacing Tape BMS 13-54, Type 3, 

Class 1

- Color White - Refer to SWPM 20-10-11.

 (a) Alternative part numbers for RT876 Heat Shrink Sleeve given in SWPM 20-00-01

AE0217

CHIME

MSG

COMM

CHIME

MSG

COMM

W2000-TK10-24

E8 EICAS RACK

A10

D883E D5063J P

R EICAS COMPUTER

M10181

M10182

E3

L EICAS COMPUTER

D881E

E3

REFERENCE: 767 WIRING DIAGRAM 31-51-33

W2000-TM10-24

1

1

S43465

DELETED WIRE OR FORMER ROUTING

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 1 OF 1)
 FIGURE 7: EICAS COMPUTER S242N701-1001 CONNECTOR KEYING CHANGE

July 23, 1998

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FIGURE 7: EICAS COMPUTER S242N701-1001 CONNECTOR KEYING CHANGE

CODE 

NUMBER

RECEPTACLE SHELL PLUG SHELL Note

Left Post Center 

Post

Right 

Post

Left Post Center 

Post

Right 

Post

63 2 3 2 3 2 3 Refer toSWPM 20-71-14 

for connector keying 

change.

DARK AREA REPRESENTS THE POST

1 2 3 4 5 6

LEFT POST RIGHT POST

CENTER POST

S35793

(SHEET 1 OF 1)
 FIGURE 8: EICAS COMPUTER INSTALLATION

July 23, 1998

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FIGURE 8: EICAS COMPUTER INSTALLATION

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE ON THE EICAS COMPUTERS

AS GIVEN IN 767 AMM 20-41-01. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO

THE EICAS COMPUTERS.

The step number shown below agrees with the number shown in the circle symbol in the figure. The QTY 

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

STEP TASK NAME PART NUMBER QTY NOTES

1 Install EICAS Computer S242N701-1001 2 767 AMM 31-41-02

MAIN EQUIPMENT CENTER

FWD 1

S35794

(SHEET 1 OF 1)
 APPENDIX A: OPC PART NUMBER BY CUSTOMER EFFECTIVITY

July 23, 1998

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APPENDIX A: OPC PART NUMBER BY CUSTOMER EFFECTIVITY

Group 1

Effectivity L Prog Pins Supl Pin OPC S/W P/N Diskette Set P/N

VB331-VB332 9C28820D 0000 310E-BCG-006-J6 242T7001-2066

VB441-VB444 9C6971AD 0000 3112-BCG-006-P0 242T7001-2110

VF171-VF172 9C6AFF2C 0000 3107-BCG-00M-97 242T7001-2224

VF180 9C6AFF2C 0000 3113-BCG-006-R3 242T7001-2123

VF251 9C317FEC 0000 3107-BCG-00M-79 242T7001-2219

VK012-VK016 9C2143AC 0000 3104-BCG-006-D2 242T7001-2012

VK090-VK099 9C21488C 0000 3105-BCG-006-D3 242T7001-2013

VK100-VK111 9C21588D 0000 3100-BCG-006-D6 242T7001-2016

VK112-VK113 9C21488C 0000 3105-BCG-006-D3 242T7001-2013

VK131-VK133 9C6B7DED 0000 310A-BCG-00M-12 242T7001-2172

VK141-VK143 9C217D6D 0000 3107-BCG-006-E0 242T7001-2020

VK144 9C217D6D 0000 3107-BCG-006-E0 242T7001-2020

VK145-VK148 9C217D6D 0000 3107-BCG-006-E0 242T7001-2020

VK181 9C2143AC 0000 3104-BCG-006-D2 242T7001-2012

VK186 9C2143AC 0000 3104-BCG-006-D2 242T7001-2012

VL701-VL702 9C285FAD 0000 310D-BCG-00M-15 242T7001-2175 

VL703 9C217F6C 0000 3105-BCG-006-E2 242T7001-2022

VL751-VL752 9C39F6AD 0000 310E-BCG-006-K7 242T7001-2077

VL753 9C617F6D 0000 3108-BCG-006-M7 242T7001-2097

VL754 9C39F6AD 0000 310E-BCG-006-K7 242T7001-2077

VL755 9C697BAD 0400 3110-BCG-006-P2 242T7001-2112

VL891-VL900 9CB9FFED 1606 3117-BCG-006-T1 242T7001-2131

VL911-VL914 9C2AD28D 0400 310B-BCG-006-L5 242T7001-2085

VL941 9C28F3AD 0400 3101-BCG-006-J9 242T7001-2069

VN055-VN061 9C214EAD 0000 3103-BCG-006-D5 242T7001-2015

VN062 9C214EAD 0000 3103-BCG-006-D5 242T7001-2015

VN063-VN064 9C285EAC 0000 310C-BCG-006-K5 242T7001-2075

VN193-VN196 9C215A8C 0000 3101-BCG-006-D7 242T7001-2017

VN197 9C215A8C 0000 3101-BCG-006-D7 242T7001-2017

VN198 9C214A8D 0000 3102-BCG-006-D4 242T7001-2014

VN231-VN234 9C2B7FED 0000 310A-BCG-006-L4 242T7001-2084

VN421 9C28F72D 0200 3108-BCG-006-K1 242T7001-2071

VN422-VN427 9C28772C 0000 310F-BCG-006-K6 242T7001-2076

VN436 9C25 TBD TBD TBD

VN471-VN472 9C28F22D 0000 3100-BCG-006-J8 242T7001-2068

VN546-VN547 9C62DF6D 0000 310E-BCG-006-N2 242T7001-2102
 APPENDIX A: OPC PART NUMBER BY CUSTOMER EFFECTIVITY

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VN634-VN635 9CB876AC 0600 310C-BCG-00M-27 242T7001-2187

VN636 9CB976AD 0200 3119-BCG-006-R9 242T7001-2129

VN637-VN638 9C39F6AD 0000 310E-BCG-006-K7 242T7001-2077

VN657-VN658 9C297FEC 0000 310C-BCG-006-J4 242T7001-2064

VN731 9C6B7BAC 0000 3117-BCG-006-P5 242T7001-2115

VN732 9C637BAD 0000 3106-BCG-006-M9 242T7001-2099

VN751-VN752 9C217F6C 0000 3105-BCG-006-E2 242T7001-2022

VN753 9C297FEC 0000 310C-BCG-006-J4 242T7001-2064

VN791 9C6973AC 0000 3113-BCG-006-P1 242T7001-2111

VN792 9C6973AC 0000 3113-BCG-006-P1 242T7001-2111

VN811 9C297FAD 0000 310B-BCG-006-J3 242T7001-2063

VN812 9C297FAD 0000 310B-BCG-006-J3 242T7001-2063

VN813 9C295B2C 0000 310E-BCG-006-H4 242T7001-2054

VN921-VN922 9C2ADB2D 0000 3108-BCG-006-L6 242T7001-2086

VN951-VN952 9C2AFF6C 0400 3109-BCG-006-L7 242T7001-2087

VN953 9C2AFF6C 0400 3109-BCG-006-L7 242T7001-2087

VN968-VN970 9C6A7FED 0400 3114-BCG-006-R4 242T7001-2124

VR401 9C214A8D 0000 3102-BCG-006-D4 242T7001-2014

VR426 9C217D6D 0000 3107-BCG-006-E0 242T7001-2020

VR461 9C2143AC 0000 3104-BCG-006-D2 242T7001-2012

VS051 9C2AD28D 0400 310B-BCG-006-L5 242T7001-2085

VS111 9C297FEC 0000 310C-BCG-006-J4 242T7001-2064

Group 2

Effectivity L Prog Pins Supl Pin OPC S/W P/N Diskette Set P/N

VR201 9C24328D 000A 3114-BCG-006-V0 242T7001-2150

VW701-VW721 9C24328D 000A 3114-BCG-006-V0 242T7001-2150

VW851 9C313F6C 0408 3171-BCG-006-03 242T7001-2002

Group 3

Effectivity L Prog Pins Supl Pin OPC S/W P/N Diskette Set P/N

VF181-VF184 9C24D32D 0000 3116-BCG-006-U1 242T7001-2141

Group 1

Effectivity L Prog Pins Supl Pin OPC S/W P/N Diskette Set P/N
 APPENDIX B: SERVICE BULLETIN GROUP TO PROGRAM PINS - LEFT EICAS COMPUTER

July 23, 1998

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APPENDIX B: SERVICE BULLETIN GROUP TO PROGRAM PINS - LEFT EICAS COMPUTER

SERVICE BULLETIN GROUP PROGRAM PINS

1, 3 9C25

2 9CA4
 APPENDIX C: SERVICE BULLETIN GROUP TO PROGRAM PINS - RIGHT EICAS COMPUTER

July 23, 1998

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APPENDIX C: SERVICE BULLETIN GROUP TO PROGRAM PINS - RIGHT EICAS COMPUTER

SERVICE BULLETIN GROUP PROGRAM PINS

1, 3 9424

2 94A5