Commercial 

Airplanes 767

Service Bulletin

Number: 767-21-0235

Original Issue: October 08, 2009

ATA System: 2158

SUBJECT: AIR CONDITIONING - Cooling - Freighter Equipment Cooling System 3-Way Valve

Control Logic Change

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2009 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Unpublished Work - All Rights Reserved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

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Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

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3.0
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BOEING SERVICE BULLETIN 767-21-0235

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

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

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 17

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

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

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176

AND W0184 - ROUTING [Group 2-3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

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BOEING SERVICE BULLETIN 767-21-0235
Commercial 

Airplanes 767

Service Bulletin

Summary Number: 767-21-0235

Original Issue: October 08, 2009

ATA System: 2158

SUBJECT: AIR CONDITIONING - Cooling - Freighter Equipment Cooling System 3-Way Valve

Control Logic Change

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to install a relay and related wiring in the P36 panel to change the control

logic for the equipment cooling 3-way valve on freighter airplanes. The logic is changed to make the 3-way valve

close when the Electrical/Electronic (E/E) cooling system is put in STBY mode, when selected from the P5

overhead panel in the flight compartment. This will result in the continued supply of cooled air to the flight

compartment avionic equipment. If this service bulletin is not done, a loss of air flow from the Air Conditioning

(A/C) packs could occur and result in a loss of the displays in the flight compartment.

A 767-300F operator experienced an air turn-back event caused by the loss of one of the first officer’s primary

displays and the loss of color on two of the captain’s primary displays. The display problems were followed by

electrical burning smells in the flight compartment, which was found to be the result of an overheat condition

from a decreased supply of cooling air to the avionic equipment in the flight compartment. The cause of the

occurrence was found to be ice accumulation in the supply line orifice, which was sufficient in quantity to block

the conditioned air flow to the flight compartment. The icing condition is found to start during ground operations

in high humidity environments and when the cooling packs are selected to full cold. The packs cannot fully

remove all moisture from the air in high humidity environments which subsequently causes small quantities of

airborne ice crystals in the released air flow. After a period of time, the ice crystals cause frost to collect on the

internal walls of the A/C ducts. If a large quantity of frost collects in the ducts and is not cleared, the frost becomes

ice. The combination of one cooling pack in operation above freezing and the other cooling pack in operation

below freezing, in humid environments, increases the amount of frost that can accumulate. To give continuous

cooling to the flight compartment avionic equipment, Boeing has made changes to the control logic for the

equipment cooling 3-way valve, which will give the pilots the option to select to have replacement cooling airflow

supplied from the E/E cooling system, if the airflow from the A/C packs becomes unavailable or not sufficient.

The changes make the operation of the valve close when the E/E cooling system is put in the STBY mode when

selected from the flight compartment.

Accomplishment of this service bulletin installs a relay in the lower section of the P36 Left Miscellaneous Electrical

Equipment Panel, with related wiring changes to change the operation of the 3-way valve when the E/E cooling

system is selected to the STBY mode from the flight compartment. This gives the pilots the option to choose an

alternative supply of cooling airflow to prevent overheating of the avionic equipment in the flight compartment.

Boeing Service Related Problem (SRP) 767-SRP-21-0173 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 767 FTD 21-08002 and 767 FTD 21-08001 are related to this service bulletin.

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ACTION (PRR B12900-255)

Group 1:

Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in

the Main Equipment Center (MEC). Add new wires and replace a wire in wire bundle W0176 and install a new

relay in the lower section of the panel. Do a functional test of the system.

Group 2-3:

Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment Panel in

the Main Equipment Center (MEC). Add new wires and replace wires in wire bundles W0176 and W0184 and

install a new relay in the lower section of the panel. Do a functional test of the system.

EFFECTIVITY

767-300F Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes.

COMPLIANCE

No compliance time is given.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Group 1 7.60 4.95

Group 2 and 3 9.50 6.85

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 767-21-0235

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

Number: 767-21-0235

Original Issue: October 08, 2009

ATA System: 2158

SUBJECT: AIR CONDITIONING - Cooling - Freighter Equipment Cooling System 3-Way Valve

Control Logic Change

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 B12900-255 for data about this change.

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

767-300F airplanes, delivered with a General Market Freighter

configuration, that have P36 panel wiring differences.

1 -

767-300F airplanes, delivered with a Manual Freighter configuration,

that have P36 panel wiring differences.

2 -

767-300F airplanes, delivered with a Manual Freighter configuration,

that have P36 panel wiring differences.

3 -

Airplane Models:

767-300F

Variable Number Group

VR201 - VR211 2

VR251 1

VR256 - VR260 1

VT501 1

VT511 - VT513 1

VT521 - VT523 1

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Variable Number Group

VT531 - VT533 1

VW701 - VW721 3

VW851 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to install a relay and related wiring in the P36 panel to change

the control logic for the equipment cooling 3-way valve on freighter airplanes. The logic is changed to

make the 3-way valve close when the Electrical/Electronic (E/E) cooling system is put in STBY mode,

when selected from the P5 overhead panel in the flight compartment. This will result in the continued

supply of cooled air to the flight compartment avionic equipment. If this service bulletin is not done, a

loss of air flow from the Air Conditioning (A/C) packs could occur and result in a loss of the displays in

the flight compartment.

A 767-300F operator experienced an air turn-back event caused by the loss of one of the first officer’s

primary displays and the loss of color on two of the captain’s primary displays. The display problems

were followed by electrical burning smells in the flight compartment, which was found to be the result

of an overheat condition from a decreased supply of cooling air to the avionic equipment in the flight

compartment. The cause of the occurrence was found to be ice accumulation in the supply line orifice,

which was sufficient in quantity to block the conditioned air flow to the flight compartment. The icing

condition is found to start during ground operations in high humidity environments and when the cooling

packs are selected to full cold. The packs cannot fully remove all moisture from the air in high humidity

environments which subsequently causes small quantities of airborne ice crystals in the released air

flow. After a period of time, the ice crystals cause frost to collect on the internal walls of the A/C ducts.

If a large quantity of frost collects in the ducts and is not cleared, the frost becomes ice. The combination

of one cooling pack in operation above freezing and the other cooling pack in operation below freezing,

in humid environments, increases the amount of frost that can accumulate. To give continuous cooling

to the flight compartment avionic equipment, Boeing has made changes to the control logic for the

equipment cooling 3-way valve, which will give the pilots the option to select to have replacement

cooling airflow supplied from the E/E cooling system, if the airflow from the A/C packs becomes

unavailable or not sufficient. The changes make the operation of the valve close when the E/E cooling

system is put in the STBY mode when selected from the flight compartment.

Accomplishment of this service bulletin installs a relay in the lower section of the P36 Left Miscellaneous

Electrical Equipment Panel, with related wiring changes to change the operation of the 3-way valve

when the E/E cooling system is selected to the STBY mode from the flight compartment. This gives

the pilots the option to choose an alternative supply of cooling airflow to prevent overheating of the

avionic equipment in the flight compartment.

Boeing Service Related Problem (SRP) 767-SRP-21-0173 is related to this service bulletin.

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BOEING SERVICE BULLETIN 767-21-0235
Boeing Fleet Team Digest (FTD) 767 FTD 21-08002 and 767 FTD 21-08001 are related to this service

bulletin.

D. Description

Group 1:

Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment

Panel in the Main Equipment Center (MEC). Make changes to wire bundle W0176 and install a new

relay in the lower section of the panel. Do a functional test of the system.

Group 2-3:

Get access and prepare the airplane to do work in the P36 Left Miscellaneous Electrical Equipment

Panel in the Main Equipment Center (MEC). Make changes to wire bundles W0176 and W0184 and

install a new relay in the lower section of the panel. Do a functional test of the system.

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

Affected Maintenance Zones

Model Zone

767-300F 119

E. Compliance

No compliance time is given.

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.

G. Manpower

The table below shows an estimate of the task hours necessary to do this service bulletin for each

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

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

of lost time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools

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BOEING SERVICE BULLETIN 767-21-0235
Group 1:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access and 1 0.50 0.50

Prepare Airplane

FIGURE 1 (Routing -

Only)

FIGURE 2 2 5.30 2.65

FIGURE 8 1 0.30 0.30

Test 1 1.00 1.00

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 7.60 4.95

Group 2:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access and 1 0.50 0.50

Prepare Airplane

FIGURE 3 (Routing -

Only)

FIGURE 4 2 5.30 2.65

FIGURE 6 1 1.90 1.90

FIGURE 8 1 0.30 0.30

Test 1 1.00 1.00

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 9.50 6.85

Group 3:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access and 1 0.50 0.50

Prepare Airplane

FIGURE 3 (Routing -

Only)

FIGURE 5 2 5.30 2.65

FIGURE 7 1 1.90 1.90

FIGURE 8 1 0.30 0.30

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BOEING SERVICE BULLETIN 767-21-0235
Group 3:

Number of Per- Task Hours Elapsed Hours

sons

Task

Test 1 1.00 1.00

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 9.50 6.85

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR B12900-255

b. Boeing Service Related Problem (SRP) 767-SRP-21-0173

c. Standard Overhaul Practices Manual (SOPM) 20-50-05, 20-50-10

d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-11, 20-10-12, 20-10-19, 20-20-00,

20-20-10, 20-81-12, 20-81-19, 20-81-22, 20-90-11

e. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 31-01-36, 32-09-02

f. 767 Fleet Team Digest (FTD) 21-08001, 21-08002

g. 767 Wiring Diagram Manual (WDM) 21-58-16

2. Data supplied with this Service Bulletin

None.

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

Drawing Number Title

MODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT288T2036

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

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BOEING SERVICE BULLETIN 767-21-0235
K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Wiring Diagram Manual 21-58

767 Illustrated Parts Catalog 21-58

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 767-21-0235
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown

below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.

More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the

date Boeing gets the purchase order.

Group 1:

Unit Price thru

May 31/10

ROLT

(Weeks)

Kit Number Name Date QTY

Top Kit - 3-Way Valve Jun 15/09 5 18 $715.00

Logic Modification

015T1839-1

Jul 14/09 4

Group 2-3:

Unit Price thru

May 31/10

ROLT

(Weeks)

Kit Number Name Date QTY

Top Kit - 3-Way Valve Jun 23/09 5 18 $955.00

Logic Modification

015T1839-2

Jul 08/09 5

Jul 22/09 5

Aug 05/09 1

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.

Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Mail to:

Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

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

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BOEING SERVICE BULLETIN 767-21-0235
C. Parts Necessary For Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 015T1839

New Part Number QTY Name Notes

-1 -2

Top Kit - 3-Way

Valve Logic Modification

015T1839-1 - .

Top Kit - 3-Way

Valve Logic Modification

015T1839-2 . -

ASSY -101

(W0176)

289T1162-101 1 1

ASSY -102

(W0184)

289T1162-102 . 1

LACING TAPE -

RED (135C) 100

FT

289T9001-21 1 1

LACING TAPE -

BLUE (135C) 100

FT

289T9001-61 . 1

BACR13CF2A 1 1 RELAY

BACT19J4 2 2 TAPE, ID

Kit 289T1162

New Part Number QTY Name Notes

-101 -102

ASSY -101

(W0176)

289T1162-101 - .

ASSY -102

(W0184)

289T1162-102 . -

ID TAPE - CONNECTOR289T1162-10101 1 .

WIRE - RAW MATERIAL289T1162-101W 1 .

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BOEING SERVICE BULLETIN 767-21-0235
Kit 289T1162

New Part Number QTY Name Notes

-101 -102

WIRE - RAW MATERIAL289T1162-102W . 1

CONTACT, SOCKETBACC47DJ1 4 .

CONTACT, SOCKETBACC47ER1 1 .

BACS16X1A 1 . RELAY SOCKET

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 3 4

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BOEING SERVICE BULLETIN 767-21-0235

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

5. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

B. WORK INSTRUCTIONS

1. Get access to the Flight Compartment and open the Main Equipment Center (MEC) access door,

119AL, to get access to the MEC. Refer to 767 AMM 06-41-00.

2. In the Flight Compartment and MEC, open the circuit breakers specified in the tables below and

attach 'DO-NOT-CLOSE' tags.

MAIN POWER DISTRIBUTION PANEL

Panel Location Name Number

P6-3 H018 CB-EQUIP COOL FAN SPLY 1 C00331

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-3 P011 CB-EQUIP COOLING SUPPLY FAN 1 C00654

3. Open the P36 Left Miscellaneous Electrical Equipment Panel to get access to the wiring and

electrical equipment. Refer to 767 AMM 31-01-36.

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BOEING SERVICE BULLETIN 767-21-0235
4. Group 1:

Make changes to wire bundle W0176 in accordance with FIGURE 1 and FIGURE 2.

5. Group 2-3:

Make changes to wire bundles W0176 and W0184 in accordance with:

Group 2:

FIGURE 3, FIGURE 4 and FIGURE 6.

Group 3:

FIGURE 3, FIGURE 5 and FIGURE 7.

6. Install a new relay in the lower section of P36 Left Miscellaneous Electrical Equipment Panel in

accordance with FIGURE 8.

7. Close the P36 Left Miscellaneous Electrical Equipment Panel.

8. In the Flight Compartment and the MEC, remove the 'DO-NOT-CLOSE' tags and close the circuit

breakers specified in the tables below.

MAIN POWER DISTRIBUTION PANEL

Panel Location Name Number

P6-3 H018 CB-EQUIP COOL FAN SPLY 1 C00331

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-3 P011 CB-EQUIP COOLING SUPPLY FAN 1 C00654

9. Do the test as follows:

Group 1:

a. Make sure the airplane is powered, the engines are OFF and the air conditioning packs are

OFF.

b. Make sure the Air/Ground Relay System is in GROUND mode. Or to put the Air/Ground Relay

System in GROUND mode, refer to 767 AMM 32-09-02 as an accepted procedure.

c. In the MEC, make sure the circuit breakers specified in the table below are closed:

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-1 A013 LEFT PACK FLOW CONT C00653

P11-4 A026 RIGHT PACK FLOW CONT C00704

P11-1 B008 EQUIPMENT COOLING STANDBY C00688

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CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-4 C019 EQUIP COOL OVERRIDE C00679

P11-4 C030 LDG GR POS AIR/GND SYS 1 C01175

P11-1 D016 ENGINE SPEED SENSE L2 C01426

P11-1 D017 ENGINE SPEED SENSE R2 C01427

d. In the Flight Compartment, set the Equipment Cooling rotary switch on the P5 overhead panel

to AUTO.

e. Disconnect connector (D20366) to Equipment Cooling Temperature Control switch (S868) at

STA 208, WL 172 and RBL 60.

f. Install a jumper from pin 1 of connector (D20366) to pin 2 of connector (D20366).

g. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

h. Disconnect connector (D2770) from the Left Flow Control Valve (V16).

NOTE: This simulates the Left Pack is ON.

i. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

j. In the MEC, select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies

(M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position.

NOTE: This simulates left and right engines ON. Two of these test switches are momentary

toggle switches and must be manually held in the 'TEST' position during all of this

test procedure by the person at the P50 Panel. For this test procedure to give correct

results, make sure these two test switches are not released from the 'TEST' position

until this procedure is complete.

k. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

l. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right

and (M1093) Left on the P50 Panel.

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m. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

n. Disconnect connector (D1276) from the Right Flow Control Valve (V17).

NOTE: This simulates the Right Pack is ON.

o. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

p. Select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092)

Right and (M1093) Left on the P50 Panel, in the 'TEST' position.

NOTE: This simulates left and right engines ON. Two of these test switches are momentary

toggle switches and must be manually held in the 'TEST' position during all of this

test procedure by the person at the P50 Panel. For this test procedure to give correct

results, make sure these two test switches are not released from the 'TEST' position

until this procedure is complete.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

q. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

r. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY.

s. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

t. Set the Equipment Cooling rotary switch on the P5 overhead panel to OVRD.

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CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE

EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS

THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT

COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF

THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION

FOR MORE THAN 5 MINUTES.

u. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

v. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

w. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

x. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right

and (M1093) Left on the P50 Panel.

y. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

z. Connect connector (D2770) back on to the Left Flow Control Valve (V16).

aa. Connect connector (D1276) back on to the Right Flow Control Valve (V17).

ab. Remove the jumper from pin 1 and pin 2 in Connector (D20366).

ac. Connect connector (D20366) back on to Equipment Cooling Temperature Control Switch

(S868) at STA 208, WL 172, and RBL 60.

ad. Put the airplane back to the configuration before the test.

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BOEING SERVICE BULLETIN 767-21-0235
Group 2-3:

a. Make sure the airplane is powered, the engines are OFF and the air conditioning packs are

OFF.

b. Make sure the Air/Ground Relay System is in GROUND mode. Or to put the Air/Ground Relay

System in GROUND mode, refer to 767 AMM 32-09-02 as an accepted procedure.

c. In the MEC, make sure the circuit breakers specified in the table below are closed:

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-1 A013 LEFT PACK FLOW CONT C00653

P11-4 A026 RIGHT PACK FLOW CONT C00704

P11-1 B008 EQUIPMENT COOLING STANDBY C00688

P11-4 C019 EQUIP COOL OVERRIDE C00679

P11-4 C030 LDG GR POS AIR/GND SYS 1 C01175

P11-1 D016 ENGINE SPEED SENSE L2 C01426

P11-1 D017 ENGINE SPEED SENSE R2 C01427

d. In the Flight Compartment, set the Equipment Cooling rotary switch on the the P5 overhead

panel to AUTO.

e. Disconnect connector (D20366) to Equipment Cooling Temperature Control switch (S868) at

STA 208, WL 172 and RBL 60.

f. Install a jumper from pin 1 of connector (D20366) to pin 2 of connector (D20366).

g. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

h. Disconnect connector (D2770) from the Left Flow Control Valve (V16).

NOTE: This simulates the Left Pack is ON.

i. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

j. In the MEC, select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies

(M1092) Right and (M1093) Left on the P50 Panel, in the 'TEST' position.

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NOTE: This simulates left and right engines ON. Two of these test switches are momentary

toggle switches and must be manually held in the 'TEST' position during all of this

test procedure by the person at the P50 Panel. For this test procedure to give correct

results, make sure these two test switches are not released from the 'TEST' position

until this procedure is complete.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

k. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

l. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY.

m. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

n. Set the Equipment Cooling rotary switch on the P5 overhead panel to OVRD.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE

EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS

THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT

COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF

THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION

FOR MORE THAN 5 MINUTES.

o. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

p. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.

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CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

q. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

r. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right

and (M1093) Left on the P50 Panel.

s. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

t. Disconnect connector (D1276) from the Right Flow Control Valve (V17).

NOTE: This simulates the Right Pack is ON.

u. Connect connector (D2770) back on to the Left Control Valve (V16).

v. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

w. Select and hold all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092)

Right and (M1093) Left on the P50 Panel, in the 'TEST' position.

NOTE: This simulates left and right engines ON. Two of these test switches are momentary

toggle switches and must be manually held in the 'TEST' position during all of this

test procedure by the person at the P50 Panel. For this test procedure to give correct

results, make sure these two test switches are not released from the 'TEST' position

until this procedure is complete.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

x. Make sure the 3-way valve is in the condition specified in the table below:

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BOEING SERVICE BULLETIN 767-21-0235
Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

y. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY.

z. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

aa. Set the equipment cooling rotary switch on the P5 overhead panel to OVRD.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. ALSO, EQUIPMENT IN THE MEC WILL BE NOT COOLED WHEN THE

EQUIPMENT COOLING ROTARY SWITCH IS SET TO THE 'OVRD' POSITION AS

THE E/E COOLING FANS ARE SHUTOFF. DAMAGE TO THE FLIGHT

COMPARTMENT INSTRUMENTS AND MEC EQUIPMENT COULD OCCUR IF

THE EQUIPMENT COOLING ROTARY SWITCH IS SET IN THE 'OVRD' POSITION

FOR MORE THAN 5 MINUTES.

ab. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

ac. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.

CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN

THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'

CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS

TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR

IF THE VALVE IS KEPT OPEN FOR MORE THAN 5 MINUTES.

ad. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

OPEN (C-B) MANIFOLD INTERCONNECT VALVE V90

ae. Release all four (4) test switches on the N2 Engine Speed Card Assemblies (M1092) Right

and (M1093) Left on the P50 Panel.

af. Make sure the 3-way valve is in the condition specified in the table below:

Condition Name Equipment Number

CLOSED (A-B) MANIFOLD INTERCONNECT VALVE V90

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BOEING SERVICE BULLETIN 767-21-0235
ag. Connect connector (D1276) back on to Right Flow Control Valve (V17).

ah. Remove the jumper from pin 1 and pin 2 in Connector (D20366).

ai. Connect connector (D20366) back on to Equipment Cooling Temperature Control Switch

(S868) at STA 208, WL 172, and RBL 60.

aj. Put the airplane back to the configuration before the test.

10. Close the MEC access door, 119AL.

11. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 1.

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

ROUTING

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 1.

REFERENCE: 767 WDM 21-58-16.

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

NOTE: Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-1 to do the work in this Figure.

FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21-0235
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to the wire kit cut and code

table, to identify the wires as

shown and to cut to the necessary

lengths.

1 WIRE - RAW MATERIAL 289T1162-101W -

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 3

REMOVABLE, PER MIL-C39029/11

2

Refer to SWPM 20-81-12 and

SWPM 20-81-22 as accepted procedures.

3 RELAY SOCKET BACS16X1A 1

Refer to SWPM 20-81-12 as an

accepted procedure.

4 CONTACT, SOCKET BACC47DJ1 4

Refer to SWPM 20-81-19 as an

accepted procedure.

5 CONTACT, SOCKET BACC47ER1 1

Identified as D21731 M/W K10717.

Install within 6 inches of equipment.

6 ID TAPE - CONNECTOR 289T1162-10101 1

Use to tie the wire bundle. Refer

to SWPM 20-10-11 as an accepted

procedure.

LACING TAPE - RED 289T9001-21 -

(135C) 100 FT

7

WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA # WIRE #

W0176 24C 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AC 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AD 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AE 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 2: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 2-3.

FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 1 OF 6)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 2 OF 6)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 3 OF 6)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 4 OF 6)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 767-21-0235
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 5 OF 6)

BOEING PROPRIETARY -

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41 of 54

BOEING SERVICE BULLETIN 767-21-0235
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLES W0176 AND

W0184 - ROUTING

(SHEET 6 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

42 of 54

BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 2.

REFERENCE: 767 WDM 21-58-16.

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

NOTE: Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-2 to do the work in this Figure.

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 1 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

43 of 54

BOEING SERVICE BULLETIN 767-21-0235
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to the wire kit cut and code

table, to identify the wires as

shown and to cut to the necessary

lengths.

1 WIRE - RAW MATERIAL 289T1162-101W -

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 3

REMOVABLE, PER MIL-C39029/11

2

Refer to SWPM 20-81-12 and

SWPM 20-81-22 as accepted procedures.

3 RELAY SOCKET BACS16X1A 1

Refer to SWPM 20-81-12 as an

accepted procedure.

4 CONTACT, SOCKET BACC47DJ1 4

Refer to SWPM 20-81-19 as an

accepted procedure.

5 CONTACT, SOCKET BACC47ER1 1

Identified as D21731 M/W K10717.

Install within 6 inches of equipment.

6 ID TAPE - CONNECTOR 289T1162-10101 1

Use to tie the wire bundle. Refer

to SWPM 20-10-11 as an accepted

procedure.

LACING TAPE - RED 289T9001-21 -

(135C) 100 FT

7

WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA # WIRE #

W0176 24C 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AC 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AD 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AE 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

44 of 54

BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-16.

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

NOTE: Use the parts supplied in wire kit 289T1162-101 and top kit 015T1839-2 to do the work in this Figure.

FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

45 of 54

BOEING SERVICE BULLETIN 767-21-0235
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to the wire kit cut and code

table, to identify the wires as

shown and to cut to the necessary

lengths.

1 WIRE - RAW MATERIAL 289T1162-101W -

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 3

REMOVABLE, PER MIL-C39029/11

2

Refer to SWPM 20-81-12 and

SWPM 20-81-22 as accepted procedures.

3 RELAY SOCKET BACS16X1A 1

Refer to SWPM 20-81-12 as an

accepted procedure.

4 CONTACT, SOCKET BACC47DJ1 4

Refer to SWPM 20-81-19 as an

accepted procedure.

5 CONTACT, SOCKET BACC47ER1 1

Identified as D21731 M/W K10717.

Install within 6 inches of equipment.

6 ID TAPE - CONNECTOR 289T1162-10101 1

Use to tie the wire bundle. Refer

to SWPM 20-10-11 as an accepted

procedure.

LACING TAPE - RED 289T9001-21 -

(135C) 100 FT

7

WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-101W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA # WIRE #

W0176 24C 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AC 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AD 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 0AE 24 PK 120 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 5: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0176 -

WIRING CHANGES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

46 of 54

BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 2.

REFERENCE: 767 WDM 21-58-16.

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

NOTE: Use the parts supplied in wire kit 289T1162-102 and top kit 015T1839-2 to do the work in this Figure.

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to the wire kit cut and code

table, to identify the wires as

shown and to cut to the necessary

lengths.

1 WIRE - RAW MATERIAL 289T1162-102W -

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 4

REMOVABLE, PER MIL-C39029/11

2

FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

47 of 54

BOEING SERVICE BULLETIN 767-21-0235
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Use to tie the wire bundle. Refer

to SWPM 20-10-11 as an accepted

procedure.

LACING TAPE - BLUE 289T9001-61 -

(135C) 100 FT

3

WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-102W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA # WIRE #

W0184 09D 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 593 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 6: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

48 of 54

BOEING SERVICE BULLETIN 767-21-0235
This Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-16.

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

NOTE: Use the parts supplied in wire kit 289T1162-102 and top kit 015T1839-2 to do the work in this Figure.

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to the wire kit cut and code

table, to identify the wires as

shown and to cut to the necessary

lengths.

1 WIRE - RAW MATERIAL 289T1162-102W -

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 4

REMOVABLE, PER MIL-C39029/11

2

FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

49 of 54

BOEING SERVICE BULLETIN 767-21-0235
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Use to tie the wire bundle. Refer

to SWPM 20-10-11 as an accepted

procedure.

LACING TAPE - BLUE 289T9001-61 -

(135C) 100 FT

3

WIRE KIT - CUT AND CODE AS NECESSARY - 289T1162-102W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA # WIRE #

W0184 09D 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 593 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 7: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W0184 -

WIRING CHANGES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

50 of 54

BOEING SERVICE BULLETIN 767-21-0235
FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION

(SHEET 1 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

51 of 54

BOEING SERVICE BULLETIN 767-21-0235
FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION

(SHEET 2 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

52 of 54

BOEING SERVICE BULLETIN 767-21-0235
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION

(SHEET 3 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

53 of 54

BOEING SERVICE BULLETIN 767-21-0235
STEP TASK NAME IDENTIFICATION QTY MORE DATA

as D21731. Refer to

SOPM 20-50-10 as

an accepted procedure.

1 Identify TAPE, ID BACT19J4 1

Identified as

D21731. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

2 Install (New) RELAY BACR13CF2A 1 (a)

as K10717. Refer to

SOPM 20-50-10 as

an accepted procedure.

3 Identify TAPE, ID BACT19J4 1

Identified as

K10717. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

(a) If the bonding jumper is removed for relay installation, the bonding jumper must be installed and tested

after the relay is installed. Refer to SWPM 20-20-00 and SWPM 20-20-10 as accepted procedures to install

and test the bonding jumper.

FIGURE 8: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL NEW RELAY - INSTALLATION

(SHEET 4 OF 4)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: October 08, 2009

767-21-0235

54 of 54

BOEING SERVICE BULLETIN 767-21-0235