Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0254

Original Issue: June 07, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief

System (FDARS) and Activation of 3-way Valve Logic Change

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

CFR 300-774). 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 © 2013 Boeing.

Unpublished Work. All Rights Reserved.

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Boeing Company.

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

B. Concurrent Requirements ....................................... 9

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

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

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

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

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

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

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

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: EXISTING DUCT REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 3: WIRE DELETION IN PANEL P50 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50 . . . . . . . . . . . . . . . . 37

FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE

DIAGRAM) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) . 40

FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM) . . . . . . . . . . . . . . . . . . . . . . 43

FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 . . . . . . . . . . . . . . . . . . . . 46

FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT . . . . . . . . . . . . 50

FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36 . . . . . . . . . . . . . . . . . . . . . . . 58

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
FIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL . . . . . . . . . . . . . . . . . . . . . . . . 64

FIGURE 12: DIODE WIRE CONNECTION AT E8 EICAS PANEL . . . . . . . . . . . . . . . . . . . . . 67

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-21A0254

Original Issue: June 07, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief

System (FDARS) and Activation of 3-way Valve Logic Change

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring, or loss

of color caused by moisture or condensation being collected inside the display units can occur during operation

in hot and humid environments. If this service bulletin is not done, there is an increased risk that the flight

compartment display units could malfunction and become unserviceable because of moisture ingress. Flight

compartment indication blanking can cause unscheduled maintenance and airplane downtime. Also, loss of the

primary attitude information on both primary display units could lead to flight crew confusion and difficulty in the

transition to standby attitude indication. The inability of the flight crew to transition from primary attitude indication

to standby attitude indication during a critical phase of flight can result in an unsafe flight condition.

Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring, or loss of

color caused by moisture or condensation being collected inside the display units during operation in hot and

humid environments. The reports have included single display unit and multiple display unit malfunctions. Boeing

is aware of instances that are the likely causes of display unit malfunctions related to moisture or condensation

ingress. These instances are as follows; an unserviceable air conditioning pack water separation system, that

allowed water to be delivered to the flight compartment in the air conditioned air, a malfunction of an air

conditioning pack which caused ice to be delivered to the flight compartment in the air conditioned air, and the

most frequent instance was display units being cold soaked by the air conditioned air delivered from the air

conditioning packs by the Electrical/Electronic cooling system through the 3-way valve (also called the manifold

interconnect valve) in hot and humid conditions. As a result of these findings, the control logic of the 3-way valve

is changed so that the valve will open after five minutes at an altitude above 10,000 feet, and close at an altitude

below 10,000 feet. Limiting the 3-way valve to open after five minutes above 10,000 feet will decrease the amount

of moisture or condensation that can collect in the display units because of the reduced water content in the

atmosphere at higher altitudes.

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The changes described above were implemented in the affected airplanes during production but were found to

cause unacceptable airflow noise on the flight deck when transitioning 10,000 feet altitude. This increased noise

made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce

airflow noise in the flight deck was not immediately available, the 3-way valve logic changes and 10,000 foot

altitude switch were deactivated before airplane delivery. The noise is resolved by adding a Flight Deck Air Relief

System (FDARS) consisting of ducting, an outlet valve, and related wiring, relays, and diodes. Airflow noise is

reduced on the flight deck by the outlet valve exhausting a portion of equipment cooling air into the area below

the flight deck when the 3-way-valve is activated at 10,000 feet. This service bulletin describes installation of

FDARS components and activation of the 10,000 foot altitude switch and related logic changes.

Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR B12900-260)

In the area forward of the main equipment center and under the flight deck floor, replace a duct for equipment

cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS) components. Install

mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring within panel P36 and among

panels and new outlet valve. Modify relay installation in P36. Install diodes in E8 EICAS panel. Do an operational

test of the revised system including the control logic of the 3-way valve (also called the manifold interconnect

valve) and the added outlet valve.

EFFECTIVITY

767-300F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

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ALERT ALERT
COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Boeing recommends that the change given in this service bulletin be done within 72 months after the original

issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of July 29, 2009. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All 54.95 31.50

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0254

Original Issue: June 07, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief

System (FDARS) and Activation of 3-way Valve Logic Change

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Serial Number data.

This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR B12900-260 for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 767-300F Airplanes identified below.

Airplane Models:

767-300F

Variable Number Group

VT551 - VT552 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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C. Reason

This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring,

or loss of color caused by moisture or condensation being collected inside the display units can occur

during operation in hot and humid environments. If this service bulletin is not done, there is an increased

risk that the flight compartment display units could malfunction and become unserviceable because of

moisture ingress. Flight compartment indication blanking can cause unscheduled maintenance and

airplane downtime. Also, loss of the primary attitude information on both primary display units could

lead to flight crew confusion and difficulty in the transition to standby attitude indication. The inability

of the flight crew to transition from primary attitude indication to standby attitude indication during a

critical phase of flight can result in an unsafe flight condition.

Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring,

or loss of color caused by moisture or condensation being collected inside the display units during

operation in hot and humid environments. The reports have included single display unit and multiple

display unit malfunctions. Boeing is aware of instances that are the likely causes of display unit

malfunctions related to moisture or condensation ingress. These instances are as follows; an

unserviceable air conditioning pack water separation system, that allowed water to be delivered to the

flight compartment in the air conditioned air, a malfunction of an air conditioning pack which caused

ice to be delivered to the flight compartment in the air conditioned air, and the most frequent instance

was display units being cold soaked by the air conditioned air delivered from the air conditioning packs

by the Electrical/Electronic cooling system through the 3-way valve (also called the manifold interconnect

valve) in hot and humid conditions. As a result of these findings, the control logic of the 3-way valve is

changed so that the valve will open after five minutes at an altitude above 10,000 feet, and close at an

altitude below 10,000 feet. Limiting the 3-way valve to open after five minutes above 10,000 feet will

decrease the amount of moisture or condensation that can collect in the display units because of the

reduced water content in the atmosphere at higher altitudes.

The changes described above were implemented in the affected airplanes during production but were

found to cause unacceptable airflow noise on the flight deck when transitioning 10,000 feet altitude.

This increased noise made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear.

Because a solution to reduce airflow noise in the flight deck was not immediately available, the 3-way

valve logic changes and 10,000 foot altitude switch were deactivated before airplane delivery. The

noise is resolved by adding a Flight Deck Air Relief System (FDARS) consisting of ducting, an outlet

valve, and related wiring, relays, and diodes. Airflow noise is reduced on the flight deck by the outlet

valve exhausting a portion of equipment cooling air into the area below the flight deck when the

3-way-valve is activated at 10,000 feet. This service bulletin describes installation of FDARS components

and activation of the 10,000 foot altitude switch and related logic changes.

Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.

D. Description

In the area forward of the main equipment center and under the flight deck floor, replace a duct for

equipment cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS)

components. Install mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring

within panel P36 and among panels and new outlet valve. Modify relay installation in P36. Install diodes

in E8 EICAS panel. Do an operational test of the revised system including the control logic of the 3-way

valve (also called the manifold interconnect valve) and the added outlet valve.

The changes in this service bulletin will not change the Engine Indication and Crew Alerting System

(EICAS).

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BOEING SERVICE BULLETIN 767-21A0254

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

Affected Maintenance Zones

Model Zone

767-300F 117, 118, 119

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done within 72 months after the

original issue date of this service bulletin.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

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 inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

FIGURE 1 1 2.00 2.00

FIGURE 2 1 3.10 3.10

FIGURE 3 1 0.10 0.10

FIGURE 4 1 0.10 0.10

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Task Number of Persons Task Hours Elapsed Hours

FIGURE 5 (Wire Dia- 2 24.70 12.35

gram) and FIGURE

9 (Wire Installation)

FIGURE 6 and FIG- 2 17.20 8.60

URE 7, (Wire Diagrams) and FIGURE

10, (Wire Installation)

FIGURE 8 1 1.00 1.00

FIGURE 11 (Diode 1 1.75 1.75

Installation) and FIGURE 12, (Wire Diagram)

Test 2 3.00 1.50

Close Access 2 1.00 0.50

TOTAL FOR EACH AIRPLANE 54.95 31.50

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All +6.7 +927.9

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12900-260

b. Boeing Service Related Problem (SRP) 767-SRP-21-0179

c. Service Bulletin Index D624T001

d. Standard Overhaul Practices Manual (SOPM) 20-50-10

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10, 20-61-11,

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

f. 767 Aircraft Maintenance Manual (AMM) 20-10-33, 21-22-02, 21-58-00, 24-22-00, 25-00-00

g. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

214T1011 Duct Installation - Flight Deck Section 41

217T2013 Duct Installation - Instrument Panel Cooling System

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Aircraft Maintenance Manual 21-58

767 Wiring Diagram Manual 21-58, Equipment List

767 Fault Isolation Manual 21-58

767 Illustrated Parts Catalog 21-22, 21-58

767 System Schematic Manual 21-58

767 Dispatch Deviations Guide 2.21-58

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 affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

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

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

TOP KIT - FLIGHT April 30, 2013 2 308 $16,338.00

DECK AIR RELIEF

SYSTEM

015T1884-1

B. Industry Support Information

Boeing warranty remedies are available for 767 airplanes in warranty as of July 29, 2009. For task hour

reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty &

Product Assurance Contracts. The kits for airplanes in warranty as of that date will be supplied at no

charge. Send a purchase order for the kits to Boeing Material Management. Please refer to this service

bulletin number and reference the airplane variable number(s) in your purchase order. The warranty

remedies will expire eight years from the original issue date of this service bulletin.

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. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 1 2 8 9 10 11

015T1884-1 1 1 1 1 1 1

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ALERT ALERT
Top Kit

Wire Kit 015T1884-1

289T1169-109 1

289T1169-110 1

289T1169-111 1

ALL

KIT 015T1884-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 8 9 10 11

Qty

141T1226Y33 . 1 . . . . STIFFENER (a), (b)

214T1120-313 . 1 . . . . DUCT ASSY

214T1120-315 . 1 . . . . DUCT ASSY

214T1120-3311 1 . . . . . DUCT ASSY 214T1120-3218 (c)

214T3436-1187 . 1 . . . . ORIFICE ASSY

214T6419Y40 . 1 . . . . BRACKET (a), (b)

217T2434U10 . 1 . . . . BRACKET (a), (b)

RETAINER CLIP

ASSY

411A4902-7 . . . 2 . .

VALVE - AIR

SHUTOFF

67-2951-001 . 1 . . . .

69B42275-4 . 1 . . . . SCREEN ASSY

LACING TAPE -

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 . . . 1 1 .

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . . . . 1 .

HOSEDUCT,

SLEEVE

AS1506-14D30 . 1 . . . .

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 . . 1 . . .

CLAMP, MISCELLANEOUSBACC10DU500ABE . 2 . . . .

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ALERT ALERT
ALL

KIT 015T1884-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 8 9 10 11

Qty

BACC10ME20-1 . 2 . . . . SUPPORT, DUCT

BONDING

JUMPER

BACJ40A20-7 . 1 . . . .

BACN10YD1G . 4 . . . . NUTPLATE

BACN10YR3CD . 3 . . . . NUT (d)

BACR13CD2 . . 1 . . . RELAY

RIVET, UNIVER- (d), (e)

SAL HD

BACR15FT6KE5C . 8 . . . .

RIVET, UNIVER- (d), (e)

SAL HD

BACR15FT6KE6C . 4 . . . .

BACR15FT6KE7C . 3 . . . . RIVET (d), (e)

BACS12GU3K7 . 7 . . . . SCREW, CAP (d)

BACS38K2 3 . . . . . STRAP (d)

BACS38K6 4 1 . . . . STRAP (d)

BACT19J4 . . 8 . . 2 TAPE, ID (d)

PACKING, PREFORMEDMS29512-08 1 . . . . .

NAS1149D0316J . 6 . . . . WASHER (d)

NAS1149D0332H . 8 . . . . WASHER, PLAIN (d)

NAS1922-0350-3 . 2 . . . . CLAMP, HOSE

NAS1922-0525-3 . 3 . . . . CLAMP, HOSE

TIME DELAY RELAY

TDH-1852-3002 . . 1 . . .

TIME DELAY RELAYTDH-8050-3003P . . 1 . . .

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 . . . . . 2

(a) This part not used in production.

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ALERT ALERT
ALL

KIT 015T1884-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 8 9 10 11

Qty

(b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify

these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts

are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this

service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service

Letter 767-SL-00-014 for more information.

(c) You cannot use the existing part to replace the new or changed part.

(d) There are more parts than are necessary.

(e) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer

than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,

substitute fasteners may be supplied in kits.

KIT 289T1169-109

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-109W 1

289T1169-10301 1 ID - CONNECTOR

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT12C12S6 1

CONTACT, SOCK- (a)

ET

BACC47CP1S 14

BACC47DE7A 5 CONTACT, PIN (a)

(a) There are more parts than are necessary.

KIT 289T1169-110

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-110W 1

289T1169-10401 1 ID - CONNECTOR

289T1169-10402 1 ID - CONNECTOR

289T1169-10403 1 ID - DIODE

BACC47DE7A 3 CONTACT, PIN (a)

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ALERT ALERT
KIT 289T1169-110

New Part Number Qty Name Notes

BACC47DE8A 3 CONTACT (a)

CONTACT, SOCK- (a)

ET

BACC47DJ1 4

CONTACT, SOCK- (a)

ET

BACC47ER1 12

BACM15C3F 1 TERMINAL BLOCK

BACS16AG1 1 RELAY SOCKET

BACS16AH1 1 RELAY SOCKET

CONTACT, PIN, (a)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 12

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 1

(a) There are more parts than are necessary.

KIT 289T1169-111

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-111W 1

BACC47CN1S 6 CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47ER1 5

CONTACT, PIN, (a)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 6

(a) There are more parts than are necessary.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Part Number / Specification QTY Name Notes

BMS5-95 4 oz SEALANT (a)

BMS10-11, TYPE I 4 oz PRIMER (a)

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ALERT ALERT
Part Number / Specification QTY Name Notes

BMS 5-157 TYPE I, CLASS 1, 5 ft TAPE (a)

GRADE A, COMPOSITION MPVF

MS20995N32 (MS20995NC32 1 ft LOCKWIRE

optional)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification

(BMS) for supplier data.

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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ALERT ALERT
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

3. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque limits to tighten nuts and bolts are in SRM Chapter 51

4. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

5. 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.

6. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

7. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

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

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

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

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

must be used.

9. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

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ALERT ALERT
10. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

11. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

B. WORK INSTRUCTIONS

1. Remove electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.

2. Gain access to the main equipment center and the area under the left and right sides of the flight

deck floor.

3. Replace existing duct with new duct in accordance with FIGURE 1.

4. Install new Flight Deck Air Relief System (FDARS) components including mounting brackets, ducts,

orifice, outlet valve and screen in accordance with FIGURE 2.

5. Modify wiring as follows:

a. Delete wire in panel P50 in accordance with FIGURE 3.

b. Delete wire between panel P36 and panel P50 in accordance with FIGURE 4.

c. Add wires and connector between panel P36 and new valve in accordance with FIGURE 5

(wire diagram) and FIGURE 9 (wire installation).

d. Modify wiring within Panel P36 in accordance with FIGURE 6 and FIGURE 7 (wire diagrams)

and FIGURE 10 (wire installation).

6. Modify relay installation in panel P36 in accordance with FIGURE 8.

7. Install diodes in accordance with FIGURE 11, (installation) and FIGURE 12, (wire diagram).

8. Restore electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.

9. Do an Operational Test - Manifold Interconnect Valve (Reconfiguration) - Post SB 767-25-0254.

Refer to 767 AMM 21-58-00 as an acceptable procedure.

NOTE: This tests operating logic of the existing 3-way-valve (also called the manifold interconnect

valve) in conjunction with the new outlet valve.

10. Put the airplane back to a serviceable condition.

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ALERT ALERT
FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 1 OF 6)

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ALERT ALERT
FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 2 OF 6)

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ALERT ALERT
FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 3 OF 6)

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ALERT ALERT
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 this figure.

Step Task Name Identification Qty More Data

1 Remove STRAP - 5

2 Remove / Keep SLEEVE AS1506-15D23 1

3 Remove / Keep SLEEVE AS1506-06D32 1

4 Remove / Keep CLAMP NH102689-0450 1

FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 4 OF 6)

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ALERT ALERT
Step Task Name Identification Qty More Data

5 Disconnect CONNECTOR D20366 -

Remove LOCKWIRE - -

TEMPERATURE CON- 3000-46-41 1

TROL SWITCH

Remove / Keep

PACKING, PRE- MS29512-08 1

FORMED

Remove

Remove / Keep SCREW BACS12GU( ) 2

Remove / Keep BRACKET 217T1438-3 1 (a)

6 Remove DUCT ASSY 214T1120-3218 1

7 Install (New) DUCT ASSY 214T1120-3311 1

8 Install (Kept) BRACKET 217T1438-3 1 (a)

Install (Kept) SCREW BACS12GU( ) 2

TEMPERATURE CON- 3000-46-41 1

TROL SWITCH

Install (Kept)

PACKING, PRE- MS29512-08 1

FORMED

Install (New)

MS20995N32 - (b)

(MS20995NC32 optional)

Install (New) LOCKWIRE

Connect CONNECTOR D20366 -

9 Install (Kept) CLAMP NH102689-0450 1

10 Install (New) STRAP BACS38K6 1 (c)

11 Install (Kept) SLEEVE AS1506-15D23 1

Install (New) STRAP BACS38K6 2 (c)

12 Install (Kept) SLEEVE AS1506-06D32 1

Install (New) STRAP BACS38K2 2 (c)

(a) Includes Marker BAC27TEC334.

(b) Refer to 767 AMM 20-10-33 as an accepted procedure.

(c) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H

OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE

STRAPS AND (8) FOR .30 WIDE STRAPS

FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 5 OF 6)

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ALERT ALERT
The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

STRAP BACS38K2 1

STRAP BACS38K6 1

FIGURE 1: EXISTING DUCT REPLACEMENT

(SHEET 6 OF 6)

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ALERT ALERT
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 1 OF 7)

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ALERT ALERT
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 2 OF 7)

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ALERT ALERT
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 3 OF 7)

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ALERT ALERT
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 this figure.

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 4 OF 7)

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ALERT ALERT
Step Task Name Identification Qty More Data

1 Retract INSULATION - - At both frames.

2 Remove STRAP - 1

For access to install

rivets.

3 Disconnect DUCT - -

AFT of side of

frame.

4 Install (New) BRACKET 214T6419Y40 1

RIVET, UNIVERSAL BACR15FT6KE5C 3

HD

Install (New)

Through frame and

chord.

5 Remove RIVET - 1

6 Install (New) BRACKET 217T2434U10 1 AFT side of frame.

Install (New) STIFFENER 141T1226Y33 1 FWD side of frame.

Through frame,

chord and stiffener.

Install (New) RIVET BACR15FT6KE7C 1

Through bracket,

frame and stiffener.

RIVET, UNIVERSAL BACR15FT6KE6C 2

HD

Install (New)

Through bracket and

frame.

RIVET, UNIVERSAL BACR15FT6KE5C 2

HD

Install (New)

Through frame and

stiffener.

RIVET, UNIVERSAL BACR15FT6KE5C 1

HD

Install (New)

7 Install (New) SUPPORT, DUCT BACC10ME20-1 2

Install (New) SCREW, CAP BACS12GU3K7 4

Install (New) WASHER NAS1149D0316J 4

Install (New) NUTPLATE BACN10YD1G 4

8 Install (New) ORIFICE ASSY 214T3436-1187 1 (a)

9 Install (New) HOSEDUCT, SLEEVE AS1506-14D30 1

Install (New) CLAMP, HOSE NAS1922-0350-3 1

10 Install (New) DUCT ASSY 214T1120-313 1

Install (New) CLAMP, HOSE NAS1922-0350-3 1

Install (New) CLAMP, HOSE NAS1922-0525-3 1

11 Install (New) DUCT ASSY 214T1120-315 1 (b)

Install (New) CLAMP, HOSE NAS1922-0525-3 1

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Step Task Name Identification Qty More Data

VALVE - AIR SHUT- 67-2951-001 1

OFF

12 Install (New)

CLAMP, MISCELLA- BACC10DU500ABE 2

NEOUS

Install (New)

13 Install (New) SCREEN ASSY 69B42275-4 1

Install (New) CLAMP, HOSE NAS1922-0525-3 1

14 Install (New) BONDING JUMPER BACJ40A20-7 1 (c)

Drill HOLE - 1 0.218 - 0.229 IN DIA

Install (New) SCREW, CAP BACS12GU3K7 2

Install (New) WASHER, PLAIN NAS1149D0332H 6

Install (New) NUT BACN10YR3CD 2

15 Connect DUCT - -

16 Install (New) STRAP BACS38K6 1 (d)

17 Repair INSULATION - -

BMS 5-157 TYPE I, - (e)

CLASS 1, GRADE A,

COMPOSITION MPVF

Install (New) TAPE

(a) Refer to 767 AMM 21-22-02 as an accepted procedure.

(b) Align the alignment mark on elbow duct to the top of the duct support to make sure that the airflow will

be exhausted downward at the catwalk surface.

(c) CLEAN, ASSEMBLE AND TEST GROUND. REFER TO SWPM 20-20-10 AS AN ACCEPTED PROCEDURE. MEASURE RESISTANCE BETWEEN VALVE BODY AND FRAME INCLUDING SCREW, NUT

AND WASHERS. MAXIMUM RESISTANCE 0.005 OHM.

(d) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H

OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE

STRAPS AND (8) FOR .30 WIDE STRAPS

(e) Use tape to repair insulation and to seal insulation to brackets. Refer to 767 AMM 25-00-00 as an accepted

procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

NUT BACN10YR3CD 1

SCREW, CAP BACS12GU3K7 1

WASHER NAS1149D0316J 2

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 6 OF 7)

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ALERT ALERT
Name Identification Qty More Data

RIVET, UNIVERSAL BACR15FT6KE5C 2

HD

RIVET, UNIVERSAL BACR15FT6KE6C 2

HD

RIVET BACR15FT6KE7C 2

WASHER, PLAIN NAS1149D0332H 2

FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION

(SHEET 7 OF 7)

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ALERT ALERT
Reference : 767 WDM 21-58-16

No parts are installed in this figure.

FIGURE 3: WIRE DELETION IN PANEL P50

(SHEET 1 OF 1)

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ALERT ALERT
Reference : 767 WDM 21-58-16

No parts are installed in this figure.

FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50

(SHEET 1 OF 1)

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ALERT ALERT
Reference : 767 WDM 21-58-41

NOTE: The parts are in Wire Kit 289T1169-109. The wire is identified as 289T1169-109W.

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

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-90-11 as an

accepted procedure.

1 CONTACT, PIN BACC47DE7A 4

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

2 CONTACT, SOCKET BACC47CP1S 12

Refer to SWPM 20-61-11 as an

accepted procedure.

CONNECTOR, ELECTRI- BACC45FT12C12S6 1

CAL, PLUG, STRAIGHT,

BAYONET COUPLING

3

Refer to SWPM 20-10-11 as an

accepted procedure.

ID - CONNECTOR 289T1169-10301 1

(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11

as an accepted procedure.

FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W0756 132 20 PA 207 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W0756 133 24 PK 436 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0756 135 20 PA 207 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W0756 136 24 PK 436 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0756 137 20 PA 207 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W0756 138 24 PK 436 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0756 139 24 PK 436 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0756 140 20 PA 207 BMS 13-48, TYPE 10, CLASS 1, AWG 20

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

CONTACT, PIN BACC47DE7A 1

CONTACT, SOCKET BACC47CP1S 2

FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21A0254

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Reference : 767 WDM 21-58-41

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
NOTE: The parts are in Wire Kit 289T1169-110. The wire is identified as 289T1169-110W.

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

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-81-19 as an

accepted procedure. (a)

1 CONTACT, SOCKET BACC47ER1 8

Refer to SWPM 20-90-11 as an

accepted procedure.

2 CONTACT, PIN BACC47DE7A 2

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 9

REMOVABLE, PER MIL-C39029/11

3

Refer to SWPM 20-81-22 as an

accepted procedure.

4 RELAY SOCKET BACS16AG1 1

Refer to SWPM 20-10-11 as an

accepted procedure.

ID - CONNECTOR 289T1169-10401 1

Refer to SWPM 20-81-22 as an

accepted procedure.

5 RELAY SOCKET BACS16AH1 1

Refer to SWPM 20-10-11 as an

accepted procedure.

ID - CONNECTOR 289T1169-10402 1

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

6 CONTACT, SOCKET BACC47DJ1 3

Refer to SWPM 20-90-11 as an

accepted procedure.

7 CONTACT BACC47DE8A 2

Refer to SWPM 20-90-11 as an

accepted procedure.

TERMINAL BLOCK RESIS- YHLZR-17 1

TOR ASSEMBLY MODULE

8

Refer to SWPM 20-90-11 as an

accepted procedure.

ID - DIODE 289T1169-10403 1

(b), Refer to SWPM 20-90-11 as

an accepted procedure.

9 TERMINAL BLOCK BACM15C3F 1

(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11

as an accepted procedure.

(b) INSTALL Z BLOCK AT POSITION 21-22 OF TB216

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W0184 597 24 PK 16 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 731 20 PA 93 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W0184 732 24 PK 45 BMS 13-48, TYPE 11, CLASS 1, AWG 24

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W0184 733 24 PK 45 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 734 20 PA 93 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W0184 735 24 PK 40 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 736 24 PK 45 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 737 24 PK 80 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 18L 24 PK 55 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 18M 24 PK 50 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 18N 24 PK 50 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 55P 24 PK 30 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0184 55R 24 PK 22 BMS 13-48, TYPE 11, CLASS 1, AWG 24

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

CONTACT, PIN BACC47DE7A 1

CONTACT BACC47DE8A 1

CONTACT, SOCKET BACC47DJ1 1

CONTACT, SOCKET BACC47ER1 2

CONTACT, PIN, M39029/11-145 1

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Reference : 767 WDM 21-58-16

FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Reference : 767 WDM 21-58-16

NOTE: The parts are in Wire Kit 289T1169-111. The wire is identified as 289T1169-111W.

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

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-81-19 as an

accepted procedure. (a)

1 CONTACT, SOCKET BACC47ER1 4

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

2 CONTACT, PIN BACC47CN1S 5

FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-90-11 as an

accepted procedure. (a)

CONTACT, PIN, CRIMP M39029/11-145 5

REMOVABLE, PER MIL-C39029/11

3

(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11

as an accepted procedure.

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W0176 89K 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 68G 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 68H 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 69K 24 PK 45 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 68F 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

W0176 68K 24 PK 60 BMS 13-48, TYPE 11, CLASS 1, AWG 24

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

CONTACT, SOCKET BACC47ER1 1

CONTACT, PIN BACC47CN1S 1

CONTACT, PIN, M39029/11-145 1

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

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FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-21A0254

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FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-21A0254

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FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
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 this figure.

Step Task Name Identification Qty More Data

K10725 Near Side,

(a)

1 Install (New) TAPE, ID BACT19J4 1

D20325 Far Side,

(a)

Install (New) TAPE, ID BACT19J4 1

Alternate part number TDH1852-30022 Install (New) TIME DELAY RELAY TDH-1852-3002 1

K10723 Near Side,

(a)

3 Install (New) TAPE, ID BACT19J4 1

D20323 Far Side,

(a)

Install (New) TAPE, ID BACT19J4 1

4 Install (New) RELAY BACR13CD2 1

VINYL MARKER (1 2 BAC27TEX4697 1 17

3...30) VERTICAL

5 Install (New)

K10718 Near Side,

(a)

6 Install (New) TAPE, ID BACT19J4 1

D31620 Far Side,

(a)

Install (New) TAPE, ID BACT19J4 -

Alternate part number TDH8050-3003P7 Install (New) TIME DELAY RELAY TDH-8050-3003P 1

8 Remove RELAY BACR13CD2 1

9 Remove TAPE, ID BACT19J4 1 D21730 Far Side

Remove TAPE, ID BACT19J4 1 K10355 Near Side

(a) Mark the ID tape with this ID. Refer to SOPM 20-50-10 as an accepted procedure.

The parts shown in the table below are provided as extra parts for this figure.

Name Identification Qty More Data

TAPE, ID BACT19J4 3

FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36

(SHEET 4 OF 4)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 1 OF 8)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 2 OF 8)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 3 OF 8)

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BOEING SERVICE BULLETIN 767-21A0254

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 4 OF 8)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 5 OF 8)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 6 OF 8)

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FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 7 OF 8)

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ALERT ALERT
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 this figure.

Step Task Name Identification Qty More Data

1 Install (New) RETAINER CLIP ASSY 411A4902-7 2

LACING TAPE - RED - 829A9001-2 1 W0756

PRESSURIZED (TEMP

135 DEG)

2 Install (New)

FIGURE 9: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT

(SHEET 8 OF 8)

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FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 1 OF 6)

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FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 2 OF 6)

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FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 3 OF 6)

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FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 4 OF 6)

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FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
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 this figure.

Step Task Name Identification Qty More Data

LACING TAPE - RED - 829A9001-2 1 W0176

PRESSURIZED (TEMP

135 DEG)

1 Install (New)

LACING TAPE - BLUE 829A9001-5 1 W0184

- PRESSURIZED

(TEMP 135 DEG)

2 Install (New)

FIGURE 10: INSTALLATION OF WIRE WITHIN PANEL P36

(SHEET 6 OF 6)

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FIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL

(SHEET 1 OF 3)

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FIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-21A0254

ALERT ALERT
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 this figure.

Step Task Name Identification Qty More Data

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

1 Install (New)

2 Install (New) TAPE, ID BACT19J4 1 R1196 (a)

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

3 Install (New)

4 Install (New) TAPE, ID BACT19J4 1 R1197 (a)

(a) Mark the ID tape with this ID. Refer to SOPM 20-50-10 as an accepted procedure.

FIGURE 11: DIODE INSTALLATION AT E8 EICAS PANEL

(SHEET 3 OF 3)

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Reference : 767 WDM 21-58-16

No parts are installed in this figure.

FIGURE 12: DIODE WIRE CONNECTION AT E8 EICAS PANEL

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 767-21A0254

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