Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0247

Original Issue: October 10, 2011

Revision 1: April 09, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - 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 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 © 2011 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing

liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

Company.

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ALERT ALERT

BLANK PAGE
Table of Contents

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

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

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

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

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 30

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 31

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION [Group 1-2] . . . . . 37

FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION [Group

1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

WIRING CHANGE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING [Group 1-2] . . . . . . . 51

FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD

FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES [Group 1-2] . . . . . . . . . . 59

FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING [Group 1-2] . . . . . . 60

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
FIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE [Group 1-2] . . 63

FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING [Group 1-2] . . . . . . . . . . . . . 64

FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE [Group 1-2] . . . . . . . . . 66

FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT

[Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

FIGURE 12: EXISTING DUCT REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . 77

FIGURE 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) [Group 1]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84

FIGURE 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM) [Group 2-3]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 1] . . . . . . . . . . . . . . . . 88

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 2-3] . . . . . . . . . . . . . . . 91

FIGURE 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 1] . . . . . . . . . . . . . . . . 94

FIGURE 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM) [Group 2-3] . . . . . . . . . . . . . . . 96

FIGURE 20: FDARS RELAY INSTALLATION IN P36 . . . . . . . . . . . . . . . . . . . . . . . . . . . 98

FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE . . . . . . . . . . . . . . . 102

FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36 . . . . . . . . . . . . . . . . . . . . . 110

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 767-21A0247

Original Issue: October 10, 2011

Revision 1: April 09, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

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.

Airplanes VR273-VR279 were added to this service bulletin effectivity.

More work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin.

Original modification instruction is now identified as Part 1 and additional modification is identified as Part 2.

Original airplanes require both Part 1 and Part 2 modification. Added airplanes require only Part 2 modification.

REASON FOR REVISION

This revision is issued to reduce noise in the flight compartment resulting when the operating logic of the

3-way-valve (also called the manifold interconnect valve) is changed as described in the original release of this

service bulletin. Noise in the flight compartment caused by the increased airflow of the 3-way valve logic system

changes made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Noise is reduced by

adding a Flight Deck Air Relief System (FDARS) consisting of ducting and an outlet valve and additional relays.

The outlet valve reduces airflow noise on the flight deck by exhausting a portion of the flight deck air distribution

air into the area below the flight deck floor when the 3-way-valve is closed (nominally below 10,000 feet).

These sections were changed:

1. Summary Section:

a. Added Revision 1 statement to Background paragraph and revised position of some existing text;

b. Added Summary Table to Background paragraph to comply with current standards;

c. Added Revision 1 statement to Action paragraph and clarified some existing text;

d. Updated Compliance paragraph to refer to Revision 1 date;

e. Updated Manpower Table;

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f. Expanded illustration.

2. PLANNING INFORMATION:

a. Paragraph 1.A., Effectivity: Added airplanes which had the intent of the original issue of this service

bulletin incorporated during production but which still require the FDARS related parts. These

airplanes are added as Group 3;

b. Paragraph 1.C., Reason - Added Revision 1 statement and revised position of some existing text;

c. Paragraph 1.D., Description - Added Revision 1 statement and clarified some existing text;

d. Paragraph 1.E., Compliance - Updated paragraph to refer to Revision 1 issue date;

e. Paragraph 1.G., Manpower - Added tables for added work;

f. Paragraph 1.Weight and Balance Changes - Updated table and added table.

3. MATERIAL INFORMATION - Updated entire section to show that kits for original airplanes (Groups 1

and 2) will be updated, before shipment, to include FDARS related parts. Kits for added airplanes

(Group 3) will include only FDARS parts. Also, additional operator-furnished material is identified.

4. ACCOMPLISHMENT INSTRUCTIONS:

a. Paragraph 3.B., WORK INSTRUCTIONS - Revised work instructions into Part 1 and Part 2. Part

1 contains original rework instructions applicable to original airplanes. Part 2 contains added rework

instructions applicable to original airplanes and added airplanes;

b. FIGURES 1-11 - Added applicability to original Figures 1 through 11 to be applicable to original

airplanes;

c. FIGURES 12-22 - Added these figures with applicability, as marked, for original airplanes and

added airplanes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-21A0247

Original Issue: October 10, 2011

Revision 1: April 09, 2013

ATA System: 2158

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

Refer to Paragraph 1.B., Concurrent Requirements.

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 could contribute to 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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Accomplishment of this service bulletin installs a new relay in the P36 Left Miscellaneous Electrical Equipment

Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch to the E8 Engine

Indication and Crew Alerting System (EICAS) rack to change the control logic of the 3-way valve operation

above and below an altitude of 10,000 feet. This change reduces the amount of moisture or condensation that

can collect in the flight compartment display units and thus reduce malfunction occurrences.

Revision 1 - Incorporation of the equivalent change in production was found to cause excessive noise in the

flight compartment caused by the increased flight deck air distribution airflow. This increased noise made the

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

the flight deck was not immediately available, Information Notice 767-21A0247 IN 01 was issued advising

operators to not do this service bulletin until further improvements could be added. This revision adds ducting,

an outlet valve, and related wiring to reduce noise in the flight compartment caused by flight deck air distribution

air flow. These added components form the Flight Deck Air Relief System (FDARS).

Revision 1 also adds airplanes to the effectivity as Group 3 airplanes. These airplanes received changes

equivalent to the original release of this service bulletin during production. Therefore, these airplanes require

only the FDARS-related additions.

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

Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 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

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
ACTION (PRR B12900-260)

Group 1-2:

Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch, and

attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Install a tube and fittings

between the pressure switch and nearby existing Pitot system tubing. Open the P36 left miscellaneous equipment

panel in the MEC and make changes to wire bundle W176. Make changes to wire bundle W596 between the

P36 left miscellaneous equipment panel and P50 Electrical Systems Card File panel. In the P50 Electrical

Systems Card File panel, make changes to wire bundle W1114. Make changes to wire bundle W1702 between

the P36 left miscellaneous equipment panel and E8 EICAS rack. At the E8 EICAS rack, make changes to wire

bundle W2000. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay

K10718. Flush and leak check the disturbed pitot system.

Revision 1 - In the area forward of the main equipment bay 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. 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).

EFFECTIVITY

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

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 6 years after the Revision 01

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

Group 1 - 2 61.85 41.65

Group 3 46.40 26.20

MATERIAL INFORMATION

Boeing Supplied Kits.

Operator Supplied Parts/Materials.

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BOEING SERVICE BULLETIN 767-21A0247

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

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ALERT ALERT
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ALERT ALERT
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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT

BLANK PAGE
Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0247

Original Issue: October 10, 2011

Revision 1: April 09, 2013

ATA System: 2158

SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control 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 Document 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

767-300F airplanes, Variable Numbers VR201 thru VR211, and

VW701 thru VW721 that must do Boeing service bulletin 767-21-0235

prior to or concurrent with this service bulletin.

1 -

767-300F airplanes, Variable Numbers VR266 thru VR272 that have

had the intent of Boeing service bulletin 767-21-0235 incorporated

prior to delivery.

2 -

767-300F airplanes, Variable Numbers VR273 thru VR279, that have

had the intent of the original issue of this service bulletin incorporated

prior to delivery.

3 -

Airplane Models:

767-300F

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Variable Number Group

VR201 - VR211 1

VR266 - VR272 2

VR273 - VR279 3

VW701 - VW721 1

2. Spares Affected

None.

B. Concurrent Requirements

Group 1:

The service bulletin listed below must be done on Group 1 airplanes before or at the same time as this

service bulletin:

Group 1:

Company Service Bulletin Description

This service bulletin gives instructions to install

a relay and related wiring in the P36 left miscellaneous equipment panel to change the control

logic of the equipment cooling 3-way valve.

767-21-0235 Original Issue or

Revision 1

Boeing

Group 2-3:

None.

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 could contribute to 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

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ALERT ALERT
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.

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

Equipment Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch

to the E8 Engine Indication and Crew Alerting System (EICAS) rack to change the control logic of the

3-way valve operation above and below an altitude of 10,000 feet. This change reduces the amount

of moisture or condensation that can collect in the flight compartment display units and thus reduce

malfunction occurrences.

Revision 1 - Incorporation of the equivalent change in production was found to cause excessive noise

in the flight compartment caused by the increased flight deck air distribution airflow. This increased

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

to reduce the noise in the flight deck was not immediately available, Information Notice 767-21A0247

IN 01 was issued advising operators to not do this service bulletin until further improvements could be

added. This revision adds ducting, an outlet valve, and related wiring to reduce noise in the flight

compartment caused by flight deck air distribution air flow. These added components form the Flight

Deck Air Relief System (FDARS).

Revision 1 also adds airplanes to the effectivity as Group 3 airplanes. These airplanes received changes

equivalent to the original release of this service bulletin during production. Therefore, these airplanes

require only the FDARS-related additions.

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

Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin.

D. Description

Group 1-2:

Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch,

and attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Install a tube

and fittings between the pressure switch and nearby existing Pitot system tubing. Open the P36 left

miscellaneous equipment panel in the MEC and make changes to wire bundle W176. Make changes

to wire bundle W596 between the P36 left miscellaneous equipment panel and P50 Electrical Systems

Card File panel. In the P50 Electrical Systems Card File panel, make changes to wire bundle W1114.

Make changes to wire bundle W1702 between the P36 left miscellaneous equipment panel and E8

EICAS rack. At the E8 EICAS rack, make changes to wire bundle W2000. In the P36 left miscellaneous

equipment panel, remove relay K10355 and install new relay K10718. Flush and leak check the disturbed

pitot system.

Revision 1 - More work is necessary on the airplane(s) changed in accordance with the original issue

of this service bulletin. These airplanes and the airplanes added to this service bulletin all require the

work summarized below and detailed in Paragraph 3.B. Accomplishment Instructions, Part 2.

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ALERT ALERT
Revision 1 - In the area forward of the main equipment bay 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. 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).

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

Affected Maintenance Zones

Model Zone

767-300F 117, 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 6 years after the

Revision 01 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. 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.

Included in the service bulletin approval is an FAA finding of compliance with the Fuel Tank Ignition

Prevention rule (14 CFR section 25.981(a)(3) Amendment 102 or higher).

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

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ALERT ALERT
• Time to find the tools.

Group 1-2:

Part 1

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

FIGURE 1 1 1.00 1.00

FIGURE 2 1 1.00 1.00

FIGURE 3 (Wire routing only) - - -

FIGURE 4 1 1.70 1.70

FIGURE 5 (Wire routing only) - - -

FIGURE 6 1 0.20 0.20

FIGURE 7 (Wire routing only) - - -

FIGURE 8 1 2.10 2.10

FIGURE 9 (Wire routing only) - - -

FIGURE 10 1 3.70 3.70

FIGURE 11 1 0.75 0.75

Close Access 1 0.50 0.50

Test 1 4.00 4.00

TOTAL FOR EACH AIRPLANE FOR PART 1 15.45 15.45

Group 1:

Part 2

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

FIGURE 12 1 1.25 1.25

FIGURE 13 1 2.50 2.50

FIGURE 14 (Wire Diagram), 2 24.60 12.30

FIGURE 21 (Wire Routing)

FIGURE 16, FIGURE 18, (Wire 2 15.80 7.90

Diagrams), FIGURE 22, (Wire

Routing)

FIGURE 20 1 0.50 0.50

Close Access 1 0.50 0.50

Test 1 0.75 0.75

TOTAL FOR EACH AIRPLANE FOR PART 2 46.40 26.20

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Group 2-3:

Part 2

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

FIGURE 12 1 1.25 1.25

FIGURE 13 1 2.50 2.50

FIGURE 15 (Wire Diagram), 2 24.60 12.30

FIGURE 21 (Wire Routing)

FIGURE 17, FIGURE 19, (Wire 2 15.80 7.90

Diagrams), FIGURE 22, (Wire

Routing)

FIGURE 20 1 0.50 0.50

Close Access 1 0.50 0.50

Test 1 0.75 0.50

TOTAL FOR EACH AIRPLANE FOR PART 2 46.40 26.20

Total Task Elapsed Hours

Hours

Total For Each Airplane

Group 1 - 2 61.85 41.65

Group 3 46.40 26.20

H. Weight and Balance Changes

Group 1-2:

Part 1 and Part 2

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-300F +7.70 +848.9

Group 3:

Part 2

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-300F +6.5 + 660.1

I. Electrical Load Data

Not changed.

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J. References

1. Existing Data:

a. Engineering Change Memo PRR B12900-260

b. Boeing Service Bulletin 767-21-0235

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

d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-05, 20-50-10, 20-50-19

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

20-20-10, 20-20-11, 20-30-16, 20-60-09, 20-61-11, 20-81-12, 20-81-19, 20-81-22, 20-90-11

f. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 20-10-33, 20-41-01, 21-22-02, 21-58-00,

24-22-00, 25-00-00, 31-01-36, 34-11-00

g. 767 Fleet Team Digest (FTD) 21-09003

h. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41, 31-41-13

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

278T4107 Tubing Installation Lower Lobe Sidewall LH, STA 132.5 Thru 290

284T0971 Rack Instl - E8

284T1040 Support Bracket, E8 Rack Instl

288T2036 Modular Wire Bundle Instl P36, Misc. Relay Panel, Left

288T2280 Modular Wire Bundle Installation E8 EICAS Rack

288T4107 Wire Bundle Installation Lower Lobe Sidewall LH, STA 132.5

288T4117 Wire Bundle Installation Lower Lobe Sidewall LH, STA 290 Thru 431

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

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Publication Chapter-Section

767 Aircraft Maintenance Manual 21-58

767 Illustrated Parts Catalog 21-58, 34-11

767 System Schematic Manual 21-58, 31-41

767 Wiring Diagram Manual 21-58, 31-41, Equipment List

767 Fault Isolation 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
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

February 28, 7 179 $21,865.00

2013

Top Kit - 767 Freighters

3-Way Valve Logic

Change With FDARS

(Group 1 - 2)

015T1860-1

March 28, 10

2013

April 25, 10

2013

May 23, 2013 10

June 21, 2

2013

February 28, 7 179 $15,959.00

2013

Top Kit - 767 Freighters

3-Way Valve Logic

Change FDARS Addition (Group 3)

015T1860-10

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 Commercial

Airplanes Group - Warranties. 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 Spares. Please refer to this service bulletin number

and reference the airplane variable numbers in your purchase order.

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.

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ALERT ALERT
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 11 12 13 20

015T1860-1 1 1 1 1 1 1

015T1860-10 - - - 1 1 1

Figure Kit

Top Kit 21 22

015T1860-1 1 1

015T1860-10 1 1

Top Kit

Wire Kit 015T1860-1 015T1860-10

015T1860-3 1 -

015T1860-2 1 -

015T1860-4 1 -

289T1169-106 1 1

289T1169-107 1 1

289T1169-108 1 1

Group 1-2:

KIT 015T1860-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 11 12 13 20

Qty

015T1860-10101 . . 1 . . . DECAL K10718

015T1860-10102 . . 1 . . . DECAL D31620

CLAMP MOUNTING INSTRUMENT123-2222-F . 1 . . . .

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

QUICK DISCONNECT

1QF2-3-64A . 1 . . . .

1QM1-3-54A . 1 . . . . DISCONNECT

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

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Group 1-2:

KIT 015T1860-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 11 12 13 20

Qty

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

214T1120-218 OR (c)

-1218 OR -3218

214T1120-3311 . . . 1 . . DUCT ASSY

214T3436-453 . . . . 1 . ORIFICE ASSY

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

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

233T9118Y105 1 . . . . . BRACKET (a), (b)

6502-10K . 1 . . . . Pressure Switch

VALVE - AIR

SHUTOFF

67-2951-001 . . . . 1 .

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

HOSEDUCT,

SLEEVE

AS1506-14D30 . . . . 1 .

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 . . . . . 1

BAC27TFDE534 . 1 . . . . VINYL DECAL

CLAMP, MISCELLANEOUSBACC10DU500ABE . . . . 2 .

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

HOSE, INSTRUMENTBACH30BC06- . 1 . . . .

0110

BONDING

JUMPER

BACJ40A20-7 . . . . 1 .

BACN10YD1G . . . . 4 . NUTPLATE

BACN10YR3CD . . . . 3 . NUT (d)

BACR13CD2 . . . . . 1 RELAY

RIVET, UNIVER- (e)

SAL HD

BACR15FT6AD5C 4 . . . . .

RIVET, UNIVER- (d), (e)

SAL HD

BACR15FT6KE5C . . . . 8 .

RIVET, UNIVER- (d), (e)

SAL HD

BACR15FT6KE6C . . . . 4 .

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ALERT ALERT
Group 1-2:

KIT 015T1860-1

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 11 12 13 20

Qty

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

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

BACS38K2 . . . 3 . . STRAP (d)

BACS38K6 . . . 4 1 . STRAP (d)

BACT19J4 . . . . . 6 TAPE, ID (d)

PACKING, PREFORMEDMS28778-5 . 1 . . . .

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 RELAYTDH-1852-3002 . . . . . 1

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

(a) This part not used in production.

(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.

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ALERT ALERT
Group 1-2:

KIT 015T1860-1

Notes

Existing Part

Name Number

Figure

New Part Number

21 22

Qty

RETAINER CLIP

ASSY

411A4902-7 2 .

LACING TAPE -

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 1 1

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . 1

Group 3:

KIT 015T1860-10

Notes

Existing Part

Name Number

Figure

New Part Number

12 13 20 21 22

Qty

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

214T1120-313 . 1 . . . DUCT ASSY

214T1120-315 . 1 . . . DUCT ASSY

214T1120-218 OR (c)

-1218 OR -3218

214T1120-3311 1 . . . . DUCT ASSY

214T3436-453 . 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

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ALERT ALERT
Group 3:

KIT 015T1860-10

Notes

Existing Part

Name Number

Figure

New Part Number

12 13 20 21 22

Qty

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 . . .

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 . . 6 . . 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

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ALERT ALERT
Group 3:

KIT 015T1860-10

Notes

Existing Part

Name Number

Figure

New Part Number

12 13 20 21 22

Qty

TIME DELAY RELAYTDH-1852-3002 . . 1 . .

(a) This part not used in production.

(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.

Group 1-2:

KIT 015T1860-2

New Part Number Qty Name Notes

015T1860-101W 1 WIRE W0176

015T1860-10104 1 TAPE, LACING

SLEEVE IDENTIFICATION, HEAT

SHRINKABLE

015T1860-10106 1

CONTACT, SOCKETBACC47CP1S 1

CONTACT, SOCKETBACC47DJ1 4

BACS16W1A 1 RELAY SOCKET

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1

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Group 1-2:

KIT 015T1860-3

New Part Number Qty Name Notes

015T1860-102W 1 WIRE W1702

BACC47CN1S 1 CONTACT, PIN

BACC47CN1SB 1 CONTACT, PIN

SLEEVE, HEAT

SHRINK

BACT63D1 1

Group 1-2:

KIT 015T1860-4

New Part Number Qty Name Notes

015T1860-103W 1 WIRE W2000

SLEEVE IDENTIFICATION, HEAT

SHRINKABLE

015T1860-10105 1

BACKSHELL

CLAMP

BACC10GH10 1

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT10A5S 1

CONTACT, SOCKETBACC47CP1S 4

BACC47DE8A 2 CONTACT

MS27488-20-1 1 PLUG

KIT 289T1169-106

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-106W 1

289T1169-10301 1 ID - CONNECTOR

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT12C12S6 1

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ALERT ALERT
KIT 289T1169-106

New Part Number Qty Name Notes

CONTACT, SOCK- (a)

ET

BACC47CP1S 14

BACC47DE7A 5 CONTACT, PIN (a)

(a) There are more parts than are necessary.

KIT 289T1169-107

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-107W 1

289T1169-10401 1 ID - CONNECTOR

289T1169-10402 1 ID - CONNECTOR

289T1169-10403 1 ID - DIODE

BACC47DE7A 3 CONTACT, PIN (a)

BACC47DE8A 3 CONTACT (a)

CONTACT, SOCK- (a)

ET

BACC47DJ1 4

CONTACT, SOCK- (a)

ET

BACC47ER1 12

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 289T1169-108

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-108W 1

BACC47CN1S 6 CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47ER1 5

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ALERT ALERT
KIT 289T1169-108

New Part Number Qty Name Notes

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

Part Number / Specification QTY Name Notes

BMS5-95 4 oz SEALANT (a)

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

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

Group 1-2:

Part 1:

Group 1-2:

The part shown below is changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane.

Group 1-2:

Existing Part QTY Name New Part Number Notes

Number

284T1040-6 1 SUPPORT BRACKET 284T1040-16 (a) (b)

(a) Make the change in accordance with this service bulletin.

(b) This is the part number after the change is done in accordance with this service bulletin.

Part 2:

None

4. Parts Removed and Not Replaced

Group 1-2:

Part 1:

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ALERT ALERT
Group 1-2:

Existing Part Number Name QTY Notes

BACC14AD06DN CAP 1 (a)

BACR13CD2 RELAY 1 (a)

BACS16AG RELAY, SOCKET 1 (a)

(a) Keep the part if there are other uses for it.

Part 2:

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

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

definition of the acronyms.

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

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are 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. 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.

7. 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.

8. 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.

9. 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.

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10. The work instructions refer to panel(s) that contain Electro-static Sensitive Devices

(ESDS). Make sure you keep contamination or unwanted materials away from the

sensitive device. Contamination or unwanted material near the sensitive device can

cause a malfunction in the sensitive device. Refer to 767 AMM 20-41-01 as an

accepted procedure.

11. Work Instructions are broken into two parts. Part 1, including Figures 1 - 11, consists

of the instructions from the original release of the service bulletin. Part 2, including

Figures 12 - 19, is the addition of Flight Deck Air Relief System (FDARS) Components

with some additional wiring changes. Both Part 1 and Part 2 are required on Group

1 and Group 2 airplanes. Only Part 2 is required for Group 3 airplanes because

Group 3 airplanes received a change equivalent to Part 1 in production.

B. WORK INSTRUCTIONS

Group 1-2:

Part 1 - 3-Way-Valve (also called manifold interconnect valve) operating logic change.

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

2. Get access to the Main Equipment Center (MEC). Refer to 767 AMM 06-41-00 as an accepted

procedure for access locations.

3. In the MEC, open the circuit breaker specified in the table below and attach a "DO-NOT-CLOSE"

tag:

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-4 C019 EQPT COOL OVERRIDE C00679

4. In the MEC, install the new bracket to the E8 Engine Indication and Crew Alerting System (EICAS)

rack at station 266.5 in accordance with FIGURE 1.

5. At the E8 EICAS rack, install the new pressure switch to the bracket and attach hardware in

accordance with FIGURE 2.

6. Open the P36 left miscellaneous equipment panel door to get access to the wiring. Refer to 767

AMM 31-01-36 for component locations.

7. In the P36 left miscellaneous equipment panel, make changes to wire bundle W176 in accordance

with FIGURE 3 and FIGURE 4.

8. In the MEC, make changes to wire bundle W596 between the P36 left miscellaneous equipment

panel and P50 electrical systems card file panel in accordance with FIGURE 5 and FIGURE 6.

9. In the P50 electrical systems card file panel, make changes to wire bundle W1114 in accordance

with FIGURE 6.

10. In the MEC, make changes to wire bundle W1702 between the P36 left miscellaneous equipment

panel and E8 EICAS rack in accordance with FIGURE 7 and FIGURE 8.

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11. At the E8 EICAS rack, make changes to wire bundle W2000 in accordance with FIGURE 9 and

FIGURE 10.

12. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay K10718

in accordance with FIGURE 11.

13. Close the P36 left miscellaneous equipment panel.

14. In the MEC, remove the "DO-NOT-CLOSE" tag and close the circuit breaker specified in the table

below:

CIRCUIT BREAKER PANEL ASSEMBLY

Panel Location Name Number

P11-4 C019 EQPT COOL OVERRIDE C00679

15. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure.

16. Flush the pitot/static system. Refer to 767 AMM 34-11-00 as an accepted procedure.

17. Do a leak test of the Auxiliary Static system No. 2 (AS2). Refer to 767 AMM 34-11-00 as an

accepted procedure.

18. Continue with Part 2.

Part 2 - Addition of Flight Deck Air Relief System (FDARS) Components.

1. Remove electrical power if not done for Part 1. 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 12.

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

orifice, outlet valve and screen in accordance with FIGURE 13.

5. Modify wiring as follows:

a. Add wires and connector between panel P36 and new valve:

(1) Group 1:

In accordance with FIGURE 14 (wire diagram) and FIGURE 21 (wire installation).

(2) Group 2-3:

In accordance with FIGURE 15 (wire diagram) and FIGURE 21 (wire installation).

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ALERT ALERT
b. Modify wiring within Panel P36:

(1) Group 1:

In accordance with FIGURE 16 and FIGURE 18 (wire diagrams) and FIGURE 22 (wire

installation).

(2) Group 2-3:

In accordance with FIGURE 17 and FIGURE 19 (wire diagrams) and FIGURE 22 (wire

installation).

6. Modify relay installation in panel P36 in accordance with FIGURE 20.

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

8. Do an Operational Test - Manifold Interconnect Valve (Reconfiguration) - Post SB 767-21A0247R1.

Refer to 767 AMM 21-58-00 as an acceptable procedure. (This will also test operation of the added

outlet valve.)

9. Put the airplane back to a serviceable condition.

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION

(SHEET 2 OF 4)

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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

on the support bracket at the position shown.1 Put / Hold BRACKET 233T9118Y105 1

0.129 inch diameter in the support

bracket to agree with bracket.

2 Drill PILOT HOLE - 4

0.191 - 0.202 inch diameter in the

support bracket and bracket.

3 Drill HOLE - 4

in the support bracket and bracket.

Break all sharp edges.

Deburr HOLE - 4

to the support bracket and bracket

mating surfaces. Refer to SOPM 20-

50-19 as an accepted procedure.

4 Apply SEALANT BMS5-95 -

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION

(SHEET 3 OF 4)

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ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

on the support bracket at the position shown.Install BRACKET 233T9118Y105 1

(New)

5

RIVET, UNIVERSAL BACR15FT6AD5C 4

HD

Install

(New)

Apply two coats to all bare metal

surfaces of the support bracket and

bracket. Refer to SOPM 20-41-02

as an accepted procedure.

6 Apply PRIMER BMS10-11, TYPE I -

to the support bracket to identify that

this change is done. Refer to SOPM

20-50-10 code RH as an accepted

procedure. (a)

7 Apply PART NUMBER - -

(a) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for applicable part number.

FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION

(SHEET 4 OF 4)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION

(SHEET 2 OF 3)

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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

CLAMP MOUNTING 123-2222-F 1 to the bracket.

INSTRUMENT

Install

(New)

1

Install Pressure Switch 6502-10K 1 in the instrument mounting clamp.

(New)

2

PACKING, PRE- MS28778-5 1 onto the pneumatic inlet port.

FORMED

Install

(New)

3

Install DISCONNECT 1QM1-3-54A 1 to the pressure switch.

(New)

to the BACH30BC01-0110 instrument hose.Install QUICK DISCONNECT 1QF2-3-64A 1

(New)

4

from the AS2 system tubing tee fitting located at STA 270, LBL70,

WL170.

5 Remove CAP BACC14AD06DN 1

between the AS2 system tubing tee

fitting and the pressure switch quick

disconnect.

Install HOSE, INSTRUMENT BACH30BC06-0110 1

(New)

6

on the bracket below the pressure

switch at the position shown. Refer

to SOPM 20-50-05 as an accepted

procedure.

Install VINYL DECAL BAC27TFDE534 1

(New)

7

FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION

(SHEET 3 OF 3)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING

(SHEET 1 OF 5)

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ALERT ALERT
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING

(SHEET 2 OF 5)

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ALERT ALERT
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING

(SHEET 3 OF 5)

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ALERT ALERT
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING

(SHEET 4 OF 5)

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ALERT ALERT
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -

ROUTING

(SHEET 5 OF 5)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING

CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
REFERENCE: 767 WDM 21-58-16

NOTE: The parts are in Wire Kit 015T1860-2.

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

Use lacing tape to tie wires. Refer to SWPM 20-

10-11 as an accepted procedure.

1 TAPE, LACING 015T1860-10104 -

Refer to cut and code table for wire kit 015T1860-

101W.

2 WIRE W0176 015T1860-101W 1

3 RELAY SOCKET BACS16W1A 1

Refer to SWPM 20-81-12 as an accepted procedure.4 CONTACT, SOCKET BACC47DJ1 4

Install within 6 inches of equipment. Refer to

SWPM 20-10-11 as an accepted procedure.

SLEEVE IDENTIFICA- 015T1860-10106 1

TION, HEAT SHRINKABLE

5

Refer to SWPM 20-61-11 as an accepted procedure.6 CONTACT, SOCKET BACC47CP1S 1

Refer to SWPM 20-90-11 as an accepted procedure.CONTACT, PIN, M39029/11-145 1

CRIMP REMOVABLE,

PER MIL-C-39029/11

7

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-101W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA# WIRE#

W0176 34G 24 PK 100 BMS 13-48, TYPE 11, CLASS 1, AWG24

W0176 34H 24 PK 100 BMS 13-48, TYPE 11, CLASS 1, AWG24

FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING

CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 1 OF 8)

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ALERT ALERT
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 2 OF 8)

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FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 3 OF 8)

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ALERT ALERT
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 4 OF 8)

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FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 5 OF 8)

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ALERT ALERT
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 6 OF 8)

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FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 7 OF 8)

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FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING

(SHEET 8 OF 8)

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ALERT ALERT
This Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-16

NOTE: The part is in Wire Kit 015T1860-3.

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

1 WIRE W596-606-24 1 Remove and discard wire.

Refer to SWPM 20-30-16 as an accepted procedure.SLEEVE, HEAT BACT63D1 1

SHRINK

2

FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD

FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES

(SHEET 1 OF 1)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING

(SHEET 3 OF 3)

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ALERT ALERT
This Figure applies only to: Group 1-2.

REFERENCE: 767 WDM 21-58-16

NOTE: The parts are in Wire Kit 015T1860-2 and 015T1860-3.

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

Use lacing tape to tie wires. Refer to SWPM 20-

10-11 as an accepted procedure.

1 TAPE, LACING 015T1860-10104 -

Refer to cut and code table for wire kit 015T1860-

102W.

2 WIRE W1702 015T1860-102W 1

Refer to SWPM 20-61-11 as an accepted procedure.3 CONTACT, PIN BACC47CN1S 1

Refer to SWPM 20-61-11 as an accepted procedure.4 CONTACT, PIN BACC47CN1SB 1

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-102W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA# WIRE#

W1702 021 24 PK 200 BMS13-48, TYPE 11, CLASS 1, AWG24

FIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING

(SHEET 1 OF 2)

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ALERT ALERT
FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
REFERENCE: 767 WDM 31-41-13

NOTE: The parts are in Wire Kit 015T1860-2 and 015T1860-4.

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

Use lacing tape to tie wires. Refer to SWPM 20-

10-11 as an accepted procedure.

1 TAPE, LACING 015T1860-10104 -

Refer to cut and code table for wire kit 015T1860-

103W

2 WIRE W2000 015T1860-103W 1

Install within 6 inches of connector. Refer to SWPM 20-10-11 as an accepted procedure.SLEEVE IDENTIFICA- 015T1860-10105 1

TION, HEAT SHRINKABLE

3

Refer to SWPM 20-61-11 as an accepted procedure.4 CONTACT, SOCKET BACC47CP1S 4

Refer to SWPM 20-61-11 as an accepted procedure.CONNECTOR, ELEC- BACC45FT10A5S 1

TRICAL, PLUG,

STRAIGHT, BAYONET

COUPLING

5

Insert contact sockets and seal plugs at each

empty contact socket hole. Refer to SWPM 20-

00-11 as an accepted procedure.

PLUG MS27488-20-1 2

Refer to SWPM 20-60-09 as an accepted procedure.BACKSHELL CLAMP BACC10GH10 1

Refer to SWPM 20-20-11 as an accepted procedure.6 CONTACT BACC47DE8A 2

WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-103W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WBA# WIRE#

W2000 0100 24 PK 100 BMS 13-48, TYPE 11, CLASS 1, AWG24

W2000 0110 20 PA 100 BMS 13-48, TYPE 10, CLASS 1, AWG20

W2000 0120 20 PA 100 BMS 13-48, TYPE 10, CLASS 1, AWG20

FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-2.

FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT

(SHEET 2 OF 3)

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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

K10355 from the

front of the relay

plate. (a)

1 Remove RELAY BACR13CD2 1

2 Remove DECAL BACT19J4 1 Imprinted K10355.

D21730 from the

rear of the relay

plate. Lower the relay plate as necessary. (a)

3 Remove SOCKET, RELAY BACS16AG 1

4 Remove DECAL BACT19J4 1 Imprinted D21730.

on the front of the

relay plate. Refer to

SOPM 20-50-05 as

an accepted procedure.

5 Install (New) DECAL K10718 015T1860-10101 1

on the rear of the relay plate. Lower the

relay plate as necessary. Refer to SOPM

20-50-05 as an accepted procedure.

6 Install (New) DECAL D31620 015T1860-10102 1

K10718 into relay

socket D31620.

7 Install (New) TIME DELAY RELAY TDH-8050-3003P 1

(a) Keep this part if there are other uses for it.

FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 12: EXISTING DUCT REPLACEMENT

(SHEET 1 OF 6)

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ALERT ALERT
FIGURE 12: EXISTING DUCT REPLACEMENT

(SHEET 2 OF 6)

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ALERT ALERT
FIGURE 12: EXISTING DUCT REPLACEMENT

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 767-21A0247

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 12: EXISTING DUCT REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 767-21A0247

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-( ) 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 12: 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 12: EXISTING DUCT REPLACEMENT

(SHEET 6 OF 6)

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ALERT ALERT
FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 1 OF 7)

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ALERT ALERT
FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 2 OF 7)

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ALERT ALERT
FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 3 OF 7)

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ALERT ALERT
FIGURE 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 767-21A0247

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 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 214T3436-453 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 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 767-21A0247

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

Apply 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 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN 767-21A0247

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 13: FDARS DUCTS AND VALVE INSTALLATION

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 1.

Reference : 767 WDM 21-58-41

NOTE: The parts are in Wire Kit 289T1169-106. The wire is identified as 289T1169-106W.

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 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 1 OF 2)

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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 14: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 2-3.

Reference : 767 WDM 21-58-41

NOTE: The parts are in Wire Kit 289T1169-106. The wire is identified as 289T1169-106W.

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 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 1 OF 2)

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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 15: W756 ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 1 OF 3)

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88 of 114

BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
Reference : 767 WDM 21-58-41

NOTE: The parts are in Wire Kit 289T1169-107. The wire is identified as 289T1169-107W.

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 9

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

(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

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

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

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 2 OF 3)

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ALERT ALERT
LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

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 3

CONTACT, PIN, M39029/11-145 3

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 16: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 2-3.

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 1 OF 3)

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91 of 114

BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
Reference : 767 WDM 21-58-41

NOTE: The parts are in Wire Kit 289T1169-107. The wire is identified as 289T1169-107W.

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 9

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

(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

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

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

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 2 OF 3)

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ALERT ALERT
LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

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 3

CONTACT, PIN, M39029/11-145 3

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 17: W184 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 3 OF 3)

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93 of 114

BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 1.

Reference : 767 WDM 21-58-16

NOTE: The parts are in Wire Kit 289T1169-108. The wire is identified as 289T1169-108W.

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 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21A0247

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 4

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 2

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 18: W176 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 2 OF 2)

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95 of 114

BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
This Figure applies only to: Group 2-3.

Reference : 767 WDM 21-58-16

NOTE: The parts are in Wire Kit 289T1169-108. The wire is identified as 289T1169-108W.

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 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 1 OF 2)

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96 of 114

BOEING SERVICE BULLETIN 767-21A0247

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 4

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 2

CRIMP REMOVABLE,

PER MIL-C-39029/11

FIGURE 19: W176 CHANGE IN PANEL P36 (WIRE DIGRAM)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21A0247

ALERT ALERT
FIGURE 20: FDARS RELAY INSTALLATION IN P36

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 20: FDARS RELAY INSTALLATION IN P36

(SHEET 2 OF 4)

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99 of 114

BOEING SERVICE BULLETIN 767-21A0247

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)

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

FIGURE 20: FDARS RELAY INSTALLATION IN P36

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-21A0247

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

Name Identification Qty More Data

TAPE, ID BACT19J4 2

FIGURE 20: FDARS RELAY INSTALLATION IN P36

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 1 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 2 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 3 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 4 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 5 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 6 OF 8)

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ALERT ALERT
FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 7 OF 8)

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BOEING SERVICE BULLETIN 767-21A0247

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 W0756

PRESSURIZED (TEMP

135 DEG)

1 Install (New)

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

FIGURE 21: W756 ROUTING BETWEEN P36 AND AIR RELIEF VALVE

(SHEET 8 OF 8)

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ALERT ALERT
FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36

(SHEET 1 OF 5)

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ALERT ALERT
FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36

(SHEET 2 OF 5)

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ALERT ALERT
FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36

(SHEET 3 OF 5)

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FIGURE 22: W176 AND W184 ROUTING WITHIN PANEL P36

(SHEET 4 OF 5)

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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

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 22: W176 AND W184 ROUTING WITHIN PANEL P36

(SHEET 5 OF 5)

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ALERT ALERT