Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0245

Original Issue: April 16, 2010

Revision 2: September 27, 2013

ATA System: 2158 2123

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

Main Cargo Air Distribution System Change And Flight Deck Air Relief System

Installation

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

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Copyright © 2010 Boeing.

Unpublished Work. All Rights Reserved.

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ALERT ALERT

BLANK PAGE
Table of Contents

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

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

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

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

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

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

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

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 42

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 43

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE [Group

1-3, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION [Group 1-3, Configuration 1]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 3: WIRE BUNDLE W176 CHANGE [Group 1-3, Configuration 1] . . . . . . . . . . . . . . . . 59

FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE [Group 1-3, Configuration 1] . . . . . . . . 61

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE [Group 1-3, Configuration 1] . . . . . . . . 62

FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING [Group 1-3, Configuration 1] . . . . . . . 64

FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING [Group 1-3, Configuration 1] . . . . . . 72

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ALERT ALERT
FIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS

CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT . . . . . . . . 77

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83

FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION . 93

FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE [Group 1-2]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE [Group 3] . 103

FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

[Group 1-3, Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE . . . 110

FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE [Group 1-2]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 113

FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE [Group 3]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115

FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION . . . . . . . . . . . . 117

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BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 767-21A0245

Original Issue: April 16, 2010

Revision 2: September 27, 2013

ATA System: 2158 2123

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

Main Cargo Air Distribution System Change And Flight Deck Air Relief System

Installation

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary on the airplanes changed in accordance with the original issue or Revision 1 of this

service bulletin. Flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck

cargo compartment must be removed and caps and an orifice installed. In addition, a Flight Deck Air Relief

System (FDARS) must be installed. This work is identified as configuration 2 for Group 1, 2, and 3 airplanes.

Airplane Variable Numbers VR251 and VR256 are moved from airplane Group 1 to new airplane Group 3.

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.

REASON FOR REVISION

This revision is sent to change the service bulletin release classification from "Standard" to "Alert" as it is related

to a safety Service Related Problem (SRP). This revision also makes sure cargo smoke detection performance

in the main deck cargo compartment continues to agree with European Aviation Safety Agency (EASA) validation

requirements. As a result of this requirement, instructions are added to remove flex ducts that connect the center

and aft parts of the air distribution diffuser in the main deck cargo compartment and install caps and an orifice

assy. This change reduces the airflow to the aft section of the main deck cargo compartment. This revision also

installs a Flight Deck Air Relief System (FDARS) to reduce flight deck noise caused by excessive airflow into

the flight deck when the 3-way valve is closed and the flight deck equipment is being cooled by the Electrical

Equipment (EE) cooling fans. This change addresses the issues in Information Notice 767-21A0245 R01 IN01.

As part of these changes, the EASA/Joint Aviation Authorities (JAA) approval statement, new kits, and new

figures are added. Also, the background information, compliance data, and manpower data is updated.

These sections are changed:

1. Subject: Updated to include the additional work.

2. Summary Background: Updated to include information about the additional work necessary and to

update the existing information. A summary evaluation table is added.

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3. Summary Action: Added actions for new groups and configurations. Existing data is updated.

4. Summary Compliance: An Airworthiness Directive (AD) statement is added and the compliance statement

is changed.

5. Summary Manpower: Changed to refer to Paragraph 1.G., Manpower.

6. Summary Illustration: Updated to include additional work.

7. Paragraph 1.A., Effectivity: Group 3 and Configuration 2 for Group 1 and Group 2 are added.

8. Paragraph 1.B., Concurrent Requirements: The concurrent requirements are updated.

9. Paragraph 1.C., Reason: Updated to include information about the additional work necessary and to

update the existing information. Fleet Team Digest (FTD) reference is added.

10. Paragraph 1.D., Description: Added actions for new groups and configurations. Existing data is updated.

11. Paragraph 1.E., Compliance: An Airworthiness Directive (AD) statement is added and the compliance

statement is changed.

12. Paragraph 1.F., Approval: The approval statement is updated.

13. Paragraph 1.G., Manpower: Tables added for all groups and configurations. The existing data is updated.

14. Paragraph 1.H., Weight and Balance Changes: Weight and balance tables are added.

15. Paragraph 1.J., References: The reference list and the installation drawings reference table are updated.

16. Paragraph 1.K., Publications Affected: The publications affected table is updated.

17. Paragraph 1.M., Software Accomplishment Summary: A software accomplishment statement is added.

18. Paragraph 2.A., Material - Price and Availability: New top kits and supplemental kits are added. Kit

pricing data is updated.

19. Paragraph 2.C.1., Kits/parts: New top kits and supplemental kits are added.

20. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Operator supplied materials are added.

21. Paragraph 3.A., General Information: The general information notes are updated.

22. Paragraph 3.B., Work Instructions: Instructions for configuration 1 airplanes are updated and instructions

for configuration 2 airplanes are added.

23. Figures 1 thru 7: The applicability is updated.

24. Figures 6 and 7: The wire routing is updated.

25. Figures 8 thru 18: Added for additional work necessary.

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

of important changes.

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ALERT ALERT
Pages with no vertical lines have no important changes.

REVISION HISTORY

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Revision 1: September 30, 2010

Revision 2: September 27, 2013

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ALERT ALERT

BLANK PAGE
Commercial

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-21A0245

Original Issue: April 16, 2010

Revision 2: September 27, 2013

ATA System: 2158 2123

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

Main Cargo Air Distribution System Change And Flight Deck Air Relief System

Installation

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 in the flight compartment

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. 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. Flight compartment indication blanking can also

cause unscheduled maintenance and airplane downtime. 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.

In addition, this service bulletin reduces airflow to the aft part of the main cargo compartment to make sure that

cargo smoke detection system performance continues to agree with European Aviation Safety Agency (EASA)

validation requirements.

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 several instances that are the likely causes of display unit malfunctions related to moisture or

condensation ingress. 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

in hot and humid conditions. Another instance was an unserviceable air conditioning pack water separation

system, which allowed water to be delivered to the flight compartment in the air conditioned air. The other

instance was a malfunction of an air conditioning pack, which caused ice to be delivered to the flight compartment

in the air conditioned air. 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

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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. As a consequence of the 3-way valve closure below 10,000 feet, excessive airflow in the flight

deck air distribution system causes increased flight deck noise which makes the Traffic Alert and Collision

Avoidance System (TCAS) difficult to hear. To prevent this, a Flight Deck Air Relief System (FDARS) is installed

to exhaust the excessive airflow into the Electrical Equipment (EE) bay when the 3-way valve is closed.

Accomplishment of this service bulletin changes the Environmental Control System (ECS) Flight Deck Cooling

System Logic to use EE cooling rather than airplane pack cooling on the ground and up to 10,000 feet. This

change reduces the amount of moisture or condensation that can collect in the flight compartment display units

and results in reduced flight compartment display unit malfunction occurrences. In addition, accomplishment of

this service bulletin installs a FDARS to exhaust excessive airflow into the right side tunnel of the EE bay when

the 3-way valve is in the closed position. This is to reduce flight deck noise caused by excessive airflow in the

flight deck air distribution system when the 3-way valve is closed and the flight deck equipment is being cooled

by the EE cooling fans.

This service bulletin also removes flex ducts that connect the center and aft parts of the air distribution diffuser

in the main deck cargo compartment and installs caps and an orifice assy. This change reduces airflow to the

aft part of the main cargo compartment to make sure the cargo smoke detection system performance continues

to agree with European Aviation Safety Agency (EASA) validation requirements.

Boeing Service Related Problem (SRP) 767-SRP-21-179 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 Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
ACTION (PRR B12900-260)

Group 1-3, Configuration 1:

1. In the Main Equipment Center (MEC) change wire bundles W596, W756, and W1702.

2. In the P36 Panel install new relays, decals, ID tape, marker, and change wire bundles W176 and W184.

3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006.

4. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies.

5. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of

the air distribution diffuser and install caps and an orifice assy.

Group 1-3, Configuration 2:

1. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies.

Change wire bundle W756. Install new relays, ID tape, marker, and change wire bundles W176 and

W184 in the P36 panel.

2. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts of

the air distribution diffuser and install caps and an orifice assy.

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 changes given in this service bulletin be done within 6 years after the Revision 2

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

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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ALERT ALERT
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BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Commercial

Airplanes 767

Service Bulletin

ALERT

Number: 767-21A0245

Original Issue: April 16, 2010

Revision 2: September 27, 2013

ATA System: 2158 2123

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

Main Cargo Air Distribution System Change And Flight Deck Air Relief System

Installation

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 airplanes 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 that must incorporate Boeing Service Bulletin

767-21-0235 before or concurrently with this service bulletin that

have wire bundles W756 and W176 with a unique configuration.

1 -

Airplanes that have not incorporated the original issue, or revision 1

of this service bulletin.

1

Airplanes that have incorporated the original issue, or revision 1 of

this service bulletin.

2

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GROUP CONFIGURATION DESCRIPTION

767-300F airplanes that had the intent of Boeing Service Bulletin

767-21-0235 incorporated in production

2 -

Airplanes that have not incorporated the original issue, or revision 1

of this service bulletin.

1

Airplanes that have incorporated the original issue, or revision 1 of

this service bulletin.

2

767-300F airplanes that must incorporate Boeing Service Bulletin

767-21-0235 before or concurrently with this service bulletin that

have wire bundles W756 and W176 with a unique configuration.

3 -

Airplanes that have not incorporated the original issue, or revision 1

of this service bulletin.

1

Airplanes that have incorporated the original issue, or revision 1 of

this service bulletin.

2

Airplane Models:

767-300F

Variable Number Group

VR251 3

VR256 3

VR257 - VR260 1

VT501 1

VT511 - VT513 1

VT521 - VT523 1

VT531 - VT533 1

VT541 - VT543 2

VW851 1

2. Spares Affected

None.

B. Concurrent Requirements

Group 1, 3:

The service bulletin listed below must be done on Group 1 and Group 3 airplanes before or at the same

time as this service bulletin:

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BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1, 3:

Company Service Bulletin Description

Boeing 767-21-0235, Original Issue, or Revision 1. 3-Way Valve Control Logic Change.

Group 2:

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 in the flight

compartment 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. 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. Flight compartment indication blanking can also cause unscheduled maintenance and

airplane downtime. 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.

In addition, this service bulletin reduces airflow to the aft part of the main cargo compartment to make

sure that cargo smoke detection system performance continues to agree with European Aviation Safety

Agency (EASA) validation requirements.

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 several instances that are the likely causes of display unit

malfunctions related to moisture or condensation ingress. 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 in hot and humid conditions. Another

instance was an unserviceable air conditioning pack water separation system, which allowed water to

be delivered to the flight compartment in the air conditioned air. The other instance was a malfunction

of an air conditioning pack, which caused ice to be delivered to the flight compartment in the air

conditioned air. 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. As a consequence of the 3-way valve closure below

10,000 feet, excessive airflow in the flight deck air distribution system causes increased flight deck

noise which makes the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. To prevent

this, a Flight Deck Air Relief System (FDARS) is installed to exhaust the excessive airflow into the

Electrical Equipment (EE) bay when the 3-way valve is closed.

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ALERT ALERT
Accomplishment of this service bulletin changes the Environmental Control System (ECS) Flight Deck

Cooling System Logic to use EE cooling rather than airplane pack cooling on the ground and up to

10,000 feet. This change reduces the amount of moisture or condensation that can collect in the flight

compartment display units and results in reduced flight compartment display unit malfunction

occurrences. In addition, accomplishment of this service bulletin installs a FDARS to exhaust excessive

airflow into the right side tunnel of the EE bay when the 3-way valve is in the closed position. This is

to reduce flight deck noise caused by excessive airflow in the flight deck air distribution system when

the 3-way valve is closed and the flight deck equipment is being cooled by the EE cooling fans.

This service bulletin also removes flex ducts that connect the center and aft parts of the air distribution

diffuser in the main deck cargo compartment and installs caps and an orifice assy. This change reduces

airflow to the aft part of the main cargo compartment to make sure the cargo smoke detection system

performance continues to agree with European Aviation Safety Agency (EASA) validation requirements.

Boeing Service Related Problem (SRP) 767-SRP-21-179 is related to this service bulletin.

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

Revision 1 was sent to make required changes found when doing this service bulletin for the first time.

Three wire contacts are added; two wire contacts are deleted; and two plug and terminal numbers are

changed. Kits and instructions are changed accordingly. Some functional test steps are also changed.

Also, airplanes VR257-VR260, which were inadvertantly omitted, are added to Group 1.

Revision 2 is sent to change the service bulletin release classification from "Standard" to "Alert" as it

is related to a safety Service Related Problem (SRP). Revision 2 also makes sure cargo smoke detection

performance in the main deck cargo compartment continues to agree with European Aviation Safety

Agency (EASA) validation requirements. As a result of this requirement, instructions are added to

remove flex ducts that connect the center and aft parts of the air distribution diffuser in the main deck

cargo compartment and install caps and an orifice assy. This change reduces the airflow to the aft

section of the main deck cargo compartment. Revision 2 also installs a Flight Deck Air Relief System

(FDARS) to reduce flight deck noise caused by excessive airflow into the flight deck when the 3-way

valve is closed and the flight deck equipment is being cooled by the Electrical Equipment (EE) cooling

fans. This change addresses the issues in Information Notice 767-21A0245 R01 IN01. As part of these

changes, the EASA/Joint Aviation Authorities (JAA) approval statement, new kits, and new figures are

added. Also, the background information, compliance data, and manpower data is updated.

D. Description

Group 1-3, Configuration 1:

1. In the Main Equipment Center (MEC) change wire bundles W596, W756, and W1702.

2. In the P36 Panel install new relays, decals, ID tape, marker, and change wire bundles W176 and

W184.

3. In the E8 EICAS rack, install two diodes and change wire bundles W2000 and W2006.

4. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies.

5. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts

of the air distribution diffuser and install caps and an orifice assy.

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ALERT ALERT
Group 1-3, Configuration 2:

1. In the Main Equipment Center (MEC), install a FDARS air shutoff valve and new duct assemblies.

Change wire bundle W756. Install new relays, ID tape, marker, and change wire bundles W176

and W184 in the P36 panel.

2. In the main deck cargo compartment, remove four flex ducts that connect the center and aft parts

of the air distribution diffuser and install caps and an orifice assy.

Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this

service bulletin.

Revision 2 - More work is necessary on the airplanes changed in accordance with the original issue

or Revision 1 of this service bulletin. Flex ducts that connect the center and aft parts of the air distribution

diffuser in the main deck cargo compartment must be removed and caps and an orifice installed. In

addition, a Flight Deck Air Relief System (FDARS) must be installed. This work is identified as

configuration 2 for Group 1, 2, and 3 airplanes.

Revision 2 - Airplanes VR251 and VR256 are moved from airplane Group 1 to new airplane Group 3.

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

Affected Maintenance Zones

Model Zone

767-300F 119, 253, 254

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 changes given in this service bulletin be done within 6 years after the

Revision 2 date of this service bulletin.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

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).

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ALERT ALERT
G. Manpower

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

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

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

time:

• Time to adjust to the workplace.

• Time to schedule the work.

• Time to inspect the work.

• Time to cure the materials.

• Time to make the parts.

• Time to find the tools.

Group 1-2, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Access 1 1.00 1.00

FIGURE 9 1 2.10 2.10

FIGURE 10 1 4.00 4.00

FIGURE 1 1 0.50 0.50

FIGURE 18 1 0.80 0.80

FIGURE 2 1 0.30 0.30

FIGURE 3 1 3.50 3.50

FIGURE 16 2 5.50 2.75

FIGURE 4 1 2.10 2.10

FIGURE 5 2 5.30 2.65

FIGURE 15 2 10.90 5.45

FIGURE 12 2 24.70 12.35

FIGURE 6 SHOWS ROUTE ONLY

FIGURE 11 SHOWS ROUTE ONLY

FIGURE 7 SHOWS ROUTE ONLY

FIGURE 8 1 1.00 1.00

Close Access 1 1.00 1.00

Test 1 2.25 2.25

TOTAL FOR EACH AIRPLANE 64.95 41.75

Group 1, Configuration 1:

This estimate does not include the task hour data given in the service bulletin in Paragraph 1.B.,

Concurrent Requirements.

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ALERT ALERT
Group 3, Configuration 1:

Task Number of Persons Task Hours Elapsed Hours

Access 1 1.00 1.00

FIGURE 9 1 2.10 2.10

FIGURE 10 1 4.00 4.00

FIGURE 1 1 0.50 0.50

FIGURE 18 1 0.80 0.80

FIGURE 2 1 0.30 0.30

FIGURE 3 1 3.50 3.50

FIGURE 17 2 5.50 2.75

FIGURE 4 1 2.10 2.10

FIGURE 5 2 5.30 2.65

FIGURE 15 2 10.90 5.45

FIGURE 13 2 24.70 12.35

FIGURE 6 SHOWS ROUTE ONLY

FIGURE 11 SHOWS ROUTE ONLY

FIGURE 7 SHOWS ROUTE ONLY

FIGURE 8 1 1.00 1.00

Close Access 1 1.00 1.00

Test 1 2.25 2.25

TOTAL FOR EACH AIRPLANE 64.95 41.75

Group 3, Configuration 1:

This estimate does not include the task hour data given in the service bulletin in Paragraph 1.B.,

Concurrent Requirements.

Group 1-2, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 8 1 1.00 1.00

FIGURE 9 1 2.10 2.10

FIGURE 10 1 4.00 4.00

FIGURE 11 SHOWS ROUTE ONLY

FIGURE 12 2 24.70 12.35

FIGURE 14 SHOWS ROUTE ONLY

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ALERT ALERT
Group 1-2, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

FIGURE 15 2 10.90 5.45

FIGURE 16 2 5.50 2.75

FIGURE 18 1 0.80 0.80

Test 1 2.25 2.25

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 53.25 32.70

Group 3, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 8 1 1.00 1.00

FIGURE 9 1 2.10 2.10

FIGURE 10 1 4.00 4.00

FIGURE 11 SHOWS ROUTE ONLY

FIGURE 13 2 24.70 12.35

FIGURE 14 SHOWS ROUTE ONLY

FIGURE 15 2 10.90 5.45

FIGURE 17 2 5.50 2.75

FIGURE 18 1 0.80 0.80

Test 1 2.25 2.25

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 53.25 32.70

H. Weight and Balance Changes

Group 1-3, Configuration 1:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-300F +4.9 +596.4

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ALERT ALERT
Group 1-3, Configuration 2:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

767-300F +4.6 +556.3

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B12900-260

b. Boeing Service Bulletin 767-21-0235

c. Boeing Service Letter 767-SL-00-014

d. Boeing Service Related Problem (SRP) 767-SRP-21-179

e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-02, 20-50-05, 20-50-10,

20-50-12

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

20-30-16, 20-61-11, 20-71-11, 20-81-12, 20-81-19, 20-81-22, 20-90-11, 21-58-16, 21-61-11

g. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 21-22-02, 21-58-00, 21-58-16, 24-22-00,

25-00-00, 25-59-01, 32-09-02, 36-00-00

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

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

j. 767-300F Structural Repair Manual (SRM) 51-40-02, 51-40-05

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

214T1011 DUCT INSTL - FLIGHT DECK, SECT 41

214T2006 DUCT INSTL - AIR DISTRIBUTION SYSTEM, SECTION 46

215T3001 SENSOR INSTL - FWD E/E COMPT

DUCT INSTL - INSTRUMENT PANEL COOLING SUPPLY (VARIABLE) 2 CREW 3 ALT217T2013

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ALERT ALERT
Drawing Number Title

MODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT288T2036

288T2280 MODULAR WIRE BUNDLE INSTALLATION - E8 EICAS RACK

WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL LH, (STA 132.5

THRU 290)

288T4107

WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL RH, STA 132.5

THRU 290

288T4108

WIRE BUNDLE INSTALLATION CREW AND MAIN DECK FLOOR

BEAMS LH, (STA 139 THRU 344)

288T4115

WIRE BUNDLE INSTL - CREW AND MAIN DECK FLOOR BEAMS

RH, (STA 139 THRU 344)

288T4116

WIRE BUNDLE INSTL - LOWER LOBE SIDEWALL LH, (STA 290

THRU 431)

288T4117

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:

Publication Chapter-Section

767 Aircraft Maintenance Manual 21-58

21-58, 31-41, 91-02, 91-21, Equipment List767 Wiring Diagram Manual

767 System Schematic Manual 21-58, 31-41

767 Fault Isolation Manual 21-58

767 Illustrated Parts Catalog 21-22, 21-23, 21-58, 31-41

2. Damage Tolerance Based Structural Inspections:

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

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

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

L. Interchangeability and Intermixability of Parts

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

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.

Group 1-2:

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 Revision 2

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 2 date of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit - 767 Freighters No Longer Available

3 - Way Valve Logic

Change

015T1853-1 (a)

Supplemental Kit - 767 - - 139 $1.10

Freighters 3 - Way

Valve Logic Change

015T1853-2 (b)

Top Kit - 767 Freighters No Longer Available

3 - Way Valve Logic

Change

015T1853-3 (c)

Supplemental Kit - 767 - - 139 $11,612.00

Freighters 3 - Way

Valve Logic Change

015T1853-5 (d) (e)

Top Kit - 767 Freighters Jul 31/13 4 149 $18,315.00

3 - Way Valve Logic

Change

015T1853-10 (f)

Sep 03/13 2

Oct 02/13 1

(a) Top kit 015T1853-1 is replaced by top kit 015T1853-10 for airplanes that have not accomplished the

original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853-

2 and 015T1853-5 are equivalent to top kit 015T1853-10.

(b) Supplemental kit 015T1853-2 is necessary for operators that have received top kit 015T1853-1, but have

not accomplished the original issue, or Revision 1 of this service bulletin.

(c) Top kit 015T1853-3 is replaced by top kit 015T1853-10 for airplanes that have not accomplished the

original issue, or Revision 1 of this service bulletin. Top kit 015T1853-3, plus supplemental kit 015T1853-

5 are equivalent to top kit 015T1853-10.

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ALERT ALERT
Group 1-2:

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 Revision 2

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 2 date of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

(d) Supplemental kit 015T1853-5 is necessary for operators that have received top kit 015T1853-1 or top kit

015T1853-3, but have not accomplished the original issue, or Revision 1 of this service bulletin.

(e) Supplemental kit 015T1853-5 is necessary for operators that have accomplished the original issue, or

Revision 1 of this service bulletin in order to incorporate the additional work necessary in Revision 2 of

this service bulletin.

(f) Top kit 015T1853-10 replaces top kits 015T1853-1 and 015T1853-3 for airplanes that have not accomplished

the original issue, or Revision 1 of this service bulletin.

Group 3:

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 Revision 2

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 2 date of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit - 767 Freighters No Longer Available

3 - Way Valve Logic

Change

015T1853-1 (a)

Supplemental Kit - 767 - - 139 $1.10

Freighters 3 - Way

Valve Logic Change

015T1853-2 (b)

Top Kit - 767 Freighters No Longer Available

3 - Way Valve Logic

Change

015T1853-3 (c)

Supplemental Kit - 767 - - 139 $11,612.00

Freighters 3 - Way

Valve Logic Change

015T1853-6 (d) (e)

Top Kit - 767 Freighters Jul 31/13 1 149 $18,315.00

3 - Way Valve Logic

Change

015T1853-11 (f)

(a) Top kit 015T1853-1 is replaced by top kit 015T1853-11 for airplanes that have not accomplished the

original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853-

2 and 015T1853-6 are equivalent to top kit 015T1853-11.

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ALERT ALERT
Group 3:

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 Revision 2

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 2 date of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

(b) Supplemental kit 015T1853-2 is necessary for operators that have received top kit 015T1853-1, but have

not accomplished the original issue, or Revision 1 of this service bulletin. Top kit 015T1853-1, plus supplemental kits 015T1853-2 and 015T1853-6 are equivalent to top kit 015T1853-11.

(c) Top kit 015T1853-3 is replaced by top kit 015T1853-11 for airplanes that have not accomplished the

original issue, or Revision 1 of this service bulletin. Top kit 015T1853-3, plus supplemental kit 015T1853-

6 are equivalent to top kit 015T1853-11.

(d) Supplemental kit 015T1853-6 is necessary for operators that have received top kit 015T1853-1 or top kit

015T1853-3, but have not accomplished the original issue, or Revision 1 of this service bulletin.

(e) Supplemental kit 015T1853-6 is necessary for operators that have accomplished the original issue, or

Revision 1 of this service bulletin in order to incorporate the additional work necessary in Revision 2 of

this service bulletin.

(f) Top kit 015T1853-11 replaces top kits 015T1853-1 and 015T1853-3 for airplanes that have not accomplished

the original issue, or Revision 1 of this service bulletin.

B. Industry Support Information

Boeing warranty remedies are available for 767airplanes 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.

NOTE: One top kit, applicable supplemental kits, 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 3 4 5 8

015T1853-5 - - - - - 1

015T1853-6 - - - - - 1

015T1853-10 1 1 1 1 1 1

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Figure Kit

Top Kit 1 2 3 4 5 8

015T1853-11 1 1 1 1 1 1

Figure Kit

Top Kit 9 10 11 12 13 15

015T1853-5 1 1 1 1 - 1

015T1853-6 1 1 1 - 1 1

015T1853-10 1 1 1 1 - 1

015T1853-11 1 1 1 - 1 1

Figure Kit

Top Kit 16 17 18

015T1853-5 - - 1

015T1853-6 - - 1

015T1853-10 1 - 1

015T1853-11 - 1 1

Top Kit

Wire Kit 015T1853-5 015T1853-6 015T1853-10

289T1169-112 1 1 1

289T1169-113 1 1 1

289T1169-114 1 1 1

Top Kit

Wire Kit 015T1853-11

289T1169-112 1

289T1169-113 1

289T1169-114 1

Group 1-2, Configuration 2:

KIT 015T1853-5

Notes

Existing Part

Name Number

Figure

New Part Number

8 9 10 11 12 15

Qty

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

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Group 1-2, Configuration 2:

KIT 015T1853-5

Notes

Existing Part

Name Number

Figure

New Part Number

8 9 10 11 12 15

Qty

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

214T1120-315 . . 1 . . . duct assy

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

214T3436-1139 1 . . . . . ORIFICE ASSY

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

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

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

RETAINER CLIP

ASSY

411A4902-7 . . . 2 . .

VALVE - AIR

SHUTOFF

67-2951-001 . . 1 . . .

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

LACING TAPE - (b)

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 . . . . 1 .

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . . . . . 1

HOSEDUCT,

SLEEVE

AS1506-14D30 . . 1 . . .

CLAMP, MISCELLANEOUSBACC10DU500ABE . . 2 . . .

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

BONDING

JUMPER

BACJ40A20-7 . . 1 . . .

BACN10YD1G . . 4 . . . NUTPLATE

BACN10YR3CD . . 2 . . . NUT

RIVET, UNIVERSAL HDBACR15FT6KE5C . . 6 . . .

RIVET, UNIVERSAL HDBACR15FT6KE6C . . 2 . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

27 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 2:

KIT 015T1853-5

Notes

Existing Part

Name Number

Figure

New Part Number

8 9 10 11 12 15

Qty

BACR15FT6KE7C . . 1 . . . RIVET

BACS12GU3K7 . . 6 . . . SCREW, CAP

BACS16AG1 . . . . . 1 RELAY SOCKET

BACS16AH1 . . . . . 1 RELAY SOCKET

BACS38K2 10 2 . . . . STRAP

BACS38K6 . 3 1 . . . STRAP

BOE2221-0007 6 . . . . . CAP

PACKING, PREFORMEDMS29512-08 . 1 . . . .

NAS1149D0316J . . 4 . . . WASHER

NAS1149D0332H . . 6 . . . WASHER, PLAIN

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

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

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 . . . . . 1

(a) 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.

(b) Lacing tape P/N 829A9001-2 is also used in FIGURE 16.

Group 1-2, Configuration 2:

KIT 015T1853-5

Notes

Existing Part

Name Number

Figure

New Part Number

18

Qty

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 1

BACR13CD2 1 RELAY

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

28 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 2:

KIT 015T1853-5

Notes

Existing Part

Name Number

Figure

New Part Number

18

Qty

BACT19J4 5 TAPE, ID

TIME DELAY RELAYTDH-1852-3002 1

Group 3, Configuration 2:

KIT 015T1853-6

Notes

Existing Part

Name Number

Figure

New Part Number

8 9 10 11 13 15

Qty

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

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

214T1120-315 . . 1 . . . duct assy

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

214T3436-1139 1 . . . . . ORIFICE ASSY

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

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

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

RETAINER CLIP

ASSY

411A4902-7 . . . 2 . .

VALVE - AIR

SHUTOFF

67-2951-001 . . 1 . . .

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

LACING TAPE - (b)

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 . . . . 1 .

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . . . . . 1

HOSEDUCT,

SLEEVE

AS1506-14D30 . . 1 . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

29 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 2:

KIT 015T1853-6

Notes

Existing Part

Name Number

Figure

New Part Number

8 9 10 11 13 15

Qty

CLAMP, MISCELLANEOUSBACC10DU500ABE . . 2 . . .

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

BONDING

JUMPER

BACJ40A20-7 . . 1 . . .

BACN10YD1G . . 4 . . . NUTPLATE

BACN10YR3CD . . 2 . . . NUT

RIVET, UNIVERSAL HDBACR15FT6KE5C . . 6 . . .

RIVET, UNIVERSAL HDBACR15FT6KE6C . . 2 . . .

BACR15FT6KE7C . . 1 . . . RIVET

BACS12GU3K7 . . 6 . . . SCREW, CAP

BACS16AG1 . . . . . 1 RELAY SOCKET

BACS16AH1 . . . . . 1 RELAY SOCKET

BACS38K2 10 2 . . . . STRAP

BACS38K6 . 3 1 . . . STRAP

BOE2221-0007 6 . . . . . CAP

PACKING, PREFORMEDMS29512-08 . 1 . . . .

NAS1149D0316J . . 4 . . . WASHER

NAS1149D0332H . . 6 . . . WASHER, PLAIN

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

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

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 . . . . . 1

(a) 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.

(b) Lacing tape P/N 829A9001-2 is also used in FIGURE 17.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

30 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 2:

KIT 015T1853-6

Notes

Existing Part

Name Number

Figure

New Part Number

18

Qty

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 1

BACR13CD2 1 RELAY

BACT19J4 5 TAPE, ID

TIME DELAY RELAYTDH-1852-3002 1

Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5 8

Qty

015T1853-101W . . 1 . . . WIRE

015T1853-102W . . 1 . . . WIRE

015T1853-103W . . . 1 . . WIRE

015T1853-104W . . . . 1 . WIRE

015T1853-105W . . . . 1 . WIRE

015T1853-106W . . . . 1 . WIRE

015T1853-107W . . . . 1 . WIRE

015T1853-10101 1 . . . . . DECAL K10718

015T1853-10102 . 1 . . . . DECAL R1197

015T1853-10103 . 1 . . . . DECAL R1196

015T1853-10104 1 . . . . . DECAL D31620

214T3436-1139 . . . . . 1 ORIFICE ASSY

826T5075-00401 . . 1 . . . ID - CONNECTOR

BACC47CN1S . . . 2 . . CONTACT, PIN

CONTACT, SOCKETBACC47CP1S . . 1 . 2 .

BACC47DE8A . . . . 6 . CONTACT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

31 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5 8

Qty

CONTACT, SOCKETBACC47DJ1 . . 4 . . .

BACS16W1A . . 1 . . . RELAY SOCKET

BACS18AR6 . 4 . . . . SPACER

BACS38K2 . . . . . 10 STRAP

BOE2221-0007 . . . . . 6 CAP

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . 1 . 1 .

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

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 . 2 . . . .

Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 12 15 16

Qty

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

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

214T1120-315 . 1 . . . . duct assy

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

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

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

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

RETAINER CLIP

ASSY

411A4902-7 . . 2 . . .

VALVE - AIR

SHUTOFF

67-2951-001 . 1 . . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

32 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 12 15 16

Qty

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

LACING TAPE - (b)

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 . . . 1 . .

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . . . . 1 .

HOSEDUCT,

SLEEVE

AS1506-14D30 . 1 . . . .

CLAMP, MISCELLANEOUSBACC10DU500ABE . 2 . . . .

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

BACC47CN1S . . . . . 6 CONTACT, PIN (c)

CONTACT, SOCK- (d)

ET

BACC47CP1S . . . 14 . .

BACC47DE8A . . . . 3 . CONTACT (e)

CONTACT, SOCK- (e)

ET

BACC47DJ1 . . . . 4 .

BONDING

JUMPER

BACJ40A20-7 . 1 . . . .

BACN10YD1G . 4 . . . . NUTPLATE

BACN10YR3CD . 2 . . . . NUT

RIVET, UNIVERSAL HDBACR15FT6KE5C . 6 . . . .

RIVET, UNIVERSAL HDBACR15FT6KE6C . 2 . . . .

BACR15FT6KE7C . 1 . . . . RIVET

BACS12GU3K7 . 6 . . . . SCREW, CAP

BACS16AG1 . . . . 1 . RELAY SOCKET

BACS16AH1 . . . . 1 . RELAY SOCKET

BACS38K2 2 . . . . . STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

33 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 12 15 16

Qty

BACS38K6 3 1 . . . . STRAP

CONTACT, PIN, (c) (e)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . . . 12 6

PACKING, PREFORMEDMS29512-08 1 . . . . .

NAS1149D0316J . 4 . . . . WASHER

NAS1149D0332H . 6 . . . . WASHER, PLAIN

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

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

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 . . . . 1 .

(a) 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.

(b) Lacing tape P/N 829A9001-2 is also used in FIGURE 16.

(c) For operator convenience, this part is provided in both this kit and wire kit 289T1169-114. There are more

parts supplied than are necessary.

(d) For operator convenience, this part is provided in both this kit and wire kit 289T1169-112. There are more

parts supplied than are necessary.

(e) For operator convenience, this part is provided in both this kit and wire kit 289T1169-113. There are more

parts supplied than are necessary.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

34 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 1-2, Configuration 1:

KIT 015T1853-10

Notes

Existing Part

Name Number

Figure

New Part Number

18

Qty

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 1

BACR13CD2 1 RELAY

BACT19J4 5 TAPE, ID

TIME DELAY RELAYTDH-1852-3002 1

Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5 8

Qty

015T1853-101W . . 1 . . . WIRE

015T1853-102W . . 1 . . . WIRE

015T1853-103W . . . 1 . . WIRE

015T1853-104W . . . . 1 . WIRE

015T1853-105W . . . . 1 . WIRE

015T1853-106W . . . . 1 . WIRE

015T1853-107W . . . . 1 . WIRE

015T1853-10101 1 . . . . . DECAL K10718

015T1853-10102 . 1 . . . . DECAL R1197

015T1853-10103 . 1 . . . . DECAL R1196

015T1853-10104 1 . . . . . DECAL D31620

214T3436-1139 . . . . . 1 ORIFICE ASSY

826T5075-00401 . . 1 . . . ID - CONNECTOR

BACC47CN1S . . . 2 . . CONTACT, PIN

CONTACT, SOCKETBACC47CP1S . . 1 . 2 .

BACC47DE8A . . . . 6 . CONTACT

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

35 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5 8

Qty

CONTACT, SOCKETBACC47DJ1 . . 4 . . .

BACS16W1A . . 1 . . . RELAY SOCKET

BACS18AR6 . 4 . . . . SPACER

BACS38K2 . . . . . 10 STRAP

BOE2221-0007 . . . . . 6 CAP

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . 1 . 1 .

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

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 . 2 . . . .

Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 13 15 17

Qty

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

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

214T1120-315 . 1 . . . . duct assy

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

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

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

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

RETAINER CLIP

ASSY

411A4902-7 . . 2 . . .

VALVE - AIR

SHUTOFF

67-2951-001 . 1 . . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

36 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 13 15 17

Qty

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

LACING TAPE - (b)

RED - PRESSURIZED (TEMP 135

DEG)

829A9001-2 . . . 1 . .

LACING TAPE -

BLUE - PRESSURIZED (TEMP 135

DEG)

829A9001-5 . . . . 1 .

HOSEDUCT,

SLEEVE

AS1506-14D30 . 1 . . . .

CLAMP, MISCELLANEOUSBACC10DU500ABE . 2 . . . .

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

BACC47CN1S . . . . . 6 CONTACT, PIN (c)

CONTACT, SOCK- (d)

ET

BACC47CP1S . . . 14 . .

BACC47DE8A . . . . 3 . CONTACT (e)

CONTACT, SOCK- (e)

ET

BACC47DJ1 . . . . 4 .

BONDING

JUMPER

BACJ40A20-7 . 1 . . . .

BACN10YD1G . 4 . . . . NUTPLATE

BACN10YR3CD . 2 . . . . NUT

RIVET, UNIVERSAL HDBACR15FT6KE5C . 6 . . . .

RIVET, UNIVERSAL HDBACR15FT6KE6C . 2 . . . .

BACR15FT6KE7C . 1 . . . . RIVET

BACS12GU3K7 . 6 . . . . SCREW, CAP

BACS16AG1 . . . . 1 . RELAY SOCKET

BACS16AH1 . . . . 1 . RELAY SOCKET

BACS38K2 2 . . . . . STRAP

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

37 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

9 10 11 13 15 17

Qty

BACS38K6 3 1 . . . . STRAP

CONTACT, PIN, (c) (e)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . . . 12 6

PACKING, PREFORMEDMS29512-08 1 . . . . .

NAS1149D0316J . 4 . . . . WASHER

NAS1149D0332H . 6 . . . . WASHER, PLAIN

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

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

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 . . . . 1 .

(a) 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.

(b) Lacing tape P/N 829A9001-2 is also used in FIGURE 17.

(c) For operator convenience, this part is provided in both this kit and wire kit 289T1169-114. There are more

parts supplied than are necessary.

(d) For operator convenience, this part is provided in both this kit and wire kit 289T1169-112. There are more

parts supplied than are necessary.

(e) For operator convenience, this part is provided in both this kit and wire kit 289T1169-113. There are more

parts supplied than are necessary.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

38 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Group 3, Configuration 1:

KIT 015T1853-11

Notes

Existing Part

Name Number

Figure

New Part Number

18

Qty

VINYL MARKER (1

2 3...30) VERTICAL

BAC27TEX4697 1

BACR13CD2 1 RELAY

BACT19J4 5 TAPE, ID

TIME DELAY RELAYTDH-1852-3002 1

KIT 289T1169-112

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-112W 1

289T1169-10301 1 ID - CONNECTOR

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT12C12S6 1

CONTACT, SOCKET

BACC47CP1S 14

BACC47DE7A 5 CONTACT, PIN

KIT 289T1169-113

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-113W 1

289T1169-10401 1 ID - CONNECTOR

289T1169-10402 1 ID - CONNECTOR

289T1169-10403 1 ID - DIODE

BACC47DE7A 3 CONTACT, PIN

BACC47DE8A 3 CONTACT

CONTACT, SOCKETBACC47DJ1 4

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

39 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
KIT 289T1169-113

New Part Number Qty Name Notes

CONTACT, SOCKETBACC47ER1 12

BACM15C3F 1 TERMINAL BLOCK

BACS16AG1 1 RELAY SOCKET

BACS16AH1 1 RELAY SOCKET

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 12

TERMINAL BLOCK

RESISTOR ASSEMBLY MODULE

YHLZR-17 1

KIT 289T1169-114

New Part Number Qty Name Notes

WIRE - RAW MATERIAL289T1169-114W 1

BACC47CN1S 6 CONTACT, PIN

CONTACT, SOCKETBACC47ER1 5

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 6

Not Available For Procurement

KIT 015T1853-1

New Part Number Qty Name Notes

015T1853-101W 1 WIRE

015T1853-102W 1 WIRE

015T1853-103W 1 WIRE

015T1853-104W 1 WIRE

015T1853-105W 1 WIRE

015T1853-106W 1 WIRE

015T1853-107W 1 WIRE

015T1853-10101 1 DECAL K10718

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: April 16, 2010

Revision 2: September 27, 2013 767-21A0245

40 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Not Available For Procurement

KIT 015T1853-1

New Part Number Qty Name Notes

015T1853-10102 1 DECAL R1197

015T1853-10103 1 DECAL R1196

015T1853-10104 1 DECAL D31620

826T5075-00401 1 ID - CONNECTOR

CONTACT, SOCKETBACC47CP1S 3

BACC47DE8A 6 CONTACT

CONTACT, SOCKETBACC47DJ1 4

BACS16W1A 1 RELAY SOCKET

BACS18AR6 4 SPACER

CONTACT, SOCKET, SIZE 20CTA-0165 1

CONTACT, PIN,

SIZE 20

CTA-0166 1

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1

TIME DELAY RELAYTDH-8050-3003P 1

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 2

Group 1-3, Configuration 1:

KIT 015T1853-2

New Part Number Qty Name Notes

BACC47CN1S 2 CONTACT, PIN

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1

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ALERT ALERT
Not Available For Procurement

KIT 015T1853-3

New Part Number Qty Name Notes

015T1853-101W 1 WIRE

015T1853-102W 1 WIRE

015T1853-103W 1 WIRE

015T1853-104W 1 WIRE

015T1853-105W 1 WIRE

015T1853-106W 1 WIRE

015T1853-107W 1 WIRE

015T1853-10101 1 DECAL K10718

015T1853-10102 1 DECAL R1197

015T1853-10103 1 DECAL R1196

015T1853-10104 1 DECAL D31620

826T5075-00401 1 ID - CONNECTOR

BACC47CN1S 2 CONTACT, PIN

CONTACT, SOCKETBACC47CP1S 3

BACC47DE8A 6 CONTACT

CONTACT, SOCKETBACC47DJ1 4

BACS16W1A 1 RELAY SOCKET

BACS18AR6 4 SPACER

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 2

TIME DELAY RELAYTDH-8050-3003P 1

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 2

2. Parts and Materials Supplied by the Operator

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

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

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

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Part Number / QTY Name Notes

Specification

BMS5-30, TYPE 1 - ADHESIVE (a)

BMS5-157, TYPE - TAPE (a)

I, CLASS 1,

GRADE A

MS20995NC32 - LOCKWIRE

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

for supplier data.

3. Parts Modified and Reidentified

None

4. Parts Removed and Not Replaced

Existing Part Name QTY Notes

Number

BACR13CD2 RELAY 1 (a)

(K10355)

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

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 and fasteners are in Structural Repair

Manual (SRM) Chapter 51

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

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

SRM Chapter 51.

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

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

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

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

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10. 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.

11. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

13. If this service bulletin is accomplished concurrently with service bulletin 767-21-0235,

the functional test, the Flight Deck Air Relief System (FDARS) installation, and the

flex duct change listed in this service bulletin are all that is required.

B. WORK INSTRUCTIONS

Group 1-3, Configuration 1:

3-Way Valve Control Logic Change, Flight Deck Air Relief System (FDARS), and Main Deck

Cargo Compartment Flex Duct Change

1. Get access to the Main Equipment Center (MEC). Refer to 767 AMM 06-41-00 for access location.

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

tag:

Panel Location Name Number

P11-4 C019 CB-EQUIP COOL OVERRIDE C00679

3. Depressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure.

4. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in

the 'OFF' position.

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

6. In the Main Equipment Center (MEC), replace the Flight Deck Air Relief System (FDARS) duct

assembly in accordance with FIGURE 9.

7. In the MEC, install a FDARS air shutoff valve and new duct assemblies in accordance with FIGURE

10.

8. Change relays, decals, ID tape, and marker in the P36 Panel in accordance with FIGURE 1 and

FIGURE 18.

9. Add two diodes in the E8 EICAS rack in accordance with FIGURE 2.

10. Change wire bundle W176:

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a. Group 1-2, Configuration 1:

in accordance with FIGURE 3 and FIGURE 16.

b. Group 3, Configuration 1:

in accordance with FIGURE 3 and FIGURE 17.

11. Change wire bundle W1702 and wire bundle W596 in accordance with FIGURE 4.

12. Change wire bundles W2000 and W2006 in accordance with FIGURE 5.

13. Change wire bundle W184 in accordance with FIGURE 15.

14. Change wire bundle W756:

a. Group 1-2, Configuration 1:

In accordance with FIGURE 12.

b. Group 3, Configuration 1:

In accordance with FIGURE 13.

15. Route wire bundles W176, W1702, and W184 in accordance with FIGURE 6.

16. Route wire bundle W756 in accordance with FIGURE 11.

17. Route wire bundles W2000 and W2006 in accordance with FIGURE 7.

18. In the main deck cargo compartment do the steps that follow to change the flex duct:

a. Remove ceiling panels to get access to the flex ducts that connect the center and aft parts of

the air distribution diffuser at STA 1502. Refer to 767 AMM 25-59-01 as an accepted procedure.

b. Remove flex ducts and install caps and an orifice assy in accordance with FIGURE 8.

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

20. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in

the 'ON' position.

21. Pressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure.

22. In the main deck cargo compartment, install ceiling panels. Refer to 767 AMM 25-59-01 as an

accepted procedure.

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

below:

Panel Location Name Number

P11-4 C019 CB-EQUIP COOL OVERRIDE C00679

24. Do a Manifold Interconnect Valve Reconfiguration Test. Refer to 767 AMM 21-58-00 as an accepted

procedure.

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ALERT ALERT
25. Do the following functional test:

Functional Test of Manifold Interconnect Valve Control Logic Modification

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

OFF.

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

NOTE: If not, then follow AMM Procedure 767 AMM 32-09-02 to reconfigure to GROUND

Mode.

c. Make sure these circuit breakers on the P11 panel are closed:

CB NO. LOC NOMENCLATURE

C00653 A13 LEFT PACK CONT

C00704 A26 RIGHT PACK CONT

C01175 C30 LDG GR POS AIR/GND SYS 1

C4078 J2 L EICAS CMPTR

C4079 J29 R EICAS CMPTR

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

e. Make sure that the EICAS MAINTENANCE ENABLE BYPASS SWITCH (S612) is set to

NORMAL.

f. Make sure that all of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

g. Remove relay K10718 in the P36 panel.

h. Install a jumper from pin X2 of relay K10718 to ground.

NOTE: This simulates a failure.

i. Make sure that all the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

j. Remove the jumper from pin X2 of relay K10718 to ground.

k. Install relay K10718 in the P36 panel.

l. Disconnect Connector (D20366) to Equipment Cooling Temperature Control Switch (S868)

at STA 208, WL 172, and RBL 60.

m. Install a jumper wire between Pin 1 of Connector (D20366) to Pin 2 of Connector (D20366).

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

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ALERT ALERT
Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

o. Disconnect Connector (D2770) from Left Flow Control Valve (V16).

NOTE: This simulates the Left Pack is ON.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

q. Disconnect Connector (D1276) from Right Flow Control Valve (V17).

NOTE: This simulates the Right Pack is ON.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

s. Make sure that there is greater than 20VDC measured from TB239D, R1197(C53) to ground.

NOTE: If the voltage measured is approximately 1.0VDC, diode R1197 is either faulty or

installed in reverse polarity.

t. Deleted

u. Deleted

v. Deleted

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

x. Configure the Air/Ground Relay System to the AIR Mode.

NOTE: Follow AMM Procedure 767 AMM 32-09-02 to reconfigure to AIR Mode.

y. Make sure that none of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

z. If circuit breakers C688 (11B8 on the P11 panel) and C651 (11P13 on the P11 panel) were

opened and the equipment cooling rotary switch on the P5 overhead panel was set to STBY

mode from the AMM procedure to reconfigure to AIR Mode, then do the four (4) sub-steps

which follow:

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(1) Remove relay K336 in the P36 panel.

(2) Remove relay K340 in the P36 panel.

(3) Close circuit breaker C688 (11B8 on the P11 panel).

(4) Set the equipment cooling rotary switch on the P5 overhead panel to the AUTO mode.

CAUTION: INSTRUMENTS IN THE FLIGHT DECK AND E/E BAY WILL NOT RECEIVE FORCED

AIR COOLING. DAMAGE TO THE FLIGHT DECK INSTRUMENTS AND/OR E/E

BAY EQUIPMENT MAY RESULT IF THE SYSTEM REMAINS IN AUTO MODE FOR

MORE THAN 10 MINUTES.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

ab. Install a ground on Pin 2 of Connector (D20950).

NOTE: This simulates a greater than 10,000 FT altitude. If access to this pin is a problem,

remove the wire from Pin 2 of connector (D20950) and ground the wire.

ac. Make sure that all the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

ad. Record the elapsed time from grounding Pin 2 until the Manifold Interconnect Valve (V90)

begins to switch to the OPEN (C-B) position.

Time = ____________ minutes _____________ seconds

Min = 4 minutes 30 seconds Max = 5 minutes 30 seconds

ae. Make sure that the recorded value in the previous step is between the minimum and maximum

allowable value.

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

Condition Nomenclature Equip No

OPEN (C-B) Manifold Interconnect Valve V90

CAUTION: INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE

REMAINS OPEN FOR MORE THAN 10 MINUTES.

ag. Set the equipment cooling rotary switch on P5 overhead panel to STBY.

ah. Wait for 15 minutes to let the equipment to cool down.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

aj. Make sure that all the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

ak. Remove relay K10718 in the P36 panel.

al. Install a jumper from pin X2 of relay K10718 to ground.

NOTE: This simulates a failure.

am. Make sure that all the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

an. Remove the jumper from pin X2 of relay K10718 to ground.

ao. Install relay K10718 in the P36 panel.

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

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

Condition Nomenclature Equip No

OPEN (C-B) Manifold Interconnect Valve V90

CAUTION: INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

ADDITIONALLY, EQUIPMENT IN THE E/E BAY WILL NOT RECEIVE COOLING

WHEN THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD

PANEL IS SET TO THE OVRD POSITION SINCE THE EQUIPMENT COOLING

FANS WILL BE SHUTOFF. DAMAGE MAY RESULT IF THE EQUIPMENT COOLING

ROTARY SWITCH ON THE P5 OVERHEAD PANEL IS SET TO THE OVRD

POSITION FOR MORE THAN 10 MINUTES.

ar. Remove the ground from Pin 2 of Connector (D20950).

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

Condition Nomenclature Equip No

OPEN (C-B) Manifold Interconnect Valve V90

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ALERT ALERT
CAUTION: INSTRUMENTS IN THE FLIGHT DECK WILL NOT RECEIVE COOLING WHEN

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE

REMAINS OPEN FOR MORE THAN 10 MINUTES.

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

CAUTION: IF CIRCUIT BREAKERS C688 (11B8 ON THE P11 PANEL) AND C651 (11P13 ON

THE P11 PANEL) WERE OPENED AND THE EQUIPMENT COOLING ROTARY

SWITCH ON THE P5 OVERHEAD PANEL WAS SET TO STBY MODE FROM THE

AMM PROCEDURE TO RECONFIGURE TO AIR MODE, THEN THE INSTRUMENTS

IN THE FLIGHT DECK AND E/E BAY WILL NOT RECEIVE FORCED AIR COOLING.

DAMAGE TO THE FLIGHT DECK INSTRUMENTS AND/OR E/E BAY EQUIPMENT

MAY RESULT IF THE SYSTEM REMAINS IN AUTO MODE FOR MORE THAN 10

MINUTES.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

av. Connect Pin 2 of Connector (D20950) on the 10K FT Altitude Pressure Switch (S921) if it was

disconnected in a previous step.

aw. Connect Connector (D20950) to the 10K FT Altitude Pressure Switch (S921) on the E8 EICAS

Rack.

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

Condition Nomenclature Equip No

CLOSED (A-B) Manifold Interconnect Valve V90

ay. Make sure that none of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

ba. Remove relay K10718 in the P36 panel.

bb. Install a jumper from pin X2 of relay K10718 to ground.

NOTE: This simulates a failure.

bc. Make sure that none of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

bd. Remove the jumper from pin X2 of relay K10718 to ground.

be. Install relay K10718 in the P36 panel.

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bf. Connect Connector (D2770) to the Left Control Valve (V16).

bg. Connect Connector (D1276) to Right Flow Control Valve (V17).

bh. Disconnect jumper from Pins 1 and 2 of Connector (D20366).

bi. Connect Connector (D20366) to Equipment Cooling Temperature Control Switch (S868) at

STA 208, WL 172, and RBL 60.

bj. If circuit breaker C688 was Closed and K366 and K340 were Removed in a previous step,

THEN do the sub-steps which follow:

(1) Open circuit breaker C688 (11B8 on the P11 panel).

(2) Install relay K366 in the P36 panel.

(3) Install relay K340 in the P36 panel.

(4) Close circuit breaker C688 (11B8 on the P11 panel).

bk. Configure the Air/Ground Relay System to the GROUND Mode.

NOTE: Follow AMM Procedure 767 AMM 32-09-02 to reconfigure to GROUND Mode.

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

26. Put the airplane back in a serviceable condition.

Group 1-3, Configuration 2:

More Work - Flight Deck Air Relief System (FDARS) and Main Deck Cargo Compartment Flex

Duct Change

1. Depressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure.

2. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in

the 'OFF' position.

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

4. In the main deck cargo compartment do the steps that follow to change the flex duct:

a. Remove ceiling panels to get access to the flex ducts that connect the center and aft parts of

the air distribution diffuser at STA 1502. Refer to 767 AMM 25-59-01 as an accepted procedure.

b. Remove flex ducts and install caps and an orifice assy in accordance with FIGURE 8.

5. In the Main Equipment Center (MEC), do the steps that follow to change the Flight Deck Air Relief

System (FDARS):

a. Replace FDARS duct assembly in accordance with FIGURE 9.

b. Install a FDARS air shutoff valve and new duct assemblies in accordance with FIGURE 10.

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c. Change wire bundle W756 between the air shutoff valve and the P36 panel:

(1) Group 1-2, Configuration 2:

in accordance with FIGURE 11 and FIGURE 12.

(2) Group 3, Configuration 2:

in accordance with FIGURE 11 and FIGURE 13.

d. Change wire bundle W184 in the P36 panel in accordance with FIGURE 14 and FIGURE 15

e. Change wire bundle W176 in the P36 panel:

(1) Group 1-2, Configuration 2:

in accordance with FIGURE 14 and FIGURE 16.

(2) Group 3, Configuration 2:

in accordance with FIGURE 14 and FIGURE 17.

f. Install new relays, marker, and ID tape on the P36 panel in accordance with FIGURE 18.

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

7. Pressurize the pneumatic system. Refer to 767 AMM 36-00-00 as an accepted procedure.

8. On the bleed air control module on the pilots overhead P5 panel, put the pack control switches in

the 'ON' position.

9. In the main deck cargo compartment, install ceiling panels. Refer to 767 AMM 25-59-01 as an

accepted procedure.

10. Do a Manifold Interconnect Valve Reconfiguration Test. Refer to 767 AMM 21-58-00 as an accepted

procedure.

11. Put the airplane back to a serviceable condition.

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE

(SHEET 1 OF 2)

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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 airplane.

Step Task Name Identification Qty More Data

1 Remove RELAY BACR13CD2 (K10355) 1

2 Remove DECAL K10355 1 Near Side.

Far Side. Lower the

relay bracket as

needed.

3 Remove DECAL D21730 1

4 Install (New) TIME DELAY RELAY TDH-8050-3003P 1 (K10718)

5 Install (New) DECAL K10718 015T1853-10101 1 Near Side.

Far Side. Lower the

relay bracket as

needed.

6 Install (New) DECAL D31620 015T1853-10104 1

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION

(SHEET 1 OF 2)

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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 each airplane.

Step Task Name Identification Qty More Data

1 Install (New) SPACER BACS18AR6 1

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

Install (New)

Install (New) SPACER BACS18AR6 1

2 Install (New) SPACER BACS18AR6 1

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

Install (New)

Install (New) SPACER BACS18AR6 1

3 Install (New) DECAL R1196 015T1853-10103 1

4 Install (New) DECAL R1197 015T1853-10102 1

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

Reference: 767 WDM 21-58-16.

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

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-81-12 as an

accepted procedure.

1 RELAY SOCKET BACS16W1A 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 4

Refer to SWPM 20-61-11 as an

accepted procedure.

3 CONTACT, SOCKET BACC47CP1S 1

4 WIRE 015T1853-101W 1

FIGURE 3: WIRE BUNDLE W176 CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-71-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 1

REMOVABLE, PER MIL-C39029/11

5

6 WIRE 015T1853-102W 1

Install within 6 inches of the

equipment.

7 ID - CONNECTOR 826T5075-00401 1

FIGURE 3: WIRE BUNDLE W176 CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

Reference: 767 WDM 21-58-16.

NOTE: OPTIONAL: Instead of removing wire W596-606-24 it is acceptable to cap and stow the ends of the

wire near connectors D4992P and D8036P. Refer to SWPM 20-10-11 as an accepted procedure. Refer

to SWPM 20-30-16 for end cap part numbers.

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 20-61-11 as an

accepted procedure. (a)

1 CONTACT, PIN BACC47CN1S 1

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

2 CONTACT, PIN BACC47CN1S 1

3 WIRE 015T1853-103W 1

(a) If Top Kit 015T1853-1 is being used, obtain this part from Supplemental Kit 015T1853-2.

FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE

(SHEET 1 OF 1)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

Reference: 767 WDM 31-41-13.

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 20-20-11 as an

accepted procedure.

1 CONTACT BACC47DE8A 6

Refer to SWPM 20-61-11 as an

accepted procedure.

2 CONTACT, SOCKET BACC47CP1S 1

3 WIRE 015T1853-104W 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 CONTACT, SOCKET BACC47CP1S 1

5 WIRE 015T1853-105W 1

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
Name Identification Qty More Data

Flag

Note

6 WIRE 015T1853-106W 1

7 WIRE 015T1853-107W 1

Refer to SWPM 20-71-11 as an

accepted procedure. (a)

CONTACT, PIN, CRIMP M39029/11-145 1

REMOVABLE, PER MIL-C39029/11

8

(a) If Top Kit 015T1853-1 is being used, obtain this part from Supplemental Kit 015T1853-2.

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 1 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 2 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 3 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 4 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 5 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 6 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 7 OF 8)

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ALERT ALERT
FIGURE 6: WIRE BUNDLES W176 AND W1702 ROUTING

(SHEET 8 OF 8)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 1.

FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING

(SHEET 1 OF 2)

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ALERT ALERT
FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE

(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 each airplane.

Step Task Name Identification Qty More Data

1 Remove / Keep GAP COVER 214T2550-11 1

2 Remove STRAP BACS38K2 6

Remove FLEX DUCT AS4804-12-0040A 3

3 Remove STRAP BACS38K2 2

Remove / Keep FLEX DUCT AS4804-12-0040A 1

to the mating surfaces of the orifice

assy and the duct

assembly. Refer to

SOPM 20-50-12 as

an accepted procedure. (a)

4 Apply ADHESIVE BMS5-30, TYPE 1 -

make sure the orifice

assy part number

and diameter identification tags are outside of the duct assembly. Refer to 767

AMM 21-22-02 as

an accepted procedure.

Install (New) ORIFICE ASSY 214T3436-1139 1

5 Install (Kept) FLEX DUCT AS4804-12-0040A 1

Install (New) STRAP BACS38K2 2 (b)

6 Install (New) CAP BOE2221-0007 6

Install (New) STRAP BACS38K2 6 (b)

7 Install (Kept) GAP COVER 214T2550-11 1

(a) Do not apply adhesive to the orifice assy part number or diameter identification tags.

(b) To apply the correct tension to the strap, use panduit tool GS4H or equivalent. Set the selector knob to

HEAVY EK position and set the tension indicator to 5 for BACS38K2 straps.

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

Name Identification Qty More Data

STRAP BACS38K2 2

FIGURE 8: MAIN DECK CARGO COMPARTMENT - AIR DISTRIBUTION DIFFUSER - FLEX DUCTS CHANGE

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 1 OF 6)

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ALERT ALERT
FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 2 OF 6)

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ALERT ALERT
FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 3 OF 6)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

from the temperature sensor. (a)ELECTRICAL CON- - 1

NECTOR

1 Disconnect

2 Remove LOCKWIRE - - (a)

TEMPERATURE SEN- 3000-46-41 1 (a)

SOR

Remove / Keep

PACKING, PRE- MS29512-08 1 (a)

FORMED

Remove

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 4 OF 6)

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ALERT ALERT
Step Task Name Identification Qty More Data

3 Remove / Keep SCREW BACS12GU( ) 3

do not remove the

marker from the

bracket.

Remove / Keep BRACKET 217T1438-3 1

4 Remove STRAP BACS38K2 2

Remove / Keep SLEEVE AS1506-06D32 1

5 Remove STRAP BACS38K6 2

Remove / Keep SLEEVE AS1506-15D23 1

6 Remove STRAP BACS38K6 1

7 Remove / Keep CLAMP NH102689-0450 1

Remove DUCT ASSY 214T1120-( ) 1

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

Install (Kept) CLAMP NH102689-0450 1

Torque CLAMP NH102689-0450 1 to 40 in-lbs.

9 Install (New) STRAP BACS38K6 1 (b)

10 Install (Kept) SLEEVE AS1506-15D23 1

Install (New) STRAP BACS38K6 2 (b)

11 Install (Kept) SLEEVE AS1506-06D32 1

Install (New) STRAP BACS38K2 2 (c)

12 Install (Kept) BRACKET 217T1438-3 1

Install (Kept) SCREW BACS12GU( ) 3

Torque SCREW BACS12GU( ) 3 to 10-15 in-lbs.

PACKING, PRE- MS29512-08 1 (a)

FORMED

13 Install (New)

TEMPERATURE SEN- 3000-46-41 1 (a)

SOR

Install (Kept)

Refer to SOPM 20-

50-02 as an accepted procedure.

Install (New) LOCKWIRE MS20995NC32 -

ELECTRICAL CON- - 1 (a)

NECTOR

14 Connect

(a) Refer to 767 AMM 21-58-16 as an accepted procedure.

(b) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit

installation tool to the 'HVY' position and the tension indicator to '8'.

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 5 OF 6)

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ALERT ALERT
Step Task Name Identification Qty More Data

(c) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit

installation tool to the 'HVY' position and the tension indicator to '5'.

FIGURE 9: FLIGHT DECK AIR RELIEF SYSTEM DUCT ASSEMBLY REPLACEMENT

(SHEET 6 OF 6)

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ALERT ALERT
FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 1 OF 10)

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ALERT ALERT
FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 2 OF 10)

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ALERT ALERT
FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 3 OF 10)

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ALERT ALERT
FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 4 OF 10)

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ALERT ALERT
FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 5 OF 10)

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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 each airplane.

Step Task Name Identification Qty More Data

to get access to the

frames.

1 Remove / Keep INSULATION - -

2 Remove STRAP - 1

to get access to install brackets. Make

sure the orifice is not

removed.

Disconnect DUCT ASSY - 1

locate as shown on

the aft side of the

frame.

3 Put / Hold BRACKET 214T6419Y40 1

use pilot hole in the

bracket to drill the

first hole and locate

the remaining holes

as shown. Refer to

767-300F SRM 51-

40-05 as an accepted procedure.

Drill HOLE - 3

4 Install (New) BRACKET 214T6419Y40 1

see fastener table

below. (a)

Install (New) FASTENER - 3

from the frame and

the chord at the location shown.

5 Remove RIVET - 1

locate as shown on

the fwd side of the

frame.

6 Put / Hold STIFFENER 141T1226Y33 1

align pilot hole with

the existing fastener

hole. Refer to 767-

300F SRM 51-40-05

as an accepted procedure.

Drill HOLE - 1

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 6 OF 10)

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ALERT ALERT
Step Task Name Identification Qty More Data

locate as shown on

the aft side of the

frame.

7 Put / Hold BRACKET 217T2434U10 1

use pilot hole in the

stiffener to drill the

first hole and locate

the remaining holes

as shown. Refer to

767-300F SRM 51-

40-05 as an accepted procedure.

Drill HOLE - 5

8 Install (New) STIFFENER 141T1226Y33 1

Install (New) BRACKET 217T2434U10 1

see fastener table

below. (a)

Install (New) FASTENER - 6

9 Install (New) SUPPORT, DUCT BACC10ME20-1 2 on the new brackets.

Install (New) NUTPLATE BACN10YD1G 4

Install (New) WASHER NAS1149D0316J 4

Install (New) SCREW, CAP BACS12GU3K7 4

to the mating surfaces of the orifice

assy and the duct

assy. Refer to

SOPM 20-50-12,

Type 48 as an accepted procedure.

(b)

10 Apply ADHESIVE BMS5-30, TYPE 1 -

to duct assy P/N

214T1120-313.

Make sure the orifice

assy part number

and diameter identification tags are outside of the duct assy. Refer to 767

AMM 21-22-02 as

an accepted procedure.

Install (New) ORIFICE ASSY 214T3436-1187 1

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 7 OF 10)

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ALERT ALERT
Step Task Name Identification Qty More Data

connect to duct assembly P/N

214T1120-3311 as

shown.

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

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

Install (New) CLAMP, HOSE NAS1922-0350-3 2

to attach duct assembly to frame.12 Install (New) CLAMP, HOSE NAS1922-0525-3 1

between duct assemblies P/N 214T1120-

313 and P/N

214T1120-315 as

shown.

VALVE - AIR SHUT- 67-2951-001 1

OFF

13 Install (New)

align the alignment

mark on the duct assy to the top of the

duct support to

make sure that the

airflow is exhausted

downward as

shown.

Install (New) duct assy 214T1120-315 1

torque to 62-67 inch

pounds.

CLAMP, MISCELLA- BACC10DU500ABE 2

NEOUS

Install (New)

to attach duct assembly to frame.14 Install (New) CLAMP, HOSE NAS1922-0525-3 1

connect to duct assembly P/N

214T1120-315 as

shown.

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

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

0.218 - 0.229 inch

diameter in the

bracket at the location shown. Refer to

767-300F SRM 51-

40-05 as an accepted procedure.

16 Drill HOLE - 1

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 8 OF 10)

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ALERT ALERT
Step Task Name Identification Qty More Data

where the bonding

jumper terminal lugs

are to be located.

Refer to SOPM 20-

30-03, abrasive

cleaning method, as

an accepted procedure.

17 Clean STRUCTURE - -

Refer to SOPM 20-

30-03, solvent

cleaning method, as

an accepted procedure.

18 Clean TERMINAL LUG - 2

parts stack-up as

shown. (c)

19 Install (New) SCREW, CAP BACS12GU3K7 2

parts stack-up as

shown. (c)

Install (New) WASHER, PLAIN NAS1149D0332H 6

parts stack-up as

shown. (c)

Install (New) BONDING JUMPER BACJ40A20-7 1

parts stack-up as

shown. (c)

Install (New) NUT BACN10YR3CD 2

between the terminal

lug and the structure. Make sure the

bonding resistance

is not more than 1.0

milliohms. If the

bond resistance is

more than 1.0 milliohms, remove the

bonding jumper and

do steps 17 thru 20

again. (c)

20 Measure BOND RESISTANCE - -

21 Connect DUCT ASSY - 1

Install (New) STRAP BACS38K6 1 (d)

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 9 OF 10)

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ALERT ALERT
Step Task Name Identification Qty More Data

that was removed to

get access to the

frames for bracket

installation. Adjust

insulation so that it

fits around new

brackets.

22 Install (Kept) INSULATION - -

use tape to repair

the insulation and to

seal the insulation to

the brackets. Refer

to 767 AMM 25-00-

00 as an accepted

procedure.

BMS5-157, TYPE I, -

CLASS 1, GRADE A

Apply TAPE

(a) Refer to 767-300F SRM 51-40-02 as an accepted procedure.

(b) Do not apply adhesive to the orifice assy part number or diameter identification tags.

(c) Refer to SWPM 20-20-10 as an accepted procedure.

(d) To apply the correct tension to the strap, use panduit installation tool GS4H or equivalent. Set panduit

installation tool to the 'HVY' position and the tension indicator to '8'.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

RIVET, UNIVERSAL BACR15FT6KE5C 3 -

HD

A

RIVET, UNIVERSAL BACR15FT6KE5C 2 -

HD

B

RIVET, UNIVERSAL BACR15FT6KE6C 2 -

HD

C

RIVET, UNIVERSAL BACR15FT6KE5C 1 -

HD

D

E RIVET BACR15FT6KE7C 1 -

FIGURE 10: FLIGHT DECK AIR RELIEF SYSTEM AIR SHUTOFF VALVE AND NEW DUCT ASSEMBLIES

INSTALLATION

(SHEET 10 OF 10)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 1 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 2 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 3 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 4 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 5 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 6 OF 8)

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ALERT ALERT
FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 7 OF 8)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

Step Task Name Identification Qty More Data

locate and install approximately as

shown between or

over insulation blanket.

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

FIGURE 11: WIRE BUNDLE W756 - ROUTING AND RETAINER CLIP ASSEMBLY INSTALLATION

(SHEET 8 OF 8)

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

REFERENCE: 767 WDM 21-58-41

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. Do not use plastic ties.

LACING TAPE - RED - 829A9001-2 1

PRESSURIZED (TEMP 135

DEG)

1

WIRE - RAW MATERIAL 289T1169-112W 1 Refer to cut and code table.

Refer to SWPM 20-20-11 as an

accepted procedure.

2 CONTACT, PIN BACC47DE7A 4

FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

3 CONTACT, SOCKET BACC47CP1S 12

Refer to SWPM 20-61-11 as an

accepted procedure.

CONNECTOR, ELECTRI- BACC45FT12C12S6 1

CAL, PLUG, STRAIGHT,

BAYONET COUPLING

4

Install equipment ID within 6 inches of equipment. 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.

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

Name Identification Qty More Data

CONTACT, SOCKET BACC47CP1S 2

CONTACT, PIN BACC47DE7A 1

WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-112W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W756 132 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 133 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 135 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 136 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 137 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 138 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 139 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 140 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

FIGURE 12: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-41

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. Do not use plastic ties.

LACING TAPE - RED - 829A9001-2 1

PRESSURIZED (TEMP 135

DEG)

1

WIRE - RAW MATERIAL 289T1169-112W 1 Refer to cut and code table.

Refer to SWPM 20-20-11 as an

accepted procedure.

2 CONTACT, PIN BACC47DE7A 4

FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

3 CONTACT, SOCKET BACC47CP1S 12

Refer to SWPM 20-61-11 as an

accepted procedure.

CONNECTOR, ELECTRI- BACC45FT12C12S6 1

CAL, PLUG, STRAIGHT,

BAYONET COUPLING

4

Install equipment ID within 6 inches of equipment. 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.

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

Name Identification Qty More Data

CONTACT, SOCKET BACC47CP1S 2

CONTACT, PIN BACC47DE7A 1

WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-112W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W756 132 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 133 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 135 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 136 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 137 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

W756 138 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 139 24 PK 436 BMS13-48 TYPE 11 CLASS 1, AWG 24

W756 140 20 PA 207 BMS13-48 TYPE 10 CLASS 1, AWG 20

FIGURE 13: P36 PANEL TO AIR SHUTOFF VALVE WIRE BUNDLE W756 - WIRE CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-3, Configuration 2.

FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

(SHEET 1 OF 5)

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ALERT ALERT
FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

(SHEET 2 OF 5)

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ALERT ALERT
FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

(SHEET 3 OF 5)

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ALERT ALERT
FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

(SHEET 4 OF 5)

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ALERT ALERT
FIGURE 14: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLES W176 AND W184 - WIRE ROUTING

(SHEET 5 OF 5)

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ALERT ALERT
REFERENCE: 767 WDM 21-58-41, SWPM 21-58-16

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE

(SHEET 1 OF 3)

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ALERT ALERT
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. Do not use plastic ties.

LACING TAPE - BLUE - 829A9001-5 1

PRESSURIZED (TEMP 135

DEG)

1

WIRE - RAW MATERIAL 289T1169-113W 1 Refer to cut and code table.

Refer to SWPM 20-81-19 as an

accepted procedure.

2 CONTACT, SOCKET BACC47ER1 9

Refer to SWPM 20-20-11 as an

accepted procedure.

3 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

4

Refer to SWPM 20-81-22 as an

accepted procedure.

5 RELAY SOCKET BACS16AG1 1

Install equipment ID within 6 inches of equipment. 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.

6 RELAY SOCKET BACS16AH1 1

Install equipment ID within 6 inches of equipment. Refer to SWPM

20-10-11 as an accepted procedure.

ID - CONNECTOR 289T1169-10402 1

Refer to SWPM 20-81-12 as an

accepted procedure. (a)

7 CONTACT, SOCKET BACC47DJ1 3

Refer to SWPM 20-90-11 as an

accepted procedure.

8 CONTACT BACC47DE8A 2

Refer to SWPM 20-90-11 as an

accepted procedure.

TERMINAL BLOCK RESIS- YHLZR-17 1

TOR ASSEMBLY MODULE

9

ID - DIODE 289T1169-10403 1 (b)

Install Z block at position 21-22 of

TB216. Refer to SWPM 20-90-11

as an accepted procedure.

10 TERMINAL BLOCK BACM15C3F 1

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

as an accepted procedure.

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE

(SHEET 2 OF 3)

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ALERT ALERT
Name Identification Qty More Data

Flag

Note

(b) Install ID tape on top of module so that the first character of ID tape is nearest the 'B' side identification

mark on the module. If necessary, trim the ID tape so that it does not overlap the sides of the module and

does not cover the 'A' and 'B' side. Refer to SWPM 20-10-11 as an accepted procedure.

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

WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-113W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W184 597 24 PK 16 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 734 20 PA 93 BMS13-48 TYPE 10 CLASS 1, AWG 20

W184 737 24 PK 80 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 735 24 PK 40 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 736 24 PK 45 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 731 20 PA 93 BMS13-48 TYPE 10 CLASS 1, AWG 20

W184 732 24 PK 45 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 733 24 PK 45 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 18N 24 PK 50 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 18M 24 PK 50 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 18L 24 PK 55 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 55P 24 PK 30 BMS13-48 TYPE 11 CLASS 1, AWG 24

W184 55R 24 PK 22 BMS13-48 TYPE 11 CLASS 1, AWG 24

FIGURE 15: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W184 - WIRE CHANGE

(SHEET 3 OF 3)

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

REFERENCE: 767 WDM 21-58-41, 767 WDM 21-58-16

FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
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. Do not use plastic ties.

LACING TAPE - RED - 829A9001-2 -

PRESSURIZED (TEMP 135

DEG)

1

WIRE - RAW MATERIAL 289T1169-114W 1 Refer to cut and code table.

Refer to SWPM 20-81-19 as an

accepted procedure. (a)

2 CONTACT, SOCKET BACC47ER1 4

Refer to SWPM 21-61-11 as an

accepted procedure. (a)

3 CONTACT, PIN BACC47CN1S 5

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 4

REMOVABLE, PER MIL-C39029/11

4

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

as an accepted procedure.

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

Name Identification Qty More Data

CONTACT, PIN BACC47CN1S 1

CONTACT, SOCKET BACC47ER1 1

CONTACT, PIN, M39029/11-145 2

CRIMP REMOVABLE,

PER MIL-C-39029/11

WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-114W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W176 89K 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68G 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68H 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 69K 24 PK 45 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68F 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68K 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

FIGURE 16: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 3.

REFERENCE: 767 WDM 21-58-41, 767 WDM 21-58-16

FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE

(SHEET 1 OF 2)

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ALERT ALERT
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. Do not use plastic ties.

LACING TAPE - RED - 829A9001-2 -

PRESSURIZED (TEMP 135

DEG)

1

WIRE - RAW MATERIAL 289T1169-114W 1 Refer to cut and code table.

Refer to SWPM 20-81-19 as an

accepted procedure. (a)

2 CONTACT, SOCKET BACC47ER1 4

Refer to SWPM 21-61-11 as an

accepted procedure. (a)

3 CONTACT, PIN BACC47CN1S 5

Refer to SWPM 20-90-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 4

REMOVABLE, PER MIL-C39029/11

4

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

as an accepted procedure.

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

Name Identification Qty More Data

CONTACT, PIN BACC47CN1S 1

CONTACT, SOCKET BACC47ER1 1

CONTACT, PIN, M39029/11-145 2

CRIMP REMOVABLE,

PER MIL-C-39029/11

WIRE LIST - CUT AND CODE AS REQUIRED - 289T1169-114W

LENGTH MATERIAL SPECIFICATION NOTES

(INCHES)

TYPE

CODE

GAGE

COLOR

WIRE

NUMBER

WIRE

BUNDLE

W176 89K 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68G 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68H 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 69K 24 PK 45 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68F 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

W176 68K 24 PK 60 BMS13-48 TYPE 11 CLASS 1, AWG 24

FIGURE 17: MAIN EQUIPMENT CENTER P36 PANEL WIRE BUNDLE W176 - WIRE CHANGE

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION

(SHEET 1 OF 5)

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ALERT ALERT
FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION

(SHEET 2 OF 5)

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ALERT ALERT
FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION

(SHEET 3 OF 5)

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Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2 September 27, 2013 767-21A0245

119 of 121

BOEING SERVICE BULLETIN 767-21A0245

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 each airplane.

Step Task Name Identification Qty More Data

as K10725. Refer to

SOPM 20-50-10 as

an accepted procedure.

1 Identify TAPE, ID BACT19J4 1

identified as

K10725. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

as D20325. Refer to

SOPM 20-50-10 as

an accepted procedure.

2 Identify TAPE, ID BACT19J4 1

identified as

D20325. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

Refer to SWPM 20-

81-22 as an accepted procedure.

3 Install (New) TIME DELAY RELAY TDH-1852-3002 1

as K10723. Refer to

SOPM 20-50-10 as

an accepted procedure.

4 Identify TAPE, ID BACT19J4 1

identified as

K10723. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

as D20323. Refer to

SOPM 20-50-10 as

an accepted procedure.

5 Identify TAPE, ID BACT19J4 1

identified as

D20323. Refer to

SOPM 20-50-05 as

an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION

(SHEET 4 OF 5)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2 September 27, 2013 767-21A0245

120 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT
Step Task Name Identification Qty More Data

Refer to SWPM 20-

81-22 as an accepted procedure.

6 Install (New) RELAY BACR13CD2 1

as R1270. Refer to

SOPM 20-50-10 as

an accepted procedure.

7 Identify TAPE, ID BACT19J4 1

identified as R1270.

Refer to SOPM 20-

50-05 as an accepted procedure.

Install (New) TAPE, ID BACT19J4 1

Refer to SOPM 20-

50-05 as an accepted procedure.

VINYL MARKER (1 2 BAC27TEX4697 1

3...30) VERTICAL

8 Install (New)

FIGURE 18: MAIN EQUIPMENT CENTER P36 PANEL RELAY INSTALLATION

(SHEET 5 OF 5)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2010

Revision 2 September 27, 2013 767-21A0245

121 of 121

BOEING SERVICE BULLETIN 767-21A0245

ALERT ALERT