# Boeing Alert Service Bulletin 767-21A0253: No revision named

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-21A0253
Original Issue: October 12, 2012
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief
System and 3-Way Valve Logic Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2012 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing
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with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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3.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ......................................... 9
B. Concurrent Requirements ....................................... 9
C. Reason ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 1
G. Manpower .............................................. 1 1
H. Weight and Balance Changes .................................... 1 2
I. Electrical Load Data ......................................... 1 2
J. References .............................................. 1 2
1. Existing Data: ......................................... 1 2
2. Data Supplied with this Service Bulletin: ........................... 1 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 3
K. Publications Affected ........................................ 1 3
L. Interchangeability and Intermixability of Parts ........................... 1 3
M. Software Accomplishment Summary ................................ 1 3
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 2 0
3. Parts Modified and Reidentified ................................ 2 0
4. Parts Removed and Not Replaced .............................. 2 0
D. Parts Necessary to Change Spares ................................. 2 0
E. Special Tooling - Price and Availability ............................... 2 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 2
FIGURE 1: EXISTING DUCT REPLACEMENT .............................. 2 3
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION ..................... 2 9
FIGURE 3: WIRE DELETION IN PANEL P50 ............................... 3 6
FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50 ................ 3 7
FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE
DIAGRAM) ........................................... 3 8
FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM) . 40
FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM) ...................... 4 3
FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36 .................... 4 6
FIGURE 9: INSTALLATION OF NEW ALTITUDE SWITCH AND PITOT TUBE ............. 5 0
FIGURE 10: CONNECTION OF EXISTING WIRING TO ALTITUDE SWITCH .............. 5 3
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FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT ............ 5 4
FIGURE 12: INSTALLATION OF WIRE WITHIN PANEL P36 ....................... 6 1
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-21A0253Original Issue: October 12, 2012
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief
System and 3-Way Valve Logic Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring, or loss
of color caused by moisture or condensation being collected inside the display units can occur during operation
in hot and humid environments. Flight compartment indication blanking can cause unscheduled maintenance
and airplane downtime. More importantly, 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. If this service
bulletin is not done, and primary display blanking occurs, the flight crew would be required to transition from
primary attitude indication to standby attitude indication during a critical phase of flight which could contribute
to an unsafe flight condition.
Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring, or loss of
color caused by moisture or condensation being collected inside the display units during operation in hot and
humid environments. The reports have included single display unit and multiple display unit malfunctions. Boeing
is aware of instances that are the likely causes of display unit malfunctions related to moisture or condensation
ingress. These instances are as follows; an unserviceable air conditioning pack water separation system that
allowed water to be delivered to the flight compartment in the air conditioned air, a malfunction of an air
conditioning pack which caused ice to be delivered to the flight compartment in the air conditioned air; and the
most frequent instance was display units being cold soaked by the air conditioned air delivered from the air
conditioning packs by the Electrical/Electronic cooling system through the 3-way valve in hot and humid conditions.
As a result of these findings, the control logic of the 3-way valve is changed so that the valve will open after five
minutes at an altitude above 10,000 feet, and close at an altitude below 10,000 feet. Limiting the 3-way valve
to open after five minutes above 10,000 feet will decrease the amount of moisture or condensation that can
collect in the display units because of the reduced water content in the atmosphere at higher altitudes.
The control logic for the 3-way valve was intended to be incorporated on affected airplanes in production.
However, the noise in the flight compartment caused by the increased airflow of the 3-way valve logic system
made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a solution to reduce
the noise in the flight deck was not available before delivery, the 3-way valve logic system was disabled.
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### Page 6

This service bulletin installs a new Flight Deck Air Relief System (FDARS) to reduce the noise in the flight
compartment and restores the 3-way valve logic to reduce the amount of moisture or condensation that can
collect in the flight compartment display units and thus reduce malfunction occurrences.
Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR B12900-260)
In the area forward of the main equipment bay and under the flight deck floor, replace a duct for equipment
cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS) components. Install
mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring within panel P36 and among
panels and new outlet valve. Install 10,000 foot altitude switch and connect it to existing pitot tubing and wiring.
Do an operational test.
EFFECTIVITY
767-300F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 72 months after the original
issue date of this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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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
Elapsed HoursTotal Task HoursAirplanes
42.0076.35All
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
REPLACE DUCT
ADD MOUNTING BRACKETS
DUCTS, ORIFICE, OUTLET
VALVE, AND SCREEN.
NOT SHOWN - ADD 10,000 FT
ALTITUDE SWITCH AND
MODIFY WIRING.
FWD
NBD  2182195
Original Issue: October 12, 2012
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### Page 9

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-21A0253
Original Issue: October 12, 2012
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - Installation of Flight Deck Air Relief
System and 3-Way Valve Logic Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR B12900-260 for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767-300F Airplanes identified below.-1
Airplane Models:
767-300F
GroupVariable Number
1VR280 - VR283
2. Spares Affected
None.
B. Concurrent Requirements
None.
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### Page 10

C. Reason
This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring,
or loss of color caused by moisture or condensation being collected inside the display units can occur
during operation in hot and humid environments. Flight compartment indication blanking can cause
unscheduled maintenance and airplane downtime. More importantly, 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. If this service bulletin is not done, and primary display blanking occurs,
the flight crew would be required to transition from primary attitude indication to standby attitude
indication during a critical phase of flight which could contribute to an unsafe flight condition.
Operators of 767-300F airplanes have reported display unit malfunctions such as blanking, blurring,
or loss of color caused by moisture or condensation being collected inside the display units during
operation in hot and humid environments. The reports have included single display unit and multiple
display unit malfunctions. Boeing is aware of instances that are the likely causes of display unit
malfunctions related to moisture or condensation ingress. These instances are as follows; an
unserviceable air conditioning pack water separation system that allowed water to be delivered to the
flight compartment in the air conditioned air, a malfunction of an air conditioning pack which caused
ice to be delivered to the flight compartment in the air conditioned air; and the most frequent instance
was display units being cold soaked by the air conditioned air delivered from the air conditioning packs
by the Electrical/Electronic cooling system through the 3-way valve in hot and humid conditions. As a
result of these findings, the control logic of the 3-way valve is changed so that the valve will open after
five minutes at an altitude above 10,000 feet, and close at an altitude below 10,000 feet. Limiting the
3-way valve to open after five minutes above 10,000 feet will decrease the amount of moisture or
condensation that can collect in the display units because of the reduced water content in the atmosphere
at higher altitudes.
The control logic for the 3-way valve was intended to be incorporated on affected airplanes in production.
However, the noise in the flight compartment caused by the increased airflow of the 3-way valve logic
system made the Traffic Alert and Collision Avoidance System (TCAS) difficult to hear. Because a
solution to reduce the noise in the flight deck was not available before delivery, the 3-way valve logic
system was disabled.
This service bulletin installs a new Flight Deck Air Relief System to reduce the noise in the flight
compartment and restores the 3-way valve logic to reduce the amount of moisture or condensation
that can collect in the flight compartment display units and thus reduce malfunction occurrences.
Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.
D. Description
In the area forward of the main equipment bay and under the flight deck floor, replace a duct for
equipment cooling with a duct that has an outlet port for the Flight Deck Air Relief System (FDARS)
components. Install mounting brackets, FDARS ducts, orifice, outlet valve and screen. Change wiring
within panel P36 and among panels and new outlet valve. Install 10,000 foot altitude switch and connect
it to existing pitot tubing and wiring. Do an operational test.
The changes in this service bulletin will not change the Engine Indication and Crew Alerting System
(EICAS).
The work in this service bulletin is done in the maintenance zone(s) given below.
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### Page 11

Affected Maintenance Zones
ZoneModel
117, 118, 119767-300F
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Boeing recommends that the change given in this service bulletin be done within 72 months after the
original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved. This service
bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as
modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
0.750.751Open Access
1.601.601FIGURE 1
1.751.751FIGURE 2
0.100.101FIGURE 3
0.100.101FIGURE 4
12.3824.752FIGURE 5
5.1010.202FIGURE 6
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Elapsed HoursTask HoursNumber of PersonsTask
16.8833.752FIGURE 7
1.501.501FIGURE 8
0.500.501FIGURE 9
0.100.101FIGURE 10
0.500.501Test
0.750.751Close Access
42.0076.35TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 966.1+ 7.0All
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR B12900-260
b. Boeing Service Related Problem (SRP) 767-SRP-21-0179
c. Service Bulletin Index D624T001
d. Standard Overhaul Practices Manual (SOPM) 20-50-10
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10, 20-61-11,
20-81-19, 20-81-22, 20-90-11
f. 767 Aircraft Maintenance Manual (AMM) 20-10-12, 20-10-33, 21-22-02, 21-58-00, 24-22-00,
25-00-00
g. 767 Wiring Diagram Manual (WDM) 21-58-16, 21-58-41
2. Data Supplied with this Service Bulletin:
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Duct Installation - Flight Deck Section 41214T1011
Duct Installation - Instrument Panel Cooling System217T2013
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
21-00, 21-51, 21-58767 Aircraft Maintenance Manual
21-58, Equipment List767 Wiring Diagram Manual
21-58767 Fault Isolation Manual
21-22, 21-58, 34-11767 Illustrated Parts Catalog
21-58767 System Schematic Manual
21767 Master Minimum Equipment List
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
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### Page 15

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$55,663.001494September 28,
2012
TOP KIT - 3-WAY
VALVE LOGIC
CHANGE
015T1883-1
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 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
12119821Top Kit
111111015T1883-1
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### Page 16

Top Kit
015T1883-1Wire Kit
1289T1169-104
1289T1169-103
1289T1169-105
ALL
KIT 015T1883-1
Notes
Existing Part
NumberName
Figure
New Part Number
12119821
Qty
CLAMP MOUNT-
ING INSTRUMENT
..1...123-2
(a), (b)STIFFENER....1.141T1226Y33
QUICK DISCON-
NECT
..1...1QF2-3-64A
DISCONNECT..1...1QM1-3-54A
DUCT ASSY....1.214T1120-313
DUCT ASSY....1.214T1120-315
(c)214T1120-3218DUCT ASSY.....1214T1120-3311
ORIFICE ASSY....1.214T3436-453
(a), (b)BRACKET....1.214T6419Y40
(a), (b)BRACKET....1.217T2434U10
RETAINER CLIP
ASSY
.2....411A4902-7
Pressure Switch..1...6502-10K
VALVE - AIR
SHUTOFF
....1.67-2951-001
SCREEN ASSY....1.69B42275-4
LACING TAPE -
RED - PRESSUR-
IZED (TEMP 135
DEG)
11....829A9001-2
LACING TAPE -
BLUE - PRESSUR-
IZED (TEMP 135
DEG)
1.....829A9001-5
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### Page 17

ALL
KIT 015T1883-1
Notes
Existing Part
NumberName
Figure
New Part Number
12119821
Qty
HOSEDUCT,
SLEEVE
....1.AS1506-14D30
VINYL MARKER (1
2 3...30) VERTI-
CAL
...1..BAC27TEX4697
VINYL DECAL..1...BAC27TFDE534
CLAMP, MISCEL-
LANEOUS
....2.BACC10DU500ABE
SUPPORT, DUCT....2.BACC10ME20-1
HOSE, INSTRU-
MENT
..1...BACH30BC06-
0110
BONDING
JUMPER
....1.BACJ40A20-7
NUTPLATE....4.BACN10YD1G
(d)NUT....3.BACN10YR3CD
RELAY...1..BACR13CD2
(d), (e)RIVET, UNIVER-
SAL HD
....8.BACR15FT6KE5C
(d), (e)RIVET, UNIVER-
SAL HD
....4.BACR15FT6KE6C
(d), (e)RIVET....3.BACR15FT6KE7C
(d)SCREW, CAP....7.BACS12GU3K7
(d)STRAP.....3BACS38K2
(d)STRAP....14BACS38K6
(d)TAPE, ID...8..BACT19J4
PACKING, PRE-
FORMED
..1...MS28778-5
PACKING, PRE-
FORMED
.....1MS29512-08
(d)WASHER....6.NAS1149D0316J
(d)WASHER, PLAIN....8.NAS1149D0332H
CLAMP, HOSE....2.NAS1922-0350-3
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BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 18

ALL
KIT 015T1883-1
Notes
Existing Part
NumberName
Figure
New Part Number
12119821
Qty
CLAMP, HOSE....3.NAS1922-0525-3
TIME DELAY RE-
LAY
...1..TDH-1852-3002
TIME DELAY RE-
LAY
...1..TDH-8050-3003P
(a) This part not used in production.
(b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify
these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts
are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this
service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service
Letter 767-SL-00-014 for more information.
(c) You cannot use the existing part to replace the new or changed part.
(d) There are more parts than are necessary.
(e) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer
than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,
substitute fasteners may be supplied in kits.
KIT 289T1169-103
NotesNameQtyNew Part Number
WIRE - RAW MA-
TERIAL
1289T1169-103W
ID - CONNECTOR1289T1169-10301
CONNECTOR,
ELECTRICAL,
PLUG, STRAIGHT,
BAYONET COU-
PLING
1BACC45FT12C12S6
(a)CONTACT, SOCK-
ET
14BACC47CP1S
(a)CONTACT, PIN5BACC47DE7A
(a) There are more parts than are necessary.
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ALERTALERT

### Page 19

KIT 289T1169-104
NotesNameQtyNew Part Number
WIRE - RAW MA-
TERIAL
1289T1169-104W
ID - CONNECTOR1289T1169-10401
ID - CONNECTOR1289T1169-10402
ID - DIODE1289T1169-10403
(a)CONTACT, SOCK-
ET
2BACC47CP1S
(a)CONTACT, PIN3BACC47DE7A
(a)CONTACT3BACC47DE8A
(a)CONTACT, SOCK-
ET
4BACC47DJ1
(a)CONTACT, SOCK-
ET
10BACC47ER1
RELAY SOCKET1BACS16AG1
RELAY SOCKET1BACS16AH1
(a)CONTACT, PIN,
CRIMP REMOV-
ABLE, PER MIL-C-
39029/11
10M39029/11-145
TERMINAL BLOCK
RESISTOR AS-
SEMBLY MODULE
1YHLZR-17
(a) There are more parts than are necessary.
KIT 289T1169-105
NotesNameQtyNew Part Number
WIRE - RAW MA-
TERIAL
1289T1169-105W
(a)CONTACT, PIN6BACC47CN1S
(a)CONTACT, SOCK-
ET
5BACC47DJ1
(a)CONTACT, SOCK-
ET
5BACC47ER1
(a)CONTACT, PIN,
CRIMP REMOV-
ABLE, PER MIL-C-
39029/11
6M39029/11-145
(a) There are more parts than are necessary.
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ALERTALERT

### Page 20

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.
NotesNameQtyPart Number/ Specification
(a)TAPE10 ftBMS 5-157 TYPE I, CLASS 1,
GRADE A, COMPOSITION
MPVF
LOCKWIRE1 ftMS20995N32  (MS20995NC32
optional)
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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ALERTALERT

### Page 21

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
8. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
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ALERTALERT

### Page 22

10. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
11. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
B. WORK INSTRUCTIONS
1. Remove electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.
2. Gain access to the main equipment center and the area under the left and right sides of the flight
deck floor.
3. Replace existing duct with new duct in accordance with FIGURE 1.
4. Install new Flight Deck Air Relief System (FDARS) components including mounting brackets, ducts,
orifice, outlet valve and screen in accordance with FIGURE 2.
5. Modify wiring as follows:
a. Delete wire in panel P50 in accordance with FIGURE 3.
b. Delete wire between panel P36 and panel P50 in accordance with FIGURE 4.
c. Add wires and connector between panel P36 and new valve in accordance with FIGURE 5
(wire diagram) and FIGURE 11 (wire installation).
d. Modify wiring within Panel P36 in accordance with FIGURE 6 and FIGURE 7 (wire diagrams)
and FIGURE 12 (wire installation).
6. Modify relay installation in panel P36 in accordance with FIGURE 8.
7. Install new 10,000 foot altitude switch and pitot tube in accordance with FIGURE 9.
8. Connect existing wiring to altitude switch in accordance with FIGURE 10.
9. Restore electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.
10. Do an Operational Test - Manifold Interconnect Valve (Reconfiguration) - Post SB 767-21A0253.
Refer to 767 AMM 21-58-00 as an acceptable procedure.
11. Put the airplane back to a serviceable condition.
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ALERTALERT

### Page 23 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
• A
P54 PANEL
AND C
FWD
INBD
2182196
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 1 OF 6)
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
180.50  STA
196.50
STA
228.50
BEFORE
2182414
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 2 OF 6)
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
180.50  STA
196.50
STA
228.50
AFTER
C  2185225
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 3 OF 6)
Original Issue: October 12, 2012
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### Page 26

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
5-STRAPRemove1
1AS1506-15D23SLEEVERemove / Keep2
1AS1506-06D32SLEEVERemove / Keep3
1NH102689-0450CLAMPRemove / Keep4
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 4 OF 6)
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ALERTALERT

### Page 27

More DataQtyIdentificationNameTaskStep
-D20366CONNECTORDisconnect5
--LOCKWIRERemove
13000-46-41TEMPERATURE CON-
TROL SWITCH
Remove / Keep
1MS29512-08PACKING, PRE-
FORMED
Remove
2BACS12GU( )SCREWRemove / Keep
(a)1217T1438-3BRACKETRemove / Keep
1214T1120-3218DUCT ASSYRemove6
1214T1120-3311DUCT ASSYInstall (New)7
(a)1217T1438-3BRACKETInstall (Kept)8
2BACS12GU( )SCREWInstall (Kept)
13000-46-41TEMPERATURE CON-
TROL SWITCH
Install (Kept)
1MS29512-08PACKING, PRE-
FORMED
Install (New)
(b)-MS20995N32
(MS20995NC32 option-
al)
LOCKWIREInstall (New)
-D20366CONNECTORConnect
1NH102689-0450CLAMPInstall (Kept)9
(c)1BACS38K6STRAPInstall (New)10
1AS1506-15D23SLEEVEInstall (Kept)11
(c)2BACS38K6STRAPInstall (New)
1AS1506-06D32SLEEVEInstall (Kept)12
(c)2BACS38K2STRAPInstall (New)
(a) Includes Marker BAC27TEC334.
(b) Refer to 767 AMM 20-10-33 as an accepted procedure.
(c) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H
OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE
STRAPS AND (8) FOR .30 WIDE STRAPS
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 5 OF 6)
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ALERTALERT

### Page 28

The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACS38K2STRAP
1BACS38K6STRAP
FIGURE 1: EXISTING DUCT REPLACEMENT
(SHEET 6 OF 6)
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ALERTALERT

### Page 29 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
• A
FWD
2182452
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 1 OF 7)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
220.50
STA
228.50
10
FRAME
2) 16)  STA
228.50
FWD
INSULATION NOT SHOWN  2182493
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 2 OF 7)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
220.50
FRAME
0.33
0.80
,0.49
1.60
0.37
*0.41  STA
220.50
2.60
FRAME
2.62
INBD  . 1.10
A-A  0.80  K0.80
88
INBD
B-B
FWD
TYPICAL 2 LOCATIONS
2182552
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 3 OF 7)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
ALIGNMENT  →0.50
LINE  C-C  FWD  DUCT  CLAMP O  © CLAMP  10) DUCT
1.49  SLEEVE 9  ORIFICE  TAB
1.29
FWD
HOLE 1A
1.35
1.15
INBD  D-D  2185451
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 4 OF 7)
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### Page 33

More DataQtyIdentificationNameTaskStep
At both frames.--INSULATIONRetract1
1-STRAPRemove2
For access to install
rivets.
--DUCTDisconnect3
AFT of side of
frame.
1214T6419Y40BRACKETInstall (New)4
3BACR15FT6KE5CRIVET, UNIVERSAL
HD
Install (New)
Through frame and
chord.
1-RIVETRemove5
AFT side of frame.1217T2434U10BRACKETInstall (New)6
FWD side of frame.1141T1226Y33STIFFENERInstall (New)
Through frame,
chord and stiffener.
1BACR15FT6KE7CRIVETInstall (New)
Through bracket,
frame and stiffener.
2BACR15FT6KE6CRIVET, UNIVERSAL
HD
Install (New)
Through bracket and
frame.
2BACR15FT6KE5CRIVET, UNIVERSAL
HD
Install (New)
Through frame and
stiffener.
1BACR15FT6KE5CRIVET, UNIVERSAL
HD
Install (New)
2BACC10ME20-1SUPPORT, DUCTInstall (New)7
4BACS12GU3K7SCREW, CAPInstall (New)
4NAS1149D0316JWASHERInstall (New)
4BACN10YD1GNUTPLATEInstall (New)
(a)1214T3436-453ORIFICE ASSYInstall (New)8
1AS1506-14D30HOSEDUCT, SLEEVEInstall (New)9
1NAS1922-0350-3CLAMP, HOSEInstall (New)
1214T1120-313DUCT ASSYInstall (New)10
1NAS1922-0350-3CLAMP, HOSEInstall (New)
1NAS1922-0525-3CLAMP, HOSEInstall (New)
(b)1214T1120-315DUCT ASSYInstall (New)11
1NAS1922-0525-3CLAMP, HOSEInstall (New)
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 5 OF 7)
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ALERTALERT

### Page 34

More DataQtyIdentificationNameTaskStep
167-2951-001VALVE - AIR SHUT-
OFF
Install (New)12
2BACC10DU500ABECLAMP, MISCELLA-
NEOUS
Install (New)
169B42275-4SCREEN ASSYInstall (New)13
1NAS1922-0525-3CLAMP, HOSEInstall (New)
(c)1BACJ40A20-7BONDING JUMPERInstall (New)14
0.218 - 0.229 IN DIA1-HOLEDrill
2BACS12GU3K7SCREW, CAPInstall (New)
6NAS1149D0332HWASHER, PLAINInstall (New)
2BACN10YR3CDNUTInstall (New)
--DUCTConnect15
(d)1BACS38K6STRAPInstall (New)16
--INSULATIONRepair17
(e)-BMS 5-157 TYPE I,
CLASS 1, GRADE A,
COMPOSITION MPVF
TAPEInstall (New)
(a) Refer to 767 AMM 21-22-02 as an accepted procedure.
(b) Align the alignment mark on elbow duct to the top of the duct support to make sure that the airflow will
be exhausted downward at the catwalk surface.
(c) CLEAN, ASSEMBLE AND TEST GROUND. REFER TO SWPM 20-20-10 AS AN ACCEPTED PROCE-
DURE. MEASURE RESISTANCE BETWEEN VALVE BODY AND FRAME INCLUDING SCREW, NUT
AND WASHERS. MAXIMUM RESISTANCE 0.005 OHM.
(d) TO APPLY CORRECT TENSION TO BACS38K() STRAP, USE PANDUIT INSTALLATION TOOL GS4H
OR EQUIVALENT, SET ON -HVY- POSITION AND TENSION INDICATOR ON (5) FOR .19 WIDE
STRAPS AND (8) FOR .30 WIDE STRAPS
(e) Use tape to repair insulation and to seal insulation to brackets. Refer to 767 AMM 25-00-00 as an accepted
procedure.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACN10YR3CDNUT
1BACS12GU3K7SCREW, CAP
2NAS1149D0316JWASHER
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 6 OF 7)
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ALERTALERT

### Page 35

More DataQtyIdentificationName
2BACR15FT6KE5CRIVET, UNIVERSAL
HD
2BACR15FT6KE6CRIVET, UNIVERSAL
HD
2BACR15FT6KE7CRIVET
2NAS1149D0332HWASHER, PLAIN
FIGURE 2: ADDITIONAL DUCT AND VALVE INSTALLATION
(SHEET 7 OF 7)
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ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
23  +AW1114-140-24741114
D10064
M1093 L N2 ENGINE
SPEED PC ASSY
AE0202
33
D8036P
P50 ELECTRICAL SYSTEMS CARD FILE
- ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  - EXISTING WIRE  2183452
Reference : 767 WDM 21-58-16
No parts are installed in this figure.
FIGURE 3: WIRE DELETION IN PANEL P50
(SHEET 1 OF 1)
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### Page 37

Reference : 767 WDM 21-58-16
No parts are installed in this figure.
FIGURE 4: WIRE DELETION BETWEEN PANEL P36 AND PANEL P50
(SHEET 1 OF 1)
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ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
AE0209
GD754-SI|[  W756-132-20  5
133-24
GD754-DC 1|  135-20
46  136-24
W176
GD754-DC I|  137-20
47  138-24  2
48  139-24
D5832P
P36  LEFT MISC  GD754-DC 1IL  W756-140-20
ELECT EQUIPMENT  DV900
• STA 220, WL 100. RBL 60  V900 FLT DECK AIR RELIEF
• ADDED WIRE OR NEW ROUTING
+  + DELETED WIRE OR FORMER ROUTING
EXISTING WIRE
Reference : 767 WDM 21-58-41
NOTE: The parts are in Wire Kit 289T1169-103. The wire is identified as 289T1169-103W.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
Flag
Note  Name  Identification  Qty  More Data
CONTACT, PIN  BACC47DE7A  Refer to SWPM 20-90-11 as an
accepted procedure.
2  CONTACT, SOCKET  BACC47CP1S  12  Refer to SWPM 20-61-11 as an
accepted procedure. (a)
CONNECTOR, ELECTRI-  BACC45FT12C12S6  Refer to SWPM 20-61-11 as an
CAL, PLUG, STRAIGHT,  accepted procedure.
BAYONET COUPLING
ID - CONNECTOR  289T1169-10301  Refer to SWPM 20-10-11 as an
accepted procedure.
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11
as an accepted procedure.
FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)
(SHEET 1 OF 2)
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### Page 39

NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE
NUMBER
WIRE
BUNDLE
BMS 13-48, TYPE 10, CLASS 1, AWG 20207PA20132W0756
BMS 13-48, TYPE 11, CLASS 1, AWG 24436PK24133W0756
BMS 13-48, TYPE 10, CLASS 1, AWG 20207PA20135W0756
BMS 13-48, TYPE 11, CLASS 1, AWG 24436PK24136W0756
BMS 13-48, TYPE 10, CLASS 1, AWG 20207PA20137W0756
BMS 13-48, TYPE 11, CLASS 1, AWG 24436PK24138W0756
BMS 13-48, TYPE 11, CLASS 1, AWG 24436PK24139W0756
BMS 13-48, TYPE 10, CLASS 1, AWG 20207PA20140W0756
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACC47DE7ACONTACT, PIN
2BACC47CP1SCONTACT, SOCKET
FIGURE 5: WIRE AND CONNECTOR ADDITION BETWEEN PANEL P36 AND NEW VALVE (WIRE DIAGRAM)
(SHEET 2 OF 2)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
39 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
W184-731-20  ДІ' GDX1-DC
W184-732-24  215
TB218
W184-733-24  YC10
TB216
W184-736-24
W184-735-24
D20323 GDX1-DC 11_  • W184-734-20  2
K10723 MIV & FLT  2
DECK RLF IND
YA17  W184-737-24
TB302  D20325
K10725 FLT DECK
MIV TIME RELAY
B1  W184-18N-24  XC4
ВЗ  • W184-18M-24  ХD4
TB218
B2  • W184-18L-24
D20360
K2193 MANIFOLD
INTERCONNECT
A17  C17
214  W184-55P-24  W184-55R-24  YA12
TB216  TB220R  TB220
R1270
AE0209
5  W184-75V-24
- 011550  D5654P
K1011  EQPT COOLING
SMOKE CLEARANCE RLY
P36 LEFT MISC ELEC EQUIPMENT
• ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  EXISTING WIRE  2183716
Reference: 767 WDM 21-58-41
FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)
(SHEET 1 OF 3)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  40 of 66

### Page 41

NOTE: The parts are in Wire Kit 289T1169-104. The wire is identified as 289T1169-104W.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataQtyIdentificationName
Flag
Note
Refer to SWPM 20-81-19 as an
accepted procedure. (a)
8BACC47ER1CONTACT, SOCKET1
Refer to SWPM 20-90-11 as an
accepted procedure.
2BACC47DE7ACONTACT, PIN2
Refer to SWPM 20-90-11 as an
accepted procedure.
9M39029/11-145CONTACT, PIN, CRIMP
REMOVABLE, PER MIL-C-
39029/11
3
Refer to SWPM 20-81-22 as an
accepted procedure.
1BACS16AG1RELAY SOCKET4
Refer to SWPM 20-10-11 as an
accepted procedure.
1289T1169-10401ID - CONNECTOR
Refer to SWPM 20-81-22 as an
accepted procedure.
1BACS16AH1RELAY SOCKET5
Refer to SWPM 20-10-11 as an
accepted procedure.
1289T1169-10402ID - CONNECTOR
Refer to SWPM 20-61-11 as an
accepted procedure. (a)
3BACC47DJ1CONTACT, SOCKET6
Refer to SWPM 20-90-11 as an
accepted procedure.
2BACC47DE8ACONTACT7
Refer to SWPM 20-61-11 as an
accepted procedure. (a)
1BACC47CP1SCONTACT, SOCKET8
Refer to SWPM 20-90-11 as an
accepted procedure.
1YHLZR-17TERMINAL BLOCK RESIS-
TOR ASSEMBLY MODULE
9
Refer to SWPM 20-90-11 as an
accepted procedure.
1289T1169-10403ID - DIODE
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11
as an accepted procedure.
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE
NUMBER
WIRE
BUNDLE
BMS 13-48, TYPE 10, CLASS 1, AWG 2093PA20731W0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2445PK24732W0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2445PK24733W0184
BMS 13-48, TYPE 10, CLASS 1, AWG 2093PA20734W0184
FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
41 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 42

NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE
NUMBER
WIRE
BUNDLE
BMS 13-48, TYPE 11, CLASS 1, AWG 2440PK24735W0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2445PK24736W0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2480PK24737W0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2455PK2418LW0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2450PK2418MW0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2450PK2418NW0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2430PK2455PW0184
BMS 13-48, TYPE 11, CLASS 1, AWG 2422PK2455RW0184
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACC47CP1SCONTACT, SOCKET
1BACC47DE7ACONTACT, PIN
1BACC47DE8ACONTACT
1BACC47DJ1CONTACT, SOCKET
2BACC47ER1CONTACT, SOCKET
1M39029/11-145CONTACT, PIN,
CRIMP REMOVABLE,
PER MIL-C-39029/11
FIGURE 6: WIRE CHANGE FOR EXISTING MANIFOLD INTERCONNECT VALVE (WIRE DIAGRAM)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
42 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
AE0209
W176
18
D4802P
8  W176-68G-24  45
W176-68H-24  46
W176-69G-24  3
D20362
K2197  MAN
VLV IND RLY  YA12  + W176-89K-24  5
TB220  • W176-89K-24
D20364
K2198 SMOKE
AND MANIFOLD
W0184-  Z15  W176-69K-24  IND RLY
TB218
XC4  W176-68F-24  47
XD4  W176-68K-24  48
TB218
D5832P
P36  LEFT MISC
ELECT EQUIPMENT
ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  EXISTING WIRE  2183798
Reference : 767 WDM 21-58-16
FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)
(SHEET 1 OF 3)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  767-21A0253
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 66

### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
- W176-24C-24 -  АЗ
D21731 K10717
- W176-24D-24 -  YA5
TB218
/ W176-24G-24 +//_||' GDX18-DC
# W176-24H-24 +/ XB1
TB218
D21730
K10355 L & R ENG
N2<50% RLY
A2
A1
Х1  W176-24H-24  Z10
TB222
X2  W176-34G-24
D31620  D5360P
K10718 MAN INT
>10FT T D RLY
P36  LEFT MISC ELECTRICAL EQUIPMENT
ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  EXISTING WIRE  2183960
Reference : 767 WDM 21-58-16
FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)
(SHEET 2 OF 3)
Original Issue: October 12, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-21A0253
Work - See page 1 for details.  44 of 66

### Page 45

NOTE: The parts are in Wire Kit 289T1169-105. The wire is identified as 289T1169-105W.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataQtyIdentificationName
Flag
Note
Refer to SWPM 20-81-19 as an
accepted procedure. (a)
4BACC47ER1CONTACT, SOCKET1
Refer to SWPM 20-61-11 as an
accepted procedure. (a)
5BACC47CN1SCONTACT, PIN2
Refer to SWPM 20-90-11 as an
accepted procedure. (a)
5M39029/11-145CONTACT, PIN, CRIMP
REMOVABLE, PER MIL-C-
39029/11
3
Refer to SWPM 20-61-11 as an
accepted procedure. (a)
4BACC47DJ1CONTACT, SOCKET4
(a) Repair or replace existing connector ID if it is damaged during wire installation. Refer to SWPM 20-10-11
as an accepted procedure.
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE
NUMBER
WIRE
BUNDLE
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2489KW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2468GW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2468HW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2445PK2469KW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2424HW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2468FW0176
BMS 13-48, TYPE 11, CLASS 1, AWG 2460PK2468KW0176
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACC47ER1CONTACT, SOCKET
1BACC47CN1SCONTACT, PIN
1M39029/11-145CONTACT, PIN,
CRIMP REMOVABLE,
PER MIL-C-39029/11
1BACC47DJ1CONTACT, SOCKET
FIGURE 7: WIRE CHANGE IN PANEL P36 (WIRE DIGRAM)
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
45 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
• P36 PANEL
MAIN EQUIPMENT CENTER
D
B
P36 PANEL
A  2183154
FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36
(SHEET 1 OF 4)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  46 of 66

### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
•
A-A  101>
69
FWD  2183234
B-B
FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36
(SHEET 2 OF 4)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  767-21A0253
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  47 of 66

### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
~
C-C
407
413  414  415  416
406
K10718  405  K1272
404
408  409  1410411 412
K2097  403
402  K2156
401
400
D-D  2183317
FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36
(SHEET 3 OF 4)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  48 of 66

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
K10725 Near Side,
(a)
1BACT19J4TAPE, IDInstall (New)1
D20325 Far Side,
(a)
1BACT19J4TAPE, IDInstall (New)
Alternate part num-
ber TDH1852-3002
1TDH-1852-3002TIME DELAY RELAYInstall (New)2
K10723 Near Side,
(a)
1BACT19J4TAPE, IDInstall (New)3
D20323 Far Side,
(a)
1BACT19J4TAPE, IDInstall (New)
1BACR13CD2RELAYInstall (New)4
171BAC27TEX4697VINYL MARKER (1 2
3...30) VERTICAL
Install (New)5
K10718 Near Side,
(a)
1BACT19J4TAPE, IDInstall (New)6
D31620 Far Side,
(a)
-BACT19J4TAPE, IDInstall (New)
Alternate part num-
ber TDH8050-3003P
1TDH-8050-3003PTIME DELAY RELAYInstall (New)7
1BACR13CD2RELAYRemove8
D21730 Far Side1BACT19J4TAPE, IDRemove9
K10355 Near Side1BACT19J4TAPE, IDRemove
(a) Mark the ID tape with this ID. Refer to SOPM 20-50-10SOPM 20-50-10 as an accepted procedure.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
3BACT19J4TAPE, ID
FIGURE 8: CHANGE TO RELAY INSTALLATION IN PANEL P36
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
49 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
E8 EICAS RACK
MAIN EQUIPMENT CENTER (MEC)
(TYPICAL)  STA
266.5
E8 EICAS
RACK
AND
2184797
FIGURE 9: INSTALLATION OF NEW ALTITUDE SWITCH AND PITOT TUBE
(SHEET 1 OF 3)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  50 of 66

### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
BEFORE
B
AFTER
2184837
FIGURE 9: INSTALLATION OF NEW ALTITUDE SWITCH AND PITOT TUBE
(SHEET 2 OF 3)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  51 of 66

### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
16502-10KPressure SwitchInstall (New)1
1123-2CLAMP MOUNTING
INSTRUMENT
Install (New)
Install on switch11QM1-3-54ADISCONNECTInstall (New)2
1MS28778-5PACKING, PRE-
FORMED
Install (New)
Install on hose.11QF2-3-64AQUICK DISCONNECTInstall (New)3
1BACC14AD06DNCAPRemove4
1BACH30BC06-0110HOSE, INSTRUMENTInstall (New)5
-BACH30BC06-0110HOSE, INSTRUMENTConnect6
Refer to 767 AMM
20-10-12 as an ac-
cepted procedure.
1BAC27TFDE534VINYL DECALInstall (New)7
FIGURE 9: INSTALLATION OF NEW ALTITUDE SWITCH AND PITOT TUBE
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
52 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
W2006
NC
AE0219
011-20  •||' GDX1-DC
10K FT  012-24  [FA40  • W1039-046-24  12  →
ALTITUDE  TB239
D6980P
013-20  D|1' GDX1-S
D20950
S921 ALTITUDE
PRESSURE SWITCH
E8  EICAS RACK
• ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING
- EXISTING WIRE
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. No parts
are added in this figure.
Flag
Note  Name  Identification  Qty  More Data
1  CONNECTOR  D20950  Connector is stowed near switch.
(a)
(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 10: CONNECTION OF EXISTING WIRING TO ALTITUDE SWITCH
(SHEET 1 OF 1)
Original Issue: October 12, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-21A0253
Work - See page 1 for details.  53 of 66

### Page 54 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
303
> A THROUGH FI
AE0209
00
A> W756
P36
PANEL
2184624
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 1 OF 7)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  54 of 66

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
276
STA
287
S-291-
W756
S-36L  2184674
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 2 OF 7)
Original Issue: October 12, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  Work - See page 1 for details.  767-21A0253  55 of 66

### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
287
W756
LBL
10
RBL
10  2184675
C
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 3 OF 7)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  56 of 66

### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
220.3
STA
236.5
STA
266.5
STA
287
W756
DV900•
S-24R
• GD754
- W756
W590
S-35R  2184673
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 4 OF 7)
Original Issue: October 12, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-21A0253
Work - See page 1 for details.  57 of 66

### Page 58 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
303
STA  RBL
287  / 60
STA
269  RBL
STA
266.5  RBL
• 80
W756
W756
2184670
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 5 OF 7)
Original Issue: October 12, 2012
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-21A0253
Work - See page 1 for details.  58 of 66

### Page 59 (OCR)

BOEING SERVICE BULLETIN 767-21A0253
ALERT  ALERT
STA
180.5
STA
212.5
STA
228.5
RBL
40
STA
246.5
W756  <→ W756
2184591
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 6 OF 7)
Original Issue: October 12, 2012
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-21A0253
Work - See page 1 for details.  59 of 66

### Page 60

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2411A4902-7RETAINER CLIP ASSYInstall (New)1
W07561829A9001-2LACING TAPE - RED -
PRESSURIZED (TEMP
135 DEG)
Install (New)2
FIGURE 11: INSTALLATION OF WIRE BETWEEN PANELS AND EQUIPMENT
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 12, 2012
767-21A0253
60 of 66
BOEING SERVICE BULLETIN 767-21A0253
ALERTALERT

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