# Boeing Alert Service Bulletin 767-21A0247: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-21A0247](https://openairdocs.org/service-documents/boeing/767-21a0247.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 59
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-21A0247
Original Issue: October 10, 2011
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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 the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 2
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
J. References .............................................. 1 3
1. Existing Data .......................................... 1 3
2. Data supplied with this Service Bulletin ............................ 1 3
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 3
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 4
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 ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 8
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION ........... 2 6
FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION . 30
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
ROUTING ............................................ 3 3
FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
WIRING CHANGE ....................................... 3 8
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING .............. 4 0
FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD
FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES ................. 4 8
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING ............. 4 9
FIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE ........ 5 2
FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING .................... 5 3
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FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE ............... 5 5
FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT
.................................................. 5 7
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-21A0247Original Issue: October 10, 2011
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring, or loss
of color caused by moisture or condensation being collected inside the display units can occur during operation
in hot and humid environments. If this service bulletin is not done, there is an increased risk that the flight
compartment display units could malfunction and become unserviceable because of moisture ingress. Loss of
the primary attitude information on both primary display units could lead to flight crew confusion and difficulty in
the transition to standby attitude indication. The inability of the flight crew to transition from primary attitude
indication to standby attitude indication during a critical phase of flight could contribute to an unsafe flight
condition. Flight compartment indication blanking can also cause unscheduled maintenance and airplane
downtime.
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.
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Accomplishment of this service bulletin installs a new relay in the P36 Left Miscellaneous Electrical Equipment
Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch to the E8 Engine
Indication and Crew Alerting System (EICAS) rack to change the control logic of the 3-way valve operation
above and below an altitude of 10,000 feet. This change reduces the amount of moisture or condensation that
can collect in the flight compartment display units and thus reduce malfunction occurrences.
Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin.
ACTION (PRR B12900-260)
Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch, and
attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Open the P36 left
miscellaneous equipment panel in the MEC and make changes to wire bundle W176. Make changes to wire
bundle W596 between the P36 left miscellaneous equipment panel and P50 Electrical Systems Card File panel.
In the P50 Electrical Systems Card File panel, make changes to wire bundle W1114. Make changes to wire
bundle W1702 between the P36 left miscellaneous equipment panel and E8 EICAS rack. At the E8 EICAS rack,
make changes to wire bundle W2000. In the P36 left miscellaneous equipment panel, remove relay K10355
and install new relay K10718. Flush and leak check the Auxiliary Static system No. 2 (AS2), and test the 3-way
valve control logic.
The changes in this service bulletin will not change the Engine Indication and Crew Alerting System (EICAS).
EFFECTIVITY
767-300F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 6 years after the original issue
date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of July 29, 2009. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
15.4515.45767-300F Airplanes
MATERIAL INFORMATION
Boeing Supplied Kits.
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BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
P36 LEFT MISCELLANEOUS
EQUIPMENT PANEL:
MAKE CHANGES TO WIRE
BUNDLE W176.
INSTALL NEW RELAY K10718.
P50 ELECTRICAL SYSTEMS
CARD FILE PANEL:
MAKE CHANGES TO WIRE
BUNDLE W1114.
MAKE CHANGES TO
WIRE BUNDLE W596.  MAKE CHANGES TO
WIRE BUNDLE W1702.
E8 EICAS RACK:
MAKE CHANGES TO WIRE BUNDLE W2000.
INSTALL NEW PRESSURE SWITCH, NEW
BRACKET, AND ATTACH NEW
HARDWARE.
MAIN EQUIPMENT CENTER (MEC)  2032531
(TYPICAL)
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-21A0247
Original Issue: October 10, 2011
ATA System: 2158
SUBJECT: AIR CONDITIONING - Equipment Cooling System - 3-Way Valve Control Logic Change
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR B12900-260 for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767-300F airplanes, Variable Numbers VR201 thru VR211, and
VW701 thru VW721 that must do Boeing service bulletin 767-21-0235
prior to or concurrent with this service bulletin.
-1
767-300F airplanes, Variable Numbers VR266 thru VR272 that have
had the intent of Boeing service bulletin 767-21-0235 incorporated
prior to delivery.
-2
Airplane Models:
767-300F
GroupVariable Number
1VR201 - VR211
2VR266 - VR272
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GroupVariable Number
1VW701 - VW721
2. Spares Affected
None.
B. Concurrent Requirements
Group 1:
The service bulletin listed below must be done on Group 1 airplanes before or at the same time as this
service bulletin:
Group 1:
DescriptionService BulletinCompany
This service bulletin gives instructions to install
a relay and related wiring in the P36 left miscel-
laneous equipment panel to change the control
logic of the equipment cooling 3-way valve.
767-21-0235 Original Issue or
Revision 1
Boeing
Group 2:
None.
C. Reason
This service bulletin is sent to reduce malfunctions of flight compartment display units. Blanking, blurring,
or loss of color caused by moisture or condensation being collected inside the display units can occur
during operation in hot and humid environments. If this service bulletin is not done, there is an increased
risk that the flight compartment display units could malfunction and become unserviceable because of
moisture ingress. Loss of the primary attitude information on both primary display units could lead to
flight crew confusion and difficulty in the transition to standby attitude indication. The inability of the
flight crew to transition from primary attitude indication to standby attitude indication during a critical
phase of flight could contribute to an unsafe flight condition. Flight compartment indication blanking
can also cause unscheduled maintenance and airplane downtime.
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
BOEING PROPRIETARY -
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result of these findings, the control logic of the 3-way valve is changed so that the valve will open after
five minutes at an altitude above 10,000 feet, and close at an altitude below 10,000 feet. Limiting the
3-way valve to open after five minutes above 10,000 feet will decrease the amount of moisture or
condensation that can collect in the display units because of the reduced water content in the atmosphere
at higher altitudes.
Accomplishment of this service bulletin installs a new relay in the P36 Left Miscellaneous Electrical
Equipment Panel, with related wiring changes, and installs a new 10,000 feet altitude pressure switch
to the E8 Engine Indication and Crew Alerting System (EICAS) rack to change the control logic of the
3-way valve operation above and below an altitude of 10,000 feet. This change reduces the amount
of moisture or condensation that can collect in the flight compartment display units and thus reduce
malfunction occurrences.
Boeing Service Related Problem (SRP) 767-SRP-21-0179 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 767 FTD 21-09003 is related to this service bulletin.
D. Description
Get access to the airplane Main Equipment Center (MEC). Install a new bracket, new pressure switch,
and attach hardware to the E8 Engine Indication and Crew Alerting System (EICAS) rack. Open the
P36 left miscellaneous equipment panel in the MEC and make changes to wire bundle W176. Make
changes to wire bundle W596 between the P36 left miscellaneous equipment panel and P50 Electrical
Systems Card File panel. In the P50 Electrical Systems Card File panel, make changes to wire bundle
W1114. Make changes to wire bundle W1702 between the P36 left miscellaneous equipment panel
and E8 EICAS rack. At the E8 EICAS rack, make changes to wire bundle W2000. In the P36 left
miscellaneous equipment panel, remove relay K10355 and install new relay K10718. Flush and leak
check the Auxiliary Static system No. 2 (AS2), and test the 3-way valve control logic.
The changes in this service bulletin will not change the Engine Indication and Crew Alerting System
(EICAS).
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
117, 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 6 years after the
original issue date of this service bulletin.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved. This service
bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as
modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
Included in the service bulletin approval is an FAA finding of compliance with the Fuel Tank Ignition
Prevention rule (14 CFR section 25.981(a)(3) Amendment 102 or higher).
G. Manpower
The table below shows an estimate of the task hours necessary to do this service bulletin for each
airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with
operator task hour data if necessary. The estimate does not include lost time. These are some examples
of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
1.001.001FIGURE 1
1.001.001FIGURE 2
---FIGURE 3 (Wire routing only)
1.701.701FIGURE 4
---FIGURE 5 (Wire routing only)
0.200.201FIGURE 6
---FIGURE 7 (Wire routing only)
2.102.101FIGURE 8
---FIGURE 9 (Wire routing only)
3.703.701FIGURE 10
0.750.751FIGURE 11
0.500.501Close Access
4.004.001Test
15.4515.45TOTAL FOR EACH AIRPLANE
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H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+188.8+1.2767-300F
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 Related Problem (SRP) 767-SRP-21-0179
d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-05, 20-50-10, 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-00-11, 20-10-11, 20-10-12, 20-10-19, 20-20-11,
20-30-16, 20-60-09, 20-61-11, 20-81-12, 20-90-11
f. 767 Aircraft Maintenance Manual (AMM) 06-41-00, 20-41-01, 24-22-00, 31-01-36, 32-09-02,
34-11-00
g. 767 Fleet Team Digest (FTD) 21-09003
h. 767 Wiring Diagram Manual (WDM) 21-58-16, 31-41-13
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Tubing Installation Lower Lobe Sidewall LH, STA 132.5 Thru 290278T4107
Rack Instl - E8284T0971
Support Bracket, E8 Rack Instl284T1040
Modular Wire Bundle Instl P36, Misc. Relay Panel, Left288T2036
Modular Wire Bundle Installation E8 EICAS Rack288T2280
Wire Bundle Installation Lower Lobe Sidewall LH, STA 132.5288T4107
Wire Bundle Installation Lower Lobe Sidewall LH, STA 290 Thru 431288T4117
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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:
Chapter-SectionPublication
21-58767 Aircraft Maintenance Manual
21-58, 34-11767 Illustrated Parts Catalog
21-58, 31-41767 System Schematic Manual
21-58, 31-41767 Wiring Diagram Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of the
original issue date of
this Service Bulletin
(US Dollars)
ROLT as of the origi-
nal issue date of this
Service Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$6,979.002803Mar 11, 2011Top Kit - 767 Freighters
3-Way Valve Logic
Change
015T1860-1
3Mar 25, 2011
1Apr 08, 2011
5Jul 18, 2011
5Aug 15, 2011
2Sep 13, 2011
1Oct 11, 2011
B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of July 29, 2009. For task hour
reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial
Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no
charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number
and reference the airplane variable numbers in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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.
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Figure Kit
1121Top Kit
111015T1860-1
Top Kit
015T1860-1Wire Kit
1015T1860-2
1015T1860-3
1015T1860-4
ALL
KIT 015T1860-1
NOTES
Existing Part
NumberName
Figure
New Part Number
1121
QTY
DECAL K107181015T1860-10101
DECAL D316201015T1860-10102
CLAMP MOUNTING INSTRUMENT1123-2222-F
QUICK DISCONNECT11QF2-3-64A
DISCONNECT11QM1-3-54A
BRACKET1233T9118Y105
Pressure Switch16502-10K
VINYL DECAL1BAC27TFDE534
HOSE, INSTRUMENT1BACH30BC06-
0110
RIVET, UNIVERSAL HD4BACR15FT6AD5C
PACKING, PREFORMED1MS28778-5
TIME DELAY RELAY1TDH-8050-3003P
KIT 015T1860-2
NotesNameQTYNew Part Number
TAPE, LACING1015T1860-10104
SLEEVE IDENTIFICATION, HEAT
SHRINKABLE
1015T1860-10106
WIRE W01761015T1860-101W
CONTACT, SOCKET1BACC47CP1S
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KIT 015T1860-2
NotesNameQTYNew Part Number
CONTACT, SOCKET4BACC47DJ1
RELAY SOCKET1BACS16W1A
CONTACT, PIN, CRIMP REMOVABLE,
PER MIL-C-39029/11
1M39029/11-145
KIT 015T1860-3
NotesNameQTYNew Part Number
WIRE W17021015T1860-102W
CONTACT, PIN1BACC47CN1S
CONTACT, PIN1BACC47CN1SB
SLEEVE, HEAT SHRINK1BACT63D1
KIT 015T1860-4
NotesNameQTYNew Part Number
SLEEVE IDENTIFICATION, HEAT
SHRINKABLE
1015T1860-10105
WIRE W20001015T1860-103W
BACKSHELL CLAMP1BACC10GH10
CONNECTOR, ELECTRICAL, PLUG,
STRAIGHT, BAYONET COUPLING
1BACC45FT10A5S
CONTACT, SOCKET4BACC47CP1S
CONTACT2BACC47DE8A
PLUG1MS27488-20-1
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number / Specification
(a)SEALANT4 ozBMS5-95
(a)PRIMER4 ozBMS10-11, TYPE I
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification
(BMS) for supplier data.
3. Parts Modified and Reidentified
The part shown below is changed as shown in this service bulletin. The quantity (QTY) is the
number of parts changed on each airplane.
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NotesNew Part NumberNameQTYExisting Part
Number
(a) (b)284T1040-16SUPPORT BRACKET1284T1040-6
(a) Make the change in accordance with this service bulletin.
(b) This is the part number after the change is done in accordance with this service bulletin.
4. Parts Removed and Not Replaced
NotesQTYNameExisting Part Number
(a)1CAPBACC14AD06DN
(a)1RELAYBACR13CD2
(a)1RELAY, SOCKETBACS16AG
(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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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in Structural Repair Manual (SRM)
Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
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8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
10. The work instructions refer to panel(s) that contain Electro-static Sensitive Devices
(ESDS). Make sure you keep contamination or unwanted materials away from the
sensitive device. Contamination or unwanted material near the sensitive device can
cause a malfunction in the sensitive device. Refer to 767 AMM 20-41-01 as an
accepted procedure.
B. WORK INSTRUCTIONS
1. Remove electrical power from the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure.
2. Get access to the Main Equipment Center (MEC). Refer to 767 AMM 06-41-00 as an accepted
procedure for access locations.
3. In the MEC, open the circuit breaker specified in the table below and attach a "DO-NOT-CLOSE"
tag:
CIRCUIT BREAKER PANEL ASSEMBLY
NumberNameLocationPanel
C00679EQPT COOL OVERRIDEC019P11-4
4. In the MEC, install the new bracket to the E8 Engine Indication and Crew Alerting System (EICAS)
rack at station 266.5 in accordance with FIGURE 1.
5. At the E8 EICAS rack, install the new pressure switch to the bracket and attach hardware in
accordance with FIGURE 2.
6. Open the P36 left miscellaneous equipment panel door to get access to the wiring. Refer to 767
AMM 31-01-36 for component locations.
7. In the P36 left miscellaneous equipment panel, make changes to wire bundle W176 in accordance
with FIGURE 3 and FIGURE 4.
8. In the MEC, make changes to wire bundle W596 between the P36 left miscellaneous equipment
panel and P50 electrical systems card file panel in accordance with FIGURE 5 and FIGURE 6.
9. In the P50 electrical systems card file panel, make changes to wire bundle W1114 in accordance
with FIGURE 6.
10. In the MEC, make changes to wire bundle W1702 between the P36 left miscellaneous equipment
panel and E8 EICAS rack in accordance with FIGURE 7 and FIGURE 8.
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11. At the E8 EICAS rack, make changes to wire bundle W2000 in accordance with FIGURE 9 and
FIGURE 10.
12. In the P36 left miscellaneous equipment panel, remove relay K10355 and install new relay K10718
in accordance with FIGURE 11.
13. Close the P36 left miscellaneous equipment panel.
14. In the MEC, remove the "DO-NOT-CLOSE" tag and close the circuit breaker specified in the table
below:
CIRCUIT BREAKER PANEL ASSEMBLY
NumberNameLocationPanel
C00679EQPT COOL OVERRIDEC019P11-4
15. Supply electrical power to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure.
16. Flush the pitot/static system. Refer to 767 AMM 34-11-00 as an accepted procedure.
17. Do a leak test of the Auxiliary Static system No. 2 (AS2). Refer to 767 AMM 34-11-00 as an
accepted procedure.
18. Do the test that follows of the 3-way valve control logic.
a. Make sure the airplane is powered, the engines are OFF and the air conditioning packs are
OFF.
b. Make sure the Air/Ground Relay System is in GROUND mode. Or to put the Air/Ground Relay
System in GROUND mode, refer to 767 AMM 32-09-02 as an accepted procedure.
c. In the MEC, make sure the circuit breakers specified in the table below are closed:
CIRCUIT BREAKER PANEL ASSEMBLY
NumberNameLocationPanel
C00653LEFT PACK FLOW CONTA013P11-1
C00704RIGHT PACK FLOW CONTA026P11-4
C01175LDG GR POS AIR/GND SYS 1C030P11-4
C04078L EICAS CMPTRJ002P11-2
C04079R EICAS CMPTRJ029P11-5
d. In the Flight Compartment, set the Equipment Cooling rotary switch on the P5 overhead panel
to AUTO.
e. Disconnect connector (D20366) to Equipment Cooling Temperature Control switch (S868) at
STA 208, WL 172 and RBL 60.
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f. Install a jumper from pin 1 of connector (D20366) to pin 2 of connector (D20366).
g. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
h. Disconnect connector (D2770) from the Left Flow Control Valve (V16).
NOTE: This simulates the Left Pack is ON.
i. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
j. Put the Air/Ground Relay System in AIR mode, refer to 767 AMM 32-09-02 as an accepted
procedure.
NOTE: If circuit breaker C00688 EQUIPMENT COOLING STANDBY on the P11-1 panel at
location B008 and circuit breaker C00651 EQUIPMENT COOLING OUTBD VALVES
on the P11-3 panel at location P013 were opened, and the Equipment Cooling rotary
switch on the P5 overhead panel was set to STBY then do the steps that follow:
1. Remove relay K336 from the P36 left miscellaneous equipment panel.
2. Remove relay K340 from the P36 left miscellaneous equipment panel.
3. Close circuit breaker C00688 EQUIPMENT COOLING STANDBY on the
P11-1 panel.
4. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.
CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT AND ELECTRICAL EQUIPMENT
BAY WILL NOT BE COOLED. DAMAGE TO THE EQUIPMENT IN THE FLIGHT
COMPARTMENT AND/OR ELECTRICAL EQUIPMENT BAY COULD OCCUR IF
THE SYSTEM STAYS IN THE AUTO MODE FOR MORE THAN 10 MINUTES.
k. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
l. Disconnect connector (D20950) from the 10,000 FT Pressure Switch (S921) on the E8 EICAS
rack.
m. Install a jumper from pin 2 of connector (D20950) to ground.
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NOTE: This simulates an altitude greater than 10,000 FT. If you cannot get access to pin 2
of connector D20950, remove the wire from pin 2 of connector D20950 and ground
the wire.
n. Make sure the elapsed time from grounding pin 2 of connector (D20950) until the Manifold
Interconnect Valve (V90) begins to move to the OPEN (C-B) position is between a minimum
of 4 minutes and 30 seconds and a maximum of 5 minutes and 30 seconds.
o. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVEOPEN (C-B)
CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN
THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'
CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS
TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR
IF THE VALVE IS KEPT OPEN FOR MORE THAN 10 MINUTES.
p. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY.
q. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
r. Wait for 15 minutes to let the equipment cool.
s. Set the Equipment Cooling rotary switch on the P5 overhead panel to OVRD.
t. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVEOPEN (C-B)
CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN
THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'
CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS
TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR
IF THE VALVE IS KEPT OPEN FOR MORE THAN 10 MINUTES.
EQUIPMENT IN THE ELECTRICAL EQUIPMENT BAY WILL NOT BE COOLED
WHEN THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD
PANEL IS SET TO OVRD, AS THE EQUIPMENT COOLING FANS WILL BE OFF.
DAMAGE TO THE ELECTRICAL EQUIPMENT BAY EQUIPMENT COULD OCCUR
IF THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD PANEL
IS KEPT IN OVRD FOR MORE THAN 10 MINUTES.
u. Remove the jumper from pin 2 of connector (D20950).
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v. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVEOPEN (C-B)
CAUTION: EQUIPMENT IN THE FLIGHT COMPARTMENT WILL NOT BE COOLED WHEN
THE MANIFOLD INTERCONNECT VALVE CONFIGURES TO THE 'OPEN (C-B)'
CONDITION, AS THE COOLING PACKS ARE NOT IN OPERATION DURING THIS
TEST. DAMAGE TO THE FLIGHT COMPARTMENT EQUIPMENT COULD OCCUR
IF THE VALVE IS KEPT OPEN FOR MORE THAN 10 MINUTES.
w. Set the Equipment Cooling rotary switch on the P5 overhead panel to AUTO.
CAUTION: IF CIRCUIT BREAKER C00688 EQUIPMENT COOLING STANDBY ON THE P11-1
PANEL AT LOCATION B008 AND CIRCUIT BREAKER C00651 EQUIPMENT
COOLING OUTBD VALVES ON THE P11-3 PANEL AT LOCATION P013 WERE
OPENED AND THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5
OVERHEAD PANEL WAS SET TO STBY TO CONFIGURE THE AIRPLANE TO
AIR MODE, THE EQUIPMENT IN THE FLIGHT COMPARTMENT AND ELECTRICAL
EQUIPMENT BAY WILL NOT BE COOLED. DAMAGE TO THE EQUIPMENT IN
THE FLIGHT COMPARTMENT AND/OR ELECTRICAL EQUIPMENT BAY COULD
OCCUR IF THE SYSTEM REMAINS IN THE AUTO MODE FOR MORE THAN 10
MINUTES.
x. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
y. If the wire was removed from pin 2 of connector D20950 then connect the wire at pin 2 of
connector D20950.
z. Connect connector (D20950) back on to the 10,000 FT Pressure Switch (S921) on the E8
EICAS rack.
aa. Make sure the 3-way valve is in the condition specified in the table below:
Equipment NumberNameCondition
V90MANIFOLD INTERCONNECT VALVECLOSED (A-B)
ab. Set the Equipment Cooling rotary switch on the P5 overhead panel to STBY.
ac. Connect connector (D2770) back on to the Left Flow Control Valve (V16).
ad. Remove the jumper from pin 1 and pin 2 in Connector (D20366).
ae. Connect connector (D20366) back on to Equipment Cooling Temperature Control Switch
(S868) at STA 208, WL 172, and RBL 60.
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af. If circuit breaker C00688 EQUIPMENT COOLING STANDBY on the P11-1 panel at location
B008 was closed, and relay K336 and relay K340 were removed from the P36 left
miscellaneous equipment panel then do the steps that follow:
(1) Open circuit breaker C00688 EQUIPMENT COOLING STANDBY on the P11-1 panel.
(2) Install relay K336 in the P36 left miscellaneous equipment panel.
(3) Install relay K340 in the P36 left miscellaneous equipment panel.
(4) Close circuit breaker C00688 EQUIPMENT COOLING STANDBY on the P11-1 panel.
ag. Put the Air/Ground Relay System in GROUND mode. Refer to 767 AMM 32-09-02 as an
accepted procedure.
ah. Put the airplane back to the configuration before the test.
19. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
E8 EICAS RACK
MAIN EQUIPMENT CENTER (MEC)  2032537
(TYPICAL)
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION
(SHEET 1 OF 4)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA  STA
266.5  246
• E8 EICAS
RACK
SUPPORT
BRACKET
TEND
STR-19L
SOME PARTS NOT SHOWN FOR CLARITY  2036499
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION
(SHEET 2 OF 4)
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### Page 28

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
on the support bracket at the posi-
tion shown.
1233T9118Y105BRACKETPut / Hold1
0.129 inch diameter in the support
bracket to agree with bracket.
4-PILOT HOLEDrill2
0.191 - 0.202 inch diameter in the
support bracket and bracket.
4-HOLEDrill3
in the support bracket and bracket.
Break all sharp edges.
4-HOLEDeburr
to the support bracket and bracket
mating surfaces. Refer to SOPM 20-
50-19 as an accepted procedure.
-BMS5-95SEALANTApply4
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION
(SHEET 3 OF 4)
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MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
on the support bracket at the posi-
tion shown.
1233T9118Y105BRACKETInstall
(New)
5
4BACR15FT6AD5CRIVET, UNIVERSAL
HD
Install
(New)
Apply two coats to all bare metal
surfaces of the support bracket and
bracket. Refer to SOPM 20-41-02
as an accepted procedure.
-BMS10-11, TYPE IPRIMERApply6
to the support bracket to identify that
this change is done. Refer to SOPM
20-50-10 code RH as an accepted
procedure. (a)
--PART NUMBERApply7
(a) Refer to Paragraph 2.C.3., Parts Modified and Reidentified for applicable part number.
FIGURE 1: E8 EICAS RACK PRESSURE SWITCH BRACKET - INSTALLATION
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
246
BEFORE CHANGE  2032540
FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION
• (SHEET 1 OF 3)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
246
STA
276
AFTER CHANGE
B  2032948
FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION
(SHEET 2 OF 3)
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### Page 32

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
to the bracket.1123-2222-FCLAMP MOUNTING
INSTRUMENT
Install
(New)
1
in the instrument mounting clamp.16502-10KPressure SwitchInstall
(New)
2
onto the pneumatic inlet port.1MS28778-5PACKING, PRE-
FORMED
Install
(New)
3
to the pressure switch.11QM1-3-54ADISCONNECTInstall
(New)
to the BACH30BC01-0110 instru-
ment hose.
11QF2-3-64AQUICK DISCONNECTInstall
(New)
4
from the AS2 system tubing tee fit-
ting located at STA 270, LBL70,
WL170.
1BACC14AD06DNCAPRemove5
between the AS2 system tubing tee
fitting and the pressure switch quick
disconnect.
1BACH30BC06-0110HOSE, INSTRUMENTInstall
(New)
6
on the bracket below the pressure
switch at the position shown. Refer
to SOPM 20-50-05 as an accepted
procedure.
1BAC27TFDE534VINYL DECALInstall
(New)
7
FIGURE 2: E8 EICAS RACK PRESSURE SWITCH AND ATTACH HARDWARE - INSTALLATION
(SHEET 3 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
P36 LEFT
MISCELLANEOUS
EQUIPMENT PANEL
MAIN EQUIPMENT CENTER  2032539
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
ROUTING
(SHEET 1 OF 5)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
303
AE0209
P36 LEFT MISCELLANEOUS  2032984
EQUIPMENT PANEL
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
ROUTING
(SHEET 2 OF 5)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
D5360J
POS 35
W176
AE0209
2032986
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
ROUTING
(SHEET 3 OF 5)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W176
2033283
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
_ ROUTING
(SHEET 4 OF 5)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
K10718
K10355
W176
•
2033284
FIGURE 3: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 -
ROUTING
(SHEET 5 OF 5)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W176
24C-24
4  24D-24
NC
7  Y+ 24G-24 7  *I' GDX18-DC
H 24H-24  ХB1 71+ W184-21J-24 + 33  - W596
TB218
D4992J
K10355  D21730
L & R ENG
N2<50% RELAY
A2
A3 NC
A1
X2  34G-24  41  - W1702
X1  34H-24  Z10  18D-24 -  D5360J
TB222
K10718  D31620
MANIFOLD
INT RELAY
P36 LEFT MISCELLANEOUS EQUIPMENT PANEL
- ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  2033313
• EXISTING WIRE
REFERENCE: 767 WDM 21-58-16
FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING
CHANGE
(SHEET 1 OF 2)
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### Page 39

NOTE: The parts are in Wire Kit 015T1860-2.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAME
FLAG
NOTE
Use lacing tape to tie wires. Refer to SWPM 20-
10-11 as an accepted procedure.
-015T1860-10104TAPE, LACING1
Refer to cut and code table for wire kit 015T1860-
101W.
1015T1860-101WWIRE W01762
1BACS16W1ARELAY SOCKET3
Refer to SWPM 20-81-12 as an accepted proce-
dure.
4BACC47DJ1CONTACT, SOCKET4
Install within 6 inches of equipment. Refer to
SWPM 20-10-11 as an accepted procedure.
1015T1860-10106SLEEVE IDENTIFICA-
TION, HEAT SHRINK-
ABLE
5
Refer to SWPM 20-61-11 as an accepted proce-
dure.
1BACC47CP1SCONTACT, SOCKET6
Refer to SWPM 20-90-11 as an accepted proce-
dure.
1M39029/11-145CONTACT, PIN,
CRIMP REMOVABLE,
PER MIL-C-39029/11
7
WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-101W
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE#WBA#
BMS 13-48, TYPE 11, CLASS 1, AWG24100PK2434GW0176
BMS 13-48, TYPE 11, CLASS 1, AWG24100PK2434HW0176
FIGURE 4: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL WIRE BUNDLE W176 - WIRING
CHANGE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
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767-21A0247
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BOEING SERVICE BULLETIN 767-21A0247
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
P36 LEFT MISCELLANEOUS
EQUIPMENT PANEL
P50 ELECTRICAL SYSTEMS
CARD FILE PANEL
W596
MAIN EQUIPMENT CENTER (MEC)  2033285
(TYPICAL)
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 1 OF 8)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
303
P36 LEFT
MISCELLANEOUS
EQUIPMENT PANEL  AE0209
00
00  > W596
2033286
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 2 OF 8)
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Copyright © Unpublished Work - See page 1 for details.  41 of 59

### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
276
STA
287
S-29L
W596
S-36L  2033287
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 3 OF 8)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
287
W596
LBL -
RBL  10  2033288
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 4 OF 8)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
266.5
STA
287
S-24R
W596
S-35R
2033289
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 5 OF 8)
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### Page 45 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W596
W596
266.5  STA  LEMO
2033305
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 6 OF 8)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA  STA  STA
212.5  228.5  246
W596
LEWD
2033304
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 7 OF 8)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
276
STA
287
P50 ELECTRICAL  W596
SYSTEMS CARD
FILE PANEL
→ D8036P
2033320
FIGURE 5: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 - ROUTING
(SHEET 8 OF 8)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W184  W1114
a
-21J-24.  33 777// W596-606-24 +1111  33  HH  -140-24-
J  D4992P  D8036P
P36 LEFT MISCELLANEOUS  P50 ELECTRICAL SYSTEMS
EQUIPMENT PANEL  CARD FILE PANEL
- ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING
EXISTING WIRE
REFERENCE: 767 WDM 21-58-16
NOTE: The part is in Wire Kit 015T1860-3.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
FLAG
NOTE  NAME  IDENTIFICATION  QTY  MORE DATA
1  WIRE  W596-606-24  1  Remove and discard wire.
2  SLEEVE, HEAT  BACT63D1  1  Refer to SWPM 20-30-16 as an accepted proce-
SHRINK  aure.
FIGURE 6: MAIN EQUIPMENT CENTER WIRE BUNDLE W596 AND P50 ELECTRICAL SYSTEMS CARD
FILE PANEL WIRE BUNDLE W1114 - WIRING CHANGES
(SHEET 1 OF 1)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
P36 LEFT MISCELLANEOUS
EQUIPMENT PANEL
W1702
E8 EICAS RACK
MAIN EQUIPMENT CENTER (MEC)  2033290
(TYPICAL)
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING
(SHEET 1 OF 3)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
STA
287
STA
287
AE0209
W1702
00
P36 LEFT
MISCELLANEOUS
EQUIPMENT PANEL
2033292
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING
(SHEET 2 OF 3)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W1702
STA
287
D6254P
-W1702
AE0221
E8 EICAS RACK  2033291
FIGURE 7: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - ROUTING
(SHEET 3 OF 3)
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### Page 52

REFERENCE: 767 WDM 21-58-16
NOTE: The parts are in Wire Kit 015T1860-2 and 015T1860-3.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAME
FLAG
NOTE
Use lacing tape to tie wires. Refer to SWPM 20-
10-11 as an accepted procedure.
-015T1860-10104TAPE, LACING1
Refer to cut and code table for wire kit 015T1860-
102W.
1015T1860-102WWIRE W17022
Refer to SWPM 20-61-11 as an accepted proce-
dure.
1BACC47CN1SCONTACT, PIN3
Refer to SWPM 20-61-11 as an accepted proce-
dure.
1BACC47CN1SBCONTACT, PIN4
WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-102W
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE#WBA#
BMS13-48, TYPE 11, CLASS 1, AWG24200PK24021W1702
FIGURE 8: MAIN EQUIPMENT CENTER WIRE BUNDLE W1702 - WIRING CHANGE
(SHEET 1 OF 1)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 10, 2011
767-21A0247
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BOEING SERVICE BULLETIN 767-21A0247
ALERTALERT

### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
AND B
MAIN EQUIPMENT CENTER
GDX2
W2000
W2000  • D6254J
POS 04
E8 EICAS RACK  AE0221
2033297
FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING
(SHEET 1 OF 2)
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### Page 54

FIGURE 9: E8 EICAS RACK WIRE BUNDLE W2000 - ROUTING
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 10, 2011
767-21A0247
54 of 59
BOEING SERVICE BULLETIN 767-21A0247
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
W2000
- W1702-021-24 -  12  - 0100-24
}
P  D6254J
2
GDX2-DC 'ID  0110-20  1
GDX2-S 1I  0120-20  5
NC  3
D20950
S921 ALTITUDE
PRESSURE SW
E8 EICAS RACK
- ADDED WIRE OR NEW ROUTING
+ DELETED WIRE OR FORMER ROUTING  2033349
- EXISTING WIRE
REFERENCE: 767 WDM 31-41-13
FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE
(SHEET 1 OF 2)
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### Page 56

NOTE: The parts are in Wire Kit 015T1860-2 and 015T1860-4.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAME
FLAG
NOTE
Use lacing tape to tie wires. Refer to SWPM 20-
10-11 as an accepted procedure.
-015T1860-10104TAPE, LACING1
Refer to cut and code table for wire kit 015T1860-
103W
1015T1860-103WWIRE W20002
Install within 6 inches of connector. Refer to SW-
PM 20-10-11 as an accepted procedure.
1015T1860-10105SLEEVE IDENTIFICA-
TION, HEAT SHRINK-
ABLE
3
Refer to SWPM 20-61-11 as an accepted proce-
dure.
4BACC47CP1SCONTACT, SOCKET4
Refer to SWPM 20-61-11 as an accepted proce-
dure.
1BACC45FT10A5SCONNECTOR, ELEC-
TRICAL, PLUG,
STRAIGHT, BAYONET
COUPLING
5
Insert contact sockets and seal plugs at each
empty contact socket hole. Refer to SWPM 20-
00-11 as an accepted procedure.
2MS27488-20-1PLUG
Refer to SWPM 20-60-09 as an accepted proce-
dure.
1BACC10GH10BACKSHELL CLAMP
Refer to SWPM 20-20-11 as an accepted proce-
dure.
2BACC47DE8ACONTACT6
WIRE KIT - CUT AND CODE AS REQUIRED - 015T1860-103W
NOTESMATERIAL SPECIFICATIONLENGTH
(INCHES)
TYPE
CODE
GAGE
COLOR
WIRE#WBA#
BMS 13-48, TYPE 11, CLASS 1, AWG24100PK240100W2000
BMS 13-48, TYPE 10, CLASS 1, AWG20100PA200110W2000
BMS 13-48, TYPE 10, CLASS 1, AWG20100PA200120W2000
FIGURE 10: E8 EICAS RACK WIRE BUNDLE W2000 - WIRING CHANGE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 10, 2011
767-21A0247
56 of 59
BOEING SERVICE BULLETIN 767-21A0247
ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
P36 LEFT
A MISCELLANEOUS  EQUIPMENT PANEL
MAIN EQUIPMENT CENTER
0000000
2033299
FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT
(SHEET 1 OF 3)
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### Page 58 (OCR)

BOEING SERVICE BULLETIN 767-21A0247
ALERT  ALERT
K2097  (K10718
urO
1)
K10355
FWD
K2095
A-A
FRONT OF RELAY PLATE (TYPICAL)
D31620  D12160  D12156
(GDX18
FWD
D12164
B-B  2033300
REAR OF RELAY PLATE (TYPICAL)
FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT
(SHEET 2 OF 3)
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### Page 59

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
K10355 from the front of the relay
plate. (a)
1BACR13CD2RELAYRemove1
Imprinted K10355.1BACT19J4DECALRemove2
D21730 from the rear of the relay
plate. Lower the relay plate as nec-
essary. (a)
1BACS16AGSOCKET, RELAYRemove3
Imprinted D21730.1BACT19J4DECALRemove4
on the front of the relay plate. Refer
to SOPM 20-50-05 as an accepted
procedure.
1015T1860-10101DECAL K10718Install
(New)
5
on the rear of the relay plate. Lower
the relay plate as necessary. Refer
to SOPM 20-50-05 as an accepted
procedure.
1015T1860-10102DECAL D31620Install
(New)
6
K10718 into relay socket D31620.1TDH-8050-3003PTIME DELAY RELAYInstall
(New)
7
(a) Keep this part if there are other uses for it.
FIGURE 11: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL - RELAY REPLACEMENT
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 10, 2011
767-21A0247
59 of 59
BOEING SERVICE BULLETIN 767-21A0247
ALERTALERT

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