Commercial 

Airplanes 767

Service Bulletin

Number: 767-21-0245

Original Issue: April 16, 2010

Revision 1: September 30, 2010

ATA System: 2158

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

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2.0
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BOEING SERVICE BULLETIN 767-21-0245

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

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

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

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

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

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

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

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

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

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

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 12

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

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

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

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

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

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

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

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19

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

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

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE . . 28

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION . . . . . . . . . . . . . 30

FIGURE 3: WIRE BUNDLE W0176 CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING . . . . . . . . . . . . . . . . . . . . . . 40

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BOEING SERVICE BULLETIN 767-21-0245

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

Revision Transmittal Sheet Number: 767-21-0245

Original Issue: April 16, 2010

Revision 1: September 30, 2010

ATA System: 2158

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

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

REASON FOR REVISION

This revision is issued to make required changes found when doing this service bulletin for the first time. Three

wire contacts are added; two wire contacts are deleted; and two plug and terminal numbers are changed. Kits

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

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

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

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: April 16, 2010

Revision 1: September 30, 2010

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BOEING SERVICE BULLETIN 767-21-0245

BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

Summary Number: 767-21-0245

Original Issue: April 16, 2010

Revision 1: September 30, 2010

ATA System: 2158

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

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin and kit of parts change the Environmental Control System (ECS) Flight Deck Cooling System

Logic to use Electrical Equipment (EE) Cooling rather than Airplane Pack Cooling on the ground and up to

10,000 feet. This prevents flight deck display unit blanking in hot and humid environments. If the change is not

done moisture or condensation could get in the flight deck display units. This could cause intermittent indications

in the flight deck display.

Operators have reported display unit blanking on 767-300F type airplanes. The reports have included single

display units and multiple units blanking during operation in hot and humid environments.

This service bulletin will change the opening of the 3-way valve (manifold interconnect valve) with a five minute

time delay after climbing past 10,000 feet altitude. The valve will close when descending below 10,000 feet

altitude. This change will reduce moisture or condensation in the flight deck display unit.

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

ACTION (PRR B12900-260)

In the Main Equipment Center, do the following change:

1. Change wire bundles W596 and W1702.

2. In the P36 Panel change relays, decals and wire bundle W176.

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

EFFECTIVITY

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

COMPLIANCE

No compliance time is given.

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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

Airplanes Total Task Hours Elapsed Hours

All 13.25 10.60

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 767-21-0245
Commercial 

Airplanes 767

Service Bulletin

Number: 767-21-0245

Original Issue: April 16, 2010

Revision 1: September 30, 2010

ATA System: 2158

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

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

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

GROUP CONFIGURATION DESCRIPTION

767-300F airplanes that must incorporate 767-21-0235 prior to or

concurrently with this bulletin.

1 -

767-300F airplanes that had the intent of 767-21-0235 incorporated

in production

2 -

Airplane Models:

767-300F

Variable Number Group

VR251 1

VR256 - VR260 1

VT501 1

VT511 - VT513 1

VT521 - VT523 1

VT531 - VT533 1

VT541 - VT543 2

VW851 1

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2. Spares Affected

None.

B. Concurrent Requirements

Group 1:

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

service bulletin:

Group 1:

Company Service Bulletin Description

Boeing 767-21-0235, Original Issue 3-Way Valve Control Logic Change

Group 2:

None

C. Reason

This service bulletin and kit of parts change the Environmental Control System (ECS) Flight Deck

Cooling System Logic to use Electrical Equipment (EE) Cooling rather than Airplane Pack Cooling on

the ground and up to 10,000 feet. This prevents flight deck display unit blanking in hot and humid

environments. If the change is not done moisture or condensation could get in the flight deck display

units. This could cause intermittent indications in the flight deck display.

Operators have reported display unit blanking on 767-300F type airplanes. The reports have included

single display units and multiple units blanking during operation in hot and humid environments.

This service bulletin will change the opening of the 3-way valve (manifold interconnect valve) with a

five minute time delay after climbing past 10,000 feet altitude. The valve will close when descending

below 10,000 feet altitude. This change will reduce moisture or condensation in the flight deck display

unit.

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

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

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

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

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

D. Description

In the Main Equipment Center, do the following change:

1. Change wire bundles W596 and W1702.

2. In the P36 Panel change relays, decals and wire bundle W176.

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

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BOEING SERVICE BULLETIN 767-21-0245
Revision 1 - Airplanes modified in accordance with the original release of this service bulletin do not

require additional work.

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

Affected Maintenance Zones

Model Zone

767-300F 119

E. Compliance

No compliance time is given.

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.

Task Number of Persons Task Hours Elapsed Hours

Figure 1 1 0.50 0.50

Figure 2 1 0.35 0.35

Figure 3 1 3.50 3.50

Figure 4 1 2.10 2.10

Figure 5 2 5.30 2.65

Figure 6 Shows Route Only

Figure 7 Shows Route Only

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BOEING SERVICE BULLETIN 767-21-0245
Task Number of Persons Task Hours Elapsed Hours

Test 1 1.50 1.50

TOTAL FOR EACH AIRPLANE 13.25 10.60

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

Concurrent Requirements.

H. Weight and Balance Changes

None.

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-21-179

d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-11, 20-30-16,

20-61-11, 20-71-11, 20-81-12, 20-90-11

e. 767 Aircraft Maintenance Manual (AMM) 32-09-02

f. 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

Drawing Number Title

MODULAR WIRE BUNDLE INSTALLATION P36, MISCELLANEOUS RELAY PANEL, LEFT288T2036

288T2280 MODULAR WIRE BUNDLE INSTALLATION - E8 EICAS RACK

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.

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BOEING SERVICE BULLETIN 767-21-0245
K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Aircraft Maintenance Manual 21-58

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

767 System Schematic Manual 21-58

767 Illustrated Parts Catalog 21-58

2. Damage Tolerance Based Structural Inspections:

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

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

Maintenance Program. This service bulletin 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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BOEING SERVICE BULLETIN 767-21-0245

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

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

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

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

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

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

2. Fax to (206) 662-7145

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

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

Unit Price as of

the Revision 1

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 1 date of

this Service Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit - 767 Freighters No Longer Available

3 - Way Valve Logic

Change

015T1853-1

Supplemental Kit - 767 08/13/10 3 120 $2.00

Freighters 3 - Way

Valve Logic Change

015T1853-2

Top Kit - 767 Freighters 09/30/10 4 199 $1,148.00

3 - Way Valve Logic

Change

015T1853-3

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 shown below, refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 767-21-0245
NOTE: One Top Kit 015T1853-3, or one Top Kit 015T1853-1 plus one Supplemental Kit

015T1853-2, 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. If Top Kit 015T1853-1 has been obtained,

one Supplemental Kit 015T1853-2 is also required.

Figure Kit

Top Kit 1 2 3 4 5

015T1853-1 1 1 1 1 1

ALL

KIT 015T1853-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5

QTY

015T1853-10101 1 DECAL K10718

015T1853-10102 1 DECAL R1197

015T1853-10103 1 DECAL R1196

015T1853-10104 1 DECAL D31620

015T1853-101W 1 WIRE

015T1853-102W 1 WIRE

015T1853-103W 1 WIRE

015T1853-104W 1 WIRE

015T1853-105W 1 WIRE

015T1853-106W 1 WIRE

015T1853-107W 1 WIRE

826T5075-00401 1 ID - CONNECTOR

CONTACT, SOCKETBACC47CP1S 1 1 1

BACC47DE8A 6 CONTACT

CONTACT, SOCKETBACC47DJ1 4

BACS16W1A 1 RELAY SOCKET

BACS18AR6 4 SPACER

CONTACT, SOCKET, SIZE 20CTA-0165 1

CONTACT, PIN,

SIZE 20

CTA-0166 1

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BOEING SERVICE BULLETIN 767-21-0245
ALL

KIT 015T1853-1

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5

QTY

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1

TIME DELAY RELAYTDH-8050-3003P 1

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 2

Kit 015T1853-2

Existing Part Notes

Number

New Part Number QTY Name

Supplements Top Kit

015T1853-1, Figure 4.

CONTACT, SOCKETBACC47CN1S 2

Supplements Top Kit

015T1853-1, Figure 5.

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1

Figure Kit

Top Kit 1 2 3 4 5

015T1853-3 1 1 1 1 1

ALL

KIT 015T1853-3

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5

QTY

015T1853-10101 1 DECAL K10718

015T1853-10102 1 DECAL R1197

015T1853-10103 1 DECAL R1196

015T1853-10104 1 DECAL D31620

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BOEING SERVICE BULLETIN 767-21-0245
ALL

KIT 015T1853-3

NOTES

Existing Part

Name Number

Figure

New Part Number

1 2 3 4 5

QTY

015T1853-101W 1 WIRE

015T1853-102W 1 WIRE

015T1853-103W 1 WIRE

015T1853-104W 1 WIRE

015T1853-105W 1 WIRE

015T1853-106W 1 WIRE

015T1853-107W 1 WIRE

826T5075-00401 1 ID - CONNECTOR

BACC47CN1S 2 CONTACT, PIN

CONTACT, SOCKETBACC47CP1S 1 2

BACC47DE8A 6 CONTACT

CONTACT, SOCKETBACC47DJ1 4

BACS16W1A 1 RELAY SOCKET

BACS18AR6 4 SPACER

CONTACT, PIN,

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 1 1

TIME DELAY RELAYTDH-8050-3003P 1

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-30 2

2. Parts and Materials Supplied by the Operator

None

3. Parts Modified and Reidentified

None

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BOEING SERVICE BULLETIN 767-21-0245
4. Parts Removed and Not Replaced

Existing Part Name QTY Notes

Number

BACR13CD2 Relay 1 (a)

(K10355)

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

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 767-21-0245

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

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

definition of the acronyms.

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

4. 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.

5. 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.

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

the functional test listed in this service bulletin is all that is required.

B. WORK INSTRUCTIONS

1. Change relays in the P36 Panel in accordance with Figure 1.

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

3. Change wire bundle W0176 in accordance with Figure 3.

4. Change wire bundle W1702 in accordance with Figure 4.

5. Change wire bundles W2000 and W2006 in accordance with Figure 5.

6. Route wire bundles W0176 and W1702 in accordance with Figure 6.

7. Route wire bundles W2000 and W2006 in accordance with Figure 7.

8. Do the following functional test.

Functional Test of Manifold Interconnect Valve Control Logic Modification

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a. MAKE SURE the airplane is powered, the engines are OFF, and the air conditioning packs

are OFF.

b. MAKE SURE the Air/Ground Relay System is in GROUND mode.

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

mode.

c. MAKE SURE the following circuit breakers on the P11 panel are closed:

CB NO. LOC NOMENCLATURE

------ --- ------------

C00653 A13 Left Pack Cont

C00704 A26 Right Pack Cont

C01175 C30 LDG GR POS Air/GND Sys 1

C4078 J2 L EICAS CMPTR

C4079 J29 R EICAS CMPTR

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

e. MAKE SURE that the EICAS MAINTENANCE ENABLE BYPASS SWITCH (S612) is set to

NORMAL.

f. VERIFY that ALL of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

g. REMOVE relay K10718 in the P36 panel.

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

NOTE: This simulates a failure.

i. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

k. REINSTALL relay K10718 in the P36 panel.

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

at STA 208, WL 172, and RBL 60.

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

n. VERIFY the following valve condition:

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BOEING SERVICE BULLETIN 767-21-0245
Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

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

NOTE: This simulates the Left Pack is ON.

p. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

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

NOTE: This simulates the Right Pack is ON

r. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

s. Verify greater than 20VDC measured from TB239D, R1197(C53) to ground.

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

installed in reverse polarity.

t. Deleted

u. Deleted

v. Deleted

w. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

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

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

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y. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

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

mode from the AMM procedure to reconfigure to AIR Mode, THEN perform the following four

(4) sub-steps:

(1) REMOVE relay K336 in the P36 panel.

(2) REMOVE relay K340 in the P36 panel.

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

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

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

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

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

MORE THAN 10 MINUTES.

aa. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

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

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

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

ac. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

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

Time = ____________ minutes _____________ seconds

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

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

allowable value.

af. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

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BOEING SERVICE BULLETIN 767-21-0245
OPEN (C-B) Manifold Interconnect Valve V90

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

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE

REMAINS OPEN FOR MORE THAN 10 MINUTES.

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

ah. WAIT for 15 minutes to allow the equipment to cool down.

ai. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

aj. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

ak. REMOVE relay K10718 in the P36 panel.

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

NOTE: This simulates a failure.

am. VERIFY that ALL the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

ao. REINSTALL relay K10718 in the P36 panel.

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

aq. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

OPEN (C-B) Manifold Interconnect Valve V90

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

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

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

WHEN THE EQUIPMENT COOLING ROTARY SWITCH ON THE P5 OVERHEAD

PANEL IS SET TO THE OVRD POSITION SINCE THE EQUIPMENT COOLING

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

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

POSITION FOR MORE THAN 10 MINUTES.

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

as. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

OPEN (C-B) Manifold Interconnect Valve V90

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

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

POSITION SINCE THE COOLING PACKS ARE NOT ACTUALLY OPERATING.

DAMAGE TO THE FLIGHT DECK INSTRUMENTS MAY RESULT IF THE VALVE

REMAINS OPEN FOR MORE THAN 10 MINUTES.

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

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

THE P11 PANEL) WERE OPENED AND THE EQUIPMENT COOLING ROTARY

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

AMM PROCEDURE TO RECONFIGURE TO AIR MODE, THEN THE INSTRUMENTS

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

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

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

MINUTES.

au. VERIFY the following valve condition:

Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

av. RECONNECT Pin 2 of Connector (D20950) on the 10K FT Altitude Pressure Switch (S921)

if it was disconnected in a previous step.

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

EICAS Rack.

ax. VERIFY the following valve condition:

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BOEING SERVICE BULLETIN 767-21-0245
Condition Nomenclature Equip No

--------- ------------ --------

CLOSED (A-B) Manifold Interconnect Valve V90

ay. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

ba. REMOVE relay K10718 in the P36 panel.

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

NOTE: This simulates a failure.

bc. VERIFY that NONE of the EICAS Maintenance Pages are selectable using the EICAS

MAINTENANCE PANEL (M10372).

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

be. REINSTALL relay K10718 in the P36 panel.

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

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

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

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

at STA 208, WL 172, and RBL 60.

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

THEN perform the following sub-steps:

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

(2) INSTALL relay K366 in the P36 panel.

(3) INSTALL relay K340 in the P36 panel.

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

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

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

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

9. Put the airplane back in a serviceable condition.

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove RELAY BACR13CD2 (K10355) 1

2 Remove DECAL K10355 1 Near Side

Far Side. Lower the

relay bracket as

needed.

3 Remove DECAL D21730 1

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

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

Far Side. Lower the

relay bracket as

needed.

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

FIGURE 1: P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL RELAY CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (New) SPACER BACS18AR6 1

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

Install (New)

Install (New) SPACER BACS18AR6 1

2 Install (New) SPACER BACS18AR6 1

Refer to SWPM 20-

90-11 as an accepted procedure.

TERMINAL BLOCK YHLZD-30 1

DIODE ASSEMBLY

MODULE

Install (New)

Install (New) SPACER BACS18AR6 1

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

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

FIGURE 2: MAIN EQUIPMENT CENTER - E8 EICAS DIODE INSTALLATION

(SHEET 2 OF 2)

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Reference: 767 WDM 21-58-16

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

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-81-12 as an

accepted procedure.

1 RELAY SOCKET BACS16W1A 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 4

Refer to SWPM 20-61-11 as an

accepted procedure.

3 CONTACT, SOCKET BACC47CP1S 1

4 WIRE 015T1853-101W 1

FIGURE 3: WIRE BUNDLE W0176 CHANGE

(SHEET 1 OF 2)

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NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-71-11 as an

accepted procedure.

CONTACT, PIN, CRIMP M39029/11-145 1

REMOVABLE, PER MIL-C39029/11

5

6 WIRE 015T1853-102W 1

Install within 6 inches of the

equipment.

7 ID - CONNECTOR 826T5075-00401 1

FIGURE 3: WIRE BUNDLE W0176 CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
Reference: 767 WDM 21-58-16

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

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

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

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

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

1 CONTACT, PIN BACC47CN1S 1

Refer to SWPM 20-61-11 as an

accepted procedure. (a)

2 CONTACT, PIN BACC47CN1S 1

3 WIRE 015T1853-103W 1

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

FIGURE 4: WIRE BUNDLE W596 AND W1702 CHANGE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 767-21-0245
Reference: 767 WDM 31-41-13

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

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-20-11 as an

accepted procedure.

1 CONTACT BACC47DE8A 6

Refer to SWPM 20-61-11 as an

accepted procedure.

2 CONTACT, SOCKET BACC47CP1S 1

3 WIRE 015T1853-104W 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 CONTACT, SOCKET BACC47CP1S 1

5 WIRE 015T1853-105W 1

6 WIRE 015T1853-106W 1

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

7 WIRE 015T1853-107W 1

Refer to SWPM 20-71-11 as an

accepted procedure. (a)

CONTACT, PIN, CRIMP M39029/11-145 1

REMOVABLE, PER MIL-C39029/11

8

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

FIGURE 5: WIRE BUNDLE W2000 AND W2006 CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 6: WIRE BUNDLES W0176 AND W01702 ROUTING

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245
FIGURE 7: WIRE BUNDLES W2000 AND W2006 ROUTING

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-21-0245