April 07, 2004

Revision 2: December 19, 2007 777-30-0012

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 47

Commercial

Airplane

Group 777

SPECIAL ATTENTION

Service Bulletin

Number: 777-30-0012

Date: April 07, 2004

Revision 2: December 19, 2007

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Ice - Number 1 Left 

and Right Window Replacement and Wire Changes

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2004 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Unpublished Work - All Rights Reserved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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or 

its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
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 Table of Contents

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BOEING SERVICE BULLETIN 777-30-0012

Table of Contents

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

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

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 20

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

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 26

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 27

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 1: CUT THE BULB SEAL FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW 34

FIGURE 2: WIRING CHANGE FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW . . 36

FIGURE 3: CUT THE BULB SEAL FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW39

FIGURE 4: WIRING CHANGE FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW. . 41

FIGURE 5: INSPECTION OF AN ELECTRICAL CONNECTION ON THE LEFT NUMBER 1 WINDOW 44

FIGURE 6: INSPECTION OF AN ELECTRICAL CONNECTION ON THE RIGHT NUMBER 1 WINDOW .

46
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BOEING SERVICE BULLETIN 777-30-0012

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Commercial

Airplane

Group 777

SPECIAL ATTENTION

Service Bulletin

Number: 777-30-0012 Revision Transmittal Sheet

Date: April 07, 2004

Revision 2: December 19, 2007

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Ice - Number 1 Left 

and Right Window Replacement and Wire Changes

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

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

bulletin. This revision is sent to change the No.1 Windshield Assembly part numbers supplied in the Top Kits.

REASON FOR REVISION

These sections were changed:

1. In Planning Information 1.J., Standard Overhaul Practices Manual (SOPM) reference 20-50-10 and Boeing 

Service Bulletin reference 777-56-0002 have been added to existing data.

2. In Material Information 2.A., Material Price and Availability, the Price and Rolt information has been 

updated.

3. In Material Information 2.C., Parts Necessary For Each Airplane, the No.1 Windshield Assembly part 

numbers been have changed.

4. In Material Information 2.E., Special Tooling - Pricing and Availability, the Tool Kit price has been updated.

5. In Accomplishment Instructions 3.B., Work Instructions, Work Package 1, the circuit breaker tables have 

been changes to open and close the circuit breakers for the left number 1 window.

6. In Accomplishment Instructions 3.B., Work Instructions, Work Package 2, the circuit breaker tables have 

been changes to open and close the circuit breakers for the right number 1 window.

7. In Accomplishment Instructions 3.B., Work Instructions, step 5 of Work Package 3 and Work Package 4, 

the No.1 Windshield Assembly part numbers have changed. 

8. In Figure 1, a new step has been added to the step table to part mark the glareshield.

9. In Figure 3, a new step has been added to the step table to part mark the glareshield.
 

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BOEING SERVICE BULLETIN 777-30-0012

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

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 07, 2004

Revision 1: June 02, 2006

Revision 2: December 19, 

2007
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Commercial

Airplane

Group 777

SPECIAL ATTENTION

Service Bulletin

Number: 777-30-0012 Summary

Date: April 07, 2004

Revision 2: December 19, 2007

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Ice - Number 1 Left 

and Right Window Replacement and Wire Changes

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None

BACKGROUND

This service bulletin gives instructions to do an inspection in the flight compartment of an electrical connection 

on the left and the right number 1 windows. Instructions are also given to replace the windows and make 

changes to their related wire bundles. A new design window is available that uses a different electrical 

connection.

Boeing received nine reports from eight operators of electrical arcs at the terminal blocks of the flight 

compartment windows. More than one of these reports included data to show that the results of the arcs were 

open flame incidents. One operator found an indication of damage at a terminal and tightened a loose 

connection. The terminal had internal damage that could not be seen. Less than six months after it was 

tightened there was a report from the operator of an open flame incident on the same windshield.

The electrical connections on the windows are made with lugs that are attached with screws. All of the windows 

in the flight compartment are electrically heated. The number 1 windows get a much larger electrical load. 

An investigation found that the cause of the electrical arcs is loose terminal connections. A loose connection 

increases the heat at the terminal which can cause damage to the internal solder joint. Damaged solder joints 

are the primary cause for the electrical arcs. The primary causes of loose connections are the incorrect torque 

of the screw or an incorrectly installed screw.

The inspection given in this service bulletin is to look for damage or a loose electrical connection on the 

windshield. If there are indications of electrical arcs or damage to the electrical connection, the windshield is 

replaced. If there is a loose electrical connection, the correct torque is applied to tighten it. If a connection 

cannot be tightened to the correct torque, the windshield is replaced. When a windshield with an electrical 

connection that uses pins and sockets is installed, the related wire bundle on the airplane is changed.
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When the changes given in this bulletin are done, the number 1 windows will have better electrical connections. 

The new connections are made with pins and sockets. The pin and socket connections will prevent the risk of 

electrical arcs as a result of loose connections.

Boeing Service Related Problem (SRP) 777-SRP-56-0015 is related to this service bulletin.

ACTION (PRR 62777-28S)

In the flight compartment, do an inspection of the J5 terminal on the left and the right number 1 windows. 

Replace number 1 windows that use screws and lugs for the electrical connections with a window that uses pins 

and sockets for the electrical connections. Cut the bulb seal to give clearance for terminals on the new 

windshield. Change the related wire bundle.

EFFECTIVITY

Refer to service bulletin Paragraph 1.A.1 for effectivity.

COMPLIANCE

See Service Bulletin Paragraph 1.E. for compliance information.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Work Package Total Task Hours Elapsed Hours

Work Package 1 0.25 0.25

Work Package 2 0.25 0.25

Work Package 3 8.5 4.75

Work Package 4 8.5 4.75
 

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BOEING SERVICE BULLETIN 777-30-0012

WORK PACKAGE 4:

CUT THE BULB SEAL.

REPLACE THE RIGHT NUMBER 1 WINDOW.

CHANGE THE RELATED WIRING.

NUMBER 1 WINDOW.

INSPECT THE RIGHT

WORK PACKAGE 2:

INSPECT THE LEFT NUMBER 1 WINDOW.

WORK PACKAGE 1:

WORK PACKAGE 3:

CUT THE BULB SEAL.

REPLACE THE LEFT NUMBER 1 WINDOW.

CHANGE THE RELATED WIRING.

363654
 

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Commercial

Airplane

Group 777

SPECIAL ATTENTION

Service Bulletin

Number: 777-30-0012

Date: April 07, 2004

Revision 2: December 19, 2007

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Ice - Number 1 Left 

and Right Window Replacement and Wire Changes

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624W001 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 62777-28 for data about this change.

Airplane models:

777-200 777-300

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AEROMEXICO (AMX)

1 WB341

AIR AUSTRAL (AUX)

1 WB366–WB367

AIR CHINA (BEJ)

1 WA241–WA250

AIR FRANCE (AFA)

1 WB311–WB335

GROUP CONFIGURATION DESCRIPTION

1 - Airplanes that have number 1 windows with 

lugs and screws for the electrical connections.
 

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BOEING SERVICE BULLETIN 777-30-0012

AIR INDIA (AIN)

1 WA007 WB058–WB059 WB070

AIRCRAFT MARKETING LTD. (CFK)

1 WA079–WA080

ALITALIA (ALI)

1 WC281–WC289

ALL NIPPON AIRWAYS (ANA)

1 WA131–WA137 WA221–WA223 WA231–WA232 WB481–WB484

WB531–WB537

AMERICAN AIRLINES (AAL)

1 WB416–WB437 WC051–WC073

ASIANA AIRLINES (AAR)

1 WC111–WC114

AUSTRIAN (AUL)

1 WB271–WB273

BRITISH AIRWAYS (BAB)

1 WA076–WA078 WB001–WB021 WB031–WB046 WB411–WB413

CATHAY PACIFIC AIRWAYS (CAT)

1 WA001 WA101–WA104 WB501–WB510

CHINA SOUTHERN AIRLINES (GUN)

1 WA116–WA119 WB121–WB125

CONTINENTAL AIRLINES (CAL)

1 WB371–WB388

DELTA AIR LINES (DAL)

1 WB446–WB453

EGYPTAIR (EGP)

1 WB151–WB155

EL AL ISRAEL AIRLINES (ELA)

1 WC101–WC104

EMIRATES (EAD)

1 WA196–WA198 WB101–WB106 WB631–WB638 WB646–WB649

ILFC (ILF)

1 WB342

JAL INTERNATIONAL (JAL)

1 WA171–WA175 WA206–WA212 WA281 WB591–WB597

WC241–WC243 WC301–WC303
 

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BOEING SERVICE BULLETIN 777-30-0012

KLM - ROYAL DUTCH AIRLINES (KLM)

1 WC381–WC385

KOREAN AIR (KAL)

1 WB131–WB139 WB551–WB554

KUWAIT AIRWAYS (KUW)

1 WB306–WB307

MALAYSIA AIRLINES (MAS)

1 WB161–WB175

MID EAST JET (SKL)

1 WB406

PAKISTAN INT'L AIRLINES (PIA)

1 WC446–WC447

ROYAL BRUNEI AIRLINES (RBA)

1 WB072–WB073

SAUDI ARABIAN AIRLINES (SVA)

1 WB276–WB286 WB291–WB302

SAUDI OGER (SAO)

1 WB476

SINGAPORE AIRLINES (SIA)

1 WB181–WB192 WB201–WB214 WB231–WB247 WB611–WB618

THAI AIRWAYS INTERNATIONAL (TII)

1 WA086–WA093 WB601–WB606

UNITED AIRLINES (UAL)

1 WA002–WA006 WA009–WA010 WA012–WA017 WA261–WA266

WB051–WB057 WB060–WB069 WB071 WB074–WB088

VARIG AIRLINES (VAR)

1 WA008 WA011

VIETNAM AIRLINES (VIE)

1 WB336–WB337 WC361–WC362 WC371–WC372

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

WA001–WA017 1

WA076–WA080 1

WA086–WA093 1

WA101–WA104 1

WA116–WA119 1
 

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BOEING SERVICE BULLETIN 777-30-0012

WA131–WA137 1

WA171–WA175 1

WA196–WA198 1

WA206–WA212 1

WA221–WA223 1

WA231–WA232 1

WA241–WA250 1

WA261–WA266 1

WA281 1

WB001–WB021 1

WB031–WB046 1

WB051–WB088 1

WB101–WB106 1

WB121–WB125 1

WB131–WB139 1

WB151–WB155 1

WB161–WB175 1

WB181–WB192 1

WB201–WB214 1

WB231–WB247 1

WB271–WB273 1

WB276–WB286 1

WB291–WB302 1

WB306–WB307 1

WB311–WB337 1

WB341–WB342 1

WB366–WB367 1

WB371–WB388 1

WB406 1

WB411–WB413 1

WB416–WB437 1

WB446–WB453 1

WB476 1

WB481–WB484 1

WB501–WB510 1

WB531–WB537 1

WB551–WB554 1

WB591–WB597 1

WB601–WB606 1

Variable Group
 

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BOEING SERVICE BULLETIN 777-30-0012

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts 

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for 

the recommended use.

B. Concurrent Requirements

None

C. Reason

This service bulletin gives instructions to do an inspection in the flight compartment of an electrical 

connection on the left and the right number 1 windows. Instructions are also given to replace the 

windows and make changes to their related wire bundles. A new design window is available that uses 

a different electrical connection.

Boeing received nine reports from eight operators of electrical arcs at the terminal blocks of the flight 

compartment windows. More than one of these reports included data to show that the results of the 

arcs were open flame incidents. One operator found an indication of damage at a terminal and 

tightened a loose connection. The terminal had internal damage that could not be seen. Less than 

six months after it was tightened there was a report from the operator of an open flame incident on the 

same windshield.

The electrical connections on the windows are made with lugs that are attached with screws. All of 

the windows in the flight compartment are electrically heated. The number 1 windows get a much 

larger electrical load. 

An investigation found that the cause of the electrical arcs is loose terminal connections. A loose 

connection increases the heat at the terminal which can cause damage to the internal solder joint. 

Damaged solder joints are the primary cause for the electrical arcs. The primary causes of loose 

connections are the incorrect torque of the screw or an incorrectly installed screw.

WB611–WB618 1

WB631–WB638 1

WB646–WB649 1

WC051–WC073 1

WC101–WC104 1

WC111–WC114 1

WC241–WC243 1

WC281–WC289 1

WC301–WC303 1

WC361–WC362 1

WC371–WC372 1

WC381–WC385 1

WC446–WC447 1

Variable Group
 

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BOEING SERVICE BULLETIN 777-30-0012

The inspection given in this service bulletin is to look for damage or a loose electrical connection on 

the windshield. If there are indications of electrical arcs or damage to the electrical connection, the 

windshield is replaced. If there is a loose electrical connection, the correct torque is applied to tighten 

it. If a connection cannot be tightened to the correct torque, the windshield is replaced. When a 

windshield with an electrical connection that uses pins and sockets is installed, the related wire bundle 

on the airplane is changed.

When the changes given in this bulletin are done, the number 1 windows will have better electrical 

connections. The new connections are made with pins and sockets. The pin and socket connections 

will prevent the risk of electrical arcs as a result of loose connections.

Boeing Service Related Problem (SRP) 777-SRP-56-0015 is related to this service bulletin.

Revision 1 is sent to add an inspection and new top kits.

The new inspection is in the flight compartment on an electrical connection of the left and the right 

number 1 windows. The number 1 window can be used if it passes the inspection. A window that 

does not pass the inspection can be replaced with the same type window. There is a time limit on how 

long the old number 1 windows can be used.

The top kit in the initial release of this bulletin only had the kits for the wiring changes. When the wiring 

changes are done, it is necessary to install a window that includes the correct electrical connections. 

New top kits are offered for the left and the right side. Each kit includes a wire kit and a number 1 

window. This makes it easy for operators to get only the top kit for the side that is changed. There can 

be a span of eight years from the replacement of one window until the replacement of the other 

window 

The Background and Reason sections have been changed. More data is given. 

The Compliance sections are revised to include tables for compliance time. The inspection 

compliance time is new in this revision to the bulletin.

A tool for the removal and installation of the number 1 window is added to the applicable sections. It 

is shown in the Special Tooling section and in the Accomplishment Instructions 

Work Packages 1 and 2 are changed to Work Packages 3 and 4. New Work Packages 1 and 2 are 

added for the inspections. Figure 5 is added for the new Work Package 1. Figure 6 is added for the 

new Work Package 2.

The Figures 2 and 4 did not include equipment identification in the wire routing illustration. The wire 

schematics were not correct. The instructions were not clear. The Figures in this revision show the 

necessary information more clearly.

The tests in the original issue of this bulletin contained errors. There were more tests in the 

instructions than were necessary. The tests referred to test equipment that was not necessary. 

Instructions were also given to do the tests given in the maintenance manual. The tests and the 

special test equipment that are not necessary are removed in Revision 1. 
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 Revision 2 is sent to change the No.1 Windshield Assembly part numbers supplied in the Top Kits.

These sections were changed:

1. In Planning Information 1.J., Standard Overhaul Practices Manual (SOPM) reference 20-50-10 

and Boeing Service Bulletin reference 777-56-0002 have been added to existing data.

2. In Material Information 2.A., Material Price and Availability, the Price and Rolt information has 

been updated.

3. In Material Information 2.C., Parts Necessary For Each Airplane, the No.1 Windshield Assembly 

part numbers have changed.

4. In Material Information 2.E., Special Tooling - Pricing and Availability, the Tool Kit price has been 

updated.

5. In Accomplishment Instructions 3.B., Work Instructions, Work Package 1, the circuit breaker 

tables have been changes to open and close the circuit breakers for the left number 1 window.

6. In Accomplishment Instructions 3.B., Work Instructions, Work Package 2, the circuit breaker 

tables have been changes to open and close the circuit breakers for the right number 1 window.

7. In Accomplishment Instructions 3.B., Work Instructions, step 5 of Work Package 3 and Work 

Package 4, the No.1 Windshield Assembly part numbers have been changed. 

8. In Figure 1, a new step has been added to the step table to part mark the glareshield.

9. In Figure 3, a new step has been added to the step table to part mark the glareshield.

D. Description

In the flight compartment, an inspection is done of the left and the right number 1 windows. A 

windshield that uses pin and socket electrical connections is installed. The bulb seal is cut to give 

clearance for terminals that are on the new windshield. When a windshield that uses the pin and 

socket electrical connections is installed, the related wire bundle is also changed.

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

service bulletin.

Revision 2 - No more work is necessary on airplanes changed as shown in Revision 1 of this service 

bulletin.
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E. Compliance

F. Approval

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

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

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

JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval 

were based on the airplane in its original Boeing delivery configuration or as modified by other 

approved Boeing changes.

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

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

approval before incorporating this service bulletin.

Compliance Sequence

Condition Action Compliance Time Repeat Interval 

Number 1 windows that 

use screws and lugs for 

the electrical connections

Do the Inspections given in 

Work Packages 1 and 2.

Within 500 flight 

hours after the date 

of revision 1 to this 

service bulletin.

Every 6000 flight 

hours until Work 

Packages 3 and 4 

are done.

Number 1 window 

replaced with the same 

screw and lug type 

window

Do the Inspections given in 

Work Packages 1 and 2.

Within 500 flight 

hours of the number 

1 window 

replacement.

Every 6000 flight 

hours until Work 

Packages 3 and 4 

are done.

Number 1 window that 

uses screws and lugs for 

the electrical connections

Replace with a window that 

uses pins and sockets for 

the electrical connections 

as given in Work Packages 

3 and 4.

No time limit. Terminating action 

for this bulletin
April 07, 2004

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G. Manpower

The tables 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 examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Work Package 1 - Inspection of the Left Number 1 Window

Task

Number of 

Persons Task-Hours Elapsed Hours

Figure 5 1 0.25 0.25

Total per Window 0.25 0.25

Work Package 2 - Inspection of the Right Number 1 Window

Task

Number of 

Persons Task-Hours Elapsed Hours

Figure 6 1 0.25 0.25

Total per Window 0.25 0.25

Work Package 3 - Replacement of the Left Number 1 Window and Changes to the Related

Wiring

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 1.0 0.50

Remove the Left 

Number 1 Window

2 2.5 1.25

Figure 1 - Cut the 

Bulb Seal

1 0.25 0.25

Figure 2 - Change 

the Wiring

1 0.5 0.5

Install the Left 

Number 1 Window

2 3.0 1.5

Test 1 0.25 0.25

Close Access 2 1.0 0.50

Total per Window 8.5 4.75
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H. Weight and Balance Changes

None

I. Electrical Load Data

Not changed

J. References

1. Existing Data:

a. Engineering Change Memo PRR 62777-28S

b. Service Related Problem (SRP) 777-SRP-56-0015

c. 777 Aircraft Maintenance Manual (AMM) 30-41-00, 56-11-01

d. 777 Wiring Diagram 30-41-11, 30-41-12

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19, 

20-30-12, 20-63-19

f. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-02, 20-43-03, 20-50-10

g. Boeing Service Bulletin 777-56-0002

2. Data supplied with this Service Bulletin:

None

Work Package 4 - Replacement of the Right Number 1 Window and Changes to the Related

Wiring

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 1.0 0.50

Remove the Right 

Number 1 Window

2 2.5 1.25

Figure 3 - Cut the 

Bulb Seal

1 0.25 0.25

Figure 4 - Change 

the Wiring

1 0.5 0.5

Install the Right 

Number 1 Window

2 3.0 1.5

Test 1 0.25 0.25

Close Access 2 1.0 0.50

Total per Window 8.5 4.75
 

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BOEING SERVICE BULLETIN 777-30-0012

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

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

L. Interchangeability and Intermixability of Parts

Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability 

information.

Drawing Number Title

288W4100 Wire Bundle Instl - R.S. Cab (STA. 126.5 - 246.0)

288W4101 Wire Bundle Instl - L.S. Cab (STA. 126.5 - 246.0)

Publication Chapter-Section

777 Maintenance Manual 56-11

777 Wiring Diagram Manual 30-41

777 Illustrated Parts Catalog 56-11
 

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BOEING SERVICE BULLETIN 777-30-0012

BLANK PAGE
 

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BOEING SERVICE BULLETIN 777-30-0012

2. MATERIAL INFORMATION

A. Material - Price and Availability

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

below. Kit availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date 

Boeing gets the purchase order.

The kits/parts are subject to the terms and conditions of the Boeing standard purchase order 

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in 

United States dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow: 

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

2. Fax to (206) 662-7145

3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

Kit Number Name

ROLT 

(Weeks)

Unit Price thru 

Dec 31/2007

005W3254-1 Top Kit, Flight Deck Window Heat 

Terminal Replacement

 13 $728.00

005W3254-4 Top Kit - Left Number 1 Window 

with New Window Heat Terminal 

Connections 

 16 $16,600.00

005W3254-5 Top Kit - Right Number 1 Window 

with New Window Heat Terminal 

Connections

 18 $16,600.00
 

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BOEING SERVICE BULLETIN 777-30-0012

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:

1. One left top kit and one right top kit and the items shown in Paragraph 2.C.2., Parts 

and Materials Supplied by the Operator, are necessary for each airplane

2. Top Kit 005W3254-1 includes the subkits to do the wiring changes for both the left 

and the right side of an airplane but it includes no windows. A subkit 005W3254-2 

and a Window 141W7400-44 are equivalent to a top kit 005W3254-5. A subkit 

005W3254-3 and a Window 141W7400-43 are equivalent to a top kit 005W3254-4.

Kit 005W3254 

New Part 

Number

QTY

-5 -4 -3 -2 -1 Name Notes

005W3254-1 . . . . - Top Kit - Flight Deck Window 

Heat Terminal Replacement

(a)

005W3254-2 1 . . - 1 Sub Kit - Flight Deck Window 

Heat Terminal Right Side

(b)

005W3254-3 . 1 - . 1 Sub Kit - Flight Deck Window 

Heat Terminal Left Side

(c)

005W3254-4 . - . . . Top Kit - Left Number 1 

Window with New Window 

Heat Terminal Connections

005W3254-5 - . . . . Top Kit - Right Number 1 

Window with New Window 

Heat Terminal Connections

005W3254-101 . . 1 . . Wire Identified 

W4123-0111-20

(d)

005W3254-102 . . 1 . . Wire Identified 

W4123-0112-20

(d)

005W3254-103 . . 1 . . Wire Identified W4123-0113-12 (e)

005W3254-104 . . 1 . . Wire Identified W4123-0114-12 (e)

005W3254-106 . . . 1 . Wire Identified W4269-0111-20 (d)

005W3254-107 . . . 1 . Wire Identified W4269-012-20 (d)

005W3254-108 . . . 1 . Wire Identified W4269-0113-12 (e)

005W3254-109 . . . 1 . Wire Identified W4269-0114-12 (e)

141W7400-43 . 1 . . . Left No.1 Window Assembly (f)(g) 

(h)(i)(k)(m)

141W7400-44 1 . . . . Right No.1 Window Assembly (f)(g) 

(h)(j)(l)(m)

D-436-37 . . 2 2 . Splice
 

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BOEING SERVICE BULLETIN 777-30-0012

D-436-38 . . 2 2 . Splice

M39029/57-358 . . 2 2 . Socket Contact

M39029/57-359 . . 2 2 . Socket Contact

(a) Top Kit 005W3254-1 includes the subkits to do the wiring changes for both the left 

and the right side of an airplane but it includes no windows.

(b) A subkit 005W3254-2 and a Window 141W7400-44 are equivalent to a top kit 

005W3254-5.

(c) A subkit 005W3254-3 and a Window 141W7400-43 are equivalent to a top kit 

005W3254-4.

(d) Wire, BMS 13-48, Type 10, Class 1, AWG 20

(e) Wire, BMS 13-48, Type 8, Class 1, AWG 12

(f) Discard the existing part.

(g) This part is used in production.

(h) You cannot use the existing part to replace the new or changed part.

(i) As an option operators can install Left Windshield part number 141W7400-31 or 

141W7400-33 with serial numbers 04xxxH or 05xxxH.

(j) As an option operators can install Right Windshield part number 141W7400-32 or 

141W7400-34 with serial numbers 04xxxH or 05xxxH.

(k) As an option operators can install Left Windshield part number 141W7400-35 or 

141W7400-41. Windshield part numbers 141W7400-35 and 141W7400-41 can be 

made from Windshield part numbers 141W7400-31 and 141W7400-33 with serial 

numbers 06339H or higher by the incorporation of Boeing Service Bulletin 777-56-0002.

(l) As an option operators can install Right Windshield part number 141W7400-36 or 

141W7400-42. Windshield part numbers 141W7400-36 and 141W7400-42 can be 

made from Windshield part numbers 141W7400-32 and 141W7400-34 with serial 

numbers 06339H or higher by the incorporation of Boeing Service Bulletin 777-56-0002.

(m) PPG Aerospace - Transparencies Div Glass (V53117)

 P.O. Box 2200

 1719 U.S. Highway 72 East 

 Huntsville, AL 35811-9660

Kit 005W3254 

New Part 

Number

QTY

-5 -4 -3 -2 -1 Name Notes
 

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BOEING SERVICE BULLETIN 777-30-0012

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

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

number of parts changed on each airplane.

4. Parts Removed and Not Replaced:

None

D. Parts Necessary to Change Spares

None

Part Number / 

Specification QTY Name Notes

BMS 13-54 10 feet Lacing Tape, Red (a) (b) (c) 

BMS 13-54 10 feet Lacing Tape, Green (a) (b) (d)

(a) Type 3, Class 1

(b) Gudebrod Incorporated (V82110)

 Griffith Towers 

 PO Box 357

 Pottstown, PA 19464

(c) BACS38K5C, red Tie Strap is optional. See the Qualified Products List at 

the end of the Boeing Material Specification (BMS) for the supplier data.

(d) BACS38K5F, green Tie Strap is optional. See the Qualified Products List 

at the end of the Boeing Material Specification (BMS) for the supplier data.

Existing Part 

Number QTY Name New Part Number Notes

233W8300-7A 1 Glareshield 233W8300-21A (a)(b)(c)

233W8300-20A 1 Glareshield 233W8300-22A (a)(b)(c)

(a) Make the change given in this service bulletin.

(b) This is the part number after the change given in this service bulletin.

(c) This part is used in production.
 

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BOEING SERVICE BULLETIN 777-30-0012

E. Special Tooling - Price and Availability

Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service 

Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the 

date the tools will be used.

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

acknowledgement. After the Price date, new price data is applicable. Prices are in United States 

dollars. Terms: Net 30 days.

Reference this service bulletin number and submit purchase order by one of the methods that follow:

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

2. Transmit a Fax to (206) 662-7145

3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

(Service Bulletin 777-30-0012 R1)

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. 

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be 

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

.

Purchase Data:

Tool Kit Number Name

Unit Price

 thru 

Dec 31/2007 

A56001-2 (part of Sling 

Set A56001-15)

Windshield Handling Sling $625.00

Tool Kit Number Name

A56001-2 (part of 

Sling Set A56001-15)

Windshield Handling Sling
 

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BOEING SERVICE BULLETIN 777-30-0012

BLANK PAGE
 

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BOEING SERVICE BULLETIN 777-30-0012

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. The work instructions are divided into work packages. Task-Hours and Elapsed-Hours 

for each package are given in Paragraph 1.G., Manpower. You can do each work 

package independently.

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

— Linear dimensions are in inches

— Torque limits to tighten nuts and bolts are given in 757 Structural Repair Manual, 

Chapter 51.

5. Refer to the Standard Wiring Practices Manual SWPM 20-10-11 and SWPM 20-10-12 

for the wire installation procedures.

6. A Detailed Inspection is defined as: An intensive examination of a specific item, 

installation, or assembly to detect damage, failure, or irregularity. Available lighting is 

normally supplemented with a direct source of good lighting at an intensity deemed 

appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. 

Surface cleaning and elaborate procedures may be required.

7. These work instructions refer to procedures included on 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 "as given 

in" are included in the instruction, the procedure in the Boeing document must be used.
 

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BOEING SERVICE BULLETIN 777-30-0012

B. WORK INSTRUCTIONS

WORK PACKAGE 1 - INSPECTION OF THE LEFT NUMBER 1 WINDOW 

WARNING: BEFORE YOU DO MAINTENANCE ON THE WINDOW HEAT SYSTEM, OPEN THE

WINDOW HEAT CIRCUIT BREAKERS. IF THESE CIRCUIT BREAKERS ARE NOT

OPEN, YOU CAN GET AN ELECTRICAL SHOCK WHEN YOU TOUCH THE

TERMINAL.

1. Open the circuit breakers shown below and attach DO-NOT-CLOSE tags to them:

2. Do an inspection of the left number 1 window as given in Figure 5. 

3. If the left number 1 window is not in a serviceable condition, replace it before the subsequent 

revenue flight. Refer to 777 AMM 56-11-01 as an accepted procedure. If the existing window is 

replaced with one of the same type, it will be necessary to do this inspection within 500 flight 

hours. Windshields in serviceable condition can continue to be used with inspections every 6000 

flight hours, or until the work given in Work Package 3 is done.

4. Remove the DO-NOT-CLOSE tags and close the circuit breakers shown below:

Panel Position Name Circuit Breaker

P110 M26 WHCU BITE 1L C30613

P100 E01 or E02 WDO HTR 1L C30301

P110 F03 WDO HT BACKUP 1L C30415

Panel Position Name Circuit Breaker

P110 M26 WHCU BITE 1L C30613

P100 E01 or E02 WDO HTR 1L C30301

P110 F03 WDO HT BACKUP 1L C30415
 

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BOEING SERVICE BULLETIN 777-30-0012

WORK PACKAGE 2 - INSPECTION OF THE RIGHT NUMBER 1 WINDOW 

WARNING: BEFORE YOU DO MAINTENANCE ON THE WINDOW HEAT SYSTEM, OPEN THE

WINDOW HEAT CIRCUIT BREAKERS. IF THESE CIRCUIT BREAKERS ARE NOT

OPEN, YOU CAN GET AN ELECTRICAL SHOCK WHEN YOU TOUCH THE

TERMINAL.

1. Open the circuit breakers shown below and attach DO-NOT-CLOSE tags to them:

2. Do an inspection of the right number 1 window as given in Figure 6. 

3. If the right number 1 window is not in a serviceable condition, replace it before the subsequent 

revenue flight. Refer to 777 AMM 56-11-01 as an accepted procedure. If the existing within 500 

flight hours. Windshields in serviceable condition can continue to be used with inspections every 

6000 flight hours, or until the work given in Work Package 4 is done.

4. Remove the DO-NOT-CLOSE tags and close the circuit breakers shown below:

Panel Position Name Circuit Breaker

P210 L08 WHCU BITE 1R C30616

P200 B04 or D11 WDO HTR 1R C30300

P210 C12 WDO HT BACKUP 1R C30414

Panel Position Name Circuit Breaker

P210 L08 WHCU BITE 1R C30616

P200 B04 or D11 WDO HTR 1R C30300

P210 C12 WDO HT BACKUP 1R C30414
 

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BOEING SERVICE BULLETIN 777-30-0012

WORK PACKAGE 3 - REPLACEMENT OF THE LEFT NUMBER 1 WINDOW AND CHANGES TO 

THE RELATED WIRE BUNDLE

WARNING: REMOVE ELECTRICAL POWER FROM THE WINDOW HEAT SYSTEM BEFORE

YOU REMOVE THE WINDOWS. IF POWER TO THE WINDOW HEAT SYSTEM IS ON,

YOU CAN GET AN ELECTRICAL SHOCK IF YOU TOUCH ELECTRICAL CONTACTS

ATTACHED TO THE WINDOW. AN ELECTRICAL SHOCK CAN CAUSE INJURY TO

PERSONS.

1. Remove electrical power from the flight compartment window heat systems. Refer to 777 AMM 

56-11-01 as an accepted procedure.

2. Remove the left number 1 window. Use the windshield handling sling, A56001-2. Refer to 777 

AMM 56-11-01 as an accepted procedure. 

3. Cut the bulb seal for the left number 1 window as given in Figure 1.

4. Change the window heat wiring for the left number 1 window as given in Figure 2. 

5. Install the left number 1 window 141W7400-43. Use the windshield handling sling, A56001-2. 

Refer to 777 AMM 56-11-01 as an accepted procedure.

6. Restore electrical power to the flight compartment window heat systems. Refer to 777 AMM 

56-11-01 as an accepted procedure.

7. Do the Window Heat Control System - Operational Test as given in 777 AMM 30-41-00.

8. Put the airplane in a serviceable condition.
 

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BOEING SERVICE BULLETIN 777-30-0012

WORK PACKAGE 4 - REPLACEMENT OF THE RIGHT NUMBER 1 WINDOW AND CHANGES TO 

THE RELATED WIRE BUNDLE

WARNING: REMOVE ELECTRICAL POWER FROM THE WINDOW HEAT SYSTEM BEFORE

YOU REMOVE THE WINDOWS. IF POWER TO THE WINDOW HEAT SYSTEM IS ON,

YOU CAN GET AN ELECTRICAL SHOCK IF YOU TOUCH ELECTRICAL CONTACTS

ATTACHED TO THE WINDOW. AN ELECTRICAL SHOCK CAN CAUSE INJURY TO

PERSONS.

1. Remove electrical power from the flight compartment window heat systems. Refer to 777 AMM 

56-11-01 as an accepted procedure.

2. Remove the right number 1 window. Use the windshield handling sling, A56001-2. Refer to 777 

AMM 56-11-01 as an accepted procedure. 

3. Cut the bulb seal for the right number 1 window as given in Figure 3.

4. Change the window heat wiring for the right number 1 window as given in Figure 4.

5. Install the right number 1 window 141W7400-44. Use the windshield handling sling, A56001-2. 

Refer to 777 AMM 56-11-01 as an accepted procedure.

6. Restore electrical power to the window heat systems for the flight compartment. Refer to 777 

AMM 56-11-01 as an accepted procedure.

7. Do the Window Heat Control System - Operational Test as given in 777 AMM 30-41-00.

8. Put the airplane in a serviceable condition.
 FIGURE 1: CUT THE BULB SEAL FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

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BOEING SERVICE BULLETIN 777-30-0012

FIGURE 1: CUT THE BULB SEAL FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

FWD

GLARESHIELD

SEE A

2

365443

(SHEET 1 OF 2)
 FIGURE 1: CUT THE BULB SEAL FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

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BOEING SERVICE BULLETIN 777-30-0012

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

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: DO NOT CUT THE STRUCTURE BELOW THE BULB SEAL. THE WINDOW

SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION

IF THE FINISH IS DAMAGED. DAMAGE TO THE FINISH MUST BE REPARED.

1

Cut Bulb Seal 233W8300-11 - to clear the new 

terminal.

NOTE: If the finish below the bulb seal is damaged, it must be sealed with chemical

treatment and primer. Refer to Standard Overhaul Practices Manual SOPM

20-41-02 and SOPM 20-43-02 as accepted procedures.

2 Identify Glareshield 233W8300-21A - (a)

(a) Part mark with new part number. Rubber-Stamp or Hand Write. 12 characters per inch. Use 

abrasive resistance ink. Refer to SOPM 20-50-10 as an accepted procedure.

BULB SEAL

A

1

1.20

1.40

FWD

384851

(SHEET 2 OF 2)
 FIGURE 2: WIRING CHANGE FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

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BOEING SERVICE BULLETIN 777-30-0012

FIGURE 2: WIRING CHANGE FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

FLIGHT COMPARTMENT

FWD

J13 INBD

J5

J1

W4123 J15

AREA

SPLICE

359711

(SHEET 1 OF 3)
 FIGURE 2: WIRING CHANGE FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

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BOEING SERVICE BULLETIN 777-30-0012

2005B-12

2005R-12

0002-20

1001-20

SM9

SM4

SM3

SM10

0111-20

0112-20

0113-12

0114-12

J15

J13

J5

J1

STA 160, WL 250, LBL 15

B30101 WINDOW 1-LEFT

STA 160, WL 250, LBL 15

B30101 WINDOW 1-LEFT

D30108

B-A

B-B

D30106

J15

J13

=1

=1

D30105

D30104

D30101

E-A

=1

=1

=1

E-B

E-C

J5

J4

J1

1

1

2

2

W4123

3

4

5

6

8

8

7

7

DELETED WIRE OR FORMER ROUTING

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

REFERENCE: WIRING DIAGRAM 30-41-11

W88286

(SHEET 2 OF 3)
 FIGURE 2: WIRING CHANGE FOR THE LEFT NUMBER 1 FLIGHT COMPARTMENT WINDOW

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BOEING SERVICE BULLETIN 777-30-0012

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

NOTE:Use the parts supplied in kit 005W3254-3 or equivalent.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Splice D-436-37 2 Refer to Standard Wiring Practices 

Manual SWPM 20-30-12 as an accepted 

procedure.

2 Splice D-436-38 2 Refer to SWPM 20-30-12 as an 

accepted procedure.

3 Wire 

Lacing Tape

005W3254-101

BMS 13-54, Type 3, 

Class 1, Red

1 (a)

or optional BACS38K5C Tie Strap (c)

4 Wire 

Lacing Tape

005W3254-102

BMS 13-54, Type 3, 

Class 1, Red

1 (a)

or optional BACS38K5C Tie Strap (c)

5 Wire 

Lacing Tape

005W3254-103

BMS 13-54, Type 3, 

Class 1, Red

1 (b)

or optional BACS38K5C Tie Strap (c)

6 Wire 

Lacing Tape

005W3254-104 

BMS 13-54, Type 3, 

Class 1, Red

1 (b)

or optional BACS38K5C Tie Strap (c)

7 Socket Contact M39029/57-358 2 Refer to SWPM 20-63-19 as an 

accepted procedure.

NOTE: Isopropyl alcohol is applied to the installation tool and on the contact before

installation of the contact. Isopropyl alcohol is a lubricant that helps with

installation of the contact in the connector.

8 Socket Contact M39029/57-359 2 Refer to SWPM 20-63-19 as an 

accepted procedure.

NOTE: Isopropyl alcohol is applied to the installation tool and on the contact before

installation of the contact. Isopropyl alcohol is a lubricant that helps with

installation of the contact in the connector.

(a) BMS 13-48, Type 10, Class 1, AWG 20

(b) BMS 13-48, Type 8, Class 1, AWG 12

(c) Red is for left channel separation. Refer to SWPM 20-10-19 as an accepted procedure.

(SHEET 3 OF 3)
 FIGURE 3: CUT THE BULB SEAL FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

April 07, 2004

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BOEING SERVICE BULLETIN 777-30-0012

FIGURE 3: CUT THE BULB SEAL FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

FWD

GLARESHIELD

SEE A

2

365437

(SHEET 1 OF 2)
 FIGURE 3: CUT THE BULB SEAL FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

April 07, 2004

Revision 2: December 19, 2007 777-30-0012

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 47

BOEING SERVICE BULLETIN 777-30-0012

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

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: DO NOT CUT THE STRUCTURE BELOW THE BULB SEAL. THE WINDOW

SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION

IF THE FINISH IS DAMAGED. DAMAGE TO THE FINISH MUST BE REPARED.

1

Cut Bulb Seal 233W8300-12 - to clear the new 

terminal.

NOTE: If the finish below the bulb seal is damaged, it must be sealed with chemical

treatment and primer. Refer to Standard Overhaul Practices Manual SOPM

20-41-02 and SOPM 20-43-03 as accepted procedures.

2 Identify Glareshield 233W8300-22A - (a)

(a) Part mark with new part number. Rubber-Stamp or Hand Write. 12 characters per inch. Use 

abrasive resistance ink. Refer to SOPM 20-50-10 as an accepted procedure.

A

1 BULB SEAL

1.20

1.40 FWD

384883

(SHEET 2 OF 2)
 FIGURE 4: WIRING CHANGE FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

April 07, 2004

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BOEING SERVICE BULLETIN 777-30-0012

FIGURE 4: WIRING CHANGE FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

FLIGHT COMPARTMENT

INBD

FWD

J13

SPLICE

AREA

W4269

J1

J15

J5

W86527

(SHEET 1 OF 3)
 FIGURE 4: WIRING CHANGE FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

April 07, 2004

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BOEING SERVICE BULLETIN 777-30-0012

D30206

D30208

D30205

D30204

D30201

STA 160, WL 250, RBL 15

B30201 WINDOW 1-RIGHT

STA 160, WL 250, RBL 15

B30201 WINDOW 1-RIGHT

J1

J4

J5

E-C

E-B

=1

=1

=1

E-A

=1

=1

J13

J15

B-B

B-A

J1

J5

J13

J15

0114-12

0113-12

0112-20

0111-20

SM10

SM3

SM4

SM9

1001-20

0002-20

2005R-12

2005B-12

W4269

7

7

8

8

6

5

4

3

2

2

1

1

REFERENCE: WIRING DIAGRAM 30-41-12

DELETED WIRE OR FORMER ROUTING

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

W86528

(SHEET 2 OF 3)
 FIGURE 4: WIRING CHANGE FOR THE RIGHT NUMBER 1 FLIGHT COMPARTMENT WINDOW

April 07, 2004

Revision 2: December 19, 2007 777-30-0012

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BOEING SERVICE BULLETIN 777-30-0012

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

NOTE: Use the parts supplied in kit 005W3254-2 or equivalent.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Splice D-436-37 2 Refer to Standard Wiring Practices 

Manual SWPM 20-30-12 as an accepted 

procedure.

2 Splice D-436-38 2 Refer to SWPM 20-30-12 as an accepted 

procedure.

3 Wire 

Lacing Tape

005W3254-106 

BMS 13-54, Type 3, 

Class 1, Green

1 (a) or optional BACS38K5F Tie Strap (c)

4 Wire 

Lacing Tape

005W3254-107 

BMS 13-54, Type 3, 

Class 1, Green

1 (a) or optional BACS38K5F Tie Strap (c)

5 Wire 

Lacing Tape

005W3254-108 

BMS 13-54, Type 3, 

Class 1, Green

1 (b) or optional BACS38K5F Tie Strap (c)

6 Wire 

Lacing Tape

005W3254-109

BMS 13-54, Type 3, 

Class 1, Green

1 (b) or optional BACS38K5F Tie Strap (c)

7 Socket Contact M39029/57-358 2 Refer to SWPM 20-63-19 as an accepted 

procedure.

NOTE: Isopropyl alcohol is applied to the installation tool and on the contact before

installation of the contact. Isopropyl alcohol is a lubricant that helps with

installation of the contact in the connector.

8 Socket Contact M39029/57-359 2 Refer to SWPM 20-63-19 as an accepted 

procedure.

NOTE: Isopropyl alcohol is applied to the installation tool and on the contact before

installation of the contact. Isopropyl alcohol is a lubricant that helps with

installation of the contact in the connector.

(a) BMS 13-48, Type 10, Class 1, AWG 20

(b) BMS 13-48, Type 8, Class 1, AWG 12

(c) Green is for right channel separation. Refer to SWPM 20-10-19 as an accepted 

procedure.

(SHEET 3 OF 3)
 FIGURE 5: INSPECTION OF AN ELECTRICAL CONNECTION ON THE LEFT NUMBER 1 WINDOW

April 07, 2004

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BOEING SERVICE BULLETIN 777-30-0012

FIGURE 5: INSPECTION OF AN ELECTRICAL CONNECTION ON THE LEFT NUMBER 1 WINDOW

FLIGHT COMPARTMENT

INBD

FWD

3

1

2 3

SCREW

J13

J5

CONNECTOR

BLOCK,

TERMINAL

LUG

J4 J15

J1 W4123

498760

(SHEET 1 OF 2)
 FIGURE 5: INSPECTION OF AN ELECTRICAL CONNECTION ON THE LEFT NUMBER 1 WINDOW

April 07, 2004

Revision 2: December 19, 2007 777-30-0012

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 47

BOEING SERVICE BULLETIN 777-30-0012

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Terminal Block - 1 at the J5 connection

Connector - 1

Wiring Wire bundle W4123 1

NOTE: If there is a melted terminal, black marks, or discoloration, the window must be

replaced.

NOTE: If there is damage to the wiring it must be repaired. Refer to Standard Wiring

Practices Manual SWPM 20-10-13 as an accepted procedure.

2

Inspect Lug - 1 to make sure it is a 

tight connection.

NOTE: If the lug at the terminal moves with light manual pressure, then the screw that

attaches it must be tightened. There are three causes for a loose terminal.

1-The screw is not tightened to the correct torque

2-The terminal is damaged

3-The incorrect screw is installed. The part number of the correct screw is

NAS1802-3-11.

CAUTION: DO NOT OVER TIGHTEN. THE TERMINAL CAN BE DAMAGED BY TOO MUCH

FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE

WINDOW.

3

Turn Screw - 1 to 25 to 30 inch pounds of torque. 

Refer to Standard Overhaul 

Practices Manual SOPM 20-43-03 

as an accepted procedure. 

Inspect Lug 1 to make sure the connection is 

tight. 

NOTE: The screw is only tightened if the lug is loose. If it is the correct screw and it cannot

be tightened to 25 to 30 inch pounds, the window must be replaced.

(SHEET 2 OF 2)
 FIGURE 6: INSPECTION OF AN ELECTRICAL CONNECTION ON THE RIGHT NUMBER 1 WINDOW

April 07, 2004

Revision 2: December 19, 2007 777-30-0012

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 47

BOEING SERVICE BULLETIN 777-30-0012

FIGURE 6: INSPECTION OF AN ELECTRICAL CONNECTION ON THE RIGHT NUMBER 1 WINDOW

FLIGHT COMPARTMENT

1

FWD

INBD

3

2 3

W4269

TERMINAL

CONNECTOR

BLOCK,

J1

SCREW

LUG

J5

J13

J15 J4

499019

(SHEET 1 OF 2)
 FIGURE 6: INSPECTION OF AN ELECTRICAL CONNECTION ON THE RIGHT NUMBER 1 WINDOW

April 07, 2004

Revision 2: December 19, 2007 777-30-0012

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 47

BOEING SERVICE BULLETIN 777-30-0012

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Terminal Block - 1 at the J5 connection

Connector - 1

Wiring Wire bundle W4269 1

NOTE: If there is a melted terminal, black marks, or discoloration, the window must be

replaced.

NOTE: If there is damage to the wiring it must be repaired. Refer to Standard Wiring

Practices Manual SWPM 20-10-13 as an accepted procedure.

2

Inspect Lug - 1 to make sure it is a 

tight connection.

NOTE: If the lug at the terminal moves with light manual pressure, then the screw that

attaches it must be tightened. There are three causes for a loose terminal.

1-The screw is not tightened to the correct torque

2-The terminal is damaged

3-The incorrect screw is installed. The part number of the correct screw is

NAS1802-3-11.

CAUTION: DO NOT OVER TIGHTEN. THE TERMINAL CAN BE DAMAGED BY TOO MUCH

FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE

WINDOW.

3

Turn Screw - 1 to 25 to 30 inch pounds of torque. 

Refer to Standard Overhaul 

Practices Manual SOPM 20-43-03 

as an accepted procedure. 

Inspect Lug 1 to make sure the connection is 

tight. 

NOTE: The screw is only tightened if the lug is loose. If it is the correct screw and it cannot

be tightened to 25 to 30 inch pounds, the window must be replaced.

(SHEET 2 OF 2)