Commercial 

Airplanes 747

Service Bulletin

Number: 747-30-2081

Original Issue: August 08, 2006

Revision 3: December 05, 2011

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing System -

Windshield Inspection and Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2006 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the

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connection with this document unless provided in writing by Boeing.

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BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 30

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 52

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 53

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD . . . . . . . . . . . . . . . . . . . . . . . . . 63

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD . . . . . . . . . . . . . . . . . . . . . . . . 69

FIGURE 3: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

1 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75

FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

2 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76

FIGURE 5: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

3 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77

FIGURE 6: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

4 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

FIGURE 7: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

5 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80

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BOEING SERVICE BULLETIN 747-30-2081
FIGURE 8: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

6 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

FIGURE 9: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

7 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82

FIGURE 10: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

8 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84

FIGURE 11: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 1

THROUGH 6 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86

FIGURE 12: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 7 - 8

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87

FIGURE 13: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 1 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88

FIGURE 14: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 2 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89

FIGURE 15: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 3 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90

FIGURE 16: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 4 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92

FIGURE 17: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 5 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93

FIGURE 18: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 6 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94

FIGURE 19: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 7 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95

FIGURE 20: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD -

GROUP 8 AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97

FIGURE 21: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP 1 - 6

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99

FIGURE 22: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP 7 - 8

AIRPLANES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100

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BOEING SERVICE BULLETIN 747-30-2081
Commercial 

Airplanes 747

Service Bulletin

Revision Transmittal Sheet Number: 747-30-2081

Original Issue: August 08, 2006

Revision 3: December 05, 2011

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing System -

Windshield Inspection and Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-221-AD is related to

this service bulletin.

No more work is necessary on the airplanes inspected in accordance with the original issue or Revision 1 or

Revision 2 of this service bulletin.

No more work is necessary on airplanes that have done the terminating action in accordance with the original

issue or Revision 1 or Revision 2 of this service bulletin.

REASON FOR REVISION

This revision is sent to add FAA Notice of Proposed Rule Making and new data to FIGURE 1 and FIGURE 2 of

the service bulletin.

These sections were changed:

1. Summary Compliance and Paragraph 1.E. Compliance, added FAA Notice of Proposed Rule Making.

2. Summary Background and Action, changed the type of inspection.

3. Paragraph 1.J.1., Existing Data, added FAA Notice of Proposed Rule Making.

4. Paragraph 2.A., Material - Price and Availability, updated pricing and ROLT data.

5. Paragraph 2.E., Special Tooling - Price and Availability, updated pricing.

6. Paragraph 3.A., General Information, changed the notes.

7. Paragraph 3.B., Work Instructions, changed the type of inspection in Work Package 1 and 2.

8. FIGURE 1 and FIGURE 2, changed the illustrations and added new data to the footnotes.

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

of important changes.

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Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: August 08, 2006

Revision 1: August 20, 2008

Revision 2: March 10, 2010

Revision 3: December 05, 2011

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BOEING SERVICE BULLETIN 747-30-2081
Commercial 

Airplanes 747

Service Bulletin

Summary Number: 747-30-2081

Original Issue: August 08, 2006

Revision 3: December 05, 2011

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing System -

Windshield Inspection and Replacement

CONCURRENT REQUIREMENTS

None

BACKGROUND

This service bulletin gives instructions to do a detailed inspection of an electrical connection on the left and the

right windshields. Instructions are also given to replace the windshields and make changes to their related wire

bundles. A new windshield design 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

windshields. 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 block and tightened a loose connector. The

terminal block 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 connectors on the windshields are attached with screws. The windshield is the number 1 window

in the flight compartment. All of the windows in the flight compartment are electrically heated. The windshield

gets a much larger electrical load.

An investigation found that the cause of the electrical arcs was a loose connector. A loose connection increases

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

the primary cause for the electrical arcs. The primary cause of a loose connector is the incorrect torque of the

screw or an incorrectly installed screw.

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

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

is replaced. If there is a loose electrical connector, the correct torque is applied to tighten it. If a connector 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 windshields 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) 747-SRP-56-0015 is related to this service bulletin.

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ACTION (PRR 85639, PRR 85901-49S)

In the flight compartment, do a detailed inspection of the A terminal block on the left and the right windshields.

Replace windshields that use screws and connectors for the electrical connections with a windshield that uses

pins and sockets for the electrical connections. Cut the bulb seal to give clearance for terminal blocks on the

new windshield. Change the related wire bundle.

EFFECTIVITY

747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C 747-200F, 747-300, 747-400, 747-400D, 747-400F,

747SP, 747SR Airplanes. Refer to Paragraph 1.A., Effectivity., Airplanes for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-221-AD, is related to

this service bulletin.

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

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the detailed inspection or the configuration changes given in this

service bulletin.

MANPOWER

Work Package Total Task Hours Elapsed Hours

Work Package 1 - Detailed Inspection of the Left 0.25 0.25

Windshield

Work Package 2 - Detailed Inspection of the Right 0.25 0.25

Windshield

Work Package 3 - Left Windshield Replacement and 9.0 5.25

Wiring Change

Work Package 4 - Right Windshield Replacement and 9.0 5.25

Wiring Change

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

Number: 747-30-2081

Original Issue: August 08, 2006

Revision 3: December 05, 2011

ATA System: 3041 5611

SUBJECT: ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing System -

Windshield Inspection and Replacement

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

production airplanes. Refer to PRR 85901-49S for data about this change.

Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses the 015U1784-1,

-2, -3, -4, -5, and -6 top kits.

1 -

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses the 015U1784-7,

-8, -9, -10, -11, and -12 top kits.

2 -

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses the 015U1784-13,

-14, -15, -16, -17, and -18 top kits.

3 -

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses the 015U1784-1,

-2, -3, -4, -5, and -6 top kits, but the current wiring configuration is

different than Group 1 airplanes.

4 -

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses the 015U1784-1,

-2, -3, -4, -5, and -6 top kits, but the current wiring configuration is

different than Group 1 or Group 3 airplanes.

5 -

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GROUP CONFIGURATION DESCRIPTION

747-100,-200,-300 airplanes with windshields that use a screw to

attach the electrical connection. This group uses 015U1784-1, -2,

-3, -4, -5, and -6 top kits, but the current wiring configuration is

different than Group 1 or Group 4 or Group 5 airplanes.

6 -

747-400 Freighters with windshields that use a screw to attach the

electrical connection. This group uses the 015U1784-19, -20, -21,

-22, -23, and -24 top kits.

7 -

747-400 Passenger model with windshields that use a screw to attach

the electrical connection. This group uses the 015U1784-25, -26,

-27, -28, -29, and -30 top kits.

8 -

Airplane Models:

747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,

747-400D, 747-400F, 747SP, 747SR

Variable Number Group

RA001 - RA026 4

RA027 - RA034 6

RA101 - RA111 4

RA112 3

RA113 4

RA114 - RA115 6

RA161 3

RA162 4

RA163 - RA164 6

RA201 - RA203 4

RA216 6

RA217 1

RA245 6

RA246 1

RA251 - RA254 4

RA255 - RA256 6

RA257 - RA266 1

RA301 - RA303 4

RA304 - RA309 6

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BOEING SERVICE BULLETIN 747-30-2081
Variable Number Group

RA310 - RA318 1

RA351 - RA360 4

RA369 4

RA370 - RA373 6

RA401 - RA408 4

RA409 - RA413 6

RA414 - RA418 1

RA501 4

RA502 6

RA521 - RA523 4

RA524 6

RA525 - RA528 1

RA532 - RA535 6

RA536 - RA548 1

RA551 - RA552 4

RA559 - RA560 6

RA561 1

RA581 - RA582 4

RA585 6

RA601 - RA602 4

RA631 5

RA632 - RA633 4

RA634 - RA635 6

RA651 - RA652 6

RA671 4

RA672 - RA677 6

RA701 - RA702 6

RA721 - RA722 6

RA723 - RA731 1

RA741 - RA743 6

RA744 - RA745 1

RA749 - RA750 1

RA761 - RA762 6

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BOEING SERVICE BULLETIN 747-30-2081
Variable Number Group

RA781 - RA782 6

RA783 - RA784 1

RA901 - RA903 3

RA904 - RA905 4

RA906 - RA907 3

RA908 - RA910 4

RA911 - RA916 6

RB001 - RB004 6

RB005 - RB012 1

RB041 - RB043 4

RB044 6

RB071 1

RB072 - RB073 6

RB074 - RB075 1

RB101 - RB102 4

RB411 - RB413 2

RB421 2

RB601 1

RB604 - RB605 1

RB607 1

RB681 - RB685 1

RB687 1

RB690 - RB697 1

RB711 1

RB721 - RB722 1

RB723 2

RB741 - RB748 1

RD001 - RD004 1

RD021 - RD022 1

RD041 - RD059 1

RD071 - RD072 1

RD081 - RD083 1

RD091 - RD092 1

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BOEING SERVICE BULLETIN 747-30-2081
Variable Number Group

RD101 - RD104 1

RD121 - RD127 1

RD131 - RD144 1

RD171 - RD172 1

RD181 - RD183 1

RD201 - RD204 1

RD221 - RD226 1

RD227 2

RD231 - RD235 2

RD241 - RD243 1

RD251 - RD257 1

RD258 - RD262 2

RD271 - RD272 1

RD291 - RD292 2

RD301 - RD302 2

RD311 2

RD351 - RD357 1

RD358 2

RD361 - RD365 1

RD366 2

RD381 - RD383 1

RD411 - RD414 1

RD421 - RD426 1

RD431 - RD435 1

RD441 - RD442 1

RD451 - RD455 1

RD456 2

RD461 1

RD471 - RD475 1

RD513 - RD519 1

RD531 - RD533 1

RD551 1

RD561 1

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BOEING SERVICE BULLETIN 747-30-2081
Variable Number Group

RD571 1

RD581 - RD583 1

RD591 - RD593 1

RD601 - RD607 1

RD621 - RD623 1

RD641 - RD649 1

RD651 - RD658 1

RD659 2

RD661 1

RD671 1

RD681 - RD682 1

RD691 - RD692 1

RD701 - RD702 1

RD721 - RD722 1

RD741 - RD742 1

RD751 - RD753 1

RD754 - RD755 2

RD761 1

RD771 1

RD772 - RD775 2

RD781 - RD783 2

RD791 - RD792 2

RE001 1

RF001 - RF006 8

RG008 - RG009 1

RG091 1

RG095 1

RG101 - RG104 1

RG122 - RG123 1

RG125 1

RG141 - RG142 1

RG161 - RG164 1

RG171 - RG174 1

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BOEING SERVICE BULLETIN 747-30-2081
Variable Number Group

RG191 1

RG193 1

RG213 1

RG221 - RG222 1

RH101 1

RH102 2

RH121 - RH122 1

RJ131 - RJ133 1

RJ151 - RJ152 1

RJ301 - RJ303 1

RJ321 - RJ322 2

RJ331 - RJ333 1

RL401 - RL403 7

RL411 - RL426 7

RL431 - RL434 7

RL451 - RL453 7

RL461 - RL462 7

RL651 - RL655 7

RL671 - RL674 7

RL681 - RL683 7

RL751 - RL752 7

RM001 - RM007 8

RM010 - RM013 8

RM021 - RM024 8

RM026 - RM030 8

RM036 - RM045 8

RM051 - RM053 8

RM071 8

RM081 - RM084 8

RM091 8

RM096 - RM097 8

RM116 - RM117 8

RM126 - RM132 8

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Variable Number Group

RM136 - RM147 8

RM156 - RM158 8

RM166 - RM177 8

RM191 - RM192 8

RM231 - RM233 8

RM241 - RM246 8

RM261 - RM264 8

RM316 - RM318 8

RM331 - RM333 8

RM341 8

RM351 - RM355 8

RM366 - RM367 8

RM401 - RM403 8

RM426 8

RM431 8

RM441 - RM442 8

RM801 - RM803 8

RM811 - RM813 8

RM851 - RM859 7

RM861 - RM862 7

RM871 - RM888 7

RM891 - RM899 7

RM901 - RM906 7

RM911 7

RR001 - RR005 1

RR021 - RR023 1

RR024 - RR025 2

RR031 1

RR201 - RR203 1

RR204 - RR206 2

RR221 - RR226 1

RR261 - RR265 1

RR266 - RR267 2

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Variable Number Group

RR301 - RR306 1

RR307 - RR310 2

RR331 - RR332 1

RR336 1

RR341 - RR345 1

RR361 - RR362 1

RR421 - RR422 1

RR431 - RR432 2

RR441 - RR442 2

RR451 2

RR501 - RR504 1

RR521 1

RR522 2

RR526 2

RR531 1

RR551 - RR556 2

RR561 1

RR566 2

RR701 7

RR721 - RR724 7

RR746 - RR748 7

RR851 - RR856 7

RR861 - RR862 7

RR951 - RR952 7

RS001 - RS002 2

RS201 1

RS211 - RS212 1

RS221 - RS222 1

RS231 - RS233 1

RS234 - RS241 2

RS251 - RS252 1

RS253 - RS259 2

RS263 2

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Variable Number Group

RS265 - RS268 2

RS271 - RS276 2

RS291 - RS292 2

RS301 - RS306 2

RS311 - RS320 2

RS331 - RS333 2

RS341 - RS342 2

RS699 2

RS701 - RS702 1

RS703 2

RS711 1

RS712 - RS713 2

RS721 - RS722 2

RS731 - RS732 2

RS741 - RS743 2

RS751 - RS752 1

RS761 - RS762 2

RS771 2

RS781 - RS782 2

RS786 2

RT001 - RT014 8

RT021 - RT022 8

RT031 - RT035 8

RT041 - RT047 8

RT061 8

RT071 - RT075 8

RT101 - RT103 8

RT121 8

RT131 - RT137 8

RT151 - RT152 8

RT161 - RT168 8

RT401 - RT412 8

RT431 - RT447 8

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Variable Number Group

RT451 - RT469 8

RT471 - RT499 8

RT501 - RT535 8

RT551 - RT568 8

RT571 - RT591 8

RT601 - RT657 8

RT671 - RT673 8

RT681 - RT682 8

RT691 - RT699 8

RT701 - RT704 8

RT711 - RT717 8

RT741 - RT757 8

RT776 - RT777 8

RT781 - RT784 8

RT801 - RT803 8

RT811 - RT814 8

RT831 - RT837 8

RT861 - RT864 8

RT876 - RT880 8

RT931 - RT932 8

RT945 - RT949 8

RT951 - RT955 8

RT966 - RT967 8

RU001 - RU006 8

RU016 - RU017 8

RU031 - RU032 8

RU051 - RU052 8

RU059 - RU062 8

RU081 - RU083 8

RU101 - RU102 8

RU121 - RU132 8

RU801 - RU809 8

RU831 - RU841 8

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BOEING SERVICE BULLETIN 747-30-2081
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., Parts

Necessary for Each Airplane for the recommended use.

B. Concurrent Requirements

None

C. Reason

This service bulletin gives instructions to do a detailed inspection of an electrical connection on the left

and the right windshields. Instructions are also given to replace the windshields and make changes to

their related wire bundles. A new windshield design 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 windshields. 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 block and

tightened a loose connector. The terminal block 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 connectors on the windshields are attached with screws. The windshield is the number

1 window in the flight compartment. All of the windows in the flight compartment are electrically heated.

The windshield gets a much larger electrical load.

An investigation found that the cause of the electrical arcs was a loose connector. A loose connection

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

solder joints are the primary cause for the electrical arcs. The primary cause of a loose connector is

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

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

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

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

it. If a connector 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 windshields 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) 747-SRP-56-0015 is related to this service bulletin.

Revision 1 was sent to add more airplanes to the effectivity. The 747-SP and SR models were omitted

in the initial release. This revision will also give more windshield options. New kits are included that

give the operators the choice between one of two suppliers for the windshields or no preference for

supplier. This will give the operators the option to order kits which are not vendor specific so that either

windshield may be in a kit when the speed of delivery is important.

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Revision 2 was sent to change the circuit breaker tables for Groups 7-8. Also the text in footnote (d)

has been changed and a new footnote (e) has been added to the step tables in FIGURE 1 and FIGURE

2.

Revision 3 is sent to add FAA Notice of Proposed Rule Making and new data to FIGURE 1 and FIGURE

2 of the service bulletin.

D. Description

In the flight compartment, a detailed inspection is done of the left and the right windshields. The bulb

seal on the glare shield is cut to give clearance for terminal block that are on the new windshield. A

windshield that uses pin and socket electrical connections is installed. When a windshield that uses

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

The changes in this service bulletin will not change the Engine Indication and Crew Alerting System

(EICAS).

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of

this service bulletin.

Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue

and Revision 1 of this service bulletin.

Revision 3 - No more work is necessary on airplanes changed in accordance with the original issue or

Revision 1 or Revision 2 of this service bulletin.

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

Group 1:

Affected Maintenance Zones

Model Zone

747-100, 747-100B, 747-200B, 221, 222

747-200C, 747-200F, 747-300,

747SP, 747SR

Group 2:

Affected Maintenance Zones

Model Zone

747-100B, 747-100B SUD, 747- 221, 222

200B, 747-200C, 747-200F,

747-300, 747SP

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BOEING SERVICE BULLETIN 747-30-2081
Group 3, 5:

Affected Maintenance Zones

Model Zone

747-100 221, 222

Group 4, 6:

Affected Maintenance Zones

Model Zone

747-100, 747-200B 221, 222

Group 7:

Affected Maintenance Zones

Model Zone

747-400F 221, 222

Group 8:

Affected Maintenance Zones

Model Zone

747-400, 747-400D 221, 222

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-221-AD, is

related to this service bulletin.

Compliance Table: 1

Repeat Interval

(Whichever Occurs

Later)

Compliance Time

(Whichever Occurs First)

Condition Action

Terminating action for

this bulletin.

Replace with windshield that ----

uses pins and sockets for window heat power connection in

accordance with Accomplishment Instructions Work Packages 3 and 4.

Windshield that uses

screws and connectors

for window heat power

connection.

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BOEING SERVICE BULLETIN 747-30-2081
Compliance Table: 1

Repeat Interval

(Whichever Occurs

Later)

Compliance Time

(Whichever Occurs First)

Condition Action

Every 6000 flight

hours or 24 months

until windshield is replaced with windshield

that uses pins and

sockets for the window heat power connection in accordance

with Accomplishment

Instructions Work

Packages 3 and 4.

Within 500 flight hours or 150

days after the Revision 3 date

of this service bulletin.

Do the actions that follow for

the "A" terminal window heat

power connection:

1. Inspect the shipside wiring

and connector (including cover), look for signs of melted or

discolored insulation.

2. Inspect the window terminal

blocks, look for signs of melting, distortion or cracking.

3. Inspect the window heat

power connection for evidence

of cross threading by making

sure the connector is parallel

with the window terminal

block.

PPG Windshield that uses screws and connectors for window heat

power connection.

4. Inspect the connector for

looseness.

5. Address the inspection

findings as described in Inspection Conditions 1 thru 4.

Every 12,000 flight

hours or 48 months

until windshield is replaced with windshield

that uses pins and

sockets for window

heat power connection

in accordance with

Accomplishment Instructions Work Packages 3 and 4.

Within 500 flight hours or 150

days, after the Revision 3

date of this service bulletin.

Do the actions that follow for

the "A" terminal window heat

power connection:

1. Inspect the shipside wiring

and connector (including cover), look for signs of melted or

discolored insulation.

2. Inspect the window terminal

blocks, look for signs of melting, distortion or cracking.

3. Inspect the window heat

power connection for evidence

of cross threading by making

sure the connector is parallel

with the window terminal

block.

GKN Windshield that uses screws and connectors for window heat

power connection.

4. Inspect the connector for

looseness.

5. Address the inspection

findings as described in Inspection Conditions 1 thru 4.

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Compliance Table: 1

Repeat Interval

(Whichever Occurs

Later)

Compliance Time

(Whichever Occurs First)

Condition Action

1. Repair or replace shipside Before further flight. ----

wiring as necessary. Refer to

Standard Wiring Practices

Manual SWPM 20-10-13 as

an accepted procedure.

Inspection Condition 1 -

If the inspection reveals

one or more signs of the

following:

1. Melted shipside wire

insulation. 2. If the connector has melted,

replace the shipside connector

and windshield in accordance

with Work Package 1, step 3,

or Work Package 2, step 3; as

applicable.

2. Discolored shipside

wire insulation.

3. Melted connector.

4. Melted cover.

1. Replace windshield in accor- Before further flight. ----

dance with Work Package 1,

step 3 or Work Package 2,

step 3; as applicable.

Inspection Condition 2 -

If the inspection reveals

one or more signs of the

following:

1. Melted window terminal block.

2. Distorted or cracked

window terminal block.

1. Inspect the connector for Before further flight. ----

looseness. If the cross threaded terminal is loose: torque the

terminal screw to 25-30 in-lb.

Inspection Condition 3 -

If the inspection reveals

evidence the window

heat power connection is

cross threaded. 2. Re-inspect connector for

looseness.

3. If connector is still loose replace windshield in accordance with Work Package 1,

step 3, or Work Package 2,

step 3; as applicable.

Within 150 days or 500 flight ----

hours after the inspection.

4. If connector is tight, replace

windshield in accordance with

Work Package 1, step 3, or

Work Package 2, step 3; as

applicable.

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Compliance Table: 1

Repeat Interval

(Whichever Occurs

Later)

Compliance Time

(Whichever Occurs First)

Condition Action

1. Torque the terminal screw Before further flight. ----

to 25-30 in-lb.

Inspection Condition 4 -

If the inspection reveals

the connector is loose. 2. Re-inspect connector for

looseness.

3. If connector is still loose

then disassemble, inspect and

reassemble the electrical connection in accordance with

Work Package 1, step 3 or

Work Package 2, step 3; as

applicable.

Within 150 days or 500 flight ----

hours, after reassembly of the

windshield heat power connection. (a)

Do a detailed inspection and

corrective actions if necessary,

in accordance with Work

Package 1, step 3 or Work

Package 2, step 3; as applicable.

Window heat power connection is reassembled

(on windshields that uses

screws and connectors

for window heat power

connection).

OR

If the windshield is replaced with same type

windshield that uses

screws and connectors

for window heat power

connection.

(a) The initial inspection after installing a new windshield or a new connector screw is to verify that the window

heat power connection is correctly made. An improperly installed screw (under torqued or cross threaded)

can be identified regardless of the time since installation. If a screw is properly installed and torqued, there

is no evidence that it will loosen over time. The inspection steps outlined in this service bulletin should be

followed. Refer to either condition "Windshield heat power connection is reassembled" or "windshield is

replaced with same type windshield" in the Compliance Table for inspection requirements.

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.

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BOEING SERVICE BULLETIN 747-30-2081
G. Manpower

The table below shows an estimate of the task-hours necessary to do this inspection or change one

window 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 - Detailed Inspection of the Left Windshield

Task Number of Persons Task-Hours Elapsed Hours

FIGURE 1 1 0.25 0.25

Total per Windshield 0.25 0.25

Work Package 2 - Detailed Inspection of the RIght Windshield

Task Number of Persons Task-Hours Elapsed Hours

FIGURE 2 1 0.25 0.25

Total per Windshield 0.25 0.25

Group 1-6:

Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring

Task Number of Persons Task-Hours Elapsed Hours

Access 2 1.0 0.5

Remove the Left Windshield 2 2.5 1.25

Change the Wiring 1 1.25 1.25

Install the Left Windshield 2 3.0 1.5

Tests 1 0.25 0.25

Close 2 1.0 0.5

Total per Windshield 9.0 5.25

Group 7-8:

Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring

Task Number of Persons Task-Hours Elapsed Hours

Access 2 1.0 0.5

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BOEING SERVICE BULLETIN 747-30-2081
Group 7-8:

Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring

Task Number of Persons Task-Hours Elapsed Hours

Remove the Left Windshield 2 2.5 1.25

Change the Wiring 1 1.25 1.25

Install the Left Windshield 2 3.0 1.5

Tests 1 0.25 0.25

Close 2 1.0 0.5

Total per Windshield 9.0 5.25

Group 1-6:

Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring

Task Number of Persons Task-Hours Elapsed Hours

Access 2 1.0 0.5

Remove the Right Windshield 2 2.5 1.25

Change the Wiring 1 1.25 1.25

Install the Right Windshield 2 3.0 1.5

Tests 1 0.25 0.25

Close 2 1.0 0.5

Total per Windshield 9.0 5.25

Group 7-8:

Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring

Task Number of Persons Task-Hours Elapsed Hours

Access 2 1.0 0.5

Remove the Right Windshield 2 2.5 1.25

Change the Wiring 1 1.25 1.25

Install the Right Windshield 2 3.0 1.5

Tests 1 0.25 0.25

Close 2 1.0 0.5

Total per Windshield 9.0 5.25

H. Weight and Balance Changes

None

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BOEING SERVICE BULLETIN 747-30-2081
I. Electrical Load Data

Not applicable - 747-100/-200/-300

Not changed - 747-400

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85639, PRR 85901-49S

b. Boeing Service Related Problem (SRP) 747-SRP-56-0015

c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2010-NM-221-AD

d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-19, 20-30-12,

20-30-16, 20-64-16, 20-64-18

e. 747-100/200/300 Aircraft Maintenance Manual (AMM) 25-13-01, 30-41-00, 56-11-01

f. 747-100/200/300 Structural Repair Manual (SRM) 51

g. 747-100/200/300 Wiring Diagram Manual (WDM) 30-41-11, 30-41-12

h. 747-400 Aircraft Maintenance Manual (AMM) 25-13-01, 30-41-00, 56-11-01

i. 747-400 Structural Repair Manual (SRM) 51

j. 747-400 Wiring Diagram Manual (WDM) 30-41-11, 30-41-12

2. Data supplied with this Service Bulletin:

None.

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

None

K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Maintenance Manual 30-41, 56-11

747 Wiring Diagram Manual 30-41

747 Fault Isolation Manual 30-41

747 Illustrated Parts Catalog 56-11

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BOEING SERVICE BULLETIN 747-30-2081
2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated 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

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

information.

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BOEING SERVICE BULLETIN 747-30-2081

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 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Top Kit Number Name

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (a)

015U1784-1

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (a)

015U1784-2

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (a)

015U1784-3

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (a)

015U1784-4

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (a)

015U1784-5

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (a)

015U1784-6

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (b)

015U1784-7

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (b)

015U1784-8

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (b)

015U1784-9

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (b)

015U1784-10

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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 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Top Kit Number Name

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (b)

015U1784-11

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (b)

015U1784-12

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (c)

015U1784-13

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (c)

015U1784-14

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (c)

015U1784-15

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (c)

015U1784-16

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (c)

015U1784-17

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (c)

015U1784-18

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (d)

015U1784-19

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (d)

015U1784-20

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (d)

015U1784-21

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (d)

015U1784-22

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (d)

015U1784-23

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (d)

015U1784-24

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (e)

015U1784-25

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

34 of 100

BOEING SERVICE BULLETIN 747-30-2081
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 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Top Kit Number Name

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,GKN (e)

015U1784-26

Top Kit, Left Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (e)

015U1784-27

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,PPG (e)

015U1784-28

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (e)

015U1784-29

Top Kit, Right Windshield and Window Heat 200 $20,147.00

Terminal Replacement,No windshield preference (e)

015U1784-30

Top Kit - Left and Right Window Heat Wiring 200 $1,300.00

- No Windshield (a) (f)

015U1784-31

Top Kit - Left and Right Window Heat Wiring 200 $1,300.00

- No Windshield (b) (f)

015U1784-32

Top Kit - Left and Right Window Heat Wiring 200 $1,302.00

- No Windshield (c) (f)

015U1784-33

Top Kit - Left and Right Window Heat Wiring 200 $698.00

- No Windshield (d) (f)

015U1784-34

Top Kit - Left and Right Window Heat Wiring 200 $698.00

- No Windshield (e) (f)

015U1784-35

(a) Airplane Groups 1, 4, 5, 6

(b) Group 2 Airplanes

(c) Group 3 Airplanes

(d) Group 7 Airplanes

(e) Group 8 Airplanes

(f) These kits contain the wiring for both the left and the right window heat wiring changes, but no windshield.

A top kit with the windshield contains the wire kit for that position. This kit is for operators who obtain their

windshields from another source.

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.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

35 of 100

BOEING SERVICE BULLETIN 747-30-2081
NOTE: One left top kit and one right top kit, each with a windshield, are necessary for each airplane.

As an alternative, a top kit with wiring only and a left and a right windshield shown in Paragraph

2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.

Operators who supply their own windshields can order the top kits that include the necessary

wiring for both the left and the right sides, but no windshields.

All the windshields in the top kits are hydrophobic coated. Operators who choose to use

uncoated windshields should order the wiring-only top kits and refer to Paragraph 2.C.2., Parts

and Materials Supplied by the Operator, for the part numbers of approved uncoated

windshields.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes or the inspection given in

this service bulletin.

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.

Group 1, 4-6:

Kit 015U1784

Existing Part Num- Notes

ber

New Part Num- QTY Name

ber -6 -5 -4 -3 -2 -1

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-1 . . . . . -

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-2 . . . . - .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-3 . . . - . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-4 . . - . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

36 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 1, 4-6:

Kit 015U1784

Existing Part Num- Notes

ber

New Part Num- QTY Name

ber -6 -5 -4 -3 -2 -1

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-5 . - . . . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-6 - . . . . .

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ), 06302,

06322, 06332, 06342,

06362, 06372, 06382,

NP-103801-( )

Windshield Assembly, Pilot - Coated141U4800-13 . 1 . . . 1

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ), 06303,

06323, 06333, 06343,

06363, 06373, 06383,

NP-103801-( )

Windshield Assembly, Co-Pilot -

Coated

141U4800-14 1 . . . 1 .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

61B20558-1 . 1 . 1 . 1

Wire Kit - Flight

Deck Window Heat

Redesign - Right

61B20558-2 1 . 1 . 1 .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ), 06302,

06322, 06332, 06342,

06362, 06372, 06382,

NP-103801-( )

Windshield Assembly, Pilot - CoatedNP-103801-117 . . . 1 . .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ), 06303,

06323, 06333, 06343,

06363, 06373, 06383,

NP-103801-( )

Windshield Assembly, Co-Pilot -

Coated

NP-103801-118 . . 1 . . .

(a) Discard the existing windshield if it fails the inspection. Keep the windshield if it passed inspection and

there are other airplanes in your fleet that can use it.

(b) This part is not used in production.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

37 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 1, 4-6:

Kit 015U1784

Existing Part Num- Notes

ber

New Part Num- QTY Name

ber -6 -5 -4 -3 -2 -1

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

(d) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004 Huntsville AL 35811 USA

(e) All of the windshields included in the top kits have a hydrophobic coating. Operators who prefer a noncoated windshield can use the information given in Paragraph 2.C.2., Parts and Materials Supplied by

the Operators to order windshields with no hydrophobic coating.

(f) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western Ave Garden Grove CA 92841 USA

Group 2:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -12 -11 -10 -9 -8 -7

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-7 . . . . . -

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-8 . . . . - .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-9 . . . - . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-10 . . - . . .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-11 . - . . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

38 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 2:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -12 -11 -10 -9 -8 -7

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-12 - . . . . .

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - Coated141U4800-13 . 1 . . . 1

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

141U4800-14 1 . . . 1 .

Wire Kit - Flight

Deck Window

Heat Redesign -

Left

61B20558-5 . 1 . 1 . 1

Wire Kit - Flight

Deck Window

Heat Redesign -

Right

61B20558-6 1 . 1 . 1 .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - CoatedNP-103801-117 . . . 1 . .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

NP-103801-118 . . 1 . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

39 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 2:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -12 -11 -10 -9 -8 -7

(a) Discard the existing windshield if it fails the inspection. Keep the windshield if it passed inspection

and there are other airplanes in your fleet that can use it

(b) This part is not used in production.

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

(d) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004 Huntsville AL 35811 USA

(e) All of the windshields included in the top kits have a hydrophobic coating. Operators who prefer

a non-coated windshield can use the information given in Paragraph 2.C.2., Parts and Materials

Supplied by the Operators to order windshields with no hydrophobic coating.

(f) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western Ave Garden Grove CA

92841 USA

Group 3:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -18 -17 -16 -15 -14 -13

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-13 . . . . . -

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-14 . . . . - .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-15 . . . - . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-16 . . - . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

40 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 3:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -18 -17 -16 -15 -14 -13

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-17 . - . . . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-18 - . . . . .

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - Coated141U4800-13 . 1 . . . 1

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

141U4800-14 1 . . . 1 .

Wire Kit - Flight

Deck Window

Heat Redesign -

Left

61B20558-7 . 1 . 1 . 1

Wire Kit - Flight

Deck Window

Heat Redesign -

Right

61B20558-8 1 . 1 . 1 .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - CoatedNP-103801-117 . . . 1 . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

41 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 3:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -18 -17 -16 -15 -14 -13

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

NP-103801-118 . . 1 . . .

(a) Discard the existing windshield if it fails the inspection. Keep the windshield if it passed inspection

and there are other airplanes in your fleet that can use it.

(b) This part is not used in production.

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

(d) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004 Huntsville AL 35811 USA

(e) All of the windshields included in the top kits have a hydrophobic coating. Operators who prefer a

non-coated windshield can use the information given in Paragraph 2.C.2., Parts and Materials

Supplied by the Operators to order windshields with no hydrophobic coating.

(f) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western Ave Garden Grove CA

92841 USA

Group 7:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -24 -23 -22 -21 -20 -19

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-19 . . . . . -

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-20 . . . . - .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-21 . . . - . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

42 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 7:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -24 -23 -22 -21 -20 -19

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-22 . . - . . .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-23 . - . . . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-24 - . . . . .

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - Coated141U4800-13 . 1 . . . 1

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

141U4800-14 1 . . . 1 .

Wire Kit - Flight

Deck Window

Heat Redesign -

Left

289U1215-1 . 1 . 1 . 1

Wire Kit - Flight

Deck Window

Heat Redesign -

Right

289U1215-2 1 . 1 . 1 .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

43 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 7:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -24 -23 -22 -21 -20 -19

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - CoatedNP-103801-117 . . . 1 . .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

NP-103801-118 . . 1 . . .

(a) Discard the existing windshield if it fails the inspection. Keep the windshield if it passed inspection

and there are other airplanes in your fleet that can use it

(b) This part is not used in production.

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

(d) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004 Huntsville AL 35811 USA

(e) All of the windshields included in the top kits have a hydrophobic coating. Operators who prefer

a non-coated windshield can use the information given in Paragraph 2.C.2., Parts and Materials

Supplied by the Operators to order windshields with no hydrophobic coating.

(f) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western Ave Garden Grove CA

92841 USA

Group 8:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -30 -29 -28 -27 -26 -25

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-25 . . . . . -

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

44 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 8:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -30 -29 -28 -27 -26 -25

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - GKN

015U1784-26 . . . . - .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-27 . . . - . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - PPG

015U1784-28 . . - . . .

Top Kit - Left

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-29 . - . . . .

Top Kit - Right

Windshield and

Window Heat Terminal Replacement - No Windshield Preference

015U1784-30 - . . . . .

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - Coated141U4800-13 . 1 . . . 1

(a) (b)

(c) (e)

(f)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

141U4800-14 1 . . . 1 .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

45 of 100

BOEING SERVICE BULLETIN 747-30-2081
Group 8:

Kit 015U1784

Existing Part Notes

Number

New Part Num- QTY Name

ber -30 -29 -28 -27 -26 -25

Wire Kit - Flight

Deck Window

Heat Redesign -

Left

289U1215-3 . 1 . 1 . 1

Wire Kit - Flight

Deck Window

Heat Redesign -

Right

289U1215-4 1 . 1 . 1 .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06302, 06322,

06332, 06342,

06362, 06372,

06382, NP103801-( )

Windshield Assembly, Pilot - CoatedNP-103801-117 . . . 1 . .

(a) (b)

(c) (d)

(e)

65B07638-( ),

60B10028-( ),

06303, 06323,

06333, 06343,

06363, 06373,

06383, NP103801-( )

Windshield Assembly, Co-Pilot -

Coated

NP-103801-118 . . 1 . . .

(a) Discard the existing windshield if it fails the inspection. Keep the windshield if it passed inspection

and there are other airplanes in your fleet that can use it.

(b) This part is not used in production.

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

(d) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004 Huntsville AL 35811 USA

(e) All of the windshields included in the top kits have a hydrophobic coating. Operators who prefer

a non-coated windshield can use the information given in Paragraph 2.C.2., Parts and Materials

Supplied by the Operators to order windshields with no hydrophobic coating.

(f) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western Ave Garden Grove CA

92841 USA

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

46 of 100

BOEING SERVICE BULLETIN 747-30-2081
Kit 015U1784 - Top Kit

Existing Part Notes

Number

New Part Num- QTY Name

ber -35 -34 -33 -32 -31

Top Kit - Left and

Right Window Heat

Wiring - No Windshield

015U1784-31 . . . . -

Top Kit - Left and

Right Window Heat

Wiring - No Windshield

015U1784-32 . . . - .

Top Kit - Left and

Right Window Heat

Wiring - No Windshield

015U1784-33 . . - . .

Top Kit - Left and

Right Window Heat

Wiring - No Windshield

015U1784-34 . - . . .

Top Kit - Left and

Right Window Heat

Wiring - No Windshield

015U1784-35 - . . . .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

289U1215-1 . 1 . . .

Wire Kit - Flight

Deck Window Heat

Redesign - Right

289U1215-2 . 1 . . .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

289U1215-3 1 . . . .

Wire Kit - Flight

Deck Window Heat

Redesign - Right

289U1215-4 1 . . . .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

61B20558-1 . . . . 1

Wire Kit - Flight

Deck Window Heat

Redesign - Right

61B20558-2 . . . . 1

Wire Kit - Flight

Deck Window Heat

Redesign - Left

61B20558-5 . . . 1 .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3: December 05, 2011 747-30-2081

47 of 100

BOEING SERVICE BULLETIN 747-30-2081
Kit 015U1784 - Top Kit

Existing Part Notes

Number

New Part Num- QTY Name

ber -35 -34 -33 -32 -31

Wire Kit - Flight

Deck Window Heat

Redesign - Right

61B20558-6 . . . 1 .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

61B20558-7 . . 1 . .

Wire Kit - Flight

Deck Window Heat

Redesign - Right

61B20558-8 . . 1 . .

Kit 289U1215 - Wire Kit

New Part Number QTY Name Notes

-4 -3 -2 -1

Wire Kit -Flight Deck

Window Heat Redesign - Left

289U1215-1 . . . -

Wire Kit -Flight Deck

Window Heat Redesign - Right

289U1215-2 . . - .

Wire Kit - Flight

Deck Window Heat

Redesign - Left

289U1215-3 . - . .

Wire Kit - Flight

Deck Window Heat

Redesign - Right

289U1215-4 - . . .

289U1215-101 . . . 1 Subkit - W4495 (a)

289U1215-102 . . 1 . Subkit - W4496 (a)

289U1215-103 . 1 . . Subkit - W4497 (a)

289U1215-104 1 . . . Subkit - W4498 (a)

(a) There are more parts than necessary.

Kit 289U1215 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-104 -103 -102 -101

289U1215-101 . . . - Subkit - W4495

289U1215-102 . . - . Subkit - W4496

289U1215-103 . - . . Subkit - W4497

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Kit 289U1215 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-104 -103 -102 -101

289U1215-104 - . . . Subkit - W4498

- . . . 1 Wire Identified W4495-001-12 (a)

- . . . 1 Wire Identified W4495-002-12 (a)

- . . 1 . Wire Identified W4496-002-12 (a)

- . . 1 . Wire Identified W4496-001-12 (a)

- . 1 . . Wire Identified W4497-001-12 (a)

- . 1 . . Wire Identified W4497-002-12 (a)

- 1 . . . Wire Identified W4498-002-12 (a)

- 1 . . . Wire Identified W4498-001-12 (a)

BACS38K5B . 10 . 10 Strap

BACS38K5E 10 . 10 . Strap

D-436-38 3 3 3 3 Splice

M39029/57-359 3 3 3 3 Socket Contact

NA728R99 1 1 1 1 BMS 13-52 Expandable Sleeve

(a) BMS 13-48, Type 10, Class 1, AWG 12, length 78 inches.

Kit 61B20558 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-8 -7 -6 -5 -2 -1

Wire Kit - Flight (a)

Deck Window Heat

- Left

61B20558-1 . . . . . -

Wire Kit - Flight (a)

Deck Window Heat

- Right

61B20558-2 . . . . - .

Wire Kit - Flight (a)

Deck Window Heat

- Left

61B20558-5 . . . - . .

Wire Kit - Flight (a)

Deck Window Heat

- Right

61B20558-6 . . - . . .

Wire Kit - Flight (a)

Deck Window Heat

- Left

61B20558-7 . - . . . .

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Kit 61B20558 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-8 -7 -6 -5 -2 -1

Wire Kit - Flight (a)

Deck Window Heat

- Right

61B20558-8 - . . . . .

Subkit -

W1372,W344

61B20558-101 . . . . . 1

Subkit -

W1548,W342

61B20558-102 . . . . 1 .

Subkit -

W1372,W344

61B20558-105 . . . 1 . .

Subkit -

W1548,W342

61B20558-106 . . 1 . . .

Subkit -

W1372,W344

61B20558-107 . 1 . . . .

Subkit -

W1548,W342

61B20558-108 1 . . . . .

(a) There are more parts than are necessary.

Kit 61B20558 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-108 -107 -106 -105 -102 -101

Subkit -

W1372,W344

61B20558-101 . . . . . -

Subkit -

W1548,W342

61B20558-102 . . . . - .

Subkit -

W1372,W344

61B20558-105 . . . - . .

Subkit -

W1548,W342

61B20558-106 . . - . . .

Subkit -

W1548,W342

61B20558-107 . - . . . .

Subkit -

W1548,W342

61B20558-108 - . . . . .

Wire Identified (a)

W342-H106-24R

- 1 . 1 . 1 .

Wire Identified (a)

W342-H107-24B

- 1 . 1 . 1 .

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Kit 61B20558 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-108 -107 -106 -105 -102 -101

Wire Identified (a)

W342-H108-24R

- 1 . 1 . 1 .

Wire Identified (a)

W342-H109-24B

- 1 . 1 . 1 .

Wire Identified (a)

W344-H99-24R

- . 1 . 1 . 1

Wire Identified (a)

W344-H100-24B

- . 1 . 1 . 1

Wire Identified (a)

W344-H101-24R

- . 1 . 1 . 1

Wire Identified (a)

W344-H102-24B

- . 1 . 1 . 1

Wire Identified (c)

W1372-H104-12R

- . . . 1 . .

Wire Identified (c)

W1372-H105-12B

- . . . 1 . .

Wire Identified (b)

W1372-H104-12

- . 1 . . . 1

Wire Identified (b)

W1372-H105-12

- . 1 . . . 1

Wire Identified (b)

W1548-H111-12

- 1 . . . 1 .

Wire Identified (b)

W1548-H112-12

- 1 . . . 1 .

Wire Identified (b)

W1548-H111-12R

- . . 1 . . .

Wire Identified (b)

W1548-H112-12B

- . . 1 . . .

61B20558-10101 . 3 . 3 . 3 Identification Tape (d)

61B20558-10102 . 3 . 3 . 3 Identification Tape (d)

61B20558-10201 3 . 3 . 3 . Identification Tape (d)

61B20558-10202 3 . 3 . 3 . Identification Tape (d)

61B20558-10501 . . . 3 . . Identification Tape

61B20558-10601 . . 3 . . . Identification Tape

BACT12AR222 5 5 5 5 5 5 Terminal (d)

324484 3 3 . . . . Terminal

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Kit 61B20558 - Wire Kit - Flight Deck Window Heat

New Part Number QTY Name Notes

-108 -107 -106 -105 -102 -101

D-436-38 3 3 3 3 3 3 Splice

D-150-0174 3 3 3 3 3 3 Splice (d)

M39029/57-359 3 3 3 3 3 3 Socket Contact

(a) BMS 13-48, Type 6, Class 2, AWG 24, length 12 inches

(b) BMS 13-48, Type 10, Class 1, AWG 12, length 12 inches

(c) BMS 13-48, Type 10, Class 2, AWG 12, length 12 inches

(d) This part is not used.

2. Parts and Materials Supplied by the Operator:

Part Number / Speci- QTY Name Notes

fication

30 Lacing Tape (a) (b)

feet

BMS 13-54, Type 3,

Class 1, Color White

(a) Gudebrod Incorporated (82110) Griffith Towers P.O. Box 357 Pottstown, PA 19464

(b) BACS38K5 Tie Strap is optional. See the Qualified Products List at the end of the Boeing

Material Specification (BMS) for supplier data.

NOTE: The information given here is only for operators who choose to install windshields without

a hydrophobic coating. These windshields are not available in top kits from Boeing but

are fully interchangeable with the new windshields.

Part Number QTY Name Notes

NP-103801-115 1 Windshield, Left, uncoated, PPG (a)

NP-103801-116 1 Windshield, Right, uncoated, PPG (a)

13912 1 Windshield, Left, uncoated, GKN (b)

13913 1 Windshield, Right, uncoated, GKN (b)

(a) PPG Industries, Inc (53117) Aircraft Products Division PO Box 040004

Huntsville AL 35811 USA

(b) GKN Aerospace Transparency Systems (UK) (U1610) 12122 Western

Ave Garden Grove CA 92841 USA

3. Parts Modified and Reidentified:

None

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4. Parts Removed and Not Replaced:

None

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service

Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of

the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase

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

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

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MY BOEING FLEET.COM OR CONTACT FIRST

RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT)

AND PRICE INFORMATION

Purchase Data:

Unit Price as of

the Revision 03

date of this Service Bulletin (US

Dollars)

Tool Kit Number Name

20HME65B07630 Windshield Handling Sling $813

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.

Tool Kit Number Name

20HME65B07630 Windshield Handling Sling

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BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

3. 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

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

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

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

SRM Chapter 51.

6. 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.

7. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

8. 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.

9. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

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BOEING SERVICE BULLETIN 747-30-2081
10. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

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

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

B. WORK INSTRUCTIONS

WORK PACKAGE 1 - INSPECTION OF THE LEFT WINDSHIELD

Group 1-6:

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

CIRCUIT BREAKERS GIVEN IN THE STEP THAT FOLLOWS. IF THESE CIRCUIT

BREAKERS ARE NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK WHEN YOU

TOUCH THE TERMINAL.

1. Group 1-6:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1L C0335

P12 WINDOW HEAT CONT 1L C0439

P6 WINDOW HEAT POWER 1L C1503

Group 7-8:

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

THESE CIRCUIT BREAKERS GIVEN IN THE STEP THAT FOLLOWS. IF THESE

CIRCUIT BREAKERS ARE NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE TERMINAL.

2. Group 7-8:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Location Panel / Name Circuit Breaker

Position

P180 / H26 WINDOW HEAT CONT 1L C0439

P6-6 / B34 WINDOW HEAT POWER 1L C1503

3. Do a detailed inspection of the left windshield and corrective actions if necessary in accordance

with FIGURE 1.

4. Group 1-6:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1L C335

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Panel Name Circuit Breaker

P12 WINDOW HEAT CONT 1L C439

P6 WINDOW HEAT POWER 1L C1503

5. Group 7-8:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Location Panel / Name Circuit Breaker

Position

P180 / H26 WINDOW HEAT CONT 1L C0439

P6-6 / B34 WINDOW HEAT POWER 1L C1503

WORK PACKAGE 2 - INSPECTION OF THE RIGHT WINDSHIELD

Group 1-6:

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

THESE CIRCUIT BREAKERS GIVEN IN THE STEP THAT FOLLOWS. IF THESE

CIRCUIT BREAKERS ARE NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE TERMINAL.

1. Group 1-6:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1R C334

P12 WINDOW HEAT CONT 1R C435

P6 WINDOW HEAT POWER 1R C1504

Group 7-8:

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

THESE CIRCUIT BREAKERS GIVEN IN THE STEP THAT FOLLOWS. IF THESE

CIRCUIT BREAKERS ARE NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE TERMINAL.

2. Group 7-8:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Location Panel / Name Circuit Breaker

Position

P180 / H12 WINDOW HEAT CONT 1R C0435

P6-5 / B17 WINDOW HEAT POWER 1R C1504

3. Do detailed inspection of the right windshield and corrective actions if necessary in accordance

with FIGURE 2.

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4. Group 1-6:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1R C334

P12 WINDOW HEAT CONT 1R C435

P6 WINDOW HEAT POWER 1R C1504

5. Group 7-8:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Location Panel / Name Circuit Breaker

Position

P180 / H12 WINDOW HEAT CONT 1R C0435

P6-5 / B17 WINDOW HEAT POWER 1R C1504

WORK PACKAGE 3 - REPLACEMENT OF THE LEFT WINDSHIELD AND CHANGES TO THE

RELATED WIRE BUNDLE

Group 1-6:

WARNING: THE WINDOW HEAT SYSTEM MUST BE DISARMED WHEN YOU REMOVE THE

WINDOWS. IF THE WINDOW POWER IS ON, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE WINDOW. THE SHOCK CAN CAUSE INJURY TO PERSONS.

1. Group 1-6:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1L C0335

P12 WINDOW HEAT CONT 1L C0439

P6 WINDOW HEAT POWER 1L C1503

Group 7-8:

WARNING: THE WINDOW HEAT SYSTEM MUST BE DISARMED WHEN YOU REMOVE THE

WINDOWS. IF THE WINDOW POWER IS ON, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE WINDOW. THE SHOCK CAN CAUSE INJURY TO PERSONS.

2. Group 7-8:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Location Panel / Name Circuit Breaker

Position

P180 / H26 WINDOW HEAT CONT 1L C0439

P6-6 / B34 WINDOW HEAT POWER 1L C1503

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3. Remove the left windshield. Refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01

as an accepted procedure.

4. Group 1:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 3 and

FIGURE 11.

5. Group 2:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 4 and

FIGURE 11.

6. Group 3:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 5 and

FIGURE 11.

7. Group 4:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 6 and

FIGURE 11.

8. Group 5:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 7 and

FIGURE 11.

9. Group 6:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 8 and

FIGURE 11.

10. Group 7:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 9 and

FIGURE 12.

11. Group 8:

Change the wiring for the window heat on the left windshield in accordance with FIGURE 10 and

FIGURE 12.

12. Install the left windshield. Refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01 as

an accepted procedure. Use one of the windshields shown below:

Description Part Number Part of Top Kit

GKN Windshield with wiper ramp, pilot 141U4800-13 015U1784-1, -7, -13, -19, -25, -31

assist handle, and hydrophobic coating.

GKN Windshield with wiper ramp, pilot 13912 Obtained from supplier/vendor

assist handle. No hydrophobic coating.

PPG Windshield with wiper ramp, pilot NP-103801-117 015U1784-3, -9, -15, -21, -27, -33

assist handle, and hydrophobic coating.

PPG Windshield with wiper ramp and NP-103801-115 Obtained from supplier/vendor

pilot assist handle. No hydrophobic

coating

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13. Group 1-6:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1L C0335

P12 WINDOW HEAT CONT 1L C0439

P6 WINDOW HEAT POWER 1L C1503

14. Group 7-8:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Location Panel / Name Circuit Breaker

Position

P180 / H26 WINDOW HEAT CONT 1L C0439

P6-6 / B34 WINDOW HEAT POWER 1L C1503

15. Do the test "Operational Test - Flight Compartment Window Anti-Icing System." Refer to

747-100/200/300 AMM 30-41-00 or 747-400 AMM 30-41-00 as an accepted procedure.

16. Put the airplane in a serviceable condition.

WORK PACKAGE 4 - REPLACEMENT OF THE RIGHT WINDSHIELD AND CHANGES TO THE

RELATED WIRE BUNDLE

Group 1-6:

WARNING: THE WINDOW HEAT SYSTEM MUST BE DISARMED WHEN YOU REMOVE THE

WINDOWS. IF THE WINDOW POWER IS ON, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE WINDOW. THE SHOCK CAN CAUSE INJURY TO PERSONS.

1. Group 1-6:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1R C334

P12 WINDOW HEAT CONT 1R C435

P6 WINDOW HEAT POWER 1R C1504

Group 7-8:

WARNING: THE WINDOW HEAT SYSTEM MUST BE DISARMED WHEN YOU REMOVE THE

WINDOWS. IF THE WINDOW POWER IS ON, YOU CAN GET AN ELECTRICAL SHOCK

WHEN YOU TOUCH THE WINDOW. THE SHOCK CAN CAUSE INJURY TO PERSONS.

2. Group 7-8:

Open these circuit breakers and attach DO-NOT-CLOSE tags to them:

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Location Panel / Name Circuit Breaker

Position

P180 / H12 WINDOW HEAT CONT 1R C0435

P6-5 / B17 WINDOW HEAT POWER 1R C1504

3. Remove the right windshield. Refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01

as an accepted procedure.

4. Group 1:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 13 and

FIGURE 21.

5. Group 2:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 14 and

FIGURE 21.

6. Group 3:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 15 and

FIGURE 21.

7. Group 4:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 16 and

FIGURE 21.

8. Group 5:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 17 and

FIGURE 21.

9. Group 6:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 18 and

FIGURE 21.

10. Group 7:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 19 and

FIGURE 22.

11. Group 8:

Change the wiring for the window heat on the right windshield in accordance with FIGURE 20 and

FIGURE 22.

12. Install the right windshield. Refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01

as an accepted procedure. Use one of the windshields shown below:

Description Part Number Part of Top Kit

GKN Windshield with wiper ramp, pilot 141U4800-14 015U1784-2, -8, -14, -20, -26, -32

assist handle, and hydrophobic coating.

GKN Windshield with wiper ramp, pilot 13913 Obtained from supplier/vendor

assist handle. No hydrophobic coating.

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Description Part Number Part of Top Kit

PPG Windshield with wiper ramp, pilot NP-103801-118 015U1784-4, -10, -16, -22, -28, -34

assist handle, and hydrophobic coating.

PPG Windshield with wiper ramp and NP-103801-116 Obtained from supplier/vendor

pilot assist handle. No hydrophobic

coating

13. Group 1-6:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Panel Name Circuit Breaker

P6 WINDOW HEAT CONT 1R C334

P12 WINDOW HEAT CONT 1R C435

P6 WINDOW HEAT POWER 1R C1504

14. Group 7-8:

Remove the DO-NOT-CLOSE tags and close these circuit breakers:

Location Panel / Name Circuit Breaker

Position

P180 / H12 WINDOW HEAT CONT 1R C0435

P6-5 / B17 WINDOW HEAT POWER 1R C1504

15. Do the test "Operational Test - Flight Compartment Window Anti-Icing System." Refer to

747-100/200/300 AMM 30-41-00 or 747-400 AMM 30-41-00 as an accepted procedure.

16. Put the airplane in a serviceable condition.

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FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 1 OF 6)

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FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 2 OF 6)

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FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

at the "A" terminal.

(a)

1 Inspect Terminal Block - 1

Inspect Connector - 1 (b)

Inspect Wiring - 1 (c)

2 Remove / Keep Cover - 1

to make sure it is a

tight connection. (d)

(e) (f)

Inspect Connector - 1

not necessary if the

connector is loose.

(g)

Install (Kept) Cover - 1

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

FORCE. A DAMAGED TERMINAL BLOCK WILL REQUIRE THE REPLACEMENT OF THE

WINDSHIELD.

to 25 to 30 inch

pounds of torque.

Refer to SWPM 20-

64-16 as an accepted procedure (h) (i)

3 Torque Screw - 1

to make sure the

connection is tight.

Inspect Connector - 1

not necessary if the

connector cannot be

tightened.

Install (Kept) Cover - 1

to make sure the

screw is installed

correctly and there

is no damage to terminal or screw.

4 Remove Screw - 1

Remove Washer - 1

Remove O-ring - 1

Inspect Connector - 1 (j)

to make sure the

terminal block is not

damaged. (k)

Inspect Terminal Block - 1

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
Step Task Name Identification Qty More Data

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

FORCE. A DAMAGED TERMINAL BLOCK WILL REQUIRE THE REPLACEMENT OF THE

WINDSHIELD.

to make sure terminal is assembled

with new, undamaged and correct

hardware. (l) (m)

5 Install (New) Screw - 1

Install (New) Wiring - 1

Install (New) O-ring - 1 (n)

to 25 to 30 inch

pounds of torque.

Refer to SWPM 20-

64-16 as an accepted procedure. (o) (p)

Torque Screw - 1

Install (Kept) Cover - 1

(a) If the terminal block has melted, distorted or cracked, replace the windshield. Refer to 747-100/200/300

AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(b) If the connector or cover has melted, replace the shipside connector, refer to SWPM 20-64-16; and replace

the windshield, refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(c) If the shipside wire insulation is melted or discolored, then repair or replace shipside wiring as necessary.

Refer to SWPM 20-10-13 as an accepted procedure.

(d) If the connector at the terminal block moves more than 10 degrees with light pressure, then the screw

that attaches it must be tightened. There are four causes for a loose connector. 1-The screw is not tightened

to the correct torque. 2- The terminal block is damaged. 3- The incorrect screw is installed. The correct

screw part number is given in SWPM 20-64-16. 4-The screw is cross threaded.

(e) On PPG windshields only, the brass terminal insert of the terminal block is not held firmly inside the terminal block. On a tight connection, this will allow for a very small movement, approximately 1-3 degrees

of the shipside connector with light manual pressure - this is a normal condition.

(f) If the connector is installed correctly, is tight, and is parallel to the terminal block, install the cover. No

more work is necessary.

(g) If the connector is loose, do step 3.

(h) 1-The screw is only tightened if the connector is loose. 2-If it is necessary to tighten the screw, the lightshield

may need to be removed for access. Refer to 747-100/200/300 AMM 25-13-01 or 747-400 AMM 25-13-

01 as an accepted procedure. 3-If it is the correct screw and it cannot be tightened to 25 to 30 inch pounds,

do steps 4 and 5.

(i) If the cross threaded screw cannot be tightened, replace the windshield. Refer to 747-100/200/300 AMM

56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
Step Task Name Identification Qty More Data

(j) If the mating surface on the connector has contamination, clean the surface. Refer to SWPM 20-20-00

Cleaning Method 5 as an accepted procedure. If the connector cannot be cleaned or show signs of arcing,

blueing, overheating, pitting, corrosion, or other surface damage, replace the connector. Refer to SWPM

20-64-16 as an accepted procedure.

(k) If the terminal block mating surface has contamination, clean the surface. Refer to SWPM 20-20-00

Cleaning Method 5 as an accepted procedure. If the terminal block shows signs of arcing, blueing, overheating, pitting, corrosion, or other surface damage, replace the windshield. Refer to 747-100/200/300

AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(l) Reassemble the connector to the terminal block with a new screw, lock washer and o-ring. Make sure

the o-ring is installed prior to assemble of the connector to the terminal block.

(m) Make sure the screw has been aligned correctly.

(n) A new o-ring is only available for the CWC01-1210 connector. Refer to SWPM 20-64-16 for the correct

screw, washer and o-ring.

(o) Do step 2 to make sure the screw has been installed correctly and is a tight connection.

(p) If the screw has been installed correctly and it is not a tight connection, replace the windshield. Refer to

747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 1 OF 6)

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FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

at the "A" terminal.

(a)

1 Inspect Terminal Block - 1

Inspect Connector - 1 (b)

Inspect Wiring - 1 (c)

2 Remove / Keep Cover - 1

to make sure it is a

tight connection. (d)

(e) (f)

Inspect Connector - 1

not necessary if the

connector is loose.

(g)

Install (Kept) Cover - 1

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

FORCE. A DAMAGED TERMINAL BLOCK WILL REQUIRE THE REPLACEMENT OF THE

WINDSHIELD.

to 25 to 30 inch

pounds of torque.

Refer to SWPM 20-

64-16 as an accepted procedure (h) (i)

3 Torque Screw - 1

to make sure the

connection is tight.

Inspect Connector - 1

not necessary if the

connector cannot be

tightened

Install (Kept) Cover - 1

to make sure the

screw is installed

correctly and there

is no damage to terminal or screw.

4 Remove Screw - 1

Remove Washer - 1

Remove O-ring - 1

Inspect Connector - 1 (j)

to make sure the

terminal block is not

damaged.(k)

Inspect Terminal Block - 1

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
Step Task Name Identification Qty More Data

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

FORCE. A DAMAGED TERMINAL BLOCK WILL REQUIRE THE REPLACEMENT OF THE

WINDSHIELD.

to make sure terminal is assembled

with new, undamaged and correct

hardware. (l) (m)

5 Install (New) Screw - 1

Install (New) Wiring - 1

Install (New) O-ring - 1 (n)

to 25 to 30 inch

pounds of torque.

Refer to SWPM 20-

64-16 as an accepted procedure. (o) (p)

Torque Screw - 1

Install (Kept) Cover - 1

(a) If the terminal block has melted, distorted or cracked, replace the windshield. Refer to 747-100/200/300

AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(b) If the connector or cover has melted, replace the shipside connector, refer to SWPM 20-64-16; and replace

the windshield, refer to 747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(c) If the shipside wire insulation is melted or discolored, then repair or replace shipside wiring as necessary.

Refer to SWPM 20-10-13 as an accepted procedure.

(d) If the connector at the terminal block moves more than 10 degrees with light pressure, then the screw

that attaches it must be tightened. There are four causes for a loose connector. 1-The screw is not tightened

to the correct torque. 2- The terminal block is damaged. 3- The incorrect screw is installed. The correct

screw part number is given in SWPM 20-64-16. 4-The screw is cross threaded.

(e) On PPG windshields only, the brass terminal insert of the terminal block is not held firmly inside the terminal block. On a tight connection, this will allow for a very small movement, approximately 1-3 degrees

of the shipside connector with light manual pressure - this is a normal condition.

(f) If the connector is installed correctly, is tight, and is parallel to the terminal block, install the cover. No

more work is necessary.

(g) If the connector is loose, do step 3.

(h) 1-The screw is only tightened if the connector is loose. 2-If it is necessary to tighten the screw, the lightshield

may need to be removed for access. Refer to 747-100/200/300 AMM 25-13-01 or 747-400 AMM 25-13-

01 as an accepted procedure. 3-If it is the correct screw and it cannot be tightened to 25 to 30 inch pounds,

do steps 4 and 5.

(i) If the cross threaded screw cannot be tightened, replace the windshield. Refer to 747-100/200/300 AMM

56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
Step Task Name Identification Qty More Data

(j) If the mating surface on the connector has contamination, clean the surface. Refer to SWPM 20-20-00

Cleaning Method 5 as an accepted procedure. If the connector cannot be cleaned or show signs of arcing,

blueing, overheating, pitting, corrosion, or other surface damage, replace the connector. Refer to SWPM

20-64-16 as an accepted procedure.

(k) If the terminal block mating surface has contamination, clean surface. Refer to SWPM 20-20-00 Cleaning

Method 5 as an accepted procedure. If the terminal block shows signs of arcing, blueing, overheating,

pitting, corrosion, or other surface damage, replace the windshield. Refer to 747-100/200/300 AMM 56-

11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

(l) Reassemble the connector to the terminal block with a new screw, lock washer and o-ring. Make sure

the o-ring is installed prior to assemble of the connector to the terminal block.

(m) Make sure the screw has been aligned correctly.

(n) A new o-ring is only available for the CWC01-1210 connector. Refer to SWPM 20-64-16 for the correct

screw, washer and o-ring.

(o) Do step 2 to make sure the screw has been installed correctly and is a tight connection.

(p) If the screw has been installed correctly and it is not a tight connection, replace the windshield. Refer to

747-100/200/300 AMM 56-11-01 or 747-400 AMM 56-11-01 as an accepted procedure.

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 3: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

1 AIRPLANES

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

4 Identification Tape 61B20558-10501 1 Imprinted "W1372-H104R/H105B-12"

(a) 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.

FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

2 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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76 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, Class - or optional BACS38K5 Tie Strap.

1, Color White

Lacing Tape

Refer to Standard Wiring Practices

SWPM 20-64-18 as an accepted

procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

FIGURE 5: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

3 AIRPLANES

(SHEET 1 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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77 of 100

BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-30-16 as an accepted procedure.4 Terminal 324484 2

(a) 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.

FIGURE 5: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

3 AIRPLANES

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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78 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, Class - or optional BACS38K5 Tie Strap.

1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 6: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

4 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

79 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 7: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

5 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

80 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 8: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

6 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-400 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

1 Wire W4495-001-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

2 Wire W4495-002-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

3 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-38 2

FIGURE 9: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

7 AIRPLANES

(SHEET 1 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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82 of 100

BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 as an accepted procedure.5 Strap BACS38K5B 10

(a) 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.

FIGURE 9: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

7 AIRPLANES

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

83 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-400 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

1 Wire W4497-001-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

2 Wire W4497-002-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

3 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-38 2

FIGURE 10: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

8 AIRPLANES

(SHEET 1 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

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BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 as an accepted procedure.5 Strap BACS38K5B 10

(a) 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.

FIGURE 10: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP

8 AIRPLANES

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

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FIGURE 11: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 1 THROUGH

6 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

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BOEING SERVICE BULLETIN 747-30-2081
FIGURE 12: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 7 - 8

AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

87 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, Class - or optional BACS38K5 Tie Strap.

1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 13: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

1 AIRPLANES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

88 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted

procedure.

3 Splice D-436-38 2

4 Identification Tape 61B20558-10601 1 Imprinted "W1548-H111R/H112B-12"

(a) 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.

FIGURE 14: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

2 AIRPLANES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

Refer to SWPM 20-30-16 as an accepted procedure.4 Terminal 324484 2

FIGURE 15: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

3 AIRPLANES

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

90 of 100

BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(a) 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.

FIGURE 15: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

3 AIRPLANES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

91 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, - or optional BACS38K5 Tie Strap.

Class 1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 16: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

4 AIRPLANES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

92 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, Class 2

1, AWG 12

1 Wire

BMS 13-54, Type 3, Class - or optional BACS38K5 Tie Strap.

1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 17: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

5 AIRPLANES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

93 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-100/200/300 WDM 30-41-11

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

BMS 13-48, Type 10, 2

Class 1, AWG 12

1 Wire

BMS 13-54, Type 3, Class - or optional BACS38K5 Tie Strap.

1, Color White

Lacing Tape

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

2 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.3 Splice D-436-38 2

(a) 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.

FIGURE 18: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

6 AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

94 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-400 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

1 Wire W4496-001-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

2 Wire W4496-002-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

3 Socket Contact M39029/57-359 2

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-38 2

FIGURE 19: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

7 AIRPLANES

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

95 of 100

BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 as an accepted procedure.5 Strap BACS38K5E 10

(a) 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.

FIGURE 19: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

7 AIRPLANES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

96 of 100

BOEING SERVICE BULLETIN 747-30-2081
REFERENCE: WIRING DIAGRAM 747-400 WDM 30-41-12

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

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

1 Wire W4498-001-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

2 Wire W4498-002-12 1

78 inch length is trimmed to full

length of new wire.

Sleeve NA728R99 1

Refer to Standard Wiring Practices

Manual SWPM 20-64-18 as an accepted procedure. (a)

3 Socket Contact M39029/37-359 2

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-38 2

FIGURE 20: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

8 AIRPLANES

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

97 of 100

BOEING SERVICE BULLETIN 747-30-2081
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 as an accepted procedure.5 Strap BACS38K5E 10

(a) 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.

FIGURE 20: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP

8 AIRPLANES

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

98 of 100

BOEING SERVICE BULLETIN 747-30-2081
FIGURE 21: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP 1 - 6

AIRPLANES

(SHEET 1 OF 1)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

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BOEING SERVICE BULLETIN 747-30-2081
FIGURE 22: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP 7 - 8

AIRPLANES

(SHEET 1 OF 1)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: August 08, 2006

Revision 3 December 05, 2011 747-30-2081

100 of 100

BOEING SERVICE BULLETIN 747-30-2081