### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2006 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 1 of 100 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 2 of 100 **BOEING SERVICE BULLETIN 747-30-2081**

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 3 of 100 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 4 of 100 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 5 of 100Pages with no vertical lines have no important changes. **REVISION HISTORY** August 08, 2006 Original Issue: August 20, 2008 Revision 1: March 10, 2010 Revision 2: December 05, 2011 Revision 3:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 6 of 100 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 7 of 100**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 Elapsed Hours**  **Total Task Hours Work Package**  0.25 0.25 Work Package 1 - Detailed Inspection of the Left Windshield 0.25 0.25 Work Package 2 - Detailed Inspection of the Right Windshield 5.25 9.0 Work Package 3 - Left Windshield Replacement and Wiring Change 5.25 9.0 Work Package 4 - Right Windshield Replacement and Wiring Change
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 8 of 100 **BOEING SERVICE BULLETIN 747-30-2081**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 9 of 100 **BOEING SERVICE BULLETIN 747-30-2081**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 10 of 100 **BOEING SERVICE BULLETIN 747-30-2081**

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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 11 of 100**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Variable Number**  4 RA001 - RA026 6 RA027 - RA034 4 RA101 - RA111 3 RA112 4 RA113 6 RA114 - RA115 3 RA161 4 RA162 6 RA163 - RA164 4 RA201 - RA203 6 RA216 1 RA217 6 RA245 1 RA246 4 RA251 - RA254 6 RA255 - RA256 1 RA257 - RA266 4 RA301 - RA303 6 RA304 - RA309

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 12 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 1 RA310 - RA318 4 RA351 - RA360 4 RA369 6 RA370 - RA373 4 RA401 - RA408 6 RA409 - RA413 1 RA414 - RA418 4 RA501 6 RA502 4 RA521 - RA523 6 RA524 1 RA525 - RA528 6 RA532 - RA535 1 RA536 - RA548 4 RA551 - RA552 6 RA559 - RA560 1 RA561 4 RA581 - RA582 6 RA585 4 RA601 - RA602 5 RA631 4 RA632 - RA633 6 RA634 - RA635 6 RA651 - RA652 4 RA671 6 RA672 - RA677 6 RA701 - RA702 6 RA721 - RA722 1 RA723 - RA731 6 RA741 - RA743 1 RA744 - RA745 1 RA749 - RA750 6 RA761 - RA762

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 13 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 6 RA781 - RA782 1 RA783 - RA784 3 RA901 - RA903 4 RA904 - RA905 3 RA906 - RA907 4 RA908 - RA910 6 RA911 - RA916 6 RB001 - RB004 1 RB005 - RB012 4 RB041 - RB043 6 RB044 1 RB071 6 RB072 - RB073 1 RB074 - RB075 4 RB101 - RB102 2 RB411 - RB413 2 RB421 1 RB601 1 RB604 - RB605 1 RB607 1 RB681 - RB685 1 RB687 1 RB690 - RB697 1 RB711 1 RB721 - RB722 2 RB723 1 RB741 - RB748 1 RD001 - RD004 1 RD021 - RD022 1 RD041 - RD059 1 RD071 - RD072 1 RD081 - RD083 1 RD091 - RD092

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 14 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 1 RD101 - RD104 1 RD121 - RD127 1 RD131 - RD144 1 RD171 - RD172 1 RD181 - RD183 1 RD201 - RD204 1 RD221 - RD226 2 RD227 2 RD231 - RD235 1 RD241 - RD243 1 RD251 - RD257 2 RD258 - RD262 1 RD271 - RD272 2 RD291 - RD292 2 RD301 - RD302 2 RD311 1 RD351 - RD357 2 RD358 1 RD361 - RD365 2 RD366 1 RD381 - RD383 1 RD411 - RD414 1 RD421 - RD426 1 RD431 - RD435 1 RD441 - RD442 1 RD451 - RD455 2 RD456 1 RD461 1 RD471 - RD475 1 RD513 - RD519 1 RD531 - RD533 1 RD551 1 RD561

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 15 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 1 RD571 1 RD581 - RD583 1 RD591 - RD593 1 RD601 - RD607 1 RD621 - RD623 1 RD641 - RD649 1 RD651 - RD658 2 RD659 1 RD661 1 RD671 1 RD681 - RD682 1 RD691 - RD692 1 RD701 - RD702 1 RD721 - RD722 1 RD741 - RD742 1 RD751 - RD753 2 RD754 - RD755 1 RD761 1 RD771 2 RD772 - RD775 2 RD781 - RD783 2 RD791 - RD792 1 RE001 8 RF001 - RF006 1 RG008 - RG009 1 RG091 1 RG095 1 RG101 - RG104 1 RG122 - RG123 1 RG125 1 RG141 - RG142 1 RG161 - RG164 1 RG171 - RG174

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 16 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 1 RG191 1 RG193 1 RG213 1 RG221 - RG222 1 RH101 2 RH102 1 RH121 - RH122 1 RJ131 - RJ133 1 RJ151 - RJ152 1 RJ301 - RJ303 2 RJ321 - RJ322 1 RJ331 - RJ333 7 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 8 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 17 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 8 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 7 RM851 - RM859 7 RM861 - RM862 7 RM871 - RM888 7 RM891 - RM899 7 RM901 - RM906 7 RM911 1 RR001 - RR005 1 RR021 - RR023 2 RR024 - RR025 1 RR031 1 RR201 - RR203 2 RR204 - RR206 1 RR221 - RR226 1 RR261 - RR265 2 RR266 - RR267

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 18 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 1 RR301 - RR306 2 RR307 - RR310 1 RR331 - RR332 1 RR336 1 RR341 - RR345 1 RR361 - RR362 1 RR421 - RR422 2 RR431 - RR432 2 RR441 - RR442 2 RR451 1 RR501 - RR504 1 RR521 2 RR522 2 RR526 1 RR531 2 RR551 - RR556 1 RR561 2 RR566 7 RR701 7 RR721 - RR724 7 RR746 - RR748 7 RR851 - RR856 7 RR861 - RR862 7 RR951 - RR952 2 RS001 - RS002 1 RS201 1 RS211 - RS212 1 RS221 - RS222 1 RS231 - RS233 2 RS234 - RS241 1 RS251 - RS252 2 RS253 - RS259 2 RS263

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 19 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 2 RS265 - RS268 2 RS271 - RS276 2 RS291 - RS292 2 RS301 - RS306 2 RS311 - RS320 2 RS331 - RS333 2 RS341 - RS342 2 RS699 1 RS701 - RS702 2 RS703 1 RS711 2 RS712 - RS713 2 RS721 - RS722 2 RS731 - RS732 2 RS741 - RS743 1 RS751 - RS752 2 RS761 - RS762 2 RS771 2 RS781 - RS782 2 RS786 8 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 20 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group**  **Variable Number** 8 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 21 of 100 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 22 of 100 **BOEING SERVICE BULLETIN 747-30-2081**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 Zone**  **Model** 221, 222 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SP, 747SR **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 221, 222 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747SP

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 23 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 3, 5:** 
**Affected Maintenance Zones Zone**  **Model** 221, 222 747-100 **Group 4, 6:**
**Affected Maintenance Zones Zone**  **Model** 221, 222 747-100, 747-200B **Group 7:**
**Affected Maintenance Zones Zone**  **Model** 221, 222 747-400F **Group 8:**
**Affected Maintenance Zones Zone**  **Model** 221, 222 747-400, 747-400D **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)**  **Action Condition** 

Terminating action for this bulletin. ---- Replace with windshield thatuses pins and sockets for window heat power connection inaccordance with Accomplishment Instructions Work Packages 3 and 4. Windshield that uses screws and connectors for window heat power connection.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 24 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Compliance Table: 1**  **Repeat Interval (Whichever Occurs**  **Later) Compliance Time**  **(Whichever Occurs First) Action**  **Condition**

Every 6000 flight hours or 24 monthsuntil windshield is replaced with windshield that uses pins andsockets 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 wiringand connector (including cover), look for signs of melted or discolored insulation. 2. Inspect the window terminalblocks, 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 inspectionfindings as described in Inspection Conditions 1 thru 4. Every 12,000 flight hours or 48 monthsuntil windshield is replaced with windshield that uses pins and sockets for window heat power connection in accordance withAccomplishment 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 wiringand connector (including cover), look for signs of melted or discolored insulation. 2. Inspect the window terminalblocks, 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 inspectionfindings as described in Inspection Conditions 1 thru 4.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 25 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Compliance Table: 1**  **Repeat Interval (Whichever Occurs**  **Later) Compliance Time**  **(Whichever Occurs First) Action**  **Condition**

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

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

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 26 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Compliance Table: 1**  **Repeat Interval (Whichever Occurs**  **Later) Compliance Time**  **(Whichever Occurs First) Action**  **Condition**

---- Before further flight. 1. Torque the terminal screw 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 andreassemble 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 thewindshield heat power connection. (a) Do a detailed inspection and corrective actions if necessary, in accordance with Work Package 1, step 3 or WorkPackage 2, step 3; as applicable.Window heat power connection is reassembled (on windshields that uses screws and connectors for window heat power connection). ORIf 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 27 of 100 **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 Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 FIGURE 1 0.25 0.25 Total per Windshield **Work Package 2 - Detailed** **Inspection of the RIght Windshield Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 FIGURE 2 0.25 0.25 Total per Windshield **Group 1-6: Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  0.5 1.0 2 Access 1.25 2.5 2 Remove the Left Windshield 1.25 1.25 1 Change the Wiring 1.5 3.0 2 Install the Left Windshield 0.25 0.25 1 Tests 0.5 1.0 2 Close 5.25 9.0 Total per Windshield **Group 7-8: Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  0.5 1.0 2 Access

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 28 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 7-8:**  **Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 1.25 2.5 2 Remove the Left Windshield 1.25 1.25 1 Change the Wiring 1.5 3.0 2 Install the Left Windshield 0.25 0.25 1 Tests 0.5 1.0 2 Close 5.25 9.0 Total per Windshield **Group 1-6: Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  0.5 1.0 2 Access 1.25 2.5 2 Remove the Right Windshield 1.25 1.25 1 Change the Wiring 1.5 3.0 2 Install the Right Windshield 0.25 0.25 1 Tests 0.5 1.0 2 Close 5.25 9.0 Total per Windshield **Group 7-8: Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  0.5 1.0 2 Access 1.25 2.5 2 Remove the Right Windshield 1.25 1.25 1 Change the Wiring 1.5 3.0 2 Install the Right Windshield 0.25 0.25 1 Tests 0.5 1.0 2 Close 5.25 9.0 Total per Windshield **H. Weight and Balance Changes** None

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 29 of 100 **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: **Chapter-Section Publication**  30-41, 56-11 747 Maintenance Manual 30-41 747 Wiring Diagram Manual 30-41 747 Fault Isolation Manual 56-11 747 Illustrated Parts Catalog

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 30 of 100 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 31 of 100 **BOEING SERVICE BULLETIN 747-30-2081**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 32 of 100 **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 Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 03 date**

**of this Service Bulletin (Calendar**  **Days) Name**  **Top Kit Number**

$20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,GKN (a) 015U1784-1 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,GKN (a) 015U1784-2 $20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,PPG (a) 015U1784-3 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,PPG (a) 015U1784-4 $20,147.00 200 Top Kit, Left Windshield and Window HeatTerminal Replacement,No windshield preference (a) 015U1784-5

$20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (a) 015U1784-6

$20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,GKN (b) 015U1784-7 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,GKN (b) 015U1784-8 $20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,PPG (b) 015U1784-9 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,PPG (b) 015U1784-10

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 33 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 Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 03 date**

**of this Service Bulletin (Calendar**  **Days) Name**  **Top Kit Number**

$20,147.00 200 Top Kit, Left Windshield and Window HeatTerminal Replacement,No windshield preference (b) 015U1784-11

$20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (b) 015U1784-12

$20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,GKN (c) 015U1784-13 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,GKN (c) 015U1784-14 $20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,PPG (c) 015U1784-15 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,PPG (c) 015U1784-16 $20,147.00 200 Top Kit, Left Windshield and Window HeatTerminal Replacement,No windshield preference (c) 015U1784-17

$20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (c) 015U1784-18

$20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,GKN (d) 015U1784-19 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,GKN (d) 015U1784-20 $20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,PPG (d) 015U1784-21 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,PPG (d) 015U1784-22 $20,147.00 200 Top Kit, Left Windshield and Window HeatTerminal Replacement,No windshield preference (d) 015U1784-23

$20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (d) 015U1784-24

$20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,GKN (e) 015U1784-25

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 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 Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 03 date**

**of this Service Bulletin (Calendar**  **Days) Name**  **Top Kit Number**

$20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,GKN (e) 015U1784-26 $20,147.00 200 Top Kit, Left Windshield and Window Heat Terminal Replacement,PPG (e) 015U1784-27 $20,147.00 200 Top Kit, Right Windshield and Window Heat Terminal Replacement,PPG (e) 015U1784-28 $20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (e) 015U1784-29

$20,147.00 200 Top Kit, Right Windshield and Window HeatTerminal Replacement,No windshield preference (e) 015U1784-30

$1,300.00 200 Top Kit - Left and Right Window Heat Wiring - No Windshield (a) (f) 015U1784-31 $1,300.00 200 Top Kit - Left and Right Window Heat Wiring - No Windshield (b) (f) 015U1784-32 $1,302.00 200 Top Kit - Left and Right Window Heat Wiring - No Windshield (c) (f) 015U1784-33 $698.00 200 Top Kit - Left and Right Window Heat Wiring - No Windshield (d) (f) 015U1784-34 $698.00 200 Top Kit - Left and Right Window Heat Wiring - 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 747-30-2081 Revision 3: December 05, 2011 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 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Num- ber**  **-1 -2**  **-3 -4**  **-5 -6**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - GKN - . . . . . 015U1784-1

Top Kit - Right Windshield andWindow Heat Terminal Replacement - GKN . - . . . . 015U1784-2

Top Kit - Left Windshield andWindow Heat Terminal Replacement - PPG . . - . . . 015U1784-3

Top Kit - Right Windshield andWindow Heat Terminal Replacement - PPG . . . - . . 015U1784-4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 36 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 1, 4-6:** 
**Kit 015U1784 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Num- ber**  **-1 -2**  **-3 -4**  **-5 -6**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - No Windshield Preference . . . . - . 015U1784-5

Top Kit - Right Windshield andWindow 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 - Coated 1

. . . 1

. 141U4800-13

(a) (b) (c) (e) (f) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373, 06383, NP-103801-( )Windshield Assembly, Co-Pilot - Coated . 1

. . . 1 141U4800-14

Wire Kit - Flight Deck Window Heat Redesign - Left 1

. 1

. 1

. 61B20558-1

Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. 1

. 1 61B20558-2

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06302, 06322, 06332, 06342, 06362, 06372, 06382, NP-103801-( )Windshield Assembly, Pilot - Coated . . 1

. . . NP-103801-117

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373, 06383, NP-103801-( )Windshield Assembly, Co-Pilot - Coated . . . 1

. . NP-103801-118

(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 747-30-2081 Revision 3: December 05, 2011 37 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 1, 4-6:** 
**Kit 015U1784 Notes**  **Existing Part Num- ber**  **Name QTY**  **New Part Num- ber**  **-1 -2**  **-3 -4**  **-5 -6**  (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 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-7 -8**  **-9 -10**  **-11 -12**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - GKN - . . . . . 015U1784-7

Top Kit - Right Windshield andWindow Heat Terminal Replacement - GKN . - . . . . 015U1784-8

Top Kit - Left Windshield andWindow Heat Terminal Replacement - PPG . . - . . . 015U1784-9

Top Kit - Right Windshield andWindow Heat Terminal Replacement - PPG . . . - . . 015U1784-10

Top Kit - Left Windshield andWindow Heat Terminal Replacement - No Windshield Preference . . . . - . 015U1784-11

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 38 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 2:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-7 -8**  **-9 -10**  **-11 -12**  Top Kit - Right Windshield andWindow 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 - Coated 1

. . . 1

. 141U4800-13

(a) (b) (c) (e) (f) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . 1

. . . 1 141U4800-14

Wire Kit - Flight Deck Window Heat Redesign - Left 1

. 1

. 1

. 61B20558-5

Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. 1

. 1 61B20558-6

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06302, 06322, 06332, 06342, 06362, 06372,06382, NP103801-( )Windshield Assembly, Pilot - Coated . . 1

. . . NP-103801-117

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . . . 1

. . NP-103801-118

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 39 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 2:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-7 -8**  **-9 -10**  **-11 -12**  (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 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-13 -14**  **-15 -16**  **-17 -18**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - GKN - . . . . . 015U1784-13

Top Kit - Right Windshield andWindow Heat Terminal Replacement - GKN . - . . . . 015U1784-14

Top Kit - Left Windshield andWindow Heat Terminal Replacement - PPG . . - . . . 015U1784-15

Top Kit - Right Windshield andWindow Heat Terminal Replacement - PPG . . . - . . 015U1784-16

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 40 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 3:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-13 -14**  **-15 -16**  **-17 -18**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - No Windshield Preference . . . . - . 015U1784-17

Top Kit - Right Windshield andWindow 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 - Coated 1

. . . 1

. 141U4800-13

(a) (b) (c) (e) (f) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . 1

. . . 1 141U4800-14

Wire Kit - Flight Deck Window Heat Redesign - Left 1

. 1

. 1

. 61B20558-7

Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. 1

. 1 61B20558-8

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06302, 06322, 06332, 06342, 06362, 06372,06382, NP103801-( )Windshield Assembly, Pilot - Coated . . 1

. . . NP-103801-117

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 41 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 3:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-13 -14**  **-15 -16**  **-17 -18**  (a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . . . 1

. . NP-103801-118

(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 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-19 -20**  **-21 -22**  **-23 -24**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - GKN - . . . . . 015U1784-19

Top Kit - Right Windshield andWindow Heat Terminal Replacement - GKN . - . . . . 015U1784-20

Top Kit - Left Windshield andWindow Heat Terminal Replacement - PPG . . - . . . 015U1784-21

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 42 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 7:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-19 -20**  **-21 -22**  **-23 -24**  Top Kit - Right Windshield andWindow Heat Terminal Replacement - PPG . . . - . . 015U1784-22

Top Kit - Left Windshield andWindow Heat Terminal Replacement - No Windshield Preference . . . . - . 015U1784-23

Top Kit - Right Windshield andWindow 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 - Coated 1

. . . 1

. 141U4800-13

(a) (b) (c) (e) (f) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . 1

. . . 1 141U4800-14

Wire Kit - Flight Deck Window Heat Redesign - Left 1

. 1

. 1

. 289U1215-1

Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. 1

. 1 289U1215-2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 43 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 7:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-19 -20**  **-21 -22**  **-23 -24**  (a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06302, 06322, 06332, 06342, 06362, 06372,06382, NP103801-( )Windshield Assembly, Pilot - Coated . . 1

. . . NP-103801-117

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . . . 1

. . NP-103801-118

(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 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-25 -26**  **-27 -28**  **-29 -30**  Top Kit - Left Windshield andWindow Heat Terminal Replacement - GKN - . . . . . 015U1784-25

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 44 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 8:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-25 -26**  **-27 -28**  **-29 -30**  Top Kit - Right Windshield andWindow Heat Terminal Replacement - GKN . - . . . . 015U1784-26

Top Kit - Left Windshield andWindow Heat Terminal Replacement - PPG . . - . . . 015U1784-27

Top Kit - Right Windshield andWindow Heat Terminal Replacement - PPG . . . - . . 015U1784-28

Top Kit - Left Windshield andWindow Heat Terminal Replacement - No Windshield Preference . . . . - . 015U1784-29

Top Kit - Right Windshield andWindow 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 - Coated 1

. . . 1

. 141U4800-13

(a) (b) (c) (e) (f) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . 1

. . . 1 141U4800-14

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 45 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Group 8:** 
**Kit 015U1784 Notes**  **Existing Part Number**  **Name QTY**  **New Part Num- ber**  **-25 -26**  **-27 -28**  **-29 -30**  Wire Kit - Flight Deck Window Heat Redesign - Left 1

. 1

. 1

. 289U1215-3

Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. 1

. 1 289U1215-4

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06302, 06322, 06332, 06342, 06362, 06372,06382, NP103801-( )Windshield Assembly, Pilot - Coated . . 1

. . . NP-103801-117

(a) (b) (c) (d) (e) 65B07638-( ), 60B10028-( ), 06303, 06323, 06333, 06343, 06363, 06373,06383, NP103801-( )Windshield Assembly, Co-Pilot - Coated . . . 1

. . NP-103801-118

(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 747-30-2081 Revision 3: December 05, 2011 46 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 015U1784 - Top Kit**  **Notes Existing Part**  **Number Name**  **QTY New Part Num-**  **ber -31**  **-32 -33**  **-34 -35**  Top Kit - Left and Right Window HeatWiring - No Windshield - . . . . 015U1784-31

Top Kit - Left and Right Window HeatWiring - No Windshield . - . . . 015U1784-32

Top Kit - Left and Right Window HeatWiring - No Windshield . . - . . 015U1784-33

Top Kit - Left and Right Window HeatWiring - No Windshield . . . - . 015U1784-34

Top Kit - Left and Right Window HeatWiring - No Windshield . . . . - 015U1784-35

Wire Kit - Flight Deck Window Heat Redesign - Left . . . 1

. 289U1215-1

Wire Kit - Flight Deck Window Heat Redesign - Right . . . 1

. 289U1215-2

Wire Kit - Flight Deck Window Heat Redesign - Left . . . . 1 289U1215-3

Wire Kit - Flight Deck Window Heat Redesign - Right . . . . 1 289U1215-4

Wire Kit - Flight Deck Window Heat Redesign - Left 1

. . . . 61B20558-1

Wire Kit - Flight Deck Window Heat Redesign - Right 1

. . . . 61B20558-2

Wire Kit - Flight Deck Window Heat Redesign - Left . 1

. . . 61B20558-5

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 47 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 015U1784 - Top Kit**  **Notes Existing Part**  **Number Name**  **QTY New Part Num-**  **ber -31**  **-32 -33**  **-34 -35**  Wire Kit - Flight Deck Window Heat Redesign - Right . 1

. . . 61B20558-6

Wire Kit - Flight Deck Window Heat Redesign - Left . . 1

. . 61B20558-7

Wire Kit - Flight Deck Window Heat Redesign - Right . . 1

. . 61B20558-8

**Kit 289U1215 - Wire Kit Notes**  **Name QTY**  **New Part Number -1**  **-2 -3**  **-4** Wire Kit -Flight DeckWindow Heat Redesign - Left - . . . 289U1215-1

Wire Kit -Flight DeckWindow 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

(a) Subkit - W4495 1

. . . 289U1215-101 (a) Subkit - W4496

. 1

. . 289U1215-102 (a) Subkit - W4497

. . 1

. 289U1215-103 (a) Subkit - W4498

. . . 1 289U1215-104 (a) There are more parts than necessary. **Kit 289U1215 - Wire Kit - Flight Deck Window Heat Notes**  **Name QTY**  **New Part Number -101**  **-102 -103**  **-104** Subkit - W4495

- . . . 289U1215-101 Subkit - W4496

. - . . 289U1215-102 Subkit - W4497

. . - . 289U1215-103

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 48 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 289U1215 - Wire Kit - Flight Deck Window Heat**  **Notes Name**  **QTY New Part Number**  **-101 -102**  **-103 -104**  Subkit - W4498

. . . - 289U1215-104 (a) Wire Identified W4495-001-12 1

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

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

. 1

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

. 1

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

. . 1

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

. . 1

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

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

. . . 1
- Strap 10

. 10

. BACS38K5B Strap

. 10

. 10 BACS38K5E Splice 3 3 3 3 D-436-38 Socket Contact 3 3 3 3 M39029/57-359 BMS 13-52 Expandable Sleeve 1 1 1 1 NA728R99 (a) BMS 13-48, Type 10, Class 1, AWG 12, length 78 inches. **Kit 61B20558 - Wire Kit - Flight Deck Window Heat Notes**  **Name QTY**  **New Part Number -1**  **-2 -5**  **-6 -7**  **-8** (a) Wire Kit - Flight Deck Window Heat - Left - . . . . . 61B20558-1

(a) Wire Kit - Flight Deck Window Heat - Right . - . . . . 61B20558-2

(a) Wire Kit - Flight Deck Window Heat - Left . . - . . . 61B20558-5

(a) Wire Kit - Flight Deck Window Heat - Right . . . - . . 61B20558-6

(a) Wire Kit - Flight Deck Window Heat - Left . . . . - . 61B20558-7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 49 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 61B20558 - Wire Kit - Flight Deck Window Heat**  **Notes Name**  **QTY New Part Number**  **-1 -2**  **-5 -6**  **-7 -8**  (a) Wire Kit - Flight Deck Window Heat - Right . . . . . - 61B20558-8

Subkit - W1372,W344 1

. . . . . 61B20558-101
Subkit - W1548,W342 . 1

. . . . 61B20558-102
Subkit - W1372,W344 . . 1

. . . 61B20558-105
Subkit - W1548,W342 . . . 1

. . 61B20558-106
Subkit - W1372,W344 . . . . 1

. 61B20558-107
Subkit - W1548,W342 . . . . . 1 61B20558-108 (a) There are more parts than are necessary. **Kit 61B20558 - Wire Kit - Flight Deck Window Heat Notes**  **Name QTY**  **New Part Number -101**  **-102 -105**  **-106 -107**  **-108** 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 (a) Wire Identified W342-H106-24R . 1

. 1

. 1
- (a) Wire Identified W342-H107-24B . 1

. 1

. 1
-

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 50 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 61B20558 - Wire Kit - Flight Deck Window Heat**  **Notes Name**  **QTY New Part Number**  **-101 -102**  **-105 -106**  **-107 -108**  (a) Wire Identified W342-H108-24R . 1

. 1

. 1
- (a) Wire Identified W342-H109-24B . 1

. 1

. 1
- (a) Wire Identified W344-H99-24R 1

. 1

. 1

. - (a) Wire Identified W344-H100-24B 1

. 1

. 1

. - (a) Wire Identified W344-H101-24R 1

. 1

. 1

. - (a) Wire Identified W344-H102-24B 1

. 1

. 1

. - (c) Wire Identified W1372-H104-12R . . 1

. . . - (c) Wire Identified W1372-H105-12B . . 1

. . . - (b) Wire Identified W1372-H104-12 1

. . . 1

. - (b) Wire Identified W1372-H105-12 1

. . . 1

. - (b) Wire Identified W1548-H111-12 . 1

. . . 1
- (b) Wire Identified W1548-H112-12 . 1

. . . 1
- (b) Wire Identified W1548-H111-12R . . . 1

. . - (b) Wire Identified W1548-H112-12B . . . 1

. . - (d) Identification Tape 3

. 3

. 3

. 61B20558-10101 (d) Identification Tape 3

. 3

. 3

. 61B20558-10102 (d) Identification Tape

. 3

. 3

. 3 61B20558-10201 (d) Identification Tape

. 3

. 3

. 3 61B20558-10202 Identification Tape

. . 3

. . . 61B20558-10501 Identification Tape

. . . 3

. . 61B20558-10601 (d) Terminal 5 5 5 5 5 5 BACT12AR222 Terminal

. . . . 3 3 324484

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 51 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Kit 61B20558 - Wire Kit - Flight Deck Window Heat**  **Notes Name**  **QTY New Part Number**  **-101 -102**  **-105 -106**  **-107 -108**  Splice 3 3 3 3 3 3 D-436-38 (d) Splice 3 3 3 3 3 3 D-150-0174 Socket Contact 3 3 3 3 3 3 M39029/57-359 (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:
**Notes Name**  **QTY Part Number / Speci-**  **fication** (a) (b) Lacing Tape 30 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.
**Notes Name**  **QTY Part Number**  (a) Windshield, Left, uncoated, PPG 1 NP-103801-115 (a) Windshield, Right, uncoated, PPG 1 NP-103801-116 (b) Windshield, Left, uncoated, GKN 1 13912 (b) Windshield, Right, uncoated, GKN 1 13913 (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 52 of 100 **BOEING SERVICE BULLETIN 747-30-2081**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 Ser**  **vice Bulletin (US Dollars)**  **Name Tool Kit Number** 

$813 Windshield Handling Sling 20HME65B07630 **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.
**Name Tool Kit Number**  Windshield Handling Sling 20HME65B07630

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 53 of 100 **BOEING SERVICE BULLETIN 747-30-2081**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 54 of 100 **BOEING SERVICE BULLETIN 747-30-2081**

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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 55 of 100 **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:
**Circuit Breaker Name**  **Panel** C0335 WINDOW HEAT CONT 1L P6 C0439 WINDOW HEAT CONT 1L P12 C1503 WINDOW HEAT POWER 1L P6 **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:
**Circuit Breaker Name**  **Location Panel / Position**  C0439 WINDOW HEAT CONT 1L P180 / H26 C1503 WINDOW HEAT POWER 1L P6-6 / B34 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:
**Circuit Breaker Name**  **Panel** C335 WINDOW HEAT CONT 1L P6

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 56 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Circuit Breaker**  **Name Panel**  C439 WINDOW HEAT CONT 1L P12 C1503 WINDOW HEAT POWER 1L P6
5.**Group 7-8:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Location Panel / Position**  C0439 WINDOW HEAT CONT 1L P180 / H26 C1503 WINDOW HEAT POWER 1L P6-6 / B34
**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:
**Circuit Breaker Name**  **Panel** C334 WINDOW HEAT CONT 1R P6 C435 WINDOW HEAT CONT 1R P12 C1504 WINDOW HEAT POWER 1R P6 **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:
**Circuit Breaker Name**  **Location Panel / Position**  C0435 WINDOW HEAT CONT 1R P180 / H12 C1504 WINDOW HEAT POWER 1R P6-5 / B17 3. Do detailed inspection of the right windshield and corrective actions if necessary in accordance with FIGURE 2.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 57 of 100 **BOEING SERVICE BULLETIN 747-30-2081**4.**Group 1-6:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Panel** C334 WINDOW HEAT CONT 1R P6 C435 WINDOW HEAT CONT 1R P12 C1504 WINDOW HEAT POWER 1R P6
5.**Group 7-8:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Location Panel / Position**  C0435 WINDOW HEAT CONT 1R P180 / H12 C1504 WINDOW HEAT POWER 1R P6-5 / B17
**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:
**Circuit Breaker Name**  **Panel** C0335 WINDOW HEAT CONT 1L P6 C0439 WINDOW HEAT CONT 1L P12 C1503 WINDOW HEAT POWER 1L P6 **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:
**Circuit Breaker Name**  **Location Panel / Position**  C0439 WINDOW HEAT CONT 1L P180 / H26 C1503 WINDOW HEAT POWER 1L P6-6 / B34

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 58 of 100 **BOEING SERVICE BULLETIN 747-30-2081**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: **Part of Top Kit Part Number**  **Description** 015U1784-1, -7, -13, -19, -25, -31 141U4800-13 GKN Windshield with wiper ramp, pilot assist handle, and hydrophobic coating. Obtained from supplier/vendor 13912 GKN Windshield with wiper ramp, pilot assist handle. No hydrophobic coating. 015U1784-3, -9, -15, -21, -27, -33 NP-103801-117 PPG Windshield with wiper ramp, pilot assist handle, and hydrophobic coating. Obtained from supplier/vendor NP-103801-115 PPG Windshield with wiper ramp and pilot assist handle. No hydrophobic coating

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 59 of 100 **BOEING SERVICE BULLETIN 747-30-2081**13.**Group 1-6:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Panel** C0335 WINDOW HEAT CONT 1L P6 C0439 WINDOW HEAT CONT 1L P12 C1503 WINDOW HEAT POWER 1L P6
14.**Group 7-8:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Location Panel / Position**  C0439 WINDOW HEAT CONT 1L P180 / H26 C1503 WINDOW HEAT POWER 1L P6-6 / B34 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:
**Circuit Breaker Name**  **Panel** C334 WINDOW HEAT CONT 1R P6 C435 WINDOW HEAT CONT 1R P12 C1504 WINDOW HEAT POWER 1R P6 **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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 60 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Circuit Breaker**  **Name Location Panel /**  **Position** C0435 WINDOW HEAT CONT 1R P180 / H12 C1504 WINDOW HEAT POWER 1R P6-5 / B17 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: **Part of Top Kit Part Number**  **Description** 015U1784-2, -8, -14, -20, -26, -32 141U4800-14 GKN Windshield with wiper ramp, pilot assist handle, and hydrophobic coating. Obtained from supplier/vendor 13913 GKN Windshield with wiper ramp, pilot assist handle. No hydrophobic coating.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 61 of 100 **BOEING SERVICE BULLETIN 747-30-2081 Part of Top Kit**  **Part Number Description**  015U1784-4, -10, -16, -22, -28, -34 NP-103801-118 PPG Windshield with wiper ramp, pilot assist handle, and hydrophobic coating. Obtained from supplier/vendor NP-103801-116 PPG Windshield with wiper ramp and pilot assist handle. No hydrophobic coating

13.**Group 1-6:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Panel** C334 WINDOW HEAT CONT 1R P6 C435 WINDOW HEAT CONT 1R P12 C1504 WINDOW HEAT POWER 1R P6
14.**Group 7-8:** Remove the DO-NOT-CLOSE tags and close these circuit breakers:
**Circuit Breaker Name**  **Location Panel / Position**  C0435 WINDOW HEAT CONT 1R P180 / H12 C1504 WINDOW HEAT POWER 1R P6-5 / B17 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3: December 05, 2011 62 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD**  **(SHEET 1 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 63 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD**  **(SHEET 2 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 64 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD**  **(SHEET 3 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 65 of 100 **BOEING SERVICE BULLETIN 747-30-2081**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**More Data Qty**  **Identification Name**  **Task Step**  at the "A" terminal. (a) 1
- Terminal Block Inspect 1 (b) 1
- Connector Inspect (c) 1
- Wiring Inspect 1
- Cover Remove / Keep 2 to make sure it is a tight connection. (d) (e) (f) 1
- Connector Inspect

not necessary if the connector is loose. (g) 1
- Cover Install (Kept)

**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) 1
- Screw Torque 3

to make sure the connection is tight. 1
- Connector Inspect not necessary if the connector cannot be tightened. 1
- Cover Install (Kept)

to make sure the screw is installed correctly and thereis no damage to terminal or screw. 1
- Screw Remove 4

1
- Washer Remove 1
- O-ring Remove (j) 1
- Connector Inspect to make sure the terminal block is not damaged. (k) 1
- Terminal Block Inspect

**FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 66 of 100 **BOEING SERVICE BULLETIN 747-30-2081 More Data**  **Qty Identification**  **Name Task**  **Step 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 assembledwith new, undamaged and correct hardware. (l) (m) 1
- Screw Install (New) 5

1
- Wiring Install (New) (n) 1
- O-ring Install (New) to 25 to 30 inch pounds of torque. Refer to SWPM 20-64-16 as an accepted procedure. (o) (p) 1
- Screw Torque

1
- Cover Install (Kept) (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 replacethe 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 67 of 100 **BOEING SERVICE BULLETIN 747-30-2081 More Data**  **Qty Identification**  **Name Task**  **Step** (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 20-20-00Cleaning 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 68 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**  **(SHEET 1 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 69 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**  **(SHEET 2 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 70 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**  **(SHEET 3 OF 6)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 71 of 100 **BOEING SERVICE BULLETIN 747-30-2081**The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
**More Data Qty**  **Identification Name**  **Task Step**  at the "A" terminal. (a) 1
- Terminal Block Inspect 1 (b) 1
- Connector Inspect (c) 1
- Wiring Inspect 1
- Cover Remove / Keep 2 to make sure it is a tight connection. (d) (e) (f) 1
- Connector Inspect

not necessary if the connector is loose. (g) 1
- Cover Install (Kept)

**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) 1
- Screw Torque 3

to make sure the connection is tight. 1
- Connector Inspect not necessary if the connector cannot be tightened 1
- Cover Install (Kept)

to make sure the screw is installed correctly and thereis no damage to terminal or screw. 1
- Screw Remove 4

1
- Washer Remove 1
- O-ring Remove (j) 1
- Connector Inspect to make sure the terminal block is not damaged.(k) 1
- Terminal Block Inspect

**FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD (SHEET 4 OF 6)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 72 of 100 **BOEING SERVICE BULLETIN 747-30-2081 More Data**  **Qty Identification**  **Name Task**  **Step 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 assembledwith new, undamaged and correct hardware. (l) (m) 1
- Screw Install (New) 5

1
- Wiring Install (New) (n) 1
- O-ring Install (New) to 25 to 30 inch pounds of torque. Refer to SWPM 20-64-16 as an accepted procedure. (o) (p) 1
- Screw Torque

1
- Cover Install (Kept) (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 replacethe 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 73 of 100 **BOEING SERVICE BULLETIN 747-30-2081 More Data**  **Qty Identification**  **Name Task**  **Step** (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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 74 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 75 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 Imprinted "W1372-H104R/H105B-12" 1 61B20558-10501 Identification Tape 4 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring Practices SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

**FIGURE 5: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 3 AIRPLANES**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 77 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-30-16 as an accepted procedure. 2 324484 Terminal 4 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 81 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  1 W4495-001-12 Wire 1 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve
1 W4495-002-12 Wire 2 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 3

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

**FIGURE 9: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 7 AIRPLANES**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 82 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-10-11 as an accepted procedure. 10 BACS38K5B Strap 5 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  1 W4497-001-12 Wire 1 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve
1 W4497-002-12 Wire 2 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 3

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

**FIGURE 10: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 8 AIRPLANES**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 84 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-10-11 as an accepted procedure. 10 BACS38K5B Strap 5 (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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 85 of 100 **BOEING SERVICE BULLETIN 747-30-2081 FIGURE 11: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD - GROUP 1 THROUGH**  **6 AIRPLANES (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 86 of 100 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 (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 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring Practices Manual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 Imprinted "W1548-H111R/H112B-12" 1 61B20558-10601 Identification Tape 4 (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 - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 89 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 Refer to SWPM 20-30-16 as an accepted procedure. 2 324484 Terminal 4

**FIGURE 15: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD - GROUP 3 AIRPLANES**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 90 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **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 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 (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 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

Refer to SWPM 20-30-12 as an accepted procedure. 2 D-436-38 Splice 3 (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 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS 13-48, Type 10, Class 1, AWG 12 Wire 1 or optional BACS38K5 Tie Strap.

- BMS 13-54, Type 3, Class 1, Color White Lacing Tape Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 2

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  1 W4496-001-12 Wire 1 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve
1 W4496-002-12 Wire 2 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/57-359 Socket Contact 3

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

**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 747-30-2081 Revision 3 December 05, 2011 95 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-10-11 as an accepted procedure. 10 BACS38K5E Strap 5 (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 747-30-2081 Revision 3 December 05, 2011 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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  1 W4498-001-12 Wire 1 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve
1 W4498-002-12 Wire 2 78 inch length is trimmed to full length of new wire. 1 NA728R99 Sleeve Refer to Standard Wiring PracticesManual SWPM 20-64-18 as an accepted procedure. (a) 2 M39029/37-359 Socket Contact 3

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

**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 747-30-2081 Revision 3 December 05, 2011 97 of 100 **BOEING SERVICE BULLETIN 747-30-2081 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-10-11 as an accepted procedure. 10 BACS38K5E Strap 5 (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 747-30-2081 Revision 3 December 05, 2011 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 08, 2006 747-30-2081 Revision 3 December 05, 2011 99 of 100 **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 747-30-2081 Revision 3 December 05, 2011 100 of 100 **BOEING SERVICE BULLETIN 747-30-2081**