December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 39 

### Commercial **Airplane Group**  

# 767

**SPECIAL ATTENTION** 

# Service Bulletin

**Number: 767-30-0041** Date: December 05, 2007 ATA System: 3041 5611 **SUBJECT:** ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing - Windshield Inspection and Replacement 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue 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unless provided in writing by Boeing.**BLANK PAGE** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

BLANK PAGE**Table of Contents** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**Table of Contents** Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 13 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 13 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 18 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 19 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD. . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD . . . . . . . . . . . . . . . . . . . 30 FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD . 32 FIGURE 5: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD . . . . . . . . 34 FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD . . . . . . . . . . . . . . . . . . 35 FIGURE 7: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD. 37 FIGURE 8: CHANGES TO THE WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39**Table of Contents** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

BLANK PAGEDecember 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 39 

### Commercial **Airplane Group**  

# 767

**SPECIAL ATTENTION** 

# Service Bulletin

**Number: 767-30-0041** 

### Summary Date: December 05, 2007 ATA System: 3041 5611 **SUBJECT:** ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing - Windshield Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS**
None **BACKGROUND** This service bulletin gives instructions to do an 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. 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 received nine reports from eight operators of electrical arcs at the terminal blocks of the flight compartment windows. More than one of these reports included data to show that the results of the arcs were open flame incidents. One operator found an indication of damage at a terminal and tightened a loose connection. The terminal had internal damage that could not be seen. Less than six months after the connection was tightened there was a report from the operator of an open flame incident on the same windshield. The electrical connections on the windows are made with lugs that are attached with screws. 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 is loose terminal connections. A loose connection increases the heat at the terminal which can cause damage to the internal solder joint. Damaged solder joints are the primary cause for the electrical arcs. The primary causes of loose connections are the incorrect torque of the screw or an incorrectly installed screw. The inspection given in this service bulletin is to look for damage or a loose electrical connection on the windshield. If there are indications of electrical arcs or damage to the electrical connection, the windshield is replaced. If there is a loose electrical connection, the correct torque is applied to tighten it. If a connection cannot be tightened to the correct torque, the windshield is replaced. When a windshield with an electrical connection that uses pins and sockets is installed, the related wire bundle on the airplane is changed.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 39 Boeing Service Related Problem (SRP) 767-SRP-56-0015 is related to this service bulletin. **ACTION** (PRR B12901-56S) In the flight compartment, do an inspection of the J5 terminal on the left and the right windshields. Replace windshields that use screws and lugs for the electrical connections with a windshield that uses pins and sockets for the electrical connections. Cut the bulb seal to give clearance for terminals on the new windshield. Change the related wire bundle. **EFFECTIVITY** 767-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** See Service Bulletin Paragraph 1.E. for compliance information. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
**MANPOWER**

**MATERIAL INFORMATION** Boeing Supplied Kits/Parts Refer to Paragraph 2.A., Material - Price and Availability. **Work Package Total Task Hours Elapsed Hours** Work Package 1 - Inspection of the Left Windshield 0.25 0.25 Work Package 2 - Inspection of the Right Windshield 0.25 0.25 Work Package 3 - Windshield and Wiring Change - Left Side 8.5 4.75 Work Package 4 - Windshield and Wiring Change - Right Side 8.5 4.75December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

WORK PACKAGE 3: CUT THE BULB SEAL AND REPLACE THE LEFT WINDSHIELD. CHANGE THE RELATED WIRING. WORK PACKAGE 1: INSPECT THE LEFT WINDSHIELD WORK PACKAGE 2: INSPECT THE RIGHT WINDSHIELD WORK PACKAGE 4: CUT THE BULB SEAL AND REPLACE THE RIGHT WINDSHIELD. CHANGE THE RELATED WIRING.481099December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

BLANK PAGEDecember 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 39 

### Commercial **Airplane Group**  

# 767

**SPECIAL ATTENTION** 

# Service Bulletin

**Number: 767-30-0041** Date: December 05, 2007 ATA System: 3041 5611 **SUBJECT:** ICE AND RAIN PROTECTION - Flight Compartment Window Anti-Icing - Windshield Inspection and Replacement

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-56S for data about this change.

Airplane models: 767-400ER IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER CONTINENTAL AIRLINES (CAL) 1 VQ071–VQ086 DELTA AIR LINES (DAL) 1 VQ001–VQ021 IDENTIFICATION BY VARIABLE NUMBER **GROUP CONFIGURATION DESCRIPTION** 1 - Airplanes with windshields that use screw and lug electrical connections.

**Variable Group** VQ001–VQ021 1 VQ071–VQ086 1December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. **B. Concurrent Requirements**
None **C. Reason** This service bulletin gives instructions to do an inspection 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. 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 received nine reports from eight operators of electrical arcs at the terminal blocks of the flight compartment windows. More than one of these reports included data to show that the results of the arcs were open flame incidents. One operator found an indication of damage at a terminal and tightened a loose connection. The terminal had internal damage that could not be seen. Less than six months after the connection was tightened there was a report from the operator of an open flame incident on the same windshield. The electrical connections on the windows are made with lugs that are attached with screws. 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 is loose terminal connections. A loose connection increases the heat at the terminal which can cause damage to the internal solder joint. Damaged solder joints are the primary cause for the electrical arcs. The primary causes of loose connections are the incorrect torque of the screw or an incorrectly installed screw. The inspection given in this service bulletin is to look for damage or a loose electrical connection on the windshield. If there are indications of electrical arcs or damage to the electrical connection, the windshield is replaced. If there is a loose electrical connection, the correct torque is applied to tighten it. If a connection cannot be tightened to the correct torque, the windshield is replaced. When a windshield with an electrical connection that uses pins and sockets is installed, the related wire bundle on the airplane is changed. Boeing Service Related Problem (SRP) 767-SRP-56-0015 is related to this service bulletin. **D. Description** In the flight compartment, an inspection is done of the left and the right windshields. A windshield that uses pin and socket electrical connections is installed. The bulb seal is cut to give clearance for terminals that are on the new windshield. When a windshield that uses the pin and socket electrical connections is installed, the related wire bundle is also changed.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**E. Compliance**

**F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/ JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. Compliance Sequence **Condition Action Compliance Time Repeat Interval** Windshield that uses screws and lugs for the electrical connections Do the Inspections given in Work Packages 1 and 2 Within 500 flight hours after the date on this service bulletin. Every 6000 flight hours until Work Packages 3 and 4 are done. Windshield replaced with the same screw and lug type windshield Do the Inspections given in Work Packages 1 and 2. Within 500 flight hours of windshield replacement. Every 6000 flight hours until Work Packages 3 and 4 are done. Windshield that uses screws and lugs for the electrical connections Replace with windshield that uses pins and sockets for the electrical connections No time limit. Terminating action for this bulletin.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 39 **G. Manpower** The table below shows an estimate of the task-hours necessary to do this change for each windshield. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Work Package 1 - Inspection of the Left Windshield
**Task Number of**  **Persons Task-Hours Elapsed Hours** Figure 1 1 0.25 0.25 Total per Windshield 0.25 0.25 Work Package 2 - Inspection of the RIght Windshield
**Task Number of**  **Persons Task-Hours Elapsed Hours** Figure 2 1 0.25 0.25 Total per Windshield 0.25 0.25 Work Package 3 - Replacement of the Left Windshield and Changes to the Related Wiring
**Task Number of**  **Persons Task-Hours Elapsed Hours** Access 2 1.0 0.50 Remove the Left Windshield 2 2.5 1.25 Figure 3 - Cut the Bulb Seal 1 0.25 0.25 Figures 4 and 5 - Change the Wiring 1 0.50 0.50
Install the Left Windshield 2 3.0 1.5 Tests 1 0.25 0.25 Close 2 1.0 0.50 Total per Windshield 8.5 4.75 Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring
**Task Number of**  **Persons Task-Hours Elapsed Hours** Access 2 1.0 0.50 Remove the Right Windshield 2 2.5 1.25 Figure 6 - Cut the Bulb Seal 1 0.25 0.25 Figures 7 and 8 - Change the Wiring 1 0.50 0.50December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**H. Weight and Balance Changes**
None **I. Electrical Load Data** Not changed **J. References** 1. Existing Data: a. Engineering Change Memo PRR B12901-56S b. Service Related Problem (SRP) 767-SRP-56-0015 c. 767 Aircraft Maintenance Manual (AMM) 30-41-00, 56-11-01 d. 767 Wiring Diagram 30-41-11, 30-41-12 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-13, 20-10-18, 20-10-19, 20-30-12, 20-63-19, 20-64-16 f. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-10 g. Boeing Service Bulletin 767-56-0012 2. Data supplied with this Service Bulletin:
None 3. Installation Drawings Used in the Preparation of this Service Bulletin:
None Install the Right Windshield 2 3.0 1.5 Tests 1 0.25 0.25 Close 2 1.0 0.50 Total per Windshield 8.5 4.75 Work Package 4 - Replacement of the Right Windshield and Changes to the Related Wiring
**Task Number of**  **Persons Task-Hours Elapsed Hours**December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**K. Publications Affected**

**L. Interchangeability and Intermixability of Parts** Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. **Publication Chapter-Section** 767 Maintenance Manual 30-41, 56-11 767 Wiring Diagram Manual 30-41 767 Illustrated Parts Catalog 56-11December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. Kit availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **Kit Number Name ROLT**  **(Weeks) Unit Price thru**  **Dec 31/2007** 015T0500-3 Top Kit - Left Windshield, PPG with Hydrophobic coating 20 $15,767.00

015T0500-4 Top Kit - Right Windshield, PPG with Hydrophobic coating 20 $15,767.00December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**C. Parts Necessary For Each Airplane** 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
**NOTE:** One left top kit and one right top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.
**Kit 015T0500**

**New Part Number QTY**  **Name Existing Part**  **Number Notes -4 -3**  015T0500-3 . - Top Kit - Left Windshield, PPG with Hydrophobic coating 015T0500-4 - . Top Kit - Right Windshield, PPG with Hydrophobic coating 141W7400-43 . 1 Left Windshield, PPG with Hydrophobic coating 141T4801-49 (a) (b) (c) (d) (e) (g) (i) 141W7400-44 1 . Right Windshield, PPG with Hydrophobic coating 141T4801-50 (a) (b) (c) (d) (f) (h) (i) 289T1146-1 . 1 Wire Kit - Change to the Left Windshield Terminal Connectors 289T1146-2 1 . Wire Kit - Change to the Right Windshield Terminal Connectors (a) Discard the existing part. (b) This part is used in production. (c) You cannot use the existing part to replace the new or changed part. (d) Operators can install Left Windshield part number 141T4801-59 and Right Windshield part number 141T4801-60 with serial numbers 04xxxH or 05xxxH. (e) As an option operators can install Left Windshield part number 141W7400-31 or 141W7400-33 with serial numbers 04xxxH or 05xxxH. (f) As an option operators can install Right Windshield part number 141W7400-32 or 141W7400-34 with serial numbers 04xxxH or 05xxxH.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

(g) As an option operators can install Left Windshield part number 141W7400-35 or 141W7400-41. Windshield part numbers 141W7400-35 and 141W7400-41 can be made from Windshield part numbers 141W7400-31 and 141W7400-33 with serial numbers 06339H or higher by incorporating Boeing Service Bulletin 767-56-0012. (h) As an option operators can install Right Windshield part number 141W7400-36 or 141W7400- 42. Windshield part numbers 141W7400-36 and 141W7400-42 can be made from Windshield part numbers 141W7400-32 and 141W7400-34 with serial numbers 06339H or higher by incorporating Boeing Service Bulletin 767-56-0012. (i) PPG Aerospace - Transparencies Div Glass (V53117) 1719 U.S. Highway 72 East P.O. Box 2200 Huntsville, AL 35811 - 9660
**Kit 289T1146**

**New Part Number QTY**  **Name Notes -102 -101 -2 -1**  289T1146-1 . . . - Wire Kit - Change to the Left Windshield Terminal Connectors 289T1146-2 . . - . Wire Kit - Change to the Right Windshield Terminal Connectors 289T1146-101 . - 1 . Wire Bundle Assembly W0622 289T1146-102 - . . 1 Wire Bundle Assembly W0624 - . 1 . . Wire Identified W0622-051-12 (a)
- . 1 . . Wire Identified W0622-052-12 (a)
- 1 . . . Wire Identified W0624-051-12 (a)
- 1 . . . Wire Identified W0624-052-12 (a) D436-38 3 3 . . Splice (b) M39029/57-359 3 3 . . Socket Contact (b) NA728R99 1 1 . . BMS 13-52 Expandable Sleeve (a) BMS 13-48, Type 10, Class 1, AWG 12, length 84 inches (b) There are more parts than are necessary. **Kit 015T0500**

**New Part Number QTY**  **Name Existing Part**  **Number Notes -4 -3** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified: The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the number of parts changed on each airplane.

4. Parts Removed and Not Replaced:
None **D. Parts Necessary to Change Spares**
None **Part Number / Specification QTY Name Notes**  BMS 13-54 10 feet Lacing Tape, Red (a) (b) (c) BMS 13-54 10 feet Lacing Tape, Green (a) (b) (d) (a) Type 3, Class 1 (b) Gudebrod Incorporated (V82110) Griffith Towers PO Box 357 Pottstown, PA 19464 (c) BACS38K5C, red Tie Strap is optional. See the Qualified Products List at the end of the Boeing Material Specification (BMS) for the supplier data. (d) BACS38K5F, green Tie Strap is optional. See the Qualified Products List at the end of the Boeing Material Specification (BMS) for the supplier data.

**Existing Part Number QTY Name New Part Number Notes**  233T8300-41 1 Glareshield 233T8300-48 (a) (b) 233T8300-47 1 Glareshield 233T8300-49 (a) (b) (a) Make the change given in this service bulletin. (b) This part is used in production.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**E. Special Tooling - Price and Availability** Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the date the tools will be used.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin number and submit purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA (Service Bulletin 767-30-0041) **F. Special Tooling Necessary to do this Service Bulletin** To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available. Purchase Data:

**Tool Kit Number Name Unit Price**  **thru Dec 31/2007**  A56001-2 (part of Sling Set A56001-15) Windshield Handling Sling $625.00

**Tool Kit Number Name** A56001-2 (part of Sling Set A56001-15) Windshield Handling SlingDecember 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

BLANK PAGEDecember 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**3. ACCOMPLISHMENT INSTRUCTIONS**
**A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
**NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. The work instructions are divided into work packages. Task-Hours and Elapsed-Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 4. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches — Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual, Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 7. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used.December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**B. WORK INSTRUCTIONS WORK PACKAGE 1 - INSPECTION OF THE LEFT WINDSHIELD** 
**WARNING:** BEFORE YOU DO MAINTENANCE ON THE WINDSHIELD HEAT SYSTEM, OPEN THE CIRCUIT BREAKER GIVEN IN THE STEP THAT FOLLOWS. IF THIS CIRCUIT BREAKER IS NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK WHEN YOU TOUCH THE TERMINAL. 1. Open this circuit breaker and attach a DO-NOT-CLOSE tag to it:

2. Do an inspection of the left windshield as given in Figure 1. 3. If the left windshield is not in a serviceable condition, replace it before the subsequent revenue flight. Refer to 767 AMM 56-11-01 as an accepted procedure. If the existing windshield is replaced with one of the same type, it will be necessary to do this inspection again within 500 flight hours. Windshields in serviceable condition can continue to be used with inspections every 6000 flight hours, or until the work given in Work Package 3 is done. 4. Remove the DO-NOT-CLOSE tag and close this circuit breaker: **Panel Position Name Circuit Breaker** P36 H4 WINDOW HT NO 1, LEFT C391

**Panel Position Name Circuit Breaker** P36 H4 WINDOW HT NO 1, LEFT C391December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**WORK PACKAGE 2 - INSPECTION OF THE RIGHT WINDSHIELD**
**WARNING:** BEFORE YOU DO MAINTENANCE ON THE WINDSHIELD HEAT SYSTEM, OPEN THE CIRCUIT BREAKER GIVEN IN THE STEP THAT FOLLOWS. IF THIS CIRCUIT BREAKER IS NOT OPEN, YOU CAN GET AN ELECTRICAL SHOCK WHEN YOU TOUCH THE TERMINAL. 1. Open this circuit breaker and attach a DO-NOT-CLOSE tag to it:

2. Do an inspection of the right windshield as given in Figure 2. 3. If the right windshield is not in a serviceable condition, replace it before the subsequent revenue flight. Refer to 767 AMM 56-11-01 as an accepted procedure. If the existing windshield is replaced with one of the same type, it will be necessary to do this inspection again within 500 flight hours. Windshields in serviceable condition can continue to be used with inspections every 6000 flight hours, or until the work given in Work Package 4 is done. 4. Remove the DO-NOT-CLOSE tag and close this circuit breaker: **Panel Position Name Circuit Breaker** P37 F4 WINDOW HT NO 1, RIGHT C392

**Panel Position Name Circuit Breaker** P37 F4 WINDOW HT NO 1, RIGHT C392December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**WORK PACKAGE 3 - REPLACEMENT OF THE LEFT WINDSHIELD AND CHANGES TO THE RELATED WIRE BUNDLE**  **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. Open this circuit breaker and attach a DO-NOT-CLOSE tag to it:

2. Remove the left windshield. Use the windshield handling sling, A56001-2. Refer to 767 AMM 56-11-01 as an accepted procedure. 3. Cut the bulb seal for the left windshield as given in Figure 3. 4. Change the wiring for the window heat on the left windshield as given in Figure 4 and Figure 5. 5. Install the left windshield. Use the windshield handling sling, A56001-2. Refer to 767 AMM 56-11-01 as an accepted procedure. The new windshield information is shown below:

6. Remove the DO-NOT-CLOSE tag and close this circuit breaker:

7. Do the test "Operational Test - Flight Compartment Window Anti-Icing System" as given in 767 AMM 30-41-00. 8. Put the airplane in a serviceable condition. **Panel Position Name Circuit Breaker** P36 H4 WINDOW HT NO 1, LEFT C391

**Supplier Part Number Description Part of Top Kit** PPG 141W7400-43 Hydrophobic Coating 015T0500-3

**Panel Position Name Circuit Breaker** P36 H4 WINDOW HT NO 1, LEFT C391December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**WORK PACKAGE 4 - REPLACEMENT OF THE RIGHT WINDSHIELD AND CHANGES TO THE RELATED WIRE BUNDLE**  **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. Open this circuit breaker and attach a DO-NOT-CLOSE tag to it:

2. Remove the right windshield. Use the windshield handling sling, A56001-2. Refer to 767 AMM 56-11-01 as an accepted procedure. 3. Cut the bulb seal for the right windshield as given in Figure 6. 4. Change the wiring for the window heat on the right windshield as given in Figure 7 and Figure 8. 5. Install the right windshield. Use the windshield handling sling, A56001-2. Refer to 767 AMM 56-11-01 as an accepted procedure. The new windshield information is shown below:

6. Remove the DO-NOT-CLOSE tag and close this circuit breaker:

7. Do the test "Operational Test - Flight Compartment Window Anti-Icing System" as given in 767 AMM 30-41-00. 8. Put the airplane in a serviceable condition. **Panel Position Name Circuit Breaker** P37 F4 WINDOW HT NO 1, RIGHT C392

**Supplier Part Number Description Part of Top Kit** PPG 141W7400-44 Hydrophobic Coating 015T0500-4

**Panel Position Name Circuit Breaker** P37 F4 WINDOW HT NO 1, RIGHT C392**FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD** 

FWD INBD TERMINAL BLOCK, CONNECTOR 1 J5 3 SCREW

LUG 2 J1 J4

W

0 6 2 2

AREA SPLICE479998

**(SHEET 1 OF 2) FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **STEP TASK NAME IDENTIFICATION QTY MORE DATA**

1 Inspect Terminal Block - 1 at the J5 connection Connector - 1 Wiring Wire bundle W0622 1 **NOTE:** If there is a melted terminal, black marks, or discoloration, the window must be replaced. **NOTE:** If there is damage to the wiring, it must be repaired. Refer to Standard Wiring Practices Manual SWPM 20-10-13 as an accepted procedure.

2 Inspect Lug - 1 to make sure it is a tight connection. **NOTE:** If the lug at the terminal moves with light manual pressure, then the screw that attaches it must be tightened. There are three causes for a loose terminal. 1-The screw is not tightened to the correct torque 2-The terminal is damaged 3-The incorrect screw is installed. The correct screw part number is given in SWPM 20-64-16. **CAUTION:** DO NOT OVER TIGHTEN. THE TERMINAL CAN BE DAMAGED BY TOO MUCH FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE WINDOW.

3 Turn Screw - 1 to 25 to 30 inch pounds of torque. Inspect Lug 1 to make sure the connection is tight. **NOTE:** The screw is only tightened if the lug is loose. If it is the correct screw and it cannot be tightened to 25 to 30 inch pounds, the window must be replaced.

**(SHEET 2 OF 2) FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**

FWD INBD TERMINAL BLOCK, CONNECTOR 1 J1 J4

J5

3 SCREW 2 LUG

AREA SPLICE W 0 6 2 4480540

**(SHEET 1 OF 2) FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. **STEP TASK NAME IDENTIFICATION QTY MORE DATA**

1 Inspect Terminal Block - 1 at the J5 connection Connector - 1 Wiring Wire bundle W0624 1 **NOTE:** If there is a melted terminal, black marks, or discoloration, the window must be replaced. **NOTE:** If there is damage to the wiring, it must be repaired. Refer to Standard Wiring Practices Manual SWPM 20-10-13 as an accepted procedure.

2 Inspect Lug - 1 to make sure it is a tight connection. **NOTE:** If the lug at the terminal moves with light manual pressure, then the screw that attaches it must be tightened. There are three causes for a loose terminal. 1-The screw is not tightened to the correct torque 2-The terminal is damaged 3-The incorrect screw is installed. The correct screw part number is given in SWPM 20-64-16. **CAUTION:** DO NOT OVER TIGHTEN. THE TERMINAL CAN BE DAMAGED BY TOO MUCH FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE WINDOW.

3 Turn Screw - 1 to 25 to 30 inch pounds of torque. Inspect Lug 1 to make sure the connection is tight. **NOTE:** The screw is only tightened if the lug is loose. If it is the correct screw and it cannot be tightened to 25 to 30 inch pounds, the window must be replaced.

**(SHEET 2 OF 2) FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD**

GLARESHIELD 1 1.20 1.40

BULB SEAL

2461858

**(SHEET 1 OF 2) FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. **STEP TASK NAME IDENTIFICATION QTY MORE DATA CAUTION:**  DO NOT CUT THE STRUCTURE BELOW THE BULB SEAL. THE WINDOW SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION IF THE FINISH IS DAMAGED. DAMAGE TO THE FINISH MUST BE REPAIRED.

1 Cut Bulb Seal 233T8300-7 - to clear the new terminal. **NOTE:** If the finish below the bulb seal is damaged, it must be sealed with chemical treatment and primer. Refer to Standard Overhaul Practices Manual SOPM 20-41-02 and SOPM 20-43-03 as accepted procedures. 2 Identify Glareshield 233T8300-48 - (a) (a) Part mark with new part number. Rubber-Stamp or Hand Write. 12 characters per inch. Use abrasive resistance ink. Refer to SOPM 20-50-10 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**FIGURE 4: CHANGES TO TH E WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD** 

(J5) (J4)

D1660 D1658 

## W0622

209R-12 209B-12

SM14 SM13 SM14 SM13

052-12 051-12 J1

J5

B35 LEFT WINDOW 1 A-C

B35 LEFT WINDOW 1 =1

=1

=1 A-B A-A D1656 (J1)

2 1 4

5 5 3

3 4480665 REFERENCE: WIRING DIAGRAM 30-41-11

DELETED WIRE OR FORMER ROUTING ADDED WIRE OR NEW ROUTING

EXISTING WIRE

**(SHEET 1 OF 2) FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 Wire BMS 13-48, Type 10, Class 1, AWG 12, 1 2 Wire BMS 13-48, Type 10, Class 1, AWG 12 1 Lacing Tape BMS 13-54, Type 3, Class 1, Red - or optional BACS38K5C Tie Strap. Red is for left channel separation. Refer to Standard Wiring Practices Manual SWPM 20-10-19 as an accepted procedure. 3 Sleeve NA728R99 2 Refer to SWPM 20-10-18 as an accepted procedure. 4 Socket Contact M39029/57-359 2 Refer to SWPM 20-63-19 as an accepted procedure. **NOTE:** Isopropyl alcohol is applied to the installation tool and on the contact before installation of the contact. Isopropyl alcohol is a lubricant that helps with installation of the contact in the connector. 5 Splice D-436-38 2 Refer to SWPM 20-30-12 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 5: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

**FIGURE 5: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD**

FWD INBD J1 W0622

W0622 J5

AREA SPLICE479762

**(SHEET 1 OF 1) FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD**

GLARESHIELD 1.40 1 BULB SEAL

1.20

2466997

**(SHEET 1 OF 2) FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. **STEP TASK NAME IDENTIFICATION QTY MORE DATA CAUTION:**  DO NOT CUT THE STRUCTURE BELOW THE BULB SEAL. THE WINDOW SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION IF THE FINISH IS DAMAGED. DAMAGE TO THE FINISH MUST BE REPAIRED.

1 Cut Bulb Seal 233T8300-8 - to clear the new terminal. **NOTE:** If the finish below the bulb seal is damaged, it must be sealed with chemical treatment and primer. Refer to Standard Overhaul Practices Manual SOPM 20-41-02 and SOPM 20-43-03 as accepted procedures. 2 Identify Glareshield 233T8300-49 - (a) (a) Part mark with new part number. Rubber-Stamp or Hand Write. 12 characters per inch. Use abrasive resistance ink. Refer to SOPM 20-50-10 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 7: CHANGES TO THE WIRING FO**  **R THE WINDOW HEAT ON THE RIGHT WINDSHIELD** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**FIGURE 7: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD**

B38 RIGHT WINDOW 1 B38 RIGHT WINDOW 1

D1670 D1668 D1666

201R-12 201B-12 

## W0624

(J5) (J4)

SM14 SM13 SM14 SM13

052-12 051-12 J1

J5 A-C =1

=1

=1 A-B A-A (J1)

2 1 4

5 5 3

3 4480669 REFERENCE: WIRING DIAGRAM 30-41-12 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING

**(SHEET 1 OF 2) FIGURE 7: CHANGES TO THE WIRING FO**  **R THE WINDOW HEAT ON THE RIGHT WINDSHIELD** December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 39 

### BOEING SERVICE BULLETIN 767-30-0041

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 Wire BMS 13-48, Type 10, Class 1, AWG 12 1 2 Wire BMS 13-48, Type 10, Class 1, AWG 12 1 Lacing Tape BMS 13-54, Type 3, Class 1, Green - or optional BACS38K5F Tie Strap. Green is for right channel separation. Refer to Standard Wiring Practices Manual SWPM 20-10-19 as an accepted procedure. 3 Sleeve NA728R99 2 Refer to SWPM 20-10-18 as an accepted procedure. 4 Socket Contact M39029/57-359 2 Refer to SWPM 20-63-19 as an accepted procedure. **NOTE:** Isopropyl alcohol is applied to the installation tool and on the contact before installation of the contact. Isopropyl alcohol is a lubricant that helps with installation of the contact in the connector. 5 Splice D-436-38 2 Refer to SWPM 20-30-12 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 8: CHANGES TO THE WIRE ROUTIN**  **G FOR THE WINDOW HEAT ON THE RIGHT WIND SHIELD**  December 05, 2007 767-30-0041 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 39 

### BOEING SERVICE BU **LLETIN 767-30-0041**

**FIGURE 8: CHANGES TO THE WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD**

J1

J5

FWD INBD W 0 6 2 4

W

0 6 2 4

SPLICE AREA480681

**(SHEET 1 OF 1)**