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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Unpublished Work - All Rights Reserved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.
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BOEING SERVICE BULLETIN 767-30-0041

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 Table of Contents

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BOEING SERVICE BULLETIN 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

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BOEING SERVICE BULLETIN 767-30-0041

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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.
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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 4.75
 

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BOEING SERVICE BULLETIN 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.

481099
 

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BOEING SERVICE BULLETIN 767-30-0041

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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 1
 

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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.
 

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BOEING SERVICE BULLETIN 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.
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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 0.50
 

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BOEING SERVICE BULLETIN 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
 

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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 56-11
 

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BOEING SERVICE BULLETIN 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 $15,767.00
 

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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 

-4 -3 Number Notes

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.
 

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BOEING SERVICE BULLETIN 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

-102 -101 -2 -1 Name Notes

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 

-4 -3 Number Notes
 

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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.
 

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BOEING SERVICE BULLETIN 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 Sling
 

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BOEING SERVICE BULLETIN 767-30-0041

BLANK PAGE
 

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BOEING SERVICE BULLETIN 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.
 

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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 C391
 

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BOEING SERVICE BULLETIN 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 C392
 

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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 C391
 

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BOEING SERVICE BULLETIN 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

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BOEING SERVICE BULLETIN 767-30-0041

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

FWD

INBD

TERMINAL

BLOCK,

CONNECTOR

1

J5

3 SCREW

2 LUG

J1 J4

W0622

AREA

SPLICE

479998

(SHEET 1 OF 2)
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 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

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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

W0624

480540

(SHEET 1 OF 2)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 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

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BOEING SERVICE BULLETIN 767-30-0041

FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD

GLARESHIELD

1 1.20

1.40

BULB SEAL

2

461858

(SHEET 1 OF 2)
 FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD

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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 233T8300-7 - 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

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BOEING SERVICE BULLETIN 767-30-0041

FIGURE 4: CHANGES TO THE 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 4

480665

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

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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, 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

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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

SPLICE

479762

(SHEET 1 OF 1)
 FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 767-30-0041

FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD

GLARESHIELD

1.40 1

BULB SEAL

1.20

2

466997

(SHEET 1 OF 2)
 FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD

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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 FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 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 4

480669

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 FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD

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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 ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 767-30-0041

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

J1

J5

FWD

INBD

W0624

W0624

SPLICE

AREA

480681

(SHEET 1 OF 1)