July 19, 2006

Revision 2: April 19, 2010 757-30-0019

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 58

Commercial

Airplane

Group 757

SPECIAL ATTENTION

Service Bulletin

Number: 757-30-0019

Date: July 19, 2006

Revision 2: April 19, 2010

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Unpublished Work - All Rights Reserved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

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

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

or otherwise.
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 Table of Contents

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BOEING SERVICE BULLETIN 757-30-0019

Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 28

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 28

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 34

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD. . . . . . . . . . . . . . . . . . . . . . . . 46

FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD . . . . . . . . . . . . . . . . . . . 51

FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD . 52

FIGURE 5: WIRE ROUTING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD . . . . . . . . 54

FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD . . . . . . . . . . . . . . . . . . 55

FIGURE 7: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD. 56

FIGURE 8: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD . . . . . . . 58
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Commercial

Airplanes 757

SPECIAL ATTENTION

Service Bulletin

Number: 757-30-0019 Revision Transmittal Sheet

Original Issue: July 19, 2006

Revision 2: April 19, 2010

ATA System: 3041 5611

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

Inspection and Replacement

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary on airplanes changed as shown in the original issue and Revision 1 of this service 

bulletin.

Operators that have not done the terminating action in the compliance of this service bulletin will now need to 

also inspect the J1 and J4 windshield lugs and terminals.

REASON FOR REVISION

This revision is sent to tell operators that have not done the terminating action in the compliance of this service 

bulletin will now need to also inspect the J1 and J4 windshield lugs and terminals.

These sections were changed:

1. Summary Background, Planning Information 1.D., Reason and 1.J.1., Existing Data, Service Related 

Problem (SRP) 757-SRP-30-0031 has been added.

2. Summary Action and Planning Information 1.D., Description, have been changed to add the inspection of 

the J1 and J4 lugs and terminals.

3. In Planning Information 1.E., Compliance, the compliance table has been changed to add the inspection 

of windshield J1 and J4 lugs and terminals.

4. In Planning Information 1.G., Manpower, manpower tables have been changed to add time for inspections 

of the J1 and J4 lugs and terminals.

5. In Planning Information 1.J.1., Existing Data, Standard Wiring Practices Manual (SWPM) reference 20-64-

16 and Illustrated Parts Catalog (IPC) reference 30-41-52 have been added.

6. In Planning Information 1.K.2., Publications Affected, Damage Tolerance Based Structural Inspection 

evaluation statement has been added.
 

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7. In Material Information 2.C.1., Kits/Parts, the kit table has been changed to show that the 280N3355-1 wire 

kit contains the -101 kit and 280N3355-2 wire kit contains the -102 kit.

8. In the Work Instructions 3.B., step 3 of Work Packages 1 and 2 has been changed to add new compliance 

time thresholds for windshield inspections. 

9. In Figure 1 and Figure 2 the illustration has been changed to add the inspection of the J1 and J4 lugs and 

terminals.

10. In Figure 1 and Figure 2 new illustrations have been added to show the installation of the lug and the correct 

alignment of the lug on the terminal.

11. In Figure 1 and Figure 2, step 2, the step table note has changed to show another cause of a loose terminal. 

The Standard Overhaul Practices Manual (SOPM) reference 20-43-03 has been changed to Standard 

Wiring Practices Manual (SWPM) reference 20-64-16 and Illustrated Parts Catalog (IPC) reference 30-41-

52 has been added. New steps have been added to give instructions to inspect the screw if it cannot be 

tightened in step 3.

12. Figure 6, in the illustration, circle note 2 has been moved to point to an area near the bulb seal. This is the 

area where the part mark can be applied.

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

paragraph for changes.

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

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: July 19, 2006

Revision 1: December 19, 2007

Revision 2: April 19, 2010
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Commercial

Airplanes 757

SPECIAL ATTENTION

Service Bulletin

Number: 757-30-0019 Summary

Original Issue: July 19, 2006

Revision 2: April 19, 2010

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 the electrical connections 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 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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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 Problems (SRP) 757-SRP-30-0031 and 757-SRP-56-0015 are related to this service 

bulletin.

As a part of a service bulletin validation program, this change was completed on airplane NB141 by Service 

Bulletin 757-30-0019 Validation Copy 1 before the initial release of this service bulletin. The change completed 

on airplane NB141 by Service Bulletin 757-30-0019 Validation Copy 1 is equivalent to the initial release of this 

service bulletin. Airplane NB141 has the configuration of a Group 1 airplane.

ACTION (PRR 54530-265S)

In the flight compartment, do an inspection of the J1, J4 and J5 terminals 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

All 757-200, -200CB, and -200PF Airplanes except NA001. Refer to Paragraph 1.A.1., Airplanes for the list of 

affected airplanes. 

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service 

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin 

mandatory.

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 1.5 1.5

Work Package 2 - Inspection of the Right Windshield 1.5 1.5

Work Package 3 - Left Windshield Replacement and 

Wiring Change 

8.5 4.75

Work Package 4 - Right Windshield Replacement 

and Wiring Change 

8.5 4.75
 

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BOEING SERVICE BULLETIN 757-30-0019

482078

CUT THE BULB SEAL AND

CUT THE BULB SEAL AND

WORK PACKAGE 4:

REPLACE THE RIGHT WINDSHIELD.

CHANGE THE RELATED WIRING.

INSPECT THE RIGHT WINDSHIELD

WORK PACKAGE 2:

WORK PACKAGE 3:

CHANGE THE RELATED WIRING.

REPLACE THE LEFT WINDSHIELD.

INSPECT THE LEFT WINDSHIELD

WORK PACKAGE 1:
 

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Commercial

Airplanes 757

SPECIAL ATTENTION

Service Bulletin

Number: 757-30-0019

Original Issue: July 19, 2006

Revision 2: April 19, 2010

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 D624N001 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 54530-265S for data about this change.

Airplane models:

757-200 757-200CB 757-200PF

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AIR ASTANA (AKZ)

1 NB561 NT231 NT411–NT412

GROUP CONFIGURATION DESCRIPTION

1 - Airplanes with windshields that use screw and 

lug electrical connections. The location of the 

circuit breaker for window heat is in a different 

location than for Group 2.

2 - Airplanes with windshields that use screw and 

lug electrical connections. The location of the 

circuit breaker for window heat is in a different 

location than for Group 1.
 

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BOEING SERVICE BULLETIN 757-30-0019

AIR CHINA SOUTHWEST BRANCH (XIN)

1 NB291–NB295 NB297–NB299 NB301–NB302 NB327

NT201–NT202

AIR FINLAND (FNL)

1 NB221 NB239 NB454

AIR GREENLAND AS (GRL)

1 NA350

AIR ITALY (RIT)

1 NC057 NE162–NE164

AIR ITALY POLSKA (IPL)

1 NE301

AIRBALTIC CORPORATION (BCB)

1 NT905 NT907

ALADIA AIRLINES (TPT)

1 NA194 NC066

AMERICA WEST AIRLINES (AMW)

1 NB039

AMERICAN AIRLINES (AAL)

1 ND011–ND044 ND046–ND059 ND111–ND113 ND161–ND166

ND168–ND199 NT352 NT731–NT750 NT971–NT985

ARROW AIR (ARW)

1 NA025

ASTRAEUS, LTD. (AUA)

1 NB134 NB142 NB204 NB225

ND401

ATLASJET AIRLINES (ABE)

1 NT375 NT910–NT911

AURELA (URE)

1 NT285

AVIANCA (AVI)

1 NA341 NA347 NA351 NA406

NB070 NB324 NB326

AVIATION CAPITAL GROUP (CGP)

1 NA348

AWAS (AWW)

1 NB133 NB135
 

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AZERBAIJAN AIRLINES (AHY)

1 ND248 NT437–NT438

BABCOCK & BROWN A/C MANAGEMENT (BBB)

1 NC062 NT281 NT283

BELAIR AIRLINES (BLB)

1 NT426–NT427

BLUE CITY HOLDING (BCY)

1 NB141

BLUE PANORAMA AIRLINES (BPA)

1 NC094 NT351

BOEING CAPITAL CORPORATION (ZMF)

1 NE302

BRITISH AIRWAYS (BAB)

1 NA237–NA239 NA303–NA305 NA398 NB581–NB583

NT401–NT403

CAM (CGM)

1 NA520

CARGOJET AIRWAYS LTD. (WNT)

1 NA343

CEBU PACIFIC AIR (CEB)

1 NA301–NA302

CHINA SOUTHERN AIRLINES (GUN)

1 NA349 NB065–NB066 NB261–NB267 NB296

CHINA XINJIANG AIRLINES (XIJ)

1 NB325 NB328 NT381–NT386 NT408–NT409

CONTINENTAL AIRLINES (CAL)

1 ND301–ND322 NT751–NT769

CORPORACION YGNUS AIR (REI)

1 NA395 ND241

DELTA AIR LINES (DAL)

1 NA501–NA519 NA521–NA586 NB001–NB004 NC076–NC084

NC091 NC093 NE008 NT353–NT354

NT360 NT371–NT373 NT701–NT730

DHL INTERNATIONAL (DHI)

1 NA201–NA204 NA206–NA213 NA215–NA236

EAGLE AVIATION (EAE)

1 NC052 NC067
 

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EL AL ISRAEL AIRLINES (ELA)

1 ND002 ND004–ND007

ESTADO NACIONAL ARGENTINO ENA (ESA)

1 NB144

ETHIOPIAN AIRLINES (ETH)

1 NC092 NE201–NE204 NT248 NT282

NT356

2 NC951

EUROATLANTIC AIRWAYS (MAE)

1 NA196–NA197

EUROPEAN AIR TRANSPORT (EPT)

1 NC059

2 NC974

EVERGREEN A/C SALES & LEASING (EVG)

1 NA006 NA008

FAR EASTERN AIR TRANSPORT (FAT)

1 NT881–NT885

2 NC973

FEDEX (FED)

1 NA346 NA394 NA444 NB064

NB073 NB131–NB132 NB140 NB167

NB424 NB501 NB503 NB508

FINNAIR (FIN)

1 NT341–NT347

FLYGLOBESPAN.COM (FGS)

1 NB224

FUNAIR (FUN)

1 NT909

GENERIC CUSTOMER/SUPPLIER (XXX)

1 NC023

HOLA AIRLINES (HLB)

1 NA399

HONEYWELL AEROSPACE (SGC)

1 NA005

IBERIA AIRLINES (IBE)

1 NT906 NT908
 

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BOEING SERVICE BULLETIN 757-30-0019

ICELANDAIR (ICE)

1 NA028 NB079 NB138–NB139 NB421

ND201–ND203 ND244–ND247 NN001–NN002 NT861–NT862

NT913 NT915–NT916

2 NC971

ILFC (ILF)

1 NC056 NC072–NC073

JET2.COM LTD (CEX)

1 NA344 NA396–NA397 NB061–NB063 NB071–NB072

NB145

JETWORKS LEASING (JTW)

1 NA442

KRASAIR (ZXD)

1 NT901–NT904

L-3 C.I.S. (CIJ)

1 NB146–NB148 NC051 NC070 NC075

NT436

LEGATUM (LGM)

1 NC060

LITHUANIAN AIRLINES (LIJ)

1 NB434

L'AVION (EYS)

1 NE003 NE166

MACQUARIE AIR FINANCE (ZGT)

1 NA026 NC058

MEXICANA (CMA)

1 NT376–NT378

MEXICO'S PRESIDENTIAL AIRCRAFT (MXG)

1 NA027

MID EAST JET (SKL)

1 NC161

MONARCH AIRLINES (MON)

1 NA401–NA405 NA407–NA408

NASA (NAS)

1 NA002

NORTH AMERICAN AIRLINES (NNA)

1 NB236 NT239–NT240 NT242 NT247
 

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BOEING SERVICE BULLETIN 757-30-0019

NORTHWEST AIRLINES (NWA)

1 NC001–NC022 NC024–NC033 NE311–NE325 NU031–NU038

OCEANAIR AIRLINES (OAL)

1 NB453

OMNI AIR INTERNATIONAL (OAE)

1 NA446 NB137

ORIENT THAI AIRLINES (OTH)

1 NA193

PACE AIRLINES (PIE)

1 ND242

PARADIGM AIR (PGD)

1 NA205

PRIMARIS AIRLINES INC. (PIM)

1 NA199 NB067 NE161

PRIVATAIR (PTS)

1 NB136

PRIVILEGE STYLE (PVG)

1 ND243

RAK AIRWAYS (RKW)

1 NT914

ROLLS-ROYCE NORTH AMERICA (RRN)

1 ND001 ND003

ROYAL AIR MAROC (RAM)

1 NC041–NC042

ROYAL BRUNEI AIRLINES (RBA)

1 NB052

ROYAL NEPAL AIRLINES (RNA)

1 ND891 ND895

ROYAL NEW ZEALAND AIR FORCE (RNZ)

1 NB451–NB452

RYAN INTERNATIONAL AIRLINES (RYN)

1 NA195 NA198 NA342

SANTA BARBARA AIRLINES C.A. (YDJ)

1 NA392–NA393 NB068

SAUDI ROYAL FLIGHT (SRF)

1 NB168
 

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BOEING SERVICE BULLETIN 757-30-0019

SHANGHAI AIRLINES (SHA)

1 NE004–NE007 NJ551–NJ555 NT358

SHANGHAI AIRLINES CARGO (CIX)

1 NE001–NE002

SKYSERVICE AIRLINES (SKB)

1 NA345

STATE AIR COMPANY "BERKUT" (ORE)

1 NB053

SUNEXPRESS (SNS)

1 NC068–NC069 NC071

TACV-CABO VERDE AIRLINES (TCV)

1 NC074 NT379

THE YUCAIPA COMPANIES (YUC)

1 NB312

THOMAS COOK AIRLINES UK (JMA)

1 NA445 NB201 NB222–NB223 NB226–NB228

NB230 NB330–NB331 NB446 NB571

NT232–NT234 NT237–NT238

THOMSONFLY (BRI)

1 NA352 NA443 NB322 NB329

NB422–NB423 NB426–NB427 NB429–NB430 NB432–NB433

NB435–NB438 NB506–NB507 NJ001–NJ004 NT245–NT246

NT404–NT407 NT431–NT432

TITAN AIRWAYS (TIU)

1 NB323 NT912

TUIFLY NORDIC (TNS)

1 NB428 NB431

TURKMENISTAN AIRLINES (TUE)

1 NB143 NB161–NB162 NT446

UNITED AIR LINES (UAL)

1 NE011–NE088 NE092–NE094 NE141–NE150 NT791–NT796

UPS (UPS)

1 NT001–NT009

2 NC901–NC950 NS601–NS616

US AIR FORCE (USF)

1 NP901–NP904
 

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BOEING SERVICE BULLETIN 757-30-0019

US AIRWAYS (USA)

1 NA003–NA004 NA007 NA009–NA010 NA012–NA016

NA018–NA020 NB021–NB023 NB036–NB038 NB040–NB041

NB502 NB504–NB505 NB509–NB523 NT286

NT288–NT289

UZBEKISTAN AIRWAYS (UZB)

1 NC151 NT355 NT357 NT359

NT441–NT442

VARIG LOGISTICA S.A. (VRG)

1 NA021–NA023 NA441 NA447

VIM AVIA (VIM)

1 NE165 NE167–NE177 NT284 NT287

VULCAN INC. (VUL)

1 NB311

VX CAPITAL PARTNERS (VXC)

1 NC061

XIAMEN AIRLINES (XIA)

1 ND221–ND225 NJ031–NJ032 NN051–NN052

XL AIRWAYS (SBE)

1 NA024 NB321

ZOOM AIRLINES (YFM)

1 NB202–NB203

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

NA002–NA028 1

NA191–NA199 1

NA201–NA239 1

NA301–NA305 1

NA341–NA352 1

NA391–NA399 1

NA401–NA408 1

NA441–NA447 1

NA501–NA586 1

NB001–NB004 1

NB021–NB023 1

NB036–NB041 1

NB051–NB053 1

NB061–NB073 1
 

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BOEING SERVICE BULLETIN 757-30-0019

NB079 1

NB131–NB148 1

NB161–NB162 1

NB166–NB168 1

NB201–NB204 1

NB221–NB228 1

NB230 1

NB236 1

NB239 1

NB261–NB267 1

NB291–NB299 1

NB301–NB302 1

NB311–NB312 1

NB321–NB331 1

NB421–NB438 1

NB446 1

NB451–NB454 1

NB501–NB523 1

NB561 1

NB571 1

NB581–NB583 1

NC001–NC033 1

NC041–NC042 1

NC051–NC052 1

NC056–NC062 1

NC066–NC084 1

NC091–NC094 1

NC151 1

NC161 1

NC901–NC951 2

NC971–NC974 2

ND001–ND007 1

ND011–ND059 1

ND111–ND113 1

ND161–ND199 1

ND201–ND203 1

ND221–ND225 1

ND241–ND248 1

ND301–ND322 1

Variable Group
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ND401 1

ND891 1

ND895 1

NE001–NE008 1

NE011–NE088 1

NE091–NE094 1

NE141–NE150 1

NE161–NE177 1

NE201–NE204 1

NE301–NE302 1

NE311–NE325 1

NJ001–NJ004 1

NJ031–NJ032 1

NJ551–NJ555 1

NN001–NN002 1

NN051–NN052 1

NP901–NP904 1

NS601–NS616 2

NT001–NT009 1

NT201–NT202 1

NT231–NT234 1

NT237–NT240 1

NT242 1

NT245–NT248 1

NT281–NT289 1

NT341–NT347 1

NT351–NT360 1

NT371–NT373 1

NT375–NT379 1

NT381–NT386 1

NT401–NT409 1

NT411–NT412 1

NT426–NT427 1

NT431–NT432 1

NT436–NT438 1

NT441–NT442 1

NT446 1

NT701–NT769 1

NT791–NT796 1

Variable Group
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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 the electrical connections 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 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.

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.

NT861–NT862 1

NT881–NT885 1

NT901–NT916 1

NT971–NT985 1

NU031–NU038 1

Variable Group
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Boeing Service Related Problems (SRP) 757-SRP-30-0031 and 757-SRP-56-0015 are related to this 

service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane NB141 by 

Service Bulletin 757-30-0019 Validation Copy 1 before the initial release of this service bulletin. The 

change completed on airplane NB141 by Service Bulletin 757-30-0019 Validation Copy 1 is equivalent 

to the initial release of this service bulletin. Airplane NB141 has the configuration of a Group 1 

airplane.

Revision 1 was sent to change the No.1 Windshield Assembly part numbers supplied in the Top Kits.

Revision 2 is sent to tell operators that have not done the terminating action in the compliance of this 

service bulletin will now need to also inspect the J1 and J4 windshield lugs and terminals.

D. Description

In the flight compartment, do an inspection of the J1, J4 and J5 lugs and terminals 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.

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 as shown in the original issue of this 

service bulletin.

Revision 2 - More work is necessary on airplanes changed as shown in the original issue and Revision 

1 of this service bulletin.

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to 

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in 

this service bulletin mandatory.

Compliance Table:

Condition Action

Compliance Time

(Whichever Occurs First)

Repeat Interval 

(Whichever Occurs 

Later)

Windshield that uses 

screws and lugs for window 

heat power connection.

Replace with windshield 

that uses pins and 

sockets for window heat 

power connection in 

accordance with 

Accomplishment 

Instructions Work 

Packages 3 and 4.

 ---- Terminating action for 

this bulletin.
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PPG Windshield that uses 

screws and lugs for window 

heat power connection.

Do the actions that follow 

for J1, J4 and J5 window 

heat power connections:

1. Inspect the shipside 

wiring and terminal lug 

(including cap) look for 

signs of melted or 

discolored insulation.

2. Inspect the window 

terminal blocks, look for 

signs of melting or 

distortion.

3. Inspect the window 

heat power connection for 

evidence of cross 

threading by making sure 

the terminal lug is parallel 

with the window terminal 

block.

4. Inspect the terminal lug 

for looseness.

5. Address the inspection 

findings as described in 

Inspection Conditions 1 

thru 4.

Within 500 flight hours or 

150 days, whichever occurs 

earlier, after the date of 

Revision 2 to the service 

bulletin.

Every 6000 flight 

hours or 24 months 

until windshield is 

replaced with 

windshield that used 

pins and sockets for 

the window heat 

power connection in 

accordance with 

Accomplishment 

Instructions Work 

Packages 3 and 4.

Compliance Table:

Condition Action

Compliance Time

(Whichever Occurs First)

Repeat Interval 

(Whichever Occurs 

Later)
 

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BOEING SERVICE BULLETIN 757-30-0019

GKN Windshield that uses 

screws and lugs for window 

heat power connection.

Do the actions that follow 

for J1, J4 and J5 window 

heat power connections:

1. Inspect the shipside 

wiring and terminal lug 

(including cap) look for 

signs of melted or 

discolored insulation.

2. Inspect the window 

terminal blocks, look for 

signs of melting or 

distortion.

3. Inspect the window 

heat power connection for 

evidence of cross 

threading by making sure 

the terminal lug is parallel 

with the window terminal 

block.

4. Inspect the terminal lug 

for looseness.

5. Address the inspection 

findings as described in 

Inspection Conditions 1 

thru 4.

Within 500 flight hours or 

150 days, whichever occurs 

earlier, after the date of 

Revision 2 to the service 

bulletin.

Every 12,000 flight 

hours or 48 months 

until windshield is 

replaced with 

windshield that used 

pins and sockets for 

window heat power 

connection in 

accordance with 

Accomplishment 

Instructions Work 

Packages 3 and 4.

Inspection Condition 1 - If 

the inspection reveals one 

or more signs of the 

following:

1. Melted shipside wire 

insulation.

2. Discolored shipside wire 

insulation.

3. Melted terminal lug.

4. Melted cap.

1. Repair or replace 

shipside wiring as 

necessary. Refer to 

Standard Wiring Practices 

Manual SWPM 20-10-13 

as an accepted 

procedure.

2. If the terminal lug has 

melted, replace the 

shipside terminal lug and 

windshield in accordance 

with Work Package 1, 

step 3. and Work Package 

2, step 3.

Before further flight. ----

Compliance Table:

Condition Action

Compliance Time

(Whichever Occurs First)

Repeat Interval 

(Whichever Occurs 

Later)
 

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BOEING SERVICE BULLETIN 757-30-0019

Inspection Condition 2 - If 

the inspection reveals one 

or more signs of the 

following:

1. Melted window terminal 

block.

2. Distorted or cracked 

window terminal block.

1. Replace windshield in 

accordance with Work 

Package 1, step 3. and 

Work Package 2, step 3.

Before further flight. ----

Inspection Condition 3 - If 

the inspection reveals 

evidence the window heat 

power connection is cross 

threaded.

1. Inspect the terminal for 

looseness. If the cross 

threaded terminal is loose: 

torque the terminal screw 

to 25-30 in-lb.

2. Re-inspect terminal lug 

for looseness.

3. If terminal lug is still 

loose replace windshield 

in accordance with Work 

Package 1, step 3. and 

Work Package 2, step 3.

Before further flight. ----

 

 

4. If terminal lug is tight, 

replace windshield in 

accordance with Work 

Package 1, step 3. and 

Work Package 2, step 3.

Within 150 days or 500 flight 

hours, whichever occurs 

earlier, after the inspection.

 ----

Inspection Condition 4 - If 

the inspection reveals the 

terminal lug is loose.

1. Torque the terminal 

screw to 25-30 in-lb.

2. Re-inspect terminal lug 

for looseness.

3. If terminal lug is still 

loose then disassemble, 

inspect and reassemble 

the electrical connection. 

Before further flight. ----

Compliance Table:

Condition Action

Compliance Time

(Whichever Occurs First)

Repeat Interval 

(Whichever Occurs 

Later)
 

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BOEING SERVICE BULLETIN 757-30-0019

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.

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

If the windshield is replaced 

with same type windshield 

that uses screws and lugs 

for window heat power 

connection.

OR

Window heat power 

connection is reassembled 

(on windshields that uses 

screws and lugs for window 

heat power connection).

Do a detailed inspection in 

accordance with 

Accomplishment 

Instructions Work 

Package 1, step 2. and 

Work Package 2, step 2.

Within 150 days or 500 flight 

hours, whichever occurs 

earlier, after installation of 

same windshield type (a).

 ----

(a) The inital inspection after installing a new window or a new termial 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 "Window heat power connection is reassembled" or "windshield is replaced with 

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

Compliance Table:

Condition Action

Compliance Time

(Whichever Occurs First)

Repeat Interval 

(Whichever Occurs 

Later)
 

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BOEING SERVICE BULLETIN 757-30-0019

— Time to find the tools.

H. Weight and Balance Changes

None

Work Package 1 - Inspection of the Left Windshield

Task

Number of 

Persons Task-Hours Elapsed Hours

Figure 1 1 1.50 1.50

Total per Windshield 1.50 1.50

Work Package 2 - Inspection of the Right Windshield

Task

Number of 

Persons Task-Hours Elapsed Hours

Figure 2 1 1.50 1.50

Total per Windshield 1.50 1.50

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

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
 

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BOEING SERVICE BULLETIN 757-30-0019

I. Electrical Load Data

Not changed

J. References

1. Existing Data:

a. Engineering Change Memo PRR 54530-265S

b. Boeing Service Related Problem (SRP) 757-SRP-30-0031, 757-SRP-56-0015

c. 757 Aircraft Maintenance Manual (AMM) 30-41-00, 56-11-01

d. 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, 20-20-00, 20-30-11, 20-63-19, 20-64-16

f. 757 Illustrated Parts Catalog (IPC) 30-41-52

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

h. 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

K. Publications Affected

1. Publications

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in 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.

Publication Chapter-Section

757 Maintenance Manual 30-41, 56-11

757 Wiring Diagram Manual 30-41

757 Illustrated Parts Catalog 56-11
 

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BOEING SERVICE BULLETIN 757-30-0019

L. Interchangeability and Intermixability of Parts

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

information.
 

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BOEING SERVICE BULLETIN 757-30-0019

BLANK PAGE
 

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BOEING SERVICE BULLETIN 757-30-0019

2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kit 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 31/07

012N8926-7 Top Kit - Left Windshield - PPG 

with hydrophobic coating

19 $16,480.00

012N8926-8 Top Kit - Right Windshield - PPG 

with hydrophobic coating

19 $16,480.00
 

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BOEING SERVICE BULLETIN 757-30-0019

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: Two top kits (one for the left side and one for the right side) and the items shown in

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

airplane.

Kit 012N8926 

New Part Number

QTY

-8 -7 Name Notes

012N8926-7 . - Top Kit - Left Windshield, PPG 

with Hydrophobic coating

012N8926-8 - . Top Kit - Right Windshield, PPG 

with Hydrophobic coating

141W7400-43 . 1 PPG Left Windshield Assembly 

with Hydrophobic coating

(a) (b) (c) (d) 

(f) (h) (j)

141W7400-44 1 . PPG Right Windshield Assembly 

with Hydrophobic coating

(a) (b) (c) (e) 

(g) (i) (j)

280N3355-1 . 1 Wire Kit - Flight Deck Window 

Heat

280N3355-2 1 . Wire Kit - Flight Deck Window 

Heat 

(a) Keep the existing part if there are other uses for it.

(b) This part is not used in production.

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

(d) As an option operators can install Left Windshield part number 141T4801-59 with serial 

numbers 04001Hxxxx through 05365Hxxxx.

(e) As an option operators can install Right Windshield part number 141T4801-60 with 

serial numbers 04001Hxxxx through 05365Hxxxx.

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

141W7400-33 with serial numbers 04001Hxxxx through 05365Hxxxx.

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

141W7400-34 with serial numbers 04001Hxxxx through 05365Hxxxx.

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

141W7400-41.

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

141W7400-42.

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

 P.O. Box 2200

 1719 U.S. Highway 72 East 

 Huntsville, AL 35811-9660
 

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BOEING SERVICE BULLETIN 757-30-0019

Kit 280N3355 

New Part 

Number

QTY

-102 -101 -2 -1 Name Notes

280N3355-1 . . . - Wire Kit - Flight Deck 

Window Heat

280N3355-2 . . - . Wire Kit - Flight Deck 

Window Heat

280N3355-101 . - . 1 Kit, Wire Bundle

W2304

280N3355-102 - . 1 . Kit, Wire Bundle

W2314

280N3355-10103 . 1 . . BMS 13-52 

Expandable Sleeve

280N3355-10203 1 . . . BMS 13-52 

Expandable Sleeve

- . 1 . . Wire Identified 

W2304-0001-12

(a)

- . 1 . . Wire Identified 

W2304-0002-12

(b)

- 1 . . . Wire Identified 

W2314-0001-12

(a)

- 1 . . . Wire Identified 

W2314-0002-12

(b)

BACT12AC-12 3 3 . . Terminal Lug (c)

M39029/57-359 3 3 . . Socket Contact (c)

(a) BMS 13-60, Type 1, Class 1, AWG 12, length 66 inches

(b) BMS 13-60, Type 1, Class 1, AWG 12, length 33 inches

(c) There are more parts than are necessary.
 

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BOEING SERVICE BULLETIN 757-30-0019

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

233N8300-( ) 1 Glareshield - (a) (b)

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

(b) There is no equivalent Boeing part number for the changed part. Identify 

on the part that the change given in this service bulletin was made.
 

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BOEING SERVICE BULLETIN 757-30-0019

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 757-30-0019)

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 31/07

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
 

July 19, 2006

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BLANK PAGE
 

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BOEING SERVICE BULLETIN 757-30-0019

3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED

MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES

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

SPARKS OR OTHER ELECTRICAL DAMAGE.

NOTE:

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

definition of the acronyms.

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

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

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

package independently.

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

— Linear dimensions are in inches

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

Chapter 51.

5. Refer to the 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 "in 

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

must be used.

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
 

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BOEING SERVICE BULLETIN 757-30-0019

TOUCH THE TERMINAL.

1. Open the circuit breaker shown below 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 the windshield before the 

subsequent revenue flight. Refer to 757 AMM 56-11-01 as an accepted procedure. 

4. Remove the DO-NOT-CLOSE tag and close the circuit breaker shown below:

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 the applicable circuit breaker shown below 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 the windshield before the 

subsequent revenue flight. Refer to 757 AMM 56-11-01 as an accepted procedure. 

4. Remove the DO-NOT-CLOSE tag and close the circuit breaker shown below:

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

Airplane 

Group

Location

Panel / Position Name Circuit Breaker

1 P70 / C13 WINDOW HEATER 1L C391

2 P31 / A05 WINDOW HEATER 1L C391

Airplane 

Group

Location

Panel / Position Name Circuit Breaker

1 P70 / C13 WINDOW HEATER 1L C391

2 P31 / A05 WINDOW HEATER 1L C391

Location

Panel / Position Name Circuit Breaker

P37 / J2 WINDOW HEATER 1R C392

Location

Panel / Position Name Circuit Breaker

P37 / J2 WINDOW HEATER 1R C392
 

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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 757 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 757 AMM 

56-11-01 as an accepted procedure. At the operator’s choice, use one of the windshields 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 757 

AMM 30-41-00 as an accepted procedure.

8. Put the airplane in a serviceable condition.

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:

Airplane 

Group

Location

Panel / Position Name Circuit Breaker

1 P70 / C13 WINDOW HEATER 1L C391

2 P31 / A05 WINDOW HEATER 1L C391

Description Part Number Part of Top Kit

PPG with Hydrophobic Coating 141W7400-43 012N8926-7

Airplane 

Group

Location

Panel / Position Name Circuit Breaker

1 P70 / C13 WINDOW HEATER 1L C391

2 P31 / A05 WINDOW HEATER 1L C391

Location

Panel / Position Name Circuit Breaker

P37 / J2 WINDOW HEATER 1R C392
 

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2. Remove the right windshield. Use the windshield handling sling, A56001-2. Refer to 757 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 window heat wiring for the right windshield as given in Figures 7 and Figure 8.

5. Install the right windshield. Use the windshield handling sling, A56001-2. Refer to 757 AMM 

56-11-01 as an accepted procedure. At the operator’s choice, use one of the windshields 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". Refer to 757 

AMM 30-41-00 as an accepted procedure.

8. Put the airplane in a serviceable condition.

Description Part Number Part of Top Kit

PPG with Hydrophobic Coating 141W7400-44 012N8926-8

Location

Panel / Position Name Circuit Breaker

P37 / J2 WINDOW HEATER 1R C392
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

FWD

INBD

TERMINAL

BLOCK,

CONNECTOR

1

3 SCREW

J4

2 LUG

J5

J1

TB5028

W2304

4

5

2

LUG

3 SCREW

4

5

3 SCREW

4

5

2

LUG

1

1

TERMINAL

BLOCK,

CONNECTOR

TERMINAL

BLOCK,

CONNECTOR

482068

(SHEET 1 OF 5)
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

LUG PARALLEL

TO TERMINAL LUG

(WB0710

SHOWN)

TERMINAL

ACCEPTABLE 

LUG PARALLEL TO TERMINAL

LUG NOT PARALLEL

TO TERMINAL

LUG

(WB0710

SHOWN)

TERMINAL

NOT ACCEPTABLE 

LUG NOT PARALLEL TO TERMINAL

WALLACE AND BLACK LUG

CORY / TRI-STAR LUG

TERMINAL TERMINAL

LUG

(CWC01-1210

SHOWN)

LUG

(CWC01-1210

SHOWN)

LUG NOT PARALLEL

TO TERMINAL AND

O-RING NOT EVENLY

COMPRESSED

LUG PARALLEL TO

TERMINAL AND

O-RING EVENLY

COMPRESSED

ACCEPTABLE 

LUG PARALLEL TO TERMINAL

NOT ACCEPTABLE 

LUG NOT PARALLEL TO TERMINAL

1650853

(SHEET 2 OF 5)
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

TERMINAL

LUG

SCREW

LOCKWASHER

COVER

SCREW

LOCKWASHER

COVER

O-RING

WALLACE AND BLACK LUG

LUG

TERMINAL

1

1

3 4 5

5

4 5

3 4 5

5

4 5

5

CORY / TRI-STAR LUG

4 2 4 6 7

4

1 2 4 6

1 4

1 3

1698037

(SHEET 3 OF 5)
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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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 J1, J4, J5 3 At the J1, J4 and J5 connections

Lug - 3

Wiring Wire bundle W2304 3

NOTE: If the terminal lug or cap has melted, replace the shipside terminal lug and windshield.

NOTE: If the terminal block has melted, distorted or cracked, replace the windshield.

NOTE: If the shipside wire insulation is melted or discolored, then repair or replace shipside

wiring as necessary. Refer to Standard Wiring Practices Manual SWPM 20-10-13 as

an accepted procedure. 

2

Inspect Lug - 3 To make sure it is a 

tight connection and not cross 

threaded.

NOTE: If the terminal lug moves while applying light manual pressure to the strain-relief on

the lug, then the screw that attaches it must be tightened. There are four 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 and Illustrated Parts Catalog 757 IPC 30-41-52.

4-The screw is cross threaded.

NOTE: If the lug is not parallel with the terminal, then the screw is cross threaded. Check for

lug alignment, the lug and terminal must be viewed from the side. It may be

necessary to view the lug and terminal from the exterior side of the window.

NOTE: If the lug shows signs of arcing, blueing, overheating or melting, replace the lug and

windshield.

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

Torque Screw - 3 To 25 to 30 inch pounds of torque. 

Refer to SWPM 20-64-16 as an 

accepted procedure. 

Inspect Lug - 3 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, do steps 4 and 5.

NOTE: If the cross threaded screw can not be tightened, replace the window.

(SHEET 4 OF 5)
 FIGURE 1: INSPECTION OF THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

4

Remove/

Keep

Cover - 3

Remove Screw - 3 To make sure the correct screw is 

installed and there is no damage to 

terminal, lug or screw.

Washer - 3

Inspect Terminal J1, J4, J5 3 To make sure the terminal or lug is 

not damaged. Lug - 3

NOTE: 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 shows signs of

arcing, blueing or overheating, the window must be replaced.

NOTE: If the mating surface on the terminal lug has contamination, clean surface. Refer to

SWPM 20-20-00 Cleaning Method 5 as an accepted procedure. If the lug cannot be

cleaned or shows signs of arcing, blueing or overheating, the lug must be replaced.

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

FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE

WINDOW.

5

Install 

(New)

Screw - 3 To make sure lug is assembled to 

terminal with new, undamaged and 

correct hardware.

Washer - 3

O-ring - 3

NOTE: Reassemble the lug to the terminal with a new screw, lock washer and o-ring. Make

sure the o-ring is installed prior to assemble of the lug to the terminal. A new o-ring is

only available for the CWC01-1210 lug. Refer to SWPM 20-64-16 and 757 IPC

30-41-52 for the correct screw, washer and o-ring.

NOTE: Make sure the screw has been aligned correctly.

Torque Screw - 3 To 25 to 30 inch pounds of torque. 

Refer to SWPM 20-64-16 as an 

accepted procedure.

Install/

Kept

Cover - 3

NOTE: Do step 2 to make sure the screw has been installed correctly and is a tight

connection.

6

Inspect Lug - 3 Apply light manual pressure to 

strain-relief on lug.

NOTE: If the lug moves with light manual pressure, replace the windshield.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 5)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

FWD

INBD

TERMINAL

BLOCK,

CONNECTOR

1

J4

3 SCREW

2 LUG

J5

J1

W2314

TB5038

4

5

3 SCREW

4

5

1

TERMINAL

BLOCK,

CONNECTOR

2

LUG

3 SCREW

4

5

2

LUG 1

TERMINAL

BLOCK,

CONNECTOR

482071

(SHEET 1 OF 5)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

LUG PARALLEL

TO TERMINAL LUG

(WB0710

SHOWN)

TERMINAL

LUG NOT PARALLEL

TO TERMINAL

LUG

(WB0710

SHOWN)

TERMINAL

WALLACE AND BLACK LUG

TERMINAL TERMINAL

LUG

(CWC01-1210

SHOWN)

LUG

(CWC01-1210

SHOWN)

LUG NOT PARALLEL

TO TERMINAL AND

O-RING NOT EVENLY

COMPRESSED

LUG PARALLEL TO

TERMINAL AND

O-RING EVENLY

COMPRESSED

ACCEPTABLE 

LUG PARALLEL TO TERMINAL

NOT ACCEPTABLE 

LUG NOT PARALLEL TO TERMINAL

CORY / TRI-STAR LUG

ACCEPTABLE 

LUG PARALLEL TO TERMINAL

NOT ACCEPTABLE 

LUG NOT PARALLEL TO TERMINAL

1650854

(SHEET 2 OF 5)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

TERMINAL

LUG

SCREW

LOCKWASHER

COVER

TERMINAL

SCREW

LOCKWASHER

COVER

O-RING

WALLACE AND BLACK LUG

LUG

1

1 4

3 4 5

1 5

4 5

1

3 4 5

5

4 5

5

CORY / TRI-STAR LUG

2 6

1 3

4

1 2 4 6

1 3

4

1672512

(SHEET 3 OF 5)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

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 J1, J4, J5 3 At the J1, J4 and J5 connections

Lug - 3

Wiring Wire bundle W2304 3

NOTE: If the terminal lug or cap has melted, replace the shipside terminal lug and windshield.

NOTE: If the terminal block has melted, distorted or cracked, replace the windshield.

NOTE: If the shipside wire insulation is melted or discolored, then repair or replace shipside

wiring as necessary. Refer to Standard Wiring Practices Manual SWPM 20-10-13 as

an accepted procedure. 

2

Inspect Lug - 3 To make sure it is a 

tight connection and not cross 

threaded.

NOTE: If the terminal lug moves while applying light manual pressure to the strain-relief on

the lug, then the screw that attaches it must be tightened. There are four 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 and Illustrated Parts Catalog 757 IPC 30-41-52.

4-The screw is cross threaded.

NOTE: If the lug is not parallel with the terminal, then the screw is cross threaded. Check for

lug alignment, the lug and terminal must be viewed from the side. It may be

necessary to view the lug and terminal from the exterior side of the window.

NOTE: If the lug shows signs of arcing, blueing, overheating or melting, replace the lug and

windshield.

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

Torque Screw - 3 To 25 to 30 inch pounds of torque. 

Refer to SWPM 20-64-16 as an 

accepted procedure. 

Inspect Lug - 3 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, do steps 4 and 5.

NOTE: If the cross threaded screw can not be tightened, replace the window.

(SHEET 4 OF 5)
 FIGURE 2: INSPECTION OF THE RIGHT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

4

Remove/

Keep

Cover - 3

Remove Screw - 3 To make sure the correct screw is 

installed and there is no damage to 

terminal, lug or screw.

Washer - 3

Inspect Terminal J1, J4, J5 3 To make sure the terminal or lug is 

not damaged. Lug - 3

NOTE: 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 shows signs of

arcing, blueing or overheating, the window must be replaced.

NOTE: If the mating surface on the terminal lug has contamination, clean surface. Refer to

SWPM 20-20-00 Cleaning Method 5 as an accepted procedure. If the lug cannot be

cleaned or shows signs of arcing, blueing or overheating, the lug must be replaced.

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

FORCE. A DAMAGED TERMINAL WILL REQUIRE THE REPLACEMENT OF THE

WINDOW.

5

Install 

(New)

Screw - 3 To make sure lug is assembled to 

terminal with new, undamaged and 

correct hardware.

Washer - 3

O-ring - 3

NOTE: Reassemble the lug to the terminal with a new screw, lock washer and o-ring. Make

sure the o-ring is installed prior to assemble of the lug to the terminal. A new o-ring is

only available for the CWC01-1210 lug. Refer to SWPM 20-64-16 and 757 IPC

30-41-52 for the correct screw, washer and o-ring.

NOTE: Make sure the screw has been aligned correctly.

Torque Screw - 3 To 25 to 30 inch pounds of torque. 

Refer to SWPM 20-64-16 as an 

accepted procedure.

Install/

Kept

Cover - 3

NOTE: Do step 2 to make sure the screw has been installed correctly and is a tight

connection.

6

Inspect Lug - 3 Apply light manual pressure to 

strain-relief on lug.

NOTE: If the lug moves with light manual pressure, replace the windshield.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 5 OF 5)
 FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

FIGURE 3: CUT THE BULB SEAL FOR THE LEFT WINDSHIELD

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

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

SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION

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

1

Cut Bulb Seal 233T8300-7 - to clear the new 

terminal.

NOTE: If the finish below the bulb seal is damaged, it will need to 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.

GLARESHIELD

BULB SEAL

1.40

1.20 1

482072

(SHEET 1 OF 1)
 FIGURE 4: CHANGES TO THE WIRING FOR THE WINDOW HEAT ON THE LEFT WINDSHIELD

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BOEING SERVICE BULLETIN 757-30-0019

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

A-AB

A-AA

2

1

W2304

0001-12

LBL 37

WL 225

STA 225

TB5028

J1

=1

B35 LEFT WINDOW 1

0002-12

J5

=1

B35 LEFT WINDOW 1

A-AC

D3324

D3326

=1

=1

D3322

=1

1

2

3

3

5

5

4

4

ADDED WIRE OR NEW ROUTING

DELETED WIRE OR FORMER ROUTING

REFERENCE: WIRING DIAGRAM 30-41-11

482073

(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 757-30-0019

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 13-60, Type 1, 

Class 1, AWG 12

1

2 Wire BMS 13-60, Type 1, 

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 280N3355-10103 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 Terminal Lug BACT12AC-12 2 Refer to SWPM 20-30-11 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 757-30-0019

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

FWD

INBD

W2304

W2304

J1

TB5028

J5

1423015

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

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BOEING SERVICE BULLETIN 757-30-0019

FIGURE 6: CUT THE BULB SEAL FOR THE RIGHT WINDSHIELD

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

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

SILL IS A HIGH MOISTURE AREA AND MOISTURE CAN CAUSE CORROSION

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

1

Cut Bulb Seal 233T8300-8 - to clear the new 

terminal.

NOTE: If the finish below the bulb seal is damaged, it will need to be sealed with

chemical treatment and primer. Refer to Standard Overhaul Practices

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

2 Identify Glareshield - (a)

(a) Part Mark with service bulletin number before new windshield is installed. Refer to SOPM 

20-50-10 as an accepted procedure.

GLARESHIELD

1.20

BULB SEAL

1 1.40

2

482075

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

Original Issue: July 19, 2006

Revision 2: April 19, 2010 757-30-0019

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 58

BOEING SERVICE BULLETIN 757-30-0019

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

B38 RIGHT WINDOW 1

B38 RIGHT WINDOW 1

RBL 40

WL 230

STA 223

TB5038

D3274

D3272

D3270

W2314

=1

=1

A-AC =1

=1

J5

0002-12

=1

J1

0001-12

1

2

A-AA

A-AB

4

4

5

5

3

3

2

1

ADDED WIRE OR NEW ROUTING

DELETED WIRE OR FORMER ROUTING

REFERENCE: WIRING DIAGRAM 30-41-12

482076

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

Original Issue: July 19, 2006

Revision 2: April 19, 2010 757-30-0019

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 58

BOEING SERVICE BULLETIN 757-30-0019

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 13-60, Type 1, 

Class 1, AWG 12

1

2 Wire BMS 13-60, Type 1, 

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 280N3355-10203 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 Terminal Lug BACT12AC-12 2 Refer to SWPM 20-30-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 8: WIRE ROUTING FOR THE WINDOW HEAT ON THE RIGHT WINDSHIELD

July 19, 2006

Revision 2: April 19, 2010 757-30-0019

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 58

BOEING SERVICE BULLETIN 757-30-0019

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

J1

J5

FWD

INBD

TB5038

W2314

W2314

1423016

(SHEET 1 OF 1)