Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-30-1058

Original Issue: July 27, 2006

Revision 4: November 03, 2011

ATA System: 3041

SUBJECT: ICE AND RAIN PROTECTION - Control Cabin Window Anti-Icing System - Coil Cord

Assembly Replacement on the Number 2 Windows in the Flight Compartment

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

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

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

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2006 The Boeing Company

Unpublished Work - All Rights Reserved

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

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

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

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

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

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

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

Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in

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4.0
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BOEING SERVICE BULLETIN 737-30-1058

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

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

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

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

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

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

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

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

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

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

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 32

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 33

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 1: CAPTAIN'S SIDE- COIL CORD AND PANEL REMOVAL [Group 1, Configuration 1] . . . 41

FIGURE 2: CAPTAIN'S SIDE- IDENTIFICATION TAPE INSTALLATION [Group 1, Configuration 1] . 44

FIGURE 3: CAPTAIN'S SIDE- CONNECTOR KEYWAY INSPECTION [Group 1, Configuration 1] . . 45

FIGURE 4: CAPTAIN'S SIDE- TURN POSITION OF THE CONNECTOR [Group 1, Configuration 1] . 47

FIGURE 5: CAPTAIN'S SIDE- COIL CORD AND PANEL INSTALLATION [Group 1, Configuration 1] . 49

FIGURE 6: FO'S SIDE- COIL CORD AND PANEL REMOVAL [Group 1, Configuration 1] . . . . . . . 51

FIGURE 7: FO'S SIDE- IDENTIFICATION TAPE INSTALLATION [Group 1, Configuration 1] . . . . . 54

FIGURE 8: FO'S SIDE- CONNECTOR KEYWAY INSPECTION [Group 1, Configuration 1] . . . . . . 55

FIGURE 9: FO'S SIDE- TURN POSITION OF THE CONNECTOR KEYWAY [Group 1, Configuration 1]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 10: FO'S SIDE- COIL CORD AND PANEL INSTALLATION [Group 1, Configuration 1] . . . . 59

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572 [Group 1, Configuration 2; Group 2] . 61

FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572 . . . . . . . . . . . . . . . . . . . . . 66

FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572 [Group 1, Configuration 2; Group 2] . . . . 72

FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572 . . . . . . . . . . . . . . . . . . . . . . . . 77

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BOEING SERVICE BULLETIN 737-30-1058
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 737-30-1058

Original Issue: July 27, 2006

Revision 4: November 03, 2011

ATA System: 3041

SUBJECT: ICE AND RAIN PROTECTION - Control Cabin Window Anti-Icing System - Coil Cord

Assembly Replacement on the Number 2 Windows in the Flight Compartment

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary for the airplanes changed in accordance with the original issue, revision 1, revision 2

or revision 3 of this service bulletin. Those airplanes from line numbers 1 through 1979 are identified as Group

1 in this service bulletin effectivity.

Airplanes from line numbers 1980 through 3798 were added as Group 2 in this service bulletin effectivity.

REASON FOR REVISION

This revision is sent to give instructions to change the keyway position of the receptacle connectors D10572.

Three operators accomplished this service bulletin before this Revision 4 had found that the wire connectors at

the two ends of the coil cord rub each other. The rub condition occurs when the window opens or is in the fully

open position. The rub condition can possibly cause damage to the wire connector and the coil cord. If the

changes added in this revision 4 is not done, the rub condition can cause part damages and possibly loss of

window heat protection.

These sections were changed:

1. In Summary Background, Action, Paragraph 1.C Reason, 1.D Description, Work Instruction Steps B.5.A,

B.9.A, Figures 4 and 9 title, reclock the connector keyway was changed to turn the receptacle connector.

2. In Summary and Paragraph 1.G Manpower, added Group 1, Configuration 2 and Group 2.

3. In Summary Illustration, added Group 1.

4. In Paragraph 1.C Reason and Paragraph 1.D Description, added Revision 4 change information.

5. In Paragraph 1.J References, added Aircraft Maintenance Manual (AMM) 25-11-21.

6. In Paragraph 3.A General Information, added Notes 6 through 14.

7. In Paragraph 3.B Work Instructions, added Group 1, Configuration 1 and Part 1 Work Instructions for

airplanes that have not done this service bulletin. In Part 1 Work Instructions Step 6, added Figure 12. In

Part 1 Work Instructions Step 10, added Figure 14.

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8. In Paragraph 3.B Work Instructions, Added Group 1, Configuration 2 and Part 2 Work Instructions for

airplanes that have done this service bulletin. Added Group 2 and Part 2 Work Instructions for the airplanes

added by this service bulletin revision. In Work Instructions Part 2, added Work Package 1 for changes at

the Captain's Side and Work Package 2 for changes at the First Officer's Side.

9. In Figure 1, changed Sheet 1 and step table. Added Sheet 2 for cover assembly removal.

10. In Figure 2, changed Sheet 1 and step table.

11. In Figure 3, changed Sheet 1 and step table.

12. In Figure 4, changed Sheet 1 and step table.

13. In Figure 5, changed Sheet 1 and step table. Added Sheet 2 for coil cord installation.

14. In Figure 6, changed Sheet 1 and step table. Added Sheet 2 for cover assembly removal.

15. In Figure 7, changed Sheet 1 and step table.

16. In Figure 8, changed Sheet 1 and step table.

17. In Figure 9, changed Sheet 1 and step table.

18. In Figure 10, changed Sheet 1 and step table. Added Sheet 2 for coil cord installation.

19. Added Figure 11 to disconnect the wire connector D10572 at the Captain's side.

20. Added Figure 12 to install the wire connector D10572 at the Captain's side.

21. Added Figure 13 to disconnect the wire connector D10572 at the First Officer's side.

22. Added Figure 14 to install the wire connector D10572 at the First Officer's side.

The data given in Information Notice 737-30-1058 IN 02 is included in this revision.

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 27, 2006

Revision 1: June 18, 2007

Revision 2: February 13, 2009

Revision 3: July 07, 2010

Revision 4: November 03, 2011

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BOEING SERVICE BULLETIN 737-30-1058
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Summary Number: 737-30-1058

Original Issue: July 27, 2006

Revision 4: November 03, 2011

ATA System: 3041

SUBJECT: ICE AND RAIN PROTECTION - Control Cabin Window Anti-Icing System - Coil Cord

Assembly Replacement on the Number 2 Windows in the Flight Compartment

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing received a report from an operator of arcing and smoke at the left number 2 window in the flight

compartment. An investigation showed the cause of this problem to be mechanical damage at the connector

backshell of the coil cord assembly. The new assembly will prevent mechanical damage which could cause a

fire in the flight compartment.

This service bulletin gives instructions to install a new coil cord assembly on the captain’s and first officer’s sides

of the number 2 windows in the flight compartment. This bulletin also gives instructions to inspect and turn the

receptacle connectors on the sidewall panels and covers if necessary.

Boeing Service Related Problem (SRP) 737NG-SRP-56-0017 is related to this service bulletin.

ACTION (PRR 38275-97)

Get access to the captain's and first officer's side windows in the flight compartment. Do an inspection of the

connector keyway’s position at the two ends of the coil cord on the sidewall panels and covers.

Turn the receptacle connectors on the sidewall panels and covers if necessary and replace the coil cord assembly.

Do the Window Heat Control Unit (WHCU) Test.

EFFECTIVITY

737-600, -700, -700C, -800, -900 Airplanes. See Service Bulletin Paragraph 1.A.1., Airplanes, for the list of

affected airplanes.

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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.

Boeing recommends that the change given in this service bulletin be done within 48 months after the Revision

3 date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of August 8, 2005. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Each Group 1, 5.50 3.25

Configuration 1

Airplane

Each Group 1, 3.90 3.90

Configuration 2

Airplane

Each Group 2 3.90 3.90

Airplane

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-30-1058

Original Issue: July 27, 2006

Revision 4: November 03, 2011

ATA System: 3041

SUBJECT: ICE AND RAIN PROTECTION - Control Cabin Window Anti-Icing System - Coil Cord

Assembly Replacement on the Number 2 Windows in the Flight Compartment

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-19567 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 PRR38275-97 for data about this change.

GROUP CONFIGURATION DESCRIPTION

Airplanes with one 90 degree and one straight connector backshell

installed on window number 2.

1 -

Airplanes from line numbers 1 through 1979 that had not

accomplished revision 0, 1, 2 or 3 of this service bulletin.

1

Airplanes from line numbers 1 through 1979 that had accomplished

revision 0, 1, 2 or 3 of this service bulletin.

2

2 - Airplanes from line numbers 1980 through 3798.

Airplane Models:

737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER

Variable Number Group

YA001 - YA099 1

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Variable Number Group

YA101 - YA199 1

YA201 - YA211 1

YA221 1

YA231 - YA242 1

YA251 - YA256 1

YA271 - YA272 1

YA291 1

YA301 - YA302 1

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA536 1

YA541 - YA552 1

YA571 - YA578 1

YA601 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA710 1

YA721 - YA722 1

YA731 - YA734 1

YA751 - YA756 1

YA801 - YA803 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YA809 1

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA977 1

YA978 2

YB001 - YB006 1

YB101 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

YB181 - YB184 1

YB201 - YB208 1

YB271 1

YB276 1

YB301 - YB310 1

YB371 - YB390 1

YB391 - YB392 2

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB579 1

YB580 2

YB581 - YB596 1

YB597 - YB598 2

YB601 - YB632 1

YB633 - YB635 2

YB651 1

YB656 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YB671 - YB672 2

YB851 - YB863 1

YB871 - YB874 1

YB881 - YB890 1

YB891 - YB893 2

YB901 - YB903 1

YB911 1

YB961 - YB964 1

YB965 - YB975 2

YB981 2

YB986 - YB998 2

YC001 - YC030 1

YC051 - YC083 1

YC084 2

YC091 - YC094 1

YC095 2

YC101 - YC104 1

YC111 - YC113 1

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC178 1

YC179 2

YC186 - YC189 1

YC190 2

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC387 1

YC391 - YC394 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC437 1

YC438 - YC439 2

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC499 1

YC501 - YC526 1

YC571 - YC583 1

YC587 - YC589 1

YC591 - YC593 1

YC601 - YC655 1

YC681 - YC696 1

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC742 1

YC743 - YC750 2

YC751 - YC752 1

YC761 - YC770 1

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

YC941 - YC951 1

YC971 - YC978 1

YC981 - YC983 1

YD001 - YD007 1

YD021 - YD025 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD110 1

YD111 - YD117 2

YD121 - YD126 1

YD151 - YD159 1

YD171 - YD172 1

YD201 - YD203 1

YD206 - YD209 1

YD216 - YD219 1

YD251 - YD254 1

YD256 - YD257 1

YD261 1

YD301 - YD334 1

YD391 1

YD401 - YD410 1

YD412 - YD414 1

YD415 - YD417 2

YD481 - YD485 1

YD491 - YD494 1

YD495 - YD499 2

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE157 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE378 1

YE379 - YE383 2

YF001 - YF011 2

YF021 - YF049 2

YF051 - YF067 2

YF086 - YF087 2

YF106 - YF107 2

YF111 - YF114 2

YF116 - YF119 2

YF121 - YF131 2

YF176 - YF178 2

YF191 - YF192 2

YF201 - YF276 2

YF401 - YF402 2

YF431 - YF432 2

YF436 - YF437 2

YF441 - YF442 2

YF451 - YF460 2

YF501 - YF599 2

YF601 - YF627 2

YF701 - YF707 2

YF801 - YF805 2

YF831 - YF832 2

YF836 - YF838 2

YF901 - YF905 2

YF921 - YF928 2

YF951 - YF954 2

YG001 - YG044 1

YG061 - YG064 1

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YG066 - YG089 1

YG091 - YG096 1

YG097 - YG099 2

YG101 1

YG102 - YG104 2

YG111 - YG114 2

YG116 - YG132 2

YG201 - YG204 1

YG205 2

YG211 - YG213 1

YG214 2

YG221 - YG224 2

YG251 - YG252 2

YG501 - YG509 1

YG510 - YG512 2

YG601 - YG602 1

YG701 2

YG711 2

YH001 - YH012 2

YH031 - YH055 2

YH071 - YH080 2

YH101 - YH132 2

YH201 - YH202 2

YH206 - YH207 2

YH301 - YH306 2

YH321 - YH322 2

YH501 - YH508 2

YH551 2

YH601 - YH602 2

YH611 - YH612 2

YH631 2

YJ001 - YJ005 1

YJ006 - YJ010 2

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YJ011 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ552 1

YJ553 - YJ579 2

YJ591 - YJ594 1

YJ595 - YJ599 2

YJ631 - YJ632 1

YJ671 - YJ685 1

YJ686 - YJ689 2

YJ690 - YJ692 1

YJ693 - YJ694 2

YJ801 - YJ867 1

YJ871 1

YJ872 - YJ880 2

YJ901 - YJ902 1

YJ903 - YJ904 2

YJ908 - YJ910 2

YJ911 - YJ928 1

YJ929 2

YJ931 - YJ936 1

YJ937 2

YJ941 - YJ947 1

YJ948 - YJ956 2

YJ961 2

YJ976 - YJ977 2

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

YK131 - YK132 1

YK133 2

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BOEING SERVICE BULLETIN 737-30-1058
Variable Number Group

YK136 - YK137 1

YK138 - YK139 2

YK141 - YK142 1

YK146 - YK147 1

YK148 2

YK151 - YK154 1

YK161 - YK167 2

YK171 2

YK176 - YK177 2

YK186 2

YK191 2

YK196 2

YK201 - YK202 2

YK301 - YK305 1

YK306 - YK314 2

YK321 - YK331 1

YK332 - YK340 2

YK361 - YK369 1

YK370 - YK378 2

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK435 1

YK436 - YK450 2

YK456 - YK460 1

YK461 - YK467 2

YK471 - YK473 2

YK476 1

YK480 - YK484 1

YK485 - YK487 2

YK491 - YK492 2

YK495 - YK498 2

YK511 - YK514 1

YK515 - YK516 2

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Variable Number Group

YK521 - YK530 2

YK551 - YK560 1

YK561 - YK570 2

YK571 1

YK576 - YK577 2

YK580 - YK585 2

YK601 - YK602 1

YK606 - YK607 2

YK611 - YK613 1

YK614 - YK616 2

YK621 - YK622 1

YK623 - YK630 2

YK631 1

YK632 - YK634 2

YK641 - YK642 1

YK643 - YK644 2

YK651 - YK665 2

YK671 - YK672 2

YK676 - YK677 2

YK681 - YK686 2

YK691 2

YK701 - YK707 1

YK708 - YK713 2

YK716 - YK719 2

YK721 1

YK722 - YK741 2

YK751 - YK770 2

YK776 - YK778 2

YK781 - YK785 2

YK791 - YK792 2

YK796 - YK797 2

YK801 - YK818 1

YK819 - YK899 2

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Variable Number Group

YK901 - YK906 1

YK907 - YK912 2

YK918 - YK919 2

YK921 - YK929 2

YK941 1

YK942 - YK997 2

YL001 - YL003 1

YL004 - YL005 2

YL011 1

YL012 - YL016 2

YL021 - YL024 2

YL051 - YL052 2

YL056 - YL057 2

YL061 2

YL066 - YL069 2

YL076 - YL077 2

YL101 - YL137 2

YL201 - YL230 2

YL241 - YL242 2

YL271 - YL272 2

YL281 - YL284 2

YL301 - YL303 2

YL311 - YL314 2

YL316 - YL321 2

YL351 - YL353 2

YL371 - YL374 2

YL401 2

YL421 - YL429 2

YL431 - YL444 2

YL461 - YL478 2

YL501 - YL509 2

YL531 - YL534 2

YL541 - YL551 2

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Variable Number Group

YL561 - YL579 2

YL591 - YL598 2

YL601 - YL606 2

YL611 - YL612 2

YL616 - YL617 2

YL621 2

YL626 2

YL631 - YL634 2

YL636 - YL637 2

YL661 - YL664 2

YL676 - YL689 2

YL691 2

YL696 - YL697 2

YL701 - YL707 2

YL731 2

YL751 - YL752 2

YL756 - YL757 2

YL761 - YL780 2

YL796 - YL797 2

YL801 - YL815 2

YL901 - YL910 2

YL921 - YL940 2

YL951 - YL968 2

YM101 - YM103 1

YM201 - YM210 1

YM211 - YM244 2

YM251 - YM292 1

YM293 - YM299 2

YM301 - YM399 2

YM401 - YM413 2

YM471 1

YM481 - YM484 1

YM501 - YM507 1

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Variable Number Group

YM508 - YM515 2

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 2

YM591 - YM592 1

YM593 - YM599 2

YM631 - YM634 2

YM641 - YM652 2

YM671 - YM674 2

YM691 - YM699 2

YM701 - YM710 2

YM761 - YM765 2

YM771 - YM778 2

YN001 - YN005 1

YN006 - YN016 2

YN021 - YN024 2

YN061 1

YN071 - YN082 2

YN091 - YN092 2

YN101 - YN105 1

YN106 - YN112 2

YN121 2

YN201 - YN202 2

YN211 - YN219 2

YN231 - YN236 2

YN261 2

YN501 2

YN531 - YN534 2

YN551 2

YN601 2

YN701 2

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Variable Number Group

YQ001 - YQ003 2

YQ011 - YQ019 2

YQ026 - YQ029 2

YQ036 - YQ044 2

YQ201 - YQ202 2

YQ231 2

YQ241 - YQ251 2

YQ281 2

YQ291 - YQ296 2

YQ301 - YQ302 2

YQ401 - YQ403 2

YQ451 - YQ454 2

YR001 - YR013 2

YR051 - YR055 2

YR101 - YR102 2

YR111 - YR116 2

YR126 - YR129 2

YR141 - YR142 2

YR166 - YR172 2

YR201 - YR204 2

YR231 - YR245 2

YR271 - YR277 2

YR286 2

YR291 - YR294 2

YR296 2

YR301 - YR310 2

YR361 2

YR401 - YR404 2

YR421 2

YR451 - YR453 2

YR501 - YR503 2

YR511 - YR512 2

YR516 - YR517 2

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Variable Number Group

YR526 2

YR601 - YR605 2

YR616 2

YR651 - YR652 2

YR701 - YR710 2

YR801 - YR804 2

YR851 - YR852 2

YS001 2

YS051 2

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

Boeing received a report from an operator of arcing and smoke at the left number 2 window in the flight

compartment. An investigation showed the cause of this problem to be mechanical damage at the

connector backshell of the coil cord assembly. The new assembly will prevent mechanical damage

which could cause a fire in the flight compartment.

This service bulletin gives instructions to install a new coil cord assembly on the captain's and first

officer's sides of the number 2 windows in the flight compartment. This bulletin also gives instructions

to inspect and turn the receptacle connectors on the sidewall panels and covers if necessary.

Revision 2 is sent to change the illustrations in Figures 2 and 7 to show the correct station (STA)

locations for the coil cord connectors.

Boeing Service Related Problem (SRP) 737-SRP-56-0017 is related to this service bulletin.

Revision 3 is sent to notify operators that the change in this service bulletin must be done within 48

months after the Revision 3 date of this service bulletin.

Revision 4: This revision is sent to give instructions to change the keyway position of the receptacle

connectors D10572. Three operators accomplished this service bulletin before this Revision 4 had

found that the wire connectors at the two ends of the coil cord rub each other. The rub condition occurs

when the window opens or is in the fully open position. The rub condition can possibly cause damage

to the wire connector and the coil cord. If the changes added in this Revision 4 is not done, the rub

condition can cause part damages and possibly loss of window heat protection.

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D. Description

Get access to the captain's and first officer's side windows in the flight compartment. Do an inspection

of the connector keyway's position at the two ends of the coil cord on the sidewall panels and covers.

Turn the receptacle connectors on the sidewall panels and covers if necessary and replace the coil

cord assembly.

Do the Window Heat Control Unit (WHCU) Test.

Revision 2: No more work is necessary on airplanes changed as shown in the original issue or Revision

1 of this service bulletin.

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

Revision 1, or Revision 2 of this service bulletin.

Revision 4: More work is necessary for the airplanes changed in accordance with the original issue,

revision 1, revision 2 or revision 3 of this service bulletin. Those airplanes from line numbers 1 through

1979 are identified as Group 1 in this service bulletin effectivity.

Airplanes from line numbers 1980 through 3798 were added as Group 2 in this service bulletin effectivity.

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

Group 1:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 211, 212

737-800, 737-900

Group 2:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 211, 212

737-800, 737-900ER

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.

Boeing recommends that the change given in this service bulletin be done within 48 months after the

Revision 3 date of this service bulletin.

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BOEING SERVICE BULLETIN 737-30-1058
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 change 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 inspect the work

• Time to cure the materials

• Time to make the parts

Group 1, Configuration 1:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 0.25 0.25

Inspect 1 0.25 0.25

Change 2 4.50 2.25

Close Access 1 0.25 0.25

Test 1 0.25 0.25

TOTAL FOR EACH AIRPLANE 5.50 3.25

Group 1, Configuration 2; Group 2:

Part 2, Work Package 1: Receptacle Connector Position Change, Captain's Side

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 0.35 0.35

FIGURE 11 1 0.50 0.50

FIGURE 12 1 0.50 0.50

Test 1 0.25 0.25

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BOEING SERVICE BULLETIN 737-30-1058
Group 1, Configuration 2; Group 2:

Part 2, Work Package 1: Receptacle Connector Position Change, Captain's Side

Number of Per- Task Hours Elapsed Hours

sons

Task

Close Access 1 0.35 0.35

TOTAL FOR EACH AIRPLANE 1.95 1.95

Work Package Number 1 can be done at the same time as Part 2, Work Package 2.

Group 1, Configuration 2; Group 2:

Part 2, Work Package 2: Receptacle Connector Position Change, First Officer's Side

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 0.35 0.35

FIGURE 13 1 0.50 0.50

FIGURE 14 1 0.50 0.50

Test 1 0.25 0.25

Close Access 1 0.35 0.35

TOTAL FOR EACH AIRPLANE 1.95 1.95

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Boeing Engineering Change Memo PRR 38275-97

b. Boeing Service Related Problem (SRP) 737NG-SRP-56-0017

c. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

d. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 24-22-00, 25-11-00, 25-11-21,

30-41-11

e. 737-600/700/800/900 Wiring Diagram Manual (WDM) 30-41-11

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BOEING SERVICE BULLETIN 737-30-1058
2. Data supplied with this Service Bulletin

None.

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

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

737 Aircraft Maintenance Manual 25-11

737 Illustrated Parts Catalog 30-41

737 System Schematic Manual 30-41

737 Wiring Diagram Manual 30-41

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.

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 737-30-1058
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.

Group 1:

Unit Price thru DEC

31/09

ROLT

(Weeks)

Kit Number Name

Top Kit, No. 2 Window Heat Coil 15 $1,608.00

Cord Assembly

012A0061-1

B. Industry Support Information

Boeing warranty remedies are available for 737 airplanes in warranty as of August 8, 2005. For task

hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Commercial Airplanes Group - Warranties. The kits for Group 1 airplanes in warranty as of that date

will be supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this

service bulletin number and reference the airplane variable numbers in your purchase order.

C. Parts Necessary For Each Airplane

1. Kits/Parts

Group 1:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Group 1:

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 012A0061 - Top Kit, No. 2 Window Heat Coil Cord Assembly

Existing Part Notes

Number

New Part Number QTY Name

-1

Top Kit, No. 2 Win- -

dow Heat Coil Cord

Assembly

012A0061-1 -

Wire Kit, No. 2 Win- -

dow Heat Coil Cord

Assembly

280A3135-1 1

S280T007-1 (a) (b)

(286A2006-001)

S280A100-1 (ABC 2 Coil Cord

57021)

(a) Discard the existing part.

(b) ABC 57021 is the vendor part number for S280A100-1.

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Kit 280A3135 - Wire Kit, No. 2 Window Heat Coil Cord Assembly

New Part Number QTY Name Notes

-102 -101 -1

Wire Kit, No. 2 Window Heat Coil Cord

Assembly

280A3135-1 . . -

Right No. 2 Window

Heat Coil Cord Assembly

280A3135-101 - 1

Left No. 2 Window

Heat Coil Cord Assembly

280A3135-102 - . 1

Connector Identifica- (a)

tion Tape. Identified

as D10572.

280A3135-10101 . 1 .

Connector Identifica- (a)

tion Tape. Identified

as D10564.

280A3135-10102 . 1 .

Connector Identifica- (a)

tion Tape. Identified

as D10572.

280A3135-10201 1 . .

Connector Identifica- (a)

tion Tape. Identified

as D10568.

280A3135-10202 1 . .

(a) Make from BACT19C-T or BACT19CT.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

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BOEING SERVICE BULLETIN 737-30-1058
F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

3. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

4. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

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

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

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

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

must be used.

6. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps.

7. The work instructions are divided into 2 parts and 2 work packages. Task Hours and

Elapsed Hours for each package are given in Paragraph 1.G., Manpower. You can

do each part and work package independently.

– Part 1- Coil Cord and Wire Connector Changes, Captain's and First Officer's

Sides

– Part 2, Work Package 1- Receptacle Connector Position Change, Captain's

Side

– Part 2, Work Package 2- Receptacle Connector Position Change, First Officer's

Side

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

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– Angular tolerance is plus or minus 2 degrees

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

Manual (SRM) Chapter 51

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

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

SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51.

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

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

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

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

grip length in accordance with SRM Chapter 51.

11. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

12. If it is necessary to remove more parts for access, you can remove those parts. If

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

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

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

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

14. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

B. WORK INSTRUCTIONS

Group 1, Configuration 1:

PART 1: COIL CORD AND WIRE CONNECTOR CHANGES

1. Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as an

accepted procedure.

2. Get access to the flight compartment.

3. Remove the coil cord and panels on the captain's side of the flight compartment in accordance

with FIGURE 1.

4. Install the identification tapes on the W2004 and W2208 wire bundles on the captain's side of the

flight compartment in accordance with FIGURE 2.

5. Inspect the position of the receptacle connector keyway on the captain's side of the flight

compartment in accordance with FIGURE 3.

a. If the keyway is not set at up or 12 o'clock position, turn the receptacle connector in accordance

with FIGURE 4.

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b. If the keyway is set at up or 12 o'clock position, no change to the receptacle connector position

is necessary.

6. Install the new coil cord and panels on the captain's side in accordance with FIGURE 5 and FIGURE

12 .

7. Remove the coil cord and panels on the first officer's side of the flight compartment in accordance

with FIGURE 6.

8. Install the identification tapes on the W2004 and W2108 wire bundles on the first officer's side of

the flight compartment in accordance with FIGURE 7.

9. Inspect the position of the receptacle connector keyway on the first officer's side of the flight

compartment in accordance with FIGURE 8.

a. If the keyway is not set at up or 12 o'clock position, turn the receptacle connector in accordance

with FIGURE 9.

b. If the keyway is set at up or 12 o'clock position, no change to the receptacle connector position

is necessary.

10. Install the new coil cord and panels on the first officer's side in accordance with FIGURE 10 and

FIGURE 14.

11. Restore electrical power removed in Step 1. Refer to 737-600/700/800/900 AMM 24-22-00 as an

accepted procedure.

12. Do the Window Heat Control Unit (WHCU) test in accordance with 737-600/700/800/900 AMM

30-41-11 as an accepted procedure.

13. Put the airplane back to a serviceable condition.

Group 1, Configuration 2; Group 2:

PART 2: RECEPTACLE CONNECTOR POSITION CHANGE

1. Work Package 1: Side Window, Captain's Side

a. Do these steps to get access.

(1) Get access to the flight compartment.

(2) Move the captain's seat forward if necessary. Refer to 737-600/700/800/900 AMM 25-11-00

as an accepted procedure.

b. Do this step to prepare the airplane.

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(1) Do one of these steps to remove electrical power.

(a) Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM

24-22-00 as an accepted procedure.

(b) In the flight compartment, at these distribution panels, open these circuit breakers

and attach DO-NOT-CLOSE tags. Refer to 737-600/700/800/900 AMM 30-41-11 as

an accepted procedure.

Panel Location Name Circuit Breaker Number

WINDOW HEAT POWER LEFT C00392

SIDE

P6-12 B9

WINDOW HEAT CONTROL LEFT C00225

SIDE AC

P18-3 D2

c. Do these steps to change the keyway position of the wire connector D10572.

(1) At the side window, remove the cover assembly and disconnect the receptacle connector

in accordance with FIGURE 11.

(2) Install the receptacle connector with changed keyway position and the cover assembly

in accordance with FIGURE 12.

d. Do these steps to make sure the window heat operates correctly.

(1) Apply electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as

an accepted procedure.

(2) In the flight compartment, at these distribution panels, remove the DO-NOT-CLOSE tags

and close these circuit breakers if they are open.

Panel Location Name Circuit Breaker Number

WINDOW HEAT POWER LEFT C00392

SIDE

P6-12 B9

WINDOW HEAT CONTROL LEFT C00225

SIDE AC

P18-3 D2

(3) Do the Window Heat Control Unit (WHCU) test. Refer to 737-600/700/800/900 AMM

30-41-11 as an accepted procedure.

(4) Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00

as an accepted procedure.

e. Put the airplane back to a serviceable condition.

2. Work Package 2: Side Window, First Officer's (FO) Side

a. Do these steps to get access.

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BOEING SERVICE BULLETIN 737-30-1058
(1) Get access to the flight compartment.

(2) Move the first officer's seat forward if necessary. Refer to 737-600/700/800/900 AMM

25-11-00 as an accepted procedure.

b. Do this step to prepare the airplane.

(1) Do one of these steps to remove electrical power.

(a) Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM

24-22-00 as an accepted procedure.

(b) In the flight compartment, at these distribution panels, open these circuit breakers

and attach DO-NOT-CLOSE tags. Refer to 737-600/700/800/900 AMM 30-41-11 as

an accepted procedure.

Panel Location Name Circuit Breaker Number

WINDOW HEAT POWER RIGHT C00393

SIDE

P6-12 B8

WINDOW HEAT CONTROL RIGHT C00227

SIDE AC

P18-3 E2

c. Do these steps to change the keyway position of the wire connector D10572.

(1) At the side window, remove the cover assembly and disconnect the receptacle connector

in accordance with FIGURE 13.

(2) Install the receptacle connector with changed keyway position and the cover assembly

in accordance with FIGURE 14.

d. Do these steps to make sure the window heat operates correctly.

(1) Apply electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as

an accepted procedure.

(2) In the flight compartment, at these distribution panels, remove the DO-NOT-CLOSE tags

and close these circuit breakers if they are open.

Panel Location Name Circuit Breaker Number

WINDOW HEAT POWER RIGHT C00393

SIDE

P6-12 B8

WINDOW HEAT CONTROL RIGHT C00227

SIDE AC

P18-3 E2

(3) Do the Window Heat Control Unit (WHCU) test. Refer to 737-600/700/800/900 AMM

30-41-11 as an accepted procedure.

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BOEING SERVICE BULLETIN 737-30-1058
(4) Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00

as an accepted procedure.

e. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 1: CAPTAIN'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
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

S280T007-1 1

(286A2006-001)

1 Remove Coil Cord

SIDEWALL PANEL - 232A1521-( ) 1 (a)

NUMBER 3 WINDOW

2 Remove / Keep

FIGURE 1: CAPTAIN'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
Step Task Name Identification Qty More Data

3 Remove / Keep SCREW WHS10F8TPKL10GY 4

Remove / Keep COVER ASSEMBLY 232A1502-( ) 1

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 1: CAPTAIN'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

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

Name Identification Qty More Data

Flag

Note

Imprinted "D10572 M/W M2675".

(a)

Connector Identification 280A3135-10201 1

Tape

1

Imprinted "D10568 M/W M2675".

(a)

Connector Identification 280A3135-10202 1

Tape

2

(a) Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 2: CAPTAIN'S SIDE- IDENTIFICATION TAPE INSTALLATION

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 3: CAPTAIN'S SIDE- CONNECTOR KEYWAY INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

For the major keyway is at the top or

12 o'clock position.

RECEPTACLE CON- D10568 1

NECTOR

1 Inspect

FIGURE 3: CAPTAIN'S SIDE- CONNECTOR KEYWAY INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 4: CAPTAIN'S SIDE- TURN POSITION OF THE CONNECTOR

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

If necessary to put

the major keyway at

the top or 12 o'clock

position. (a)

RECEPTACLE CON- D10568 1

NECTOR

1 Adjust

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 4: CAPTAIN'S SIDE- TURN POSITION OF THE CONNECTOR

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 5: CAPTAIN'S SIDE- COIL CORD AND PANEL INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

Left Panel - No. 3 Win- 232A1521-( ) 1 (a)

dow

1 Install (Kept)

280A100-1 (ABC 1

57021)

2 Install (New) Coil Cord

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 5: CAPTAIN'S SIDE- COIL CORD AND PANEL INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 6: FO'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
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

S280T007-1 1

(286A2006-001)

1 Remove Coil Cord

SIDEWALL PANEL - 232A1521-( ) 1 (a)

NUMBER 3 WINDOW

2 Remove / Keep

FIGURE 6: FO'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
Step Task Name Identification Qty More Data

3 Remove / Keep SCREW WHS10F8TPKL10GY 4

Remove / Keep COVER ASSEMBLY 232A1502-( ) 1

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 6: FO'S SIDE- COIL CORD AND PANEL REMOVAL

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

REFERENCE WIRE DIAGRAM: 737-600/700/800/900 WDM 30-41-11

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

Name Identification Qty More Data

Flag

Note

Imprinted "D10572 M\/W M2675".

(a)

Connector Identification 280A3135-10101 1

Tape

1

Imprinted "D10564 M/W M2675".

(a)

Connector Identification 280A3135-10102 1

Tape

2

(a) Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 7: FO'S SIDE- IDENTIFICATION TAPE INSTALLATION

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 8: FO'S SIDE- CONNECTOR KEYWAY INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

For the major keyway is at the top or

12 o'clock position.

RECEPTACLE CON- D10564 1

NECTOR

1 Inspect

FIGURE 8: FO'S SIDE- CONNECTOR KEYWAY INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 9: FO'S SIDE- TURN POSITION OF THE CONNECTOR KEYWAY

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

If necessary to put

the major keyway at

the top or 12 o'clock

position. (a)

RECEPTACLE CON- D10564 1

NECTOR

1 Adjust

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 9: FO'S SIDE- TURN POSITION OF THE CONNECTOR KEYWAY

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 1.

FIGURE 10: FO'S SIDE- COIL CORD AND PANEL INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
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

SIDEWALL PANEL - 232A1521-( ) 1 (a)

NUMBER 3 WINDOW

1 Install (Kept)

S280A100-1 (ABC 1

57021)

2 Install (New) Coil Cord

(a) Refer to 737-600/700/800/900 AMM 25-11-21 as an accepted procedure.

FIGURE 10: FO'S SIDE- COIL CORD AND PANEL INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 2; Group 2.

FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
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 side of the airplane.

Step Task Name Identification Qty More Data

From connector

D10572 at the cover.

1 Disconnect COIL CORD S280A100-1 1

2 Remove / Keep SCREW WHS10F8TPKL10GY 4

3 Remove / Keep COVER ASSEMBLY 232A1502-( ) 1

4 Remove / Keep SCREW BACS12HN04-6 4

Remove / Keep WASHER NAS1149DN416J 4

From the receptacle

connector.

5 Disconnect NUTPLATE BRACKET FS1268-( ) 1

90 degree in the

counter-clockwise

direction.

CONNECTOR RECEP- BACC45FN10-( ) 1

TACLE, D10572

6 Turn

FIGURE 11: CAPTAIN'S SIDE- REMOVE CONNECTOR D10572

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
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

On the cover at the

initial location.

CONNECTOR RECEP- BACC45FN10-( ) 1

TACLE, D10572

1 Attach

On the receptacle

connector, D10572.

2 Put / Hold NUTPLATE BRACKET FS1268-( ) 1

FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
Step Task Name Identification Qty More Data

3 Install (Kept) SCREW BACS12HN04-6 4

Install (Kept) WASHER NAS1149DN416J 4

4 Install (Kept) COVER ASSEMBLY 232A1502-( ) 1 At the initial location.

Install (Kept) SCREW WHS10F8TPKL10GY 4

To the receptacle

connector, D10572.

5 Connect COIL CORD S280A100-1 1

FIGURE 12: CAPTAIN'S SIDE- INSTALL CONNECTOR D10572

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
This Figure applies only to: Group 1, Configuration 2; Group 2.

FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
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

From the connector

D10572 at the cover.

1 Disconnect COIL CORD S280A100-1 1

2 Remove / Keep SCREW WHS10F8TPKL10GY 4

3 Remove / Keep COVER ASSEMBLY 232A1502-( ) 1

4 Remove / Keep SCREW BACS12HN04-6 4

Remove / Keep WASHER NAS1149DN416J 4

From the receptacle

connector.

5 Disconnect NUTPLATE BRACKET FS1268-( ) 1

90 degree in the

clockwise direction.

CONNECTOR RECEP- BACC45FN10-( ) 1

TACLE, D10572

6 Turn

FIGURE 13: FO'S SIDE- REMOVE CONNECTOR D10572

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
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

On the cover at the

initial location.

CONNECTOR RECEP- BACC45FN10-( ) 1

TACLE, D10572

1 Attach

On the receptacle

connector, D10572.

2 Put / Hold NUTPLATE BRACKET FS1268-( ) 1

FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058
Step Task Name Identification Qty More Data

3 Install (Kept) SCREW BACS12HN04-6 4

Install (Kept) WASHER NAS1149DN416J 4

4 Install (Kept) COVER ASSEMBLY 232A1502-( ) 1 At the initial location.

Install (Kept) SCREW WHS10F8TPKL10GY 4

To the receptacle

connector, D10572.

5 Connect COIL CORD S280A100-1 1

FIGURE 14: FO'S SIDE- INSTALL CONNECTOR D10572

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 737-30-1058