Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-27-1282

Original Issue: March 15, 2007

Revision 1: June 14, 2010

ATA System: 2721

SUBJECT: FLIGHT CONTROLS - Rudder and Rudder Trim Control System - Wire Bundle W443

and Left Forward Rudder Quadrant Clearance Inspection

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 © 2007 The Boeing Company

Unpublished Work - All Rights Reserved

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

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

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

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

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

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

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

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

connection with this document unless provided in writing by Boeing.

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2.0
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BOEING SERVICE BULLETIN 737-27-1282

BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 26

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 27

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 1: WIRE BUNDLE W443 INSPECTION FOR DAMAGE . . . . . . . . . . . . . . . . . . . . 35

FIGURE 2: WIRE BUNDLE W443 CLEARANCE ADJUSTMENT . . . . . . . . . . . . . . . . . . . . 37

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BOEING SERVICE BULLETIN 737-27-1282
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BOEING SERVICE BULLETIN 737-27-1282

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 737-27-1282

Original Issue: March 15, 2007

Revision 1: June 14, 2010

ATA System: 2721

SUBJECT: FLIGHT CONTROLS - Rudder and Rudder Trim Control System - Wire Bundle W443

and Left Forward Rudder Quadrant Clearance Inspection

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is required for airplanes inspected by the original issue of this service bulletin.

The following airplanes were added to this service bulletin: 2018-2591, 2593-2597, 2600-2602, 2640-2793,

2795-2800, 2802, 2803, 2805, 2807, 2810, 2812.

REASON FOR REVISION

This service bulletin is sent to tell operators that additional airplanes have been added to this service bulletin

effectivity. The airplanes added may have been delivered with no inspection of the wire bundle W443 done in

production.

The following airplanes were added to the service bulletin and Group 1 by Revision 01: 2018-2591, 2593-2597,

2600-2602, 2640-2793, 2795-2800, 2802, 2803, 2805, 2807, 2810, 2812.

Revision 1; The following Paragraphs are changed:

• Paragraph 1.A., Effectivity is revised to add airplanes.

• Paragraph 1.C., Reason is revised to add reason for revision 1.

• Paragraph 1.D., Description is revised to add "No more work required" and maintenance zones.

No more work is required for airplanes inspected by the original issue of this service bulletin.

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: March 15, 2007

Revision 1: June 14, 2010

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BOEING SERVICE BULLETIN 737-27-1282

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Summary Number: 737-27-1282

Original Issue: March 15, 2007

Revision 1: June 14, 2010

ATA System: 2721

SUBJECT: FLIGHT CONTROLS - Rudder and Rudder Trim Control System - Wire Bundle W443

and Left Forward Rudder Quadrant Clearance Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin is sent to tell operators that on some airplanes an interference (riding) condition may exist

between wire bundle W443 and the Left Forward rudder quadrant. The interference can occur during full Right

Rudder travel. Restricted control surface movement and wire bundle damage can occur when there is not

sufficient clearance between wire bundle W443 and the left forward rudder quadrant. If this Service Bulletin is

not done, the wire bundle could restrict the free movement of the rudder quadrant. If the wire bundle is damaged,

uncommanded stabilizer trim or autopilot disconnects could occur.

This condition was found on airplane YK904 during pre-flight checks at Boeing's Renton Field facility. A pilot

reported light interference during full right travel. The problem was identified as contact between the left forward

rudder quadrant and wire bundle W443. On investigation it was found that the wire bundle was installed with

too much slack between clamps. An Non-Conformance Record (NCR) was created to inspect all airplanes prior

to delivery and to rework the wire bundle installation as necessary. 32 airplanes were inspected, of which 20

were found to have contact between the left forward quadrant and the wire bundle. Boeing has revised the

installation drawing to add clarification to the wire bundle routing.

Accomplishment of this service bulletin inspects the left forward rudder quadrant for sufficient clearance with

wire bundle W443. Instructions are also given to adjust the routing of the wire bundle W443 and repair, if

necessary.

Boeing Service Related Problem (SRP) 737NG-SRP-27-0190 is related to this service bulletin.

ACTION

Get access to the airplane flight compartment and left forward rudder quadrant through the forward access door

112A.

Part 1: Wire Bundle W443 Inspection for damage.

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— Do a detail inspection and measure the minimum clearance between the wire bundle W443 and the left

forward rudder quadrant.

Part 2: Wire Bundle W443 Clearance Adjustment.

— Adjust the wire bundle W443 routing to obtain a sufficient clearance between wire bundle and rudder

quadrant.

— Do an operational test of the rudder control system.

Part 3: Wire Bundle W443 Repair and Adjustment.

— Repair damaged wire bundle W443.

— Measure the minimum clearance between the wire bundle W443 and the left forward rudder quadrant.

— Do an operational test of the rudder control system as given in Part 2.

— Test applicable systems affected by wire bundle damage.

EFFECTIVITY

737-600/-700/-700C/-800/-900/-900ER Airplanes. 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.

Boeing recommends this service bulletin be incorporated within 60 months from the date on this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of May 12, 2006. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 737-27-1282
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BOEING SERVICE BULLETIN 737-27-1282

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-27-1282

Original Issue: March 15, 2007

Revision 1: June 14, 2010

ATA System: 2721

SUBJECT: FLIGHT CONTROLS - Rudder and Rudder Trim Control System - Wire Bundle W443

and Left Forward Rudder Quadrant Clearance Inspection

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.

GROUP CONFIGURATION DESCRIPTION

737-600/ -700/ -700C/ -800/ -900/ -900ER with possible interference

(riding) condition between wire bundle W443 and Left Forward Rudder

Quadrant, line numbers 1 through 1842, 1844 through 1902, 1904

through 1905, and 1907.

1 -

Airplane Models:

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

Variable Number Group

YA001 - YA099 1

YA101 - YA199 1

YA201 - YA211 1

YA221 1

YA231 - YA242 1

YA251 - YA256 1

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Variable Number Group

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

YA809 1

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YA891 - YA892 1

YA961 - YA976 1

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 - YB387 1

YB392 1

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB579 1

YB581 - YB595 1

YB601 - YB632 1

YB651 1

YB656 1

YB671 - YB672 1

YB851 - YB863 1

YB871 - YB874 1

YB881 - YB893 1

YB901 - YB903 1

YB911 1

YB961 - YB974 1

YB986 1

YC001 - YC030 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YC051 - YC084 1

YC091 - YC094 1

YC101 - YC104 1

YC111 - YC113 1

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC179 1

YC186 - YC190 1

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC386 1

YC391 - YC394 1

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC439 1

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

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC741 1

YC744 - 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

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD110 1

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 - YD413 1

YD415 1

YD481 - YD485 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YD491 - YD492 1

YD496 - YD499 1

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

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE375 1

YE381 - YE383 1

YF001 - YF002 1

YF021 1

YF023 - YF027 1

YF052 - YF053 1

YF106 - YF107 1

YF111 1

YF176 - YF177 1

YF501 - YF508 1

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG103 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YG111 - YG114 1

YG116 - YG121 1

YG201 - YG203 1

YG211 - YG212 1

YG214 1

YG251 - YG252 1

YG501 - YG509 1

YG601 - YG602 1

YG701 1

YG711 1

YH002 - YH012 1

YH031 - YH032 1

YH051 - YH052 1

YH055 1

YH101 - YH109 1

YH111 - YH119 1

YH201 - YH202 1

YH206 1

YH301 - YH302 1

YJ001 - YJ008 1

YJ010 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ552 1

YJ555 - YJ562 1

YJ564 - YJ570 1

YJ591 - YJ596 1

YJ598 1

YJ631 - YJ632 1

YJ671 - YJ689 1

YJ694 1

YJ801 - YJ867 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YJ871 - YJ873 1

YJ875 - YJ876 1

YJ901 - YJ904 1

YJ908 - YJ909 1

YJ911 - YJ929 1

YJ931 - YJ937 1

YJ941 - YJ943 1

YJ948 - YJ956 1

YJ976 - YJ977 1

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

YK131 - YK132 1

YK136 - YK139 1

YK141 - YK142 1

YK148 1

YK151 1

YK163 - YK166 1

YK171 1

YK177 1

YK186 1

YK301 - YK304 1

YK306 - YK310 1

YK321 - YK330 1

YK334 - YK339 1

YK361 - YK367 1

YK370 - YK373 1

YK375 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK434 1

YK438 - YK450 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YK456 - YK461 1

YK480 - YK486 1

YK495 1

YK511 - YK516 1

YK521 - YK523 1

YK551 - YK554 1

YK565 1

YK567 - YK571 1

YK576 - YK577 1

YK580 - YK585 1

YK601 - YK602 1

YK606 - YK607 1

YK611 - YK612 1

YK614 1

YK616 1

YK621 1

YK624 - YK634 1

YK643 - YK644 1

YK651 - YK661 1

YK671 - YK672 1

YK676 1

YK681 1

YK701 - YK706 1

YK708 - YK711 1

YK713 1

YK716 - YK719 1

YK722 - YK741 1

YK751 - YK763 1

YK791 - YK792 1

YK796 - YK797 1

YK801 - YK814 1

YK819 - YK884 1

YK888 - YK899 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YK901 - YK902 1

YK904 1

YK907 - YK912 1

YK918 1

YK921 - YK926 1

YK941 - YK955 1

YK961 - YK971 1

YK981 - YK986 1

YL001 1

YL012 - YL016 1

YL021 - YL024 1

YL051 - YL052 1

YL056 - YL057 1

YL061 1

YL066 - YL069 1

YL076 - YL077 1

YL101 - YL114 1

YL116 - YL124 1

YL201 - YL207 1

YL209 - YL210 1

YL271 - YL272 1

YL281 - YL282 1

YL301 - YL303 1

YL311 - YL312 1

YL316 - YL318 1

YL320 1

YL351 - YL353 1

YL371 - YL373 1

YL401 1

YL421 - YL426 1

YL431 - YL437 1

YL461 - YL471 1

YL473 - YL474 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YL501 - YL506 1

YL531 - YL534 1

YL541 1

YL561 1

YL563 - YL565 1

YL591 1

YL601 - YL606 1

YL611 1

YL616 - YL617 1

YL621 1

YL663 - YL664 1

YL676 1

YL901 - YL903 1

YL905 - YL909 1

YL931 - YL934 1

YL952 - YL953 1

YM101 - YM103 1

YM201 - YM208 1

YM212 - YM236 1

YM238 1

YM251 - YM282 1

YM298 - YM299 1

YM301 - YM366 1

YM369 - YM376 1

YM471 1

YM481 - YM484 1

YM501 - YM507 1

YM509 - YM515 1

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 1

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BOEING SERVICE BULLETIN 737-27-1282
Variable Number Group

YM632 - YM634 1

YM641 - YM648 1

YM651 1

YM671 - YM672 1

YM691 - YM693 1

YM701 - YM707 1

YN001 - YN004 1

YN007 - YN016 1

YN021 - YN024 1

YN061 1

YN071 - YN079 1

YN091 - YN092 1

YN101 1

YN106 - YN112 1

YN121 1

YN201 - YN202 1

YN211 - YN216 1

YN231 - YN234 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin is sent to tell operators that on some airplanes an interference (riding) condition

may exist between wire bundle W443 and the Left Forward rudder quadrant. The interference can

occur during full Right Rudder travel. Restricted control surface movement and wire bundle damage

can occur when there is not sufficient clearance between wire bundle W443 and the left forward rudder

quadrant. If this Service Bulletin is not done, the wire bundle could restrict the free movement of the

rudder quadrant. If the wire bundle is damaged, uncommanded stabilizer trim or autopilot disconnects

could occur.

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BOEING SERVICE BULLETIN 737-27-1282
This condition was found on airplane YK904 during pre-flight checks at Boeing's Renton Field facility.

A pilot reported light interference during full right travel. The problem was identified as contact between

the left forward rudder quadrant and wire bundle W443. On investigation it was found that the wire

bundle was installed with too much slack between clamps. An Non-Conformance Record (NCR) was

created to inspect all airplanes prior to delivery and to rework the wire bundle installation as necessary.

32 airplanes were inspected, of which 20 were found to have contact between the left forward quadrant

and the wire bundle. Boeing has revised the installation drawing to add clarification to the wire bundle

routing.

Accomplishment of this service bulletin inspects the left forward rudder quadrant for sufficient clearance

with wire bundle W443. Instructions are also given to adjust the routing of the wire bundle W443 and

repair, if necessary.

Boeing Service Related Problem (SRP) 737NG-SRP-27-0190 is related to this service bulletin

Revision 01: This service bulletin is sent to tell operators that additional airplanes have been added to

this service bulletin effectivity. The airplanes added may have been delivered with no inspection of the

wire bundle W443 done in production.

Revision 1; The following Paragraphs are changed:

• Paragraph 1.A., Effectivity is revised to add airplanes.

• Paragraph 1.C., Reason is revised to add reason for revision 1.

• Paragraph 1.D., Description is revised to add "No more work required" and maintenance zones.

D. Description

Get access to the airplane flight compartment and left forward rudder quadrant through the forward

access door 112A.

Part 1: Wire Bundle W443 Inspection for damage.

— Do a detail inspection and measure the minimum clearance between the wire bundle W443 and

the left forward rudder quadrant.

Part 2: Wire Bundle W443 Clearance Adjustment.

— Adjust the wire bundle W443 routing to obtain a sufficient clearance between wire bundle and

rudder quadrant.

— Do an operational test of the rudder control system.

Part 3: Wire Bundle W443 Repair and Clearance Adjustment.

— Repair damaged wire bundle W443.

— Measure the minimum clearance between the wire bundle W443 and the left forward rudder

quadrant.

— Do an operational test of the rudder control system as given in Part 2.

— Test applicable systems affected by wire bundle damage.

Revision 1 - No more work is necessary on airplanes changed in accordance with original issue of this

service bulletin.

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

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BOEING SERVICE BULLETIN 737-27-1282
Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 114, 115

737-800, 737-900, 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 this service bulletin be incorporated within 60 months from the date on this service

bulletin.

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 tables below show an estimate of the task-hours necessary to do this service bulletin for each

airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with

operator task-hour data if necessary. The estimate does not include lost time. These are some examples

of lost time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

The table below shows the time necessary to do Part 1: Wire Bundle W443 Inspection for damage.

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.75 0.75

Figure 1 2 0.50 0.25

Close Access 1 0.75 0.75

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BOEING SERVICE BULLETIN 737-27-1282
Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE 2.00 1.75

The table below shows the time necessary to do Part 1: Wire Bundle W443 Inspection for damage and

Part 2: Wire Bundle W443 Clearance Adjustment.

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.75 0.75

Figure 1 2 0.50 0.25

Figure 2 2 1.00 0.50

Close Access 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 3.00 2.25

The table below shows the time necessary to do Part 1: Wire Bundle W443 Inspection for damage and

Part 3: Wire Bundle Repair and Clearance Adjustment.

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.75 0.75

Figure 1 2 0.50 0.25

Figure 2 2 1.00 0.50

Close Access 1 0.75 0.75

Test(s) 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 3.75 (a) 3.00 (a)

(a) This estimate does not include the time necessary to repair wire bundle W443 if

damage is found. More time could be necessary to do the repair as the quantity of

damage is not known.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

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BOEING SERVICE BULLETIN 737-27-1282
J. References

1. Existing Data:

a. Service Related Problem (SRP) 737NG-SRP-27-0190.

b. 737 Maintenance Manual (AMM) Subject 06-41-00, 22-11-00, 23-11-00, 24-22-00, 27-21-00,

27-41-00, 33-11-00.

c. Boeing Standard Wiring Practices Manual (SWPM) 20-10-06, 20-10-11, 20-10-12, 20-10-13,

20-10-19.

2. Data supplied with this Service Bulletin:

None.

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

Drawing Number Title

288A4140 Sheet 433 Wire Bundle Instl - Flight Deck Floor Beams

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

K. Publications Affected

None.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 737-27-1282
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are available for 737 airplanes in warranty as of May 12, 2006. For inspection

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

the condition described in this service bulletin is found during the inspection for airplanes in warranty

as of that date and additional task hours are required, send a claim to Boeing Warranty. Please refer

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

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

Part Number / Specification QTY Name Notes

BMS 13-54 Grade D, Type III, 1 Lacing Tape (a) (c)

Class 1, Finish C

BACS38K9 20 Plastic Tie Strap (a) (b) (c)

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

(b) Use as an approved alternative.

(c) See the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

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 737-27-1282
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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BOEING SERVICE BULLETIN 737-27-1282
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 Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for

the wire installation procedures.

4. 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.

5. 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.

6. Hydraulic systems A, B, and standby must have pressure removed before

maintenance is done on the rudder control system. This is to prevent injury to persons

because of accidental operation of the control system while you do maintenance.

You must be careful to put maintenance stands and equipment away from control

surface travel.

B. WORK INSTRUCTIONS

1. Make sure that the hydraulic systems A, B, and standby have pressure removed. Refer to

737-600/700/800/900 AMM 27-21-00 as an accepted procedure.

2. Make sure that the electrical power is removed from the airplane. Refer to 737-600/700/800/900

AMM 24-22-00, as an accepted procedure. Use an independent power source for lighting.

3. Get access to the left forward rudder quadrant through the forward access door 112A. Refer to

737-600/700/800/900 AMM 06-41-00, as an accepted procedure.

4. Get access to the flight compartment.

5. Part 1: Wire Bundle W443 Inspection for damage.

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BOEING SERVICE BULLETIN 737-27-1282
a. Push and hold the pilot's right rudder pedal fully to the travel stops.

b. Do a detail inspection of the wire bundle W443 for damage and measure for sufficient clearance

in accordance with Figure 1.

(1) If the wire bundle is not damaged and a minimum 0.5 inch clearance exists between the

forward rudder quadrant, then put the airplane back to a serviceable condition.

(2) If the wire bundle is not damaged and a 0.5 inch clearance does not exist between the

forward rudder quadrant, then do Part 2: Wire Bundle W443 Clearance Adjustment.

(3) If the wire bundle is damaged then repair in accordance with Part 3: Wire Bundle W443

Repair and Clearance Adjustment.

c. Slowly release the pilot's right rudder pedal fully.

6. Part 2: Wire Bundle W443 Clearance Adjustment.

a. Adjust the wire bundle clearance in accordance with Figure 2.

b. Push and hold the pilot's right rudder pedal fully to the travel stops. Make sure there is sufficient

clearance in accordance with Figure 2.

c. Slowly release the pilot's right rudder pedal fully.

d. Do the operational check that follows of the rudder control system.

(1) Push the pilot's right rudder pedal fully forward to the travel stops. Make sure the rudder

pedal travel is smooth and there is no evidence of interference, slowly release the rudder

pedal.

(2) Push the pilot's left rudder pedal fully forward to the travel stops. Make sure the rudder

pedal travel is smooth and there is no evidence of interference, slowly release the rudder

pedal.

e. Put the airplane back to a serviceable condition

7. Part 3: Wire Bundle W443 Repair and Clearance Adjustment.

a. Repair damaged wire bundle. Refer to SWPM 20-10-13, as an accepted procedure.

b. Adjust the wire bundle clearance in accordance with Part 2: Wire Bundle W443 Clearance

Adjustment.

c. Restore the electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00,

as an accepted procedure.

d. Do a test of the applicable system that was repaired as necessary:

Control Column Check (if necessary)

(1) Do a check of the control column:

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(a) Move the control column full forward then full aft.

1) Make sure the control column operates correctly and smoothly.

(b) Turn the control wheel through full travel.

1) Make sure the control wheel operates correctly and smoothly.

Stabilizer Trim system test (if necessary)

(1) Make sure the circuit breakers that follow are closed on the P6-2 panel:

Row Column Number Name

B 10 C00207 FLIGHT CONTROL STAB TRIM CONT

D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR

(2) Do a test of the stabilizer trim control switch on the control wheel:

(a) Move the STAB TRIM CUTOUT switch to the NORMAL position.

(b) Move the STAB TRIM switches to APL NOSE UP and then to APL NOSE DOWN.

(c) Make sure the stabilizer moves correctly.

Memory device lighting system test (if necessary)

(1) Make sure the circuit breakers that follow are closed on the P6-3 panel:

Row Column Number Name

B 9 C00331 PANEL & INSTR 28V PRI CAPT & CTR

B 10 C00335 PANEL & INSTR 28V PRI F/O

(2) Do a test of the memory device lighting:

(a) At the P1 panel, set the CAPT'S AND CENTER PANEL LIGHTING CONTROL switch

to the dim position and then to the bright position.

1) Make sure the intensity of the light changes from dim to bright.

(b) Set the switch to the off position.

Autopilot disconnect system test (if necessary)

(1) Make sure the circuit breakers that follow are closed on the P18-1 panel:

Row Column Number Name

C 4 C00456 AFCS SYS A MACH TRIM AC

C 5 C01041 AFCS SYS A SNSR EXC AC

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Row Column Number Name

D 1 C01049 AFCS SYS A WARN LIGHT (BAT)

D 2 C01045 AFCS SYS A FCC DC

D 3 C01048 AFCS SYS A ENGAGE INTLK

D 4 C00457 AFCS SYS A MACH TRIM DC

D 5 C01044 AFCS MCP DC 1

(2) Make sure the circuit breakers that follow are closed on the P6-2 panel:

Row Column Number Name

B 1 C00374 AFCS SYS B WARN LIGHT (BAT)

B 2 C01064 AFCS SYS B MACH TRIM DC

B 3 C01046 AFCS SYS B FCC DC

B 4 C00716 AFCS SYS B ENGAGE INTLK

C 1 C01037 AFCS SYS B MACH TRIM AC

C 2 C01042 AFCS SYS B SNSR EXC AC

C 3 C01047 AFCS MCP DC 2

(3) Make sure that the autopilot stab trim cutout switch, on the control stand, is in the NORMAL

position.

(4) Make sure that the VHF NAV and IRS switches, on the P5 forward overhead panel, are

in the NORMAL position.

(5) Set the left and right IRS switches, on the P5 overhead panel, to the ALIGN or NAV

position.

WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL

SURFACES. THE AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS,

SPOILERS, STABILIZER AND NOSE GEAR CAN MOVE SUDDENLY WHEN

YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS

AND DAMAGE TO EQUIPMENT.

(6) Supply hydraulic power to hydraulic systems A and B. Refer to 737-600/700/800/900

AMM 29-11-00, as an accepted procedure.

(7) Do a test of the autopilot disengage switch on the control wheel:

(a) Push the CMD A or CMD B autopilot engage switch on the mode control panel to

engage the autopilot.

1) Make sure that the CMD A or CMD B autopilot engage switch light comes on.

(b) Push the captain or first officer autopilot disengage switch on the control wheel to

disengage the autopilot.

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1) Make sure that the A/P warning lights flash.

2) Make sure that the A/P disengage warning sound comes on.

3) Push the captain or first officer autopilot disengage switch again.

a) Make sure that the A/P warning lights go off.

b) Make sure that there is no A/P disengage warning sound.

(8) Set the left and right IRS switches, on the P5 overhead panel, to the OFF position.

(9) Remove hydraulic power from hydraulic systems A and B. Refer to 737-600/700/800/900

AMM 29-11-00, as an accepted procedure.

Push-to-talk switches system test (if necessary)

(1) Make sure the circuit breakers that follow are closed on the P6-2 panel:

Row Column Number Name

C 21 C00560 INTERPHONE POWER F/O DC 2

C 22 C00561 INTERPHONE POWER F/O BAT

C 23 C00239 INTERPHONE POWER CAPT DC 2

C 24 C00240 INTERPHONE POWER CAPT BAT

D 22 C00086 AUDIO F/O

D 23 C00083 AUDIO CAPT

(2) Do an operational test of the PTT switch on the control wheel:

NOTE: The label for the microphone selector switch on the audio control panel (ACP)

is FLT INT or INT dependant on the ACP fitted to the airplane.

In the operational test that follows the microphone selector switch is referred to

as the INT microphone selector switch for either case.

(a) Push the INT microphone selector switch on the pilot's audio control panel (ACP) to

on.

(b) Push the volume control for the INT microphone selector switch.

(c) Turn the volume control for the INT microphone selector switch clockwise to the

middle position.

(d) Push the SPKR volume control switch to on.

(e) Turn the SPKR volume control switch clockwise to the middle position or to the

volume level you are comfortable with.

(f) Push and hold the PTT switch on the pilot's control wheel to the MIC position.

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(g) Speak into the pilot's boom microphone.

1) Make sure you hear the voice clearly on the headsets.

(h) Release the PTT switch.

1) Make sure the switch goes to the center (off) position.

(i) Push and hold the PTT switch on the pilot's control wheel to the INT position.

(j) Speak into the pilot's boom microphone.

1) Make sure you hear the voice clearly on the headsets.

(k) Release the PTT switch.

1) Make sure the switch goes to the center (off) position.

e. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 737-27-1282
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

FIGURE 1: WIRE BUNDLE W443 INSPECTION FOR DAMAGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-27-1282
STEP TASK NAME IDENTIFICATION QTY MORE DATA

do a detail inspection for chafing or damage.

Refer to SWPM 20-10-06, as an accepted

procedure. (a)

1 Inspect Wire Bundle W443 -

for a minimum clearance of 0.5 inch from left

forward rudder quadrant full travel motion.

Wire Bundle W443 -

Clearance

2 Measure

(a) Check if there is damage to wire bundle protection sleeve, and/or damage to the wire jacket or insulation.

FIGURE 1: WIRE BUNDLE W443 INSPECTION FOR DAMAGE

(SHEET 2 OF 2)

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

FIGURE 2: WIRE BUNDLE W443 CLEARANCE ADJUSTMENT

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-27-1282
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Adjust Wire Bundle W443 - route as straight as possible.

Refer to SWPM 20-10-11 and SWPM 20-10-

12, as accepted procedures.

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

Route / At- Wire Bundle W443 - to the adjacent wire bundles, as necessary.

tach

2

Refer to SWPM 20-10-11 and SWPM 20-10-

19, as accepted procedures.

(b) (c) (d)

for a minimum clearance of 0.5 inch from left

forward rudder quadrant full travel motion.

Wire Bundle W443 -

Clearance

3 Measure

(a) Minimize bend radius.

(b) Adjust wire bundle to make sure that contact is not made with any part that moves.

(c) Adjust wire bundle to increase the minimum clearance to 0.5 inch.

Cut and install lacing tape (part number BMS 13-54 Type III) or install plastic tie straps (part number

BACS38K9), as an approved alternative, to hold wire bundle in position.

(d)

FIGURE 2: WIRE BUNDLE W443 CLEARANCE ADJUSTMENT

(SHEET 2 OF 2)

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