### 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.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 1 of 38 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 2 of 38 **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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 3 of 38 **BOEING SERVICE BULLETIN 737-27-1282**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 4 of 38 **BOEING SERVICE BULLETIN 737-27-1282**

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### 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** March 15, 2007 Original Issue: June 14, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 5 of 38BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 6 of 38 **BOEING SERVICE BULLETIN 737-27-1282**

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### 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 7 of 38— 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 8 of 38 **BOEING SERVICE BULLETIN 737-27-1282**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 9 of 38 **BOEING SERVICE BULLETIN 737-27-1282**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 10 of 38 **BOEING SERVICE BULLETIN 737-27-1282**

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### 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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Variable Number** 1 YA001 - YA099 1 YA101 - YA199 1 YA201 - YA211 1 YA221 1 YA231 - YA242 1 YA251 - YA256

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 11 of 38**Group Variable Number** 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 YA809 1 YA811 - YA814 1 YA831 - YA835 1 YA841 - YA862 1 YA881 - YA882

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 12 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 13 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 14 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 15 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 16 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 17 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 18 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 19 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 20 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 21 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Group**  **Variable Number**1 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 22 of 38 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 23 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Affected Maintenance Zones** **Zone Model**  114, 115 737-600, 737-700, 737-700C, 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. **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

0.75 0.75 1 Open Access 0.25 0.50 2 Figure 1 0.75 0.75 1 Close Access

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 24 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 

1.75 2.00 TOTAL FOR EACH AIRPLANE 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. **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

0.75 0.75 1 Open Access 0.25 0.50 2 Figure 1 0.50 1.00 2 Figure 2 0.75 0.75 1 Close Access 2.25 3.00 TOTAL FOR EACH AIRPLANE 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. **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**

0.75 0.75 1 Open Access 0.25 0.50 2 Figure 1 0.50 1.00 2 Figure 2 0.75 0.75 1 Close Access 0.75 0.75 1 Test(s) 3.00 (a) 3.75 (a) TOTAL FOR EACH AIRPLANE (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 25 of 38 **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:
**Title Drawing Number**  Wire Bundle Instl - Flight Deck Floor Beams 288A4140 Sheet 433 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 26 of 38 **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:
**Notes Name**  **QTY Part Number / Specification**  (a) (c) Lacing Tape 1 BMS 13-54 Grade D, Type III, Class 1, Finish C (a) (b) (c) Plastic Tie Strap 20 BACS38K9 (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 27 of 38 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 28 of 38 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 29 of 38 **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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 30 of 38 **BOEING SERVICE BULLETIN 737-27-1282**(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:
**Name Number**  **Column Row**  FLIGHT CONTROL STAB TRIM CONT C00207 10 B FLIGHT CONTROL STAB TRIM ACTUATOR C00840 10 D(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:
**Name Number**  **Column Row**  PANEL & INSTR 28V PRI CAPT & CTR C00331 9 B PANEL & INSTR 28V PRI F/O C00335 10 B (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:
**Name Number**  **Column Row**  AFCS SYS A MACH TRIM AC C00456 4 C AFCS SYS A SNSR EXC AC C01041 5 C

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 31 of 38 **BOEING SERVICE BULLETIN 737-27-1282 Name**  **Number Column**  **Row** AFCS SYS A WARN LIGHT (BAT) C01049 1 D AFCS SYS A FCC DC C01045 2 D AFCS SYS A ENGAGE INTLK C01048 3 D AFCS SYS A MACH TRIM DC C00457 4 D AFCS MCP DC 1 C01044 5 D(2) Make sure the circuit breakers that follow are closed on the P6-2 panel:
**Name Number**  **Column Row**  AFCS SYS B WARN LIGHT (BAT) C00374 1 B AFCS SYS B MACH TRIM DC C01064 2 B AFCS SYS B FCC DC C01046 3 B AFCS SYS B ENGAGE INTLK C00716 4 B AFCS SYS B MACH TRIM AC C01037 1 C AFCS SYS B SNSR EXC AC C01042 2 C AFCS MCP DC 2 C01047 3 C(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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 32 of 38 **BOEING SERVICE BULLETIN 737-27-1282**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:
**Name Number**  **Column Row**  INTERPHONE POWER F/O DC 2 C00560 21 C INTERPHONE POWER F/O BAT C00561 22 C INTERPHONE POWER CAPT DC 2 C00239 23 C INTERPHONE POWER CAPT BAT C00240 24 C AUDIO F/O C00086 22 D AUDIO CAPT C00083 23 D (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 33 of 38 **BOEING SERVICE BULLETIN 737-27-1282**(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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1: June 14, 2010 34 of 38 **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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1 June 14, 2010 35 of 38 **BOEING SERVICE BULLETIN 737-27-1282 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** do a detail inspection for chafing or damage. Refer to SWPM 20-10-06, as an accepted procedure. (a) - W443 Wire Bundle Inspect 1

for a minimum clearance of 0.5 inch from left forward rudder quadrant full travel motion. - W443 Wire Bundle Clearance Measure 2 (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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1 June 14, 2010 36 of 38 **BOEING SERVICE BULLETIN 737-27-1282**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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1 June 14, 2010 37 of 38 **BOEING SERVICE BULLETIN 737-27-1282 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** route as straight as possible.

- W443 Wire Bundle Adjust 1 Refer to SWPM 20-10-11 and SWPM 20-10- 12, as accepted procedures. (a) (b) (c) (d) to the adjacent wire bundles, as necessary.

- W443 Wire Bundle Route / At- 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. - W443 Wire Bundle Clearance Measure 3

Minimize bend radius. (a) Adjust wire bundle to make sure that contact is not made with any part that moves. (b) Adjust wire bundle to increase the minimum clearance to 0.5 inch. (c) 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)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 15, 2007 737-27-1282 Revision 1 June 14, 2010 38 of 38 **BOEING SERVICE BULLETIN 737-27-1282**