### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-29-1113**  Original Issue: March 23, 2011 ATA System: 2900 **SUBJECT:** HYDRAULIC POWER - Right Main Landing Gear Wheel Well - Wire Bundle and Hydraulic Tubing - Inspection, Repair and New Clamps Installation 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 1 of 35 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 2 of 35 **BOEING SERVICE BULLETIN 737-29-1113**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 23 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 24 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC TUBING AND WIRE BUNDLES - INSPECTION. . . . . . . . . . . . . . . . . . . . . . . 31 FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS - INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 3 of 35 **BOEING SERVICE BULLETIN 737-29-1113**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 4 of 35 **BOEING SERVICE BULLETIN 737-29-1113**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 737-29-1113** Original Issue: March 23, 2011 ATA System: 2900 **SUBJECT:** HYDRAULIC POWER - Right Main Landing Gear Wheel Well - Wire Bundle and Hydraulic Tubing - Inspection, Repair and New Clamps Installation BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** This service bulletin is sent to prevent possible wire chafing damage to wire bundles W6128, W7122, W8122 and W8222, caused by insufficient separation from hydraulic tubing in two locations below Electric Motor Driven Pump (EMDP) 'B' in the Main Landing Gear (MLG) wheel well. If this service bulletin is not done, wire chafing could result in arcing, which could also cause damage to wires and hydraulic tubing that could then result in operational disruption and unplanned maintenance. Boeing has received a report, from a 737-800 operator, which told of damage to wire W8222-6011-18. The wire was arcing to hydraulic tubing in a location below EMDP 'B' on the forward bulkhead of the MLG wheel well. The short circuit to the hydraulic tubing caused a circuit breaker to open. Boeing inspected some airplanes in production and found that there was not sufficient separation between the wire bundles, that include W8222, and adjacent hydraulic tubing at that location. As a result, Boeing added a new clamping configuration to production airplanes from line number 3348 and on. Airplanes before line number 1060 do not need this change, because of a configuration difference, in the applicable area. Boeing is issuing this service bulletin as a fix for applicable in-service airplanes. New clamps are added, at the location where damage occurred, to secure wire bundles W6128, W7122, W8122 and W8222 and keep sufficient clearance between the wire bundles and adjacent hydraulic tubing. Accomplishment of this service bulletin will inspect the four wire bundles, located below EMDP 'B', for wire chafing damage and repair as necessary. The related hydraulic tubing will also be inspected and replaced or repaired as necessary. New clamps are installed between the wire bundles and the adjacent hydraulic tubing, P/N 272A4451-136 at STA663 RBL10 WL161, to give sufficient separation to prevent possible wire chafing damage. Boeing Service Related Problem (SRP) 737NG-24-0138 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737NG FTD 20-10001 is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 5 of 35**ACTION (PRR 38275-173S)** Get access to the right side of the MLG wheel well. Do a General Visual Inspection (GVI) for wire chafing damage of wire bundles W6128, W7122, W8122 and W8222 and hydraulic tubing, P/N 272A4451-136 and 272A4451-137, in an area below Electric Motor Driven Pump 'B' on the forward bulkhead. If any wire bundles are found to be damaged, repair as necessary. If any hydraulic tubing is found to be damaged, replace or repair as necessary. Install new clamps at the intersection between the wire bundles and the hydraulic tubing, P/N 272A4451-136. Do a test of applicable electrical systems, where wire bundles were repaired. Service the hydraulic system if hydraulic tubing was replaced or repaired. Put airplane back to a serviceable condition. **EFFECTIVITY** 737-600, -700, -700C, -800, -900 and -900ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Boeing recommends that the inspection, change and repair given in this service bulletin be done within 24 months after the original issue date of this service bulletin. 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. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for 737 airplanes in warranty as of May 20, 2010. 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 23, 2011 737-29-1113 6 of 35 **BOEING SERVICE BULLETIN 737-29-1113**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 7 of 35 **BOEING SERVICE BULLETIN 737-29-1113**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 8 of 35 **BOEING SERVICE BULLETIN 737-29-1113**

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### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-29-1113**  Original Issue: March 23, 2011 ATA System: 2900 **SUBJECT:** HYDRAULIC POWER - Right Main Landing Gear Wheel Well - Wire Bundle and Hydraulic Tubing - Inspection, Repair and New Clamps Installation 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 PRR 38275-173S for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 737-600/700/700C/800/900/900ER airplanes, line numbers 1060 thru 3447, without sufficient separation between hydraulic tubing, P/N 272A4451-136 / -137, and wire bundles W6128, W7122, W8122 and W8222. - 1

Airplane Models: 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **Group Variable Number** 1 YA119 - YA199 1 YA211 1 YA221 1 YA341 - YA345 1 YA357 1 YA367

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 9 of 35**Group Variable Number** 1 YA371 - YA377 1 YA551 - YA552 1 YA630 - YA631 1 YA636 1 YA641 - YA642 1 YA648 - YA650 1 YA657 - YA659 1 YA666 - YA667 1 YA671 - YA672 1 YA691 1 YA707 - YA710 1 YA835 1 YA857 - YA862 1 YA967 - YA978 1 YB111 - YB132 1 YB156 - YB158 1 YB163 - YB164 1 YB184 1 YB206 - YB208 1 YB306 - YB310 1 YB371 - YB392 1 YB522 - YB526 1 YB541 - YB544 1 YB551 1 YB561 - YB598 1 YB601 - YB635 1 YB651 1 YB656 1 YB671 - YB672 1 YB851 - YB863 1 YB871 - YB874 1 YB881 - YB893 1 YB901 - YB903

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 10 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YB911 1 YB961 - YB974 1 YB986 - YB995 1 YC029 - YC030 1 YC083 - YC084 1 YC091 - YC095 1 YC168 - YC170 1 YC176 - YC179 1 YC186 - YC190 1 YC201 - YC203 1 YC206 - YC207 1 YC304 - YC305 1 YC383 - YC387 1 YC393 - YC394 1 YC415 1 YC422 1 YC427 - YC428 1 YC436 - YC439 1 YC490 - YC499 1 YC525 - YC526 1 YC582 - YC583 1 YC654 - YC655 1 YC738 - YC750 1 YC881 - YC892 1 YC921 - YC922 1 YC949 - YC951 1 YC977 - YC978 1 YD006 - YD007 1 YD054 - YD057 1 YD108 - YD110 1 YD153 - YD159 1 YD208 - YD209 1 YD216 - YD219

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 11 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YD252 - YD254 1 YD256 - YD257 1 YD261 1 YD317 - YD334 1 YD391 1 YD408 - YD410 1 YD412 - YD416 1 YD481 - YD485 1 YD491 - YD499 1 YD507 - YD512 1 YD535 1 YD543 - YD547 1 YD561 - YD564 1 YD571 - YD572 1 YD591 - YD595 1 YD612 1 YD651 - YD655 1 YE204 - YE206 1 YE301 - YE305 1 YE321 - YE326 1 YE371 - YE383 1 YF001 - YF009 1 YF021 - YF043 1 YF046 - YF047 1 YF051 - YF060 1 YF086 1 YF106 - YF107 1 YF111 - YF114 1 YF116 - YF117 1 YF121 - YF125 1 YF176 - YF178 1 YF191 - YF192 1 YF201 - YF256

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 12 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YF401 - YF402 1 YF441 - YF442 1 YF451 - YF455 1 YF501 - YF588 1 YF701 - YF707 1 YF801 - YF803 1 YF831 - YF832 1 YF836 - YF837 1 YF901 - YF904 1 YF921 - YF923 1 YG043 - YG044 1 YG083 - YG089 1 YG091 - YG099 1 YG101 - YG103 1 YG111 - YG114 1 YG116 - YG126 1 YG201 - YG205 1 YG211 - YG214 1 YG221 - YG224 1 YG251 - YG252 1 YG505 - YG510 1 YG701 1 YG711 1 YH001 - YH012 1 YH031 - YH055 1 YH071 - YH072 1 YH101 - YH130 1 YH201 - YH202 1 YH206 - YH207 1 YH301 - YH305 1 YH321 - YH322 1 YJ001 - YJ013 1 YJ021

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 13 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YJ472 - YJ480 1 YJ514 - YJ517 1 YJ531 - YJ579 1 YJ591 - YJ599 1 YJ631 - YJ632 1 YJ671 - YJ694 1 YJ801 - YJ867 1 YJ871 - YJ880 1 YJ901 - YJ904 1 YJ908 - YJ929 1 YJ931 - YJ937 1 YJ941 - YJ956 1 YJ976 - YJ977 1 YK001 - YK007 1 YK101 - YK104 1 YK111 - YK112 1 YK121 - YK122 1 YK131 - YK133 1 YK136 - YK139 1 YK141 - YK142 1 YK146 - YK148 1 YK151 - YK154 1 YK161 - YK167 1 YK171 1 YK176 - YK177 1 YK186 1 YK191 1 YK196 1 YK201 - YK202 1 YK301 - YK314 1 YK321 - YK340 1 YK361 - YK378 1 YK401 - YK406

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 14 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YK426 - YK427 1 YK431 - YK450 1 YK456 - YK466 1 YK471 - YK473 1 YK476 1 YK480 - YK487 1 YK495 - YK498 1 YK511 - YK516 1 YK521 - YK530 1 YK551 - YK571 1 YK576 - YK577 1 YK580 - YK585 1 YK601 - YK602 1 YK606 - YK607 1 YK611 - YK616 1 YK621 - YK634 1 YK641 - YK644 1 YK651 - YK665 1 YK671 - YK672 1 YK676 - YK677 1 YK681 - YK686 1 YK691 1 YK701 - YK713 1 YK716 - YK719 1 YK721 - YK741 1 YK751 - YK770 1 YK776 - YK778 1 YK781 - YK782 1 YK791 - YK792 1 YK796 - YK797 1 YK801 - YK899 1 YK901 - YK912 1 YK918 - YK919

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 15 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YK921 - YK927 1 YK941 - YK957 1 YK961 - YK992 1 YL001 - YL005 1 YL011 - YL016 1 YL021 - YL024 1 YL051 - YL052 1 YL056 - YL057 1 YL061 1 YL066 - YL069 1 YL076 - YL077 1 YL101 - YL134 1 YL201 - YL221 1 YL271 - YL272 1 YL281 - YL284 1 YL301 - YL303 1 YL311 - YL313 1 YL316 - YL321 1 YL351 - YL353 1 YL371 - YL374 1 YL401 1 YL421 - YL429 1 YL431 - YL444 1 YL461 - YL478 1 YL501 - YL509 1 YL531 - YL534 1 YL541 - YL544 1 YL561 - YL568 1 YL591 - YL595 1 YL601 - YL606 1 YL611 - YL612 1 YL616 - YL617 1 YL621

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 16 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YL626 1 YL631 - YL634 1 YL661 - YL664 1 YL676 - YL681 1 YL691 1 YL701 - YL704 1 YL731 1 YL751 - YL752 1 YL756 1 YL761 - YL774 1 YL796 1 YL801 - YL811 1 YL901 - YL910 1 YL921 - YL940 1 YL951 - YL964 1 YM101 - YM103 1 YM201 - YM242 1 YM251 - YM299 1 YM301 - YM393 1 YM471 1 YM481 - YM484 1 YM501 - YM515 1 YM521 - YM522 1 YM541 1 YM551 - YM553 1 YM571 - YM572 1 YM581 - YM582 1 YM591 - YM599 1 YM631 - YM634 1 YM641 - YM652 1 YM671 - YM674 1 YM691 - YM697 1 YM701 - YM710

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 17 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Group**  **Variable Number**1 YM761 - YM764 1 YN001 - YN016 1 YN021 - YN024 1 YN061 1 YN071 - YN082 1 YN091 - YN092 1 YN101 - YN112 1 YN121 1 YN201 - YN202 1 YN211 - YN219 1 YN231 - YN235 1 YN261 1 YQ001 - YQ003 1 YQ011 - YQ012 1 YQ026 1 YQ036 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** This service bulletin is sent to prevent possible wire chafing damage to wire bundles W6128, W7122, W8122 and W8222, caused by insufficient separation from hydraulic tubing in two locations below Electric Motor Driven Pump (EMDP) 'B' in the Main Landing Gear (MLG) wheel well. If this service bulletin is not done, wire chafing could result in arcing, which could also cause damage to wires and hydraulic tubing that could then result in operational disruption and unplanned maintenance. Boeing has received a report, from a 737-800 operator, which told of damage to wire W8222-6011-18. The wire was arcing to hydraulic tubing in a location below EMDP 'B' on the forward bulkhead of the MLG wheel well. The short circuit to the hydraulic tubing caused a circuit breaker to open. Boeing inspected some airplanes in production and found that there was not sufficient separation between the wire bundles, that include W8222, and adjacent hydraulic tubing at that location. As a result, Boeing

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 18 of 35 **BOEING SERVICE BULLETIN 737-29-1113**added a new clamping configuration to production airplanes from line number 3348 and on. Airplanes before line number 1060 do not need this change, because of a configuration difference, in the applicable area. Boeing is issuing this service bulletin as a fix for applicable in-service airplanes. New clamps are added, at the location where damage occurred, to secure wire bundles W6128, W7122, W8122 and W8222 and keep sufficient clearance between the wire bundles and adjacent hydraulic tubing. Accomplishment of this service bulletin will inspect the four wire bundles, located below EMDP 'B', for wire chafing damage and repair as necessary. The related hydraulic tubing will also be inspected and replaced or repaired as necessary. New clamps are installed between the wire bundles and the adjacent hydraulic tubing, P/N 272A4451-136, at STA663 RBL10 WL161, to give sufficient separation to prevent possible wire chafing damage. Boeing Service Related Problem (SRP) 737NG-24-0138 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 737NG FTD 20-10001 is related to this service bulletin. **D. Description** Get access to the right side of the MLG wheel well. Do a General Visual Inspection (GVI) for wire chafing damage of wire bundles W6128, W7122, W8122 and W8222 and hydraulic tubing, P/N 272A4451-136 and 272A4451-137, in an area below Electric Motor Driven Pump 'B' on the forward bulkhead. If any wire bundles are found to be damaged, repair as necessary. If any hydraulic tubing is found to be damaged, replace or repair as necessary. Install new clamps at the intersection between the wire bundles and the hydraulic tubing, P/N 272A4451-136. Do a test of applicable electrical systems, where wire bundles were repaired. Service the hydraulic system if hydraulic tubing was replaced or repaired. Put airplane back to a serviceable condition. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 134 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **E. Compliance** Boeing recommends that the inspection, change and repair given in this service bulletin be done within 24 months after the original issue date of this service bulletin. 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. **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 19 of 35 **BOEING SERVICE BULLETIN 737-29-1113**If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task hours necessary to do this inspection/repair and 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 find the tools. **Elapsed Hours Task Hours**  **Number of Persons Task**  0.50 0.50 1 Open Access 0.50 0.50 1 FIGURE 1 0.25 0.25 1 FIGURE 2 0.50 0.50 1 Close Access 1.75 1.75 TOTAL FOR EACH AIRPLANE (a) (a) Estimate assumes no damage is found on wires or hydraulic tubing. If damage is found more time will be necessary. **H. Weight and Balance Changes** None. **I. Electrical Load Data** Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 38275-173S. b. Boeing Service Related Problem (SRP) 737NG-24-0138. c. Standard Overhaul Practices Manual (SOPM) 20-30-03. d. Standard Wiring Practices Manual (SWPM) 20-10-06, 20-10-11, 20-10-12, 20-10-13, 20-10-19.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 20 of 35 **BOEING SERVICE BULLETIN 737-29-1113**e. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 12-12-00, 20-10-51, 24-22-00, 26-18-02, 27-09-31, 27-09-61, 27-11-00, 27-61-12, 27-81-00, 28-21-00, 29-09-00, 29-11-00, 29-11-21, 29-11-81, 29-21-00, 29-22-00, 29-22-31, 29-32-00, 31-51-00, 32-00-01, 33-42-02. f. 737-600/700/800/900 Wiring Diagram Manual (WDM) 26-12-11, 27-11-11, 27-23-11, 27-23-14, 27-61-11, 27-81-51, 28-21-11, 29-11-11, 29-11-12, 29-23-11, 29-25-11, 29-32-11, 29-33-11, 29-34-11, 31-31-15, 31-53-11, 31-62-24, 33-42-11. g. 737NG Fleet Team Digest (FTD) 20-10001. 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 - MAIN WHEEL WELL, FWD BULKHEAD, STA 663.75 288A4434
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** 1. Publications: **Chapter-Section Publication**  29-11, 29-18 737 Aircraft Maintenance Manual 29-18 737 Illustrated Parts Catalog 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** 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 23, 2011 737-29-1113 21 of 35 **BOEING SERVICE BULLETIN 737-29-1113**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 22 of 35 **BOEING SERVICE BULLETIN 737-29-1113**

BLANK PAGE**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 20, 2010. For labor hour and material reimbursement for airplanes in warranty as of that date, send a claim to Boeing Warranty & Product Assurance Contracts. **C. Parts Necessary For Each Airplane** 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** Wire Bundle Clamp 1 BACC10JU104 Loop Clamp 1 M85052/2-6 Screw 1 BACS12GU3K16 Nut 1 BACN10JC3CM Spacer 1 NAS43DD3-32FC Washer 1 NAS1149D0316J (b) Hydraulic Tubing 1 272A4451-136 (b) Hydraulic Tubing 1 272A4451-137 (a) (c) Lacing Tape

- BMS 13-54 Grade D, Type III, Class 1, Finish C (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) These parts are only necessary if the existing hydraulic tubing is found to be damaged, and is replaced. Hydraulic tubing can also be repaired. (c) This part is only necessary if wire bundle repairs are done. Refer to SWPM 20-10-13.
3. Parts Modified and Reidentified None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 23 of 35 **BOEING SERVICE BULLETIN 737-29-1113**4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **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 23, 2011 737-29-1113 24 of 35 **BOEING SERVICE BULLETIN 737-29-1113 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. Unless shown differently, these dimensions and tolerances are used: – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. 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. 5. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 6. 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. 7. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 25 of 35 **BOEING SERVICE BULLETIN 737-29-1113**8. 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. 9. 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. 10. 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** 1. Install downlock pins in all landing gears. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure. 2. Put chocks around the tires of all landing gears. 3. Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as an accepted procedure 4. Get access to the right main wheel well in the forward bulkhead area. 5. Do a General Visual Inspection (GVI) of hydraulic tubing, P/N 272A4451-136 and 272A4451-137, and wire bundles W6128, W7122, W8122 and W8222, for wire chafing or damage in accordance with FIGURE 1. a. If any of the wire bundles are found to be damaged, repair them. Refer to SWPM 20-10-13 as an accepted procedure. Record all wire numbers repaired to refer to for system tests. b. If the hydraulic tubing is found to be damaged: (1) Remove pressure from hydraulic systems A, B and Standby. Refer to 737-600/700/800/900 AMM 29-09-00 as an accepted procedure. (2) Replace or repair damaged hydraulic tubing, P/N 272A4451-136 and 272A4451-137, as necessary. Refer to 737-600/700/800/900 AMM 20-10-51 as an accepted procedure. 6. Install new clamps in the right MLG wheel well in accordance with FIGURE 2. 7. If you replaced or repaired hydraulic tubing, P/N 272A4451-136 or 272A4451-137, service the hydraulic reservoir as necessary. Refer to 737-600/700/800/900 AMM 12-12-00, as an accepted procedure. 8. Restore the electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00, as an accepted procedure. 9. Restore pressure to hydraulic systems A, B and Standby, if necessary. Refer to 737-600/700/800/900 AMM 29-11-00 for hydraulic systems A and B and 737-600/700/800/900 AMM 29-21-00 for the standby hydraulic system, as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 26 of 35 **BOEING SERVICE BULLETIN 737-29-1113**10. If you replaced or repaired hydraulic tubing, P/N 272A4451-136 or 272A4451-137, check for leaks at hydraulic tubing connections. 11. If any of the wire bundles were repaired. Do the tests that follow, as necessary. **NOTE:**The tables that follow include tests for all wires related to wire bundles W6128, W7122, W8122 and W8222. Operators only need to test the systems that were disturbed as a result of wire repairs. a. If wire bundle W6128 was repaired:
**Test - Refer to AMM Chapter as an Accept**  **ed Procedure Refer to WDM Chapter**  **System Name Applicable Wire Re-**  **paired**
737-600/700/800/900AMM 33-42-02 Retractable Landing Light- Light Assembly Replacement. (a) 737-600/700/800/900 WDM 33-42-11 Retractable Landing Lights 0001 thru 0006

737-600/700/800/900 AMM 29-11-21 Electric Motor Driven Pump (EMDP) Test. 737-600/700/800/900 WDM 29-11-12 Hydraulic Systems A and B Electric Motor Driven Pump (EMDP) 0501, 0503 thru 0506 and YAAF

737-600/700/800/900 AMM 29-32-00 Case Drain Overheat Switch Test. 737-600/700/800/900 WDM 29-34-11System A Pump Overheat Warning System (ELEC 2) 0502 and 0507 thru 0509

737-600/700/800/900AMM 28-21-00 Pressure Fueling System - Test. 737-600/700/800/900 WDM 28-21-11Pressure Fueling System 6011

(a) It is only necessary to do the test of the existing retractable landing lights. b. If wire bundle W7122 was repaired:
**Test - Refer to AMM Chapter as an Accept**  **ed Procedure Refer to WDM Chapter**  **System Name Applicable Wire Re-**  **paired**
737-600/700/800/900 AMM 29-22-00 Power Transfer Unit (PTU) System Test. 737-600/700/800/900 WDM 29-25-11Hydraulic Power Transfer Unit (PTU) System 0501 thru 0503

737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test. 737-600/700/800/900 WDM 27-23-14 Flight Control Low Pressure Indication 0504, 0505

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 27 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Test - Refer to AMM** **Chapter as an Accept ed Procedure**  **Refer to WDM Chapter System Name**  **Applicable Wire Re- paired** 
737-600/700/800/900 AMM 27-61-12 Spoiler Shutoff Valve Test. 737-600/700/800/900 WDM 27-61-11 Spoiler Shutoff Valve System A 0506 thru 0508

737-600/700/800/900 AMM 27-09-31 Flight Controls Shutoff Valve Test. 737-600/700/800/900 WDM 27-23-11 Flight Control System A Shutoff Valve 0510 thru 0512

737-600/700/800/900 AMM 27-11-00 Aileron Trim Response Test. 737-600/700/800/900 WDM 27-11-11 Aileron Trim Actuator Control 0518 thru 0521

737-600/700/800/900 AMM 29-22-31 Power Transfer Unit (PTU)Control Valve Installation Test. 737-600/700/800/900 WDM 29-23-11 Landing Gear Transfer Valve Control 0522

737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test. 737-600/700/800/900 WDM 31-31-15 or 737- 600/700/800/900 WDM 27-23-14 (a) Flight Control Low Pressure Indication 0530

(a) Check Wire Diagram Manual for applicability of Wire 0530. c. If wire bundle W8122 was repaired:
**Test - Refer to AMM Chapter as an Accept**  **ed Procedure Refer to WDM Chapter**  **System Name Applicable Wire Re-**  **paired**
737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test. 737-600/700/800/900 WDM 27-23-14 Flight Control Low Pressure Indication 0501 and 0502

737-600/700/800/900 AMM 29-22-00 Power Transfer Unit (PTU) System Test. 737-600/700/800/900 WDM 29-25-11Hydraulic Power Transfer Unit (PTU) System 0503 and 0504

737-600/700/800/900 AMM 29-22-31 Power Transfer Unit (PTU)Control Valve Installation Test. 737-600/700/800/900 WDM 29-23-11 Landing Gear Transfer Valve Control 0505 thru 0510

737-600/700/800/900 AMM 27-09-31 Flight Controls Shutoff Valve Test. 737-600/700/800/900 WDM 27-23-11 Flight Control System B Shutoff Valve 0511 thru 0513

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 28 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Test - Refer to AMM** **Chapter as an Accept ed Procedure**  **Refer to WDM Chapter System Name**  **Applicable Wire Re- paired** 
737-600/700/800/900 AMM 27-81-00 Leading Edge Uncommanded Motion Protection Test. 737-600/700/800/900 WDM 27-81-51Leading Edge Uncommanded Motion Protection Shutoff Valve 0515, 0516 and YAAF

737-600/700/800/900 AMM 27-09-61 Low Pressure Warning Switch Test. 737-600/700/800/900 WDM 31-31-15 or 737- 600/700/800/900 WDM 27-23-14 (a) Flight Control Low Pressure Indication 0530

737-600/700/800/900 AMM 27-61-12 Spoiler Shutoff Valve Test. 737-600/700/800/900 WDM 27-61-11 Spoiler Shutoff Valve System B 0542 thru 0544

737-600/700/800/900 AMM 31-51-00 Takeoff Warning System Test. 737-600/700/800/900 WDM 31-53-11 Aural Takeoff Warning System 3201B,3201R and 3201Y (a) Check Wire Diagram Manual for applicability of Wire 0530. d. If wire bundle W8222 was repaired:
**Test - Refer to AMM Chapter as an Accept**  **ed Procedure Refer to WDM Chapter**  **System Name Applicable Wire Re-**  **paired**
737-600/700/800/900AMM 29-11-00 Operational Test of the Hydraulic Systems A and B. 737-600/700/800/900 WDM 29-33-11 System B, Pump LowPressure Warning System (ENG 2 and ELEC 1) 0501, 0506, 0507 and 0511

737-600/700/800/900 AMM 29-11-81 EDP Supply Shutoff Valve Operational Test. 737-600/700/800/900 WDM 29-11-11Hydraulic Engine Driven Pump (EDP) Control (Engine 2 Shutoff Valve) 0502, 0503 and 508

737-600/700/800/900AMM 29-11-00 Operational Test of the Hydraulic Systems A and B. 737-600/700/800/900 WDM 29-32-11System B, Low Pressure Warning System 0504, 0505 and 509

737-600/700/800/900 AMM 29-11-81 EDP Supply Shutoff Valve Operational Test. 737-600/700/800/900 WDM 31-62-24Hydraulic Engine Driven Pump (EDP) Control (Engine 2 Shutoff Valve) 513

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 29 of 35 **BOEING SERVICE BULLETIN 737-29-1113 Test - Refer to AMM** **Chapter as an Accept ed Procedure**  **Refer to WDM Chapter System Name**  **Applicable Wire Re- paired** 
737-600/700/800/900 AMM 26-18-02 Wing, Wheel Well and Lower Aft Body Overheat Sensing Element Test. (a) 737-600/700/800/900 WDM 26-12-11Wheel Well Fire Detection 6001R

737-600/700/800/900AMM 28-21-00 Pressure Fueling System - Test. 737-600/700/800/900 WDM 28-21-11Pressure Fueling System 6011

(a) Test main wheel well fire detector M270. 12. Remove downlock pins from all landing gears. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure. 13. Remove chocks from around the tires of all landing gears. 14. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 30 of 35 **BOEING SERVICE BULLETIN 737-29-1113 FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC**  **TUBING AND WIRE BUNDLES - INSPECTION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 31 of 35 **BOEING SERVICE BULLETIN 737-29-1113**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 each airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  do a General Visual Inspection (GVI) forwire chafing or damage. Refer to SWPM20-10-06 and SWPM 20-10-13 as accepted procedures. - W6128, W7122, W8122 AND W8222 Wire Bundles Inspect 1

do a GVI for wire chafing or damage. Refer to 737- 600/700/800/900 AMM 20-10-51 asan accepted procedure. - 272A4451-136 AND 272A4451-137 Hydraulic Tubing Inspect 2

**FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC TUBING AND WIRE BUNDLES - INSPECTION**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 32 of 35 **BOEING SERVICE BULLETIN 737-29-1113 FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -**  **INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 33 of 35 **BOEING SERVICE BULLETIN 737-29-1113**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 each airplane.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  in the area to be clamped. Refer to SOPM 20-30-03 asan accepted procedure. - 272A4451-136 Hydraulic Tubing Clean 1

on the wire bundle. (a) 1 BACC10JU104 Wire Bundle Clamp Install (New) 2 on the hydraulic tubing as shown. (d) 1 M85052/2-6 Loop Clamp Install (New)

1 BACS12GU3K16 Screw Install (New) 1 NAS43DD3-32FC Spacer Install (New) 1 NAS1149D0316J Washer Install (New) loosely to let wire bundle be adjusted. 1 BACN10JC3CM Nut Install (New)

**FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS - INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 34 of 35 **BOEING SERVICE BULLETIN 737-29-1113 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** refer to SWPM 20- 10-11 and SWPM20-10-12, as accepted procedures. (a) (b) - - Wire Bundles Adjust 3

to 35 in-lb. (c) 1 BACN10JC3CM Nut Torque 4 (a) To redistribute any extra wire slack and to make sure any wire bundle splices are not located in the new wire bundle clamp. Also, make sure there is a minimum clearance of 0.5 inch from adjacent structure (b) If wire repairs have been made, cut and install lacing tape, P/N BMS 13-54 Type III, to hold the wire bundle together. (c) Check the wire bundle clamp for a correct fit, on the wire bundle, after the nut is tightened. If the wire bundle clamp does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. (d) The loop clamp can be installed with the fastener hole on the inboard side of the hydraulic tubing, as necessary, to make sure any wire bundle splices are not located in the new wire bundle clamp.

**FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS - INSTALLATION**  **(SHEET 3 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: March 23, 2011 737-29-1113 35 of 35 **BOEING SERVICE BULLETIN 737-29-1113**