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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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3.0
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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

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BOEING SERVICE BULLETIN 737-29-1113

BLANK PAGE
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.

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737-29-1113

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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.

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BOEING SERVICE BULLETIN 737-29-1113

BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

YA119 - YA199 1

YA211 1

YA221 1

YA341 - YA345 1

YA357 1

YA367 1

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Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-29-1113
Variable Number Group

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 1

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

Model Zone

737-600, 737-700, 737-700C, 134

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.

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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.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

FIGURE 1 1 0.50 0.50

FIGURE 2 1 0.25 0.25

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE (a) 1.75 1.75

(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.

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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

Drawing Number Title

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:

Publication Chapter-Section

737 Aircraft Maintenance Manual 29-11, 29-18

737 Illustrated Parts Catalog 29-18

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.

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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

Part Number / QTY Name Notes

Specification

BACC10JU104 1 Wire Bundle Clamp

M85052/2-6 1 Loop Clamp

BACS12GU3K16 1 Screw

BACN10JC3CM 1 Nut

NAS43DD3-32FC 1 Spacer

NAS1149D0316J 1 Washer

272A4451-136 1 Hydraulic Tubing (b)

272A4451-137 1 Hydraulic Tubing (b)

BMS 13-54 Grade - Lacing Tape (a) (c)

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.

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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.

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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.

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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.

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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 Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

paired

737-600/700/800/900

AMM 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 29-34-11

System A Pump Overheat Warning System

(ELEC 2)

0502 and 0507 thru

0509

737-600/700/800/900

AMM 28-21-00 Pressure Fueling System -

Test.

737-600/700/800/900

WDM 28-21-11

Pressure Fueling System6011

(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 Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

paired

737-600/700/800/900

AMM 29-22-00 Power

Transfer Unit (PTU)

System Test.

737-600/700/800/900

WDM 29-25-11

Hydraulic Power Transfer Unit (PTU) System0501 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

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Test - Refer to AMM

Chapter as an Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

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 Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

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 29-25-11

Hydraulic Power Transfer Unit (PTU) System0503 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

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BOEING SERVICE BULLETIN 737-29-1113
Test - Refer to AMM

Chapter as an Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

paired

737-600/700/800/900

AMM 27-81-00 Leading

Edge Uncommanded

Motion Protection Test.

737-600/700/800/900

WDM 27-81-51

Leading Edge Uncommanded Motion Protection Shutoff Valve0515, 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 Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

paired

737-600/700/800/900

AMM 29-11-00 Operational Test of the Hydraulic Systems A and

B.

737-600/700/800/900

WDM 29-33-11

System B, Pump Low

Pressure 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 29-11-11

Hydraulic Engine Driven Pump (EDP) Control

(Engine 2 Shutoff

Valve)

0502, 0503 and 508

737-600/700/800/900

AMM 29-11-00 Operational Test of the Hydraulic Systems A and

B.

737-600/700/800/900

WDM 29-32-11

System B, Low Pressure Warning System0504, 0505 and 509

737-600/700/800/900

AMM 29-11-81 EDP

Supply Shutoff Valve

Operational Test.

737-600/700/800/900

WDM 31-62-24

Hydraulic Engine Driven Pump (EDP) Control

(Engine 2 Shutoff

Valve)

513

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Test - Refer to AMM

Chapter as an Accepted Procedure

Applicable Wire Re- System Name Refer to WDM Chapter

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 26-12-11

Wheel Well Fire Detection6001R

737-600/700/800/900

AMM 28-21-00 Pressure Fueling System -

Test.

737-600/700/800/900

WDM 28-21-11

Pressure Fueling System6011

(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.

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

do a General Visual

Inspection (GVI) for

wire chafing or damage. Refer to SWPM

20-10-06 and SWPM 20-10-13 as accepted procedures.

W6128, W7122, W8122 -

AND W8222

1 Inspect Wire Bundles

do a GVI for wire

chafing or damage.

Refer to 737-

600/700/800/900

AMM 20-10-51 as

an accepted procedure.

272A4451-136 AND -

272A4451-137

2 Inspect Hydraulic Tubing

FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC

TUBING AND WIRE BUNDLES - INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-29-1113
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -

INSTALLATION

(SHEET 1 OF 3)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

in the area to be

clamped. Refer to

SOPM 20-30-03 as

an accepted procedure.

1 Clean Hydraulic Tubing 272A4451-136 -

on the wire bundle.

(a)

2 Install (New) Wire Bundle Clamp BACC10JU104 1

on the hydraulic tubing as shown. (d)Install (New) Loop Clamp M85052/2-6 1

Install (New) Screw BACS12GU3K16 1

Install (New) Spacer NAS43DD3-32FC 1

Install (New) Washer NAS1149D0316J 1

loosely to let wire

bundle be adjusted.

Install (New) Nut BACN10JC3CM 1

FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -

INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-29-1113
STEP TASK NAME IDENTIFICATION QTY MORE DATA

refer to SWPM 20-

10-11 and SWPM

20-10-12, as accepted procedures. (a)

(b)

3 Adjust Wire Bundles - -

4 Torque Nut BACN10JC3CM 1 to 35 in-lb. (c)

(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)

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