# Boeing Special Attention Service Bulletin 737-29-1113: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0985; AD 2013-19-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Special Attention Service Bulletin 737-29-1113](https://openairdocs.org/service-documents/boeing/sb-737-29-1113.md)
- Title as filed: U.S. DOT/FAA - SB-737-29-1113-01-01
- Pages: 37
- PDF: https://openairdocs.org/files/sha256/39/75/3975c698ea7b1da59124c04415dfafd5eb16874815569abed3f1fc7aa39a7339
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
SPECIAL ATTENTION
Number: 737-29-1113
Original Issue: March 23, 2011
Revision 1: March 29, 2013
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 300-774). 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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2011 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
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 Boeing
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with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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737-29-1113Revision 1: March 29, 2013
1 of 37
4.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 0
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 0
D. Description .............................................. 2 1
E. Compliance .............................................. 2 1
F. Approval ............................................... 2 2
G. Manpower .............................................. 2 2
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 2
1. Existing Data: ......................................... 2 2
2. Data Supplied with this Service Bulletin: ........................... 2 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 3
K. Publications Affected ........................................ 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 4
M. Software Accomplishment Summary ................................ 2 4
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary for Each Airplane ................................. 2 5
1. Kits/Parts ............................................ 2 5
2. Parts and Materials Supplied by the Operator ........................ 2 5
3. Parts Modified and Reidentified ................................ 2 5
4. Parts Removed and Not Replaced .............................. 2 6
D. Parts Necessary to Change Spares ................................. 2 6
E. Special Tooling - Price and Availability ............................... 2 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBING AND WIRE BUNDLES - INSPECTION ....................... 3 3
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION ......................................... 3 5
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Commercial 
Airplanes
737
Service Bulletin
SPECIAL ATTENTION
Revision Transmittal SheetNumber: 737-29-1113Original Issue: March 23, 2011
Revision 1: March 29, 2013
ATA System: 2900
SUBJECT: HYDRAULIC POWER - Right Main Landing Gear Wheel Well - Wire Bundle and
Hydraulic Tubing - Inspection, Repair and New Clamps Installation
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-250-AD, is related to
this service bulletin.
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
Airplanes line numbers 3138, 3158, 3169, 3175, 3216, 3224, 3253, 3274, 3290 thru 3293 and 3295 thru 3347
are removed from the service bulletin effectivity.
REASON FOR REVISION
This revision is sent to remove airplanes line numbers 3138, 3158, 3169, 3175, 3216, 3224, 3253, 3274, 3290
thru 3293 and 3295 thru 3347 from the service bulletin effectivity. These airplanes were reworked out of sequence
in production and have incorporated the change given in this service bulletin. FAA NPRM 2011-NM-250-AD is
also added.
These sections are changed:
1. Summary Compliance: Added new FAA NPRM.
2. Paragraph 1.A., Effectivity: Changed effectivity for Group 1 and corrected group configuration description
column.
3. Paragraph 1.E., Compliance: Added new FAA NPRM.
4. Paragraph 1.J., References: Updated.
5. Paragraph 1.M., Software Accomplishment Summary: Added.
6. Figure 2 step table: Corrected footnote (a).
The applicable data given in Information Notice 737-29-1113 IN 01 is included in this revision.
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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 23, 2011Original Issue:
March 29, 2013Revision 1:
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BOEING SERVICE BULLETIN 737-29-1113

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Commercial 
Airplanes
737
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 737-29-1113Original Issue: March 23, 2011
Revision 1: March 29, 2013
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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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
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-250-AD, is related to
this service bulletin.
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.
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
MAIN LANDING GEAR WHEEL WELL
FORWARD BULKHEAD, RIGHT SIDE
HYDRAULIC
TUBING
DO A GENERAL VISUAL INSPECTION (GVI) FOR
WIRE CHAFING DAMAGE, OF WIRE BUNDLES  INBD
W6128, W7122, W8122 AND W8222 AND
HYDRAULIC TÚBING, P/N 272A4451-136 AND
272A4451-137, IN THE AREA BELOW THE
ELECTRIC MOTOR DRIVEN PUMP 'B', ON THE
RIGHT SIDE OF THE MLG WHEEL WELL
FORWARD BULKHEAD. REPAIR THE WIRE  BUNDLES AND REPLACE  WIRE  BUNDLES W6128,  NEW WIRE  BUNDLE CLAMPS
HYDRAULIC TUBING IF NECESSARY. INSTALL  W7122, W8122 AND
NEW CLAMPS AND ADJUST WIRE BUNDLES.  W8222  2038913
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Commercial 
Airplanes
737
Service Bulletin
SPECIAL ATTENTION
Number: 737-29-1113
Original Issue: March 23, 2011
Revision 1: March 29, 2013
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.
DESCRIPTIONCONFIGURATIONGROUP
737-600/700/700C/800/900/900ER airplanes, line numbers 1060
thru 3289 and 3294, but excluding line numbers 3138, 3158, 3169,
3175, 3216, 3224, 3253 and 3274, 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
GroupVariable Number
1YA119 - YA199
1YA211
1YA221
1YA341 - YA345
1YA357
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GroupVariable Number
1YA367
1YA371 - YA377
1YA551 - YA552
1YA630 - YA631
1YA636
1YA641 - YA642
1YA648 - YA650
1YA657 - YA659
1YA666 - YA667
1YA671 - YA672
1YA691
1YA707 - YA710
1YA835
1YA857 - YA862
1YA967 - YA978
1YB111 - YB132
1YB156 - YB158
1YB163 - YB164
1YB184
1YB206 - YB208
1YB306 - YB310
1YB371 - YB392
1YB522 - YB526
1YB541 - YB544
1YB551
1YB561 - YB598
1YB601 - YB635
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
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GroupVariable Number
1YB901 - YB903
1YB911
1YB961 - YB974
1YB986 - YB995
1YC029 - YC030
1YC083 - YC084
1YC091 - YC095
1YC168 - YC170
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
1YC206 - YC207
1YC304 - YC305
1YC383 - YC387
1YC393 - YC394
1YC415
1YC422
1YC427 - YC428
1YC436 - YC439
1YC490 - YC499
1YC525 - YC526
1YC582 - YC583
1YC654 - YC655
1YC738 - YC750
1YC881 - YC892
1YC921 - YC922
1YC949 - YC951
1YC977 - YC978
1YD006 - YD007
1YD054 - YD057
1YD108 - YD110
1YD153 - YD159
1YD208 - YD209
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GroupVariable Number
1YD216 - YD219
1YD252 - YD254
1YD256 - YD257
1YD261
1YD317 - YD334
1YD391
1YD408 - YD410
1YD412 - YD416
1YD481 - YD485
1YD491 - YD499
1YD507 - YD512
1YD535
1YD543 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD612
1YD651 - YD655
1YE204 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF007
1YF021 - YF040
1YF046
1YF051 - YF060
1YF086
1YF106 - YF107
1YF111 - YF114
1YF116 - YF117
1YF121 - YF124
1YF176 - YF178
1YF191 - YF192
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GroupVariable Number
1YF201 - YF249
1YF401 - YF402
1YF451 - YF455
1YF501 - YF585
1YF701 - YF706
1YF801 - YF803
1YF831 - YF832
1YF836 - YF837
1YF901 - YF903
1YF921 - YF922
1YG043 - YG044
1YG083 - YG089
1YG091 - YG099
1YG101 - YG103
1YG111 - YG114
1YG116 - YG125
1YG201 - YG205
1YG211 - YG214
1YG221 - YG223
1YG251 - YG252
1YG505 - YG509
1YG701
1YG711
1YH001 - YH012
1YH031 - YH048
1YH051 - YH055
1YH101 - YH130
1YH201 - YH202
1YH206 - YH207
1YH301 - YH305
1YH321 - YH322
1YJ001 - YJ013
1YJ021
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GroupVariable Number
1YJ472 - YJ480
1YJ514 - YJ517
1YJ531 - YJ570
1YJ578
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
1YJ976 - YJ977
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK133
1YK136 - YK139
1YK141 - YK142
1YK146 - YK148
1YK151 - YK154
1YK161 - YK167
1YK171
1YK176 - YK177
1YK186
1YK191
1YK196
1YK201 - YK202
1YK301 - YK314
1YK321 - YK340
1YK361 - YK378
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GroupVariable Number
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK466
1YK471
1YK476
1YK480 - YK487
1YK495 - YK497
1YK511 - YK516
1YK521 - YK530
1YK551 - YK571
1YK576 - YK577
1YK580 - YK585
1YK601 - YK602
1YK606 - YK607
1YK611 - YK616
1YK621 - YK634
1YK641 - YK644
1YK651 - YK665
1YK671 - YK672
1YK676 - YK677
1YK681 - YK686
1YK691
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK782
1YK791 - YK792
1YK796 - YK797
1YK801 - YK899
1YK901 - YK912
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GroupVariable Number
1YK918 - YK919
1YK921 - YK927
1YK941 - YK956
1YK961 - YK992
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL133
1YL201 - YL219
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL312
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL544
1YL561 - YL568
1YL591 - YL594
1YL601 - YL606
1YL611 - YL612
1YL616 - YL617
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GroupVariable Number
1YL621
1YL626
1YL631 - YL634
1YL661 - YL664
1YL676 - YL681
1YL691
1YL701 - YL704
1YL731
1YL751 - YL752
1YL761 - YL772
1YL801 - YL809
1YL901 - YL910
1YL921 - YL936
1YL951 - YL963
1YM101 - YM103
1YM201 - YM242
1YM251 - YM299
1YM301 - YM391
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
1YM641 - YM652
1YM671 - YM674
1YM691 - YM696
1YM701 - YM710
1YM761 - YM763
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GroupVariable Number
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN201 - YN202
1YN211 - YN219
1YN231 - YN235
1YN261
1YQ001 - YQ003
1YQ011
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
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.
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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.
Revision 1 is sent to remove airplanes line numbers 3138, 3158, 3169, 3175, 3216, 3224, 3253, 3274,
3290 thru 3293 and 3295 thru 3347 from the service bulletin effectivity. These airplanes were reworked
out of sequence in production and have incorporated the change given in this service bulletin. FAA
NPRM 2011-NM-250-AD is also added.
The applicable data given in Information Notice 737-29-1113 IN 01 is included in this revision.
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.
Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original
issue of this service bulletin. Airplanes line numbers 3138, 3158, 3169, 3175, 3216, 3224, 3253, 3274,
3290 thru 3293 and 3295 thru 3347 are removed from the service bulletin effectivity.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
134737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-250-AD, is
related to this service bulletin.
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.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this 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 HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.500.501FIGURE 1
0.250.251FIGURE 2
0.500.501Close Access
1.751.75TOTAL 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.
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b. Boeing Service Related Problem (SRP) 737NG-24-0138.
c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2011-NM-250-AD.
d. Standard Overhaul Practices Manual (SOPM) 20-30-03.
e. Standard Wiring Practices Manual (SWPM) 20-10-06, 20-10-11, 20-10-11, 20-10-12, 20-10-12,
20-10-13, 20-10-19.
f. 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.
g. 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.
h. 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:
TitleDrawing 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-SectionPublication
29-11, 29-18737 Aircraft Maintenance Manual
29-18737 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.
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L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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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
NotesNameQTYPart Number /
Specification
Wire Bundle Clamp1BACC10JU104
Loop Clamp1M85052/2-6
Screw1BACS12GU3K16
Nut1BACN10JC3CM
Spacer1NAS43DD3-32FC
Washer1NAS1149D0316J
(b)Hydraulic Tubing1272A4451-136
(b)Hydraulic Tubing1272A4451-137
(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.
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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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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.
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.
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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.
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.
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a. If wire bundle W6128 was repaired:
Test - Refer to AMM
Chapter as an Accept-
ed Procedure
Refer to WDM ChapterSystem NameApplicable Wire Re-
paired
737-600/700/800/900
AMM 33-42-02 Re-
tractable Landing Light
- Light Assembly Re-
placement. (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 Over-
heat Warning System
(ELEC 2)
0502 and 0507 thru
0509
737-600/700/800/900
AMM 28-21-00 Pres-
sure Fueling System -
Test.
737-600/700/800/900
WDM 28-21-11
Pressure Fueling Sys-
tem
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 ChapterSystem NameApplicable Wire Re-
paired
737-600/700/800/900
AMM 29-22-00 Power
Transfer Unit (PTU)
System Test.
737-600/700/800/900
WDM 29-25-11
Hydraulic Power Trans-
fer 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
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
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Test - Refer to AMM
Chapter as an Accept-
ed Procedure
Refer to WDM ChapterSystem NameApplicable Wire Re-
paired
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 Installa-
tion 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 ChapterSystem NameApplicable 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 29-25-11
Hydraulic Power Trans-
fer Unit (PTU) System
0503 and 0504
737-600/700/800/900
AMM 29-22-31 Power
Transfer Unit (PTU)
Control Valve Installa-
tion 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
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 Uncom-
manded Motion Protec-
tion Shutoff Valve
0515, 0516 and YAAF
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Test - Refer to AMM
Chapter as an Accept-
ed Procedure
Refer to WDM ChapterSystem NameApplicable Wire Re-
paired
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 ChapterSystem NameApplicable Wire Re-
paired
737-600/700/800/900
AMM 29-11-00 Opera-
tional Test of the Hy-
draulic Systems A and
B.
737-600/700/800/900
WDM 29-33-11
System B, Pump Low
Pressure Warning Sys-
tem (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 Driv-
en Pump (EDP) Control
(Engine 2 Shutoff
Valve)
0502, 0503 and 508
737-600/700/800/900
AMM 29-11-00 Opera-
tional Test of the Hy-
draulic Systems A and
B.
737-600/700/800/900
WDM 29-32-11
System B, Low Pres-
sure 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 31-62-24
Hydraulic Engine Driv-
en Pump (EDP) Control
(Engine 2 Shutoff
Valve)
513
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 Detec-
tion
6001R
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Test - Refer to AMM
Chapter as an Accept-
ed Procedure
Refer to WDM ChapterSystem NameApplicable Wire Re-
paired
737-600/700/800/900
AMM 28-21-00 Pres-
sure Fueling System -
Test.
737-600/700/800/900
WDM 28-21-11
Pressure Fueling Sys-
tem
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.
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BOEING SERVICE BULLETIN 737-29-1113
MAIN LANDING GEAR WHEEL WELL  2038914
FORWARD BULKHEAD, RIGHT SIDE
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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### Page 34

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 DATAQTYIDENTIFICATIONNAMETASKSTEP
do a General Visual
Inspection (GVI) for
wire chafing or dam-
age. Refer to SWPM
20-10-06 and SW-
PM 20-10-13 as ac-
cepted procedures.
-W6128, W7122, W8122
AND W8222
Wire BundlesInspect1
do a GVI for wire
chafing or damage.
Refer to 737-
600/700/800/900
AMM 20-10-51 as
an accepted proce-
dure.
-272A4451-136 AND
272A4451-137
Hydraulic TubingInspect2
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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34 of 37
BOEING SERVICE BULLETIN 737-29-1113

### Page 35 (OCR)

BOEING SERVICE BULLETIN 737-29-1113
MAIN LANDING GEAR WHEEL WELL  2038917
FORWARD BULKHEAD, RIGHT SIDE
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 1 OF 3)
Original Issue: March 23, 2011
Revision 1 March 29, 2013  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-29-1113
Work - See page 1 for details.  35 of 37

### Page 36

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 DATAQTYIDENTIFICATIONNAMETASKSTEP
in the area to be
clamped. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
-272A4451-136Hydraulic TubingClean1
on the wire bundle.
(a)
1BACC10JU104Wire Bundle ClampInstall (New)2
on the hydraulic tub-
ing as shown. (d)
1M85052/2-6Loop ClampInstall (New)
1BACS12GU3K16ScrewInstall (New)
1NAS43DD3-32FCSpacerInstall (New)
1NAS1149D0316JWasherInstall (New)
loosely to let wire
bundle be adjusted.
1BACN10JC3CMNutInstall (New)
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 23, 2011
737-29-1113Revision 1 March 29, 2013
36 of 37
BOEING SERVICE BULLETIN 737-29-1113

### Page 37

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
refer to SWPM 20-
10-11 and SWPM
20-10-12, as accept-
ed procedures. (a)
(b)
--Wire BundlesAdjust3
to 35 in-lb. (c)1BACN10JC3CMNutTorque4
(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 between the wire bundles
and the hydraulic tubing.
(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)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: March 23, 2011
737-29-1113Revision 1 March 29, 2013
37 of 37
BOEING SERVICE BULLETIN 737-29-1113

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