# Boeing Alert Service Bulletin 737-29A1119: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-0462; AD 2016-22-14 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-29A1119](https://openairdocs.org/service-documents/boeing/737-29a1119.md)
- Title as filed: SB-737-29A1119-01--
- Pages: 52
- PDF: https://openairdocs.org/files/sha256/1c/9f/1c9f2f4cb60f1c36568e1243a101ee06d99fcfda29371da55df7b278e6924f43
- Page: https://openairdocs.org/service-documents/boeing/737-29a1119/file/1c9f2f4cb60f

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-29A1119
Original Issue: August 04, 2015
Revision 1: June 23, 2016
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Hydraulic Systems A and B - Wire Bundles and Hydraulic Tube
Clamp 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 © 2015 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Unpublished Work.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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries 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.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
1 of 52
3.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
2 of 52
BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT
BLANK PAGE

### Page 3

Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 31
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 35
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 36
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38
FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION  [Group 1] . . . . . . . . . . . . . . . . . . . 42
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION  [Group 2] . . . . . . . . . . . . . . . . . . . 44
FIGURE 3: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
FIGURE 4: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
APPENDIX A: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
3 of 52
BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
4 of 52
BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-29A1119Original Issue: August 04, 2015
Revision 1: June 23, 2016
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Hydraulic Systems A and B - Wire Bundles and Hydraulic Tube
Clamp 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 2015-NM-144-AD, is related to
this service bulletin.
Effects of this Revision on airplanes on which the Original Issue was previously done:
None.
REASON FOR REVISION
This revision is sent to incorporate changes identified during validation of the Original Issue. Also, the work
instructions have been rewritten to improve operator usability.
As a part of a service bulletin validation program, this change was completed on airplane YM346 by Service
Bulletin 737-29A1119 Original Issue before the release of Revision 1 of this service bulletin. The change
completed on airplane YM346 by Service Bulletin 737-29A1119 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane YM346 has the configuration of a Group 1 airplane.
The data given in Information Notice 737-29A1119 IN01 and IN02 is included in this revision.
These sections were changed:
1. Summary: Added validation summary, updated Summary Evaluation Table.
2. Paragraph 1.C. Reason: Added validation summary.
3. Paragraph 1.E. Compliance: Deleted compliance table and updated boilerplate. Added reference to
NPRM.
4. Paragraph 1.J.1. References: Changed references.
5. Paragraph 1.K.1. Publications Affected: Changed publication.
6. Paragraph 2.A. Material - Price and Availability: Updated kit pricing.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
5 of 52

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7. Paragraph 2.C.1. Parts Necessary for Each Airplane: Changed part number.
8. Paragraph 3.A. General Information: Updated notes.
9. Paragraph 3.B. Work Instructions: Consolidated work instructions, removed references to parts,
conditions, and actions, added Required for Compliance (RC) notation.
10. Paragraph 3.B. Work Instructions, Step 14.a: Changed reference.
11. FIGURE 1 and FIGURE 2, Step Table: Changed reference.
12. FIGURE 3 and FIGURE 4, Step Table: Changed part number and Footnote (a), corrected part number
in Footnote (b), deleted interal reference in Step 1.
13. Appendix A: Deleted Logic Diagram.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
August 04, 2015Original Issue:
June 23, 2016Revision 1:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
6 of 52
BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT

### Page 7

Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-29A1119Original Issue: August 04, 2015
Revision 1: June 23, 2016
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Hydraulic Systems A and B - Wire Bundles and Hydraulic Tube
Clamp Installation
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin is sent to prevent possible wire chafing damage to wire bundles W6128 and W8122 caused
by insufficient separation from a hydraulic tube in the Main Landing Gear (MLG) wheel well. If this service bulletin
is not done, wire chafing between the wire bundle and hydraulic tube could cause arcing and a loss of hydraulic
fluid, which may result in a wheel well fire.
Boeing has received a report of damage to wire W6128-0506-10. The wire had chafed and arced to an adjacent
hydraulic tube located in the forward bulkhead of the MLG wheel well. The chafing and electrical arc created a
small hole in the System B hydraulic tube and also caused damage to the wire bundle, which resulted in a ground
fault detection on the System A Electrical Motor-Driven Pump (EMDP). The small hole led to a total loss of
System B hydraulic fluid and the ground fault resulted in removal of power from the System A EMDP and
illumination of the System A EMDP low power light. Boeing investigated this problem and found that there was
not sufficient separation between the wire bundles W6128 and W8122 and the adjacent hydraulic tube at that
location. As a result, Boeing is issuing this service bulletin to add clamps to separate the wire bundles from the
hydraulic tube on airplanes from line number 1060 and on. Airplanes before line number 1060 do not need this
change because of a configuration difference in the applicable area. This change will be incorporated on
in-production airplanes starting at line number 5432.
Boeing Service Related Problem (SRP) 737NG-SRP-29-0112 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737NG FTD 29-15001 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane YM346 by Service
Bulletin 737-29A1119 Original Issue before the release of Revision 1 of this service bulletin. The change
completed on airplane YM346 by Service Bulletin 737-29A1119 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane YM346 has the configuration of a Group 1 airplane.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
7 of 52

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This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
In the right side of the Main Landing Gear wheel well, do a Detailed Inspection for damage of wire bundles and
a hydraulic tube. If the wire bundles are found to be damaged, repair as necessary. If the hydraulic tube is found
to be damaged, replace or repair as necessary. Install clamps and an optional spacer between the wire bundle
and hydraulic tube. Do a test of applicable electrical systems if the wire bundle was repaired. Service the hydraulic
system if the hydraulic tube was replaced or repaired.
EFFECTIVITY
737-600, -700, -700C, -800, -900 and -900ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of
affected airplane(s).
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspection, and repair procedures
given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
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BOEING SERVICE BULLETIN 737-29A1119
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MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 04, 2015
737-29A1119Revision 1: June 23, 2016
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BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT

### Page 10 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
DO A DETAILED INSPECTION FOR CHAFING
DAMAGE OF WIRE BUNDLES AND A HYDRAULIC
TUBE. IF THE WIRE BUNDLES ARE FOUND TO BE
MAIN LANDING GEAR WHEEL WELL  DAMAGED,  REPAIR AS NECESSARY. IF THE
(FORWARD BULKHEAD, RIGHT SIDE)  HYDRAULIC TUBE IS FOUND TO BE DAMAGED  REPLACE OR REPAIR AS NECESSARY. INSTALL
CLAMPS AND AN OPTIONAL SPACER BETWEEN
THE WIRE BUNDLES AND HYDRAULIC TUBE. DO A
TEST OF APPLICABLE ELECTRICAL SYSTEMS IF
THE WIRE BUNDLES WERE REPAIRED. SERVICE  2432609
THE HYDRAULIC SYSTEM IF THE HYDRAULIC
TUBE WAS REPLACED OR REPAIRED.
Original Issue: August 04, 2015
Revision 1: June 23, 2016  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-29A1119
Work - See page 1 for detalls.  10 of 52

### Page 11

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-29A1119
Original Issue: August 04, 2015
Revision 1: June 23, 2016
ATA System: 2911
SUBJECT: HYDRAULIC POWER - Hydraulic Systems A and B - Wire Bundles and Hydraulic Tube
Clamp Installation
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 737-600, -700, -700C, -800, -900 and -900ER Airplanes, line
numbers 1060 to 5431 in 2 Groups. The Variable Numbers and Group Information for the applicable
airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
737-600/700/800/900 with Hydraulic Tube P/N 272A4451-56 adjacent
to W6128 and W8122.
-1
737-600/700/800/900 with Hydraulic Tube P/N 272A4451-1044
adjacent to W6128 and W8122.
-2
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA119 - YA199
1YA211
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GroupVariable Number
1YA221
1YA341 - YA345
1YA357
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
2YB636
1YB651
1YB656
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GroupVariable Number
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB974
2YB975
2YB981
1YB986 - YB995
2YB996 - YB998
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
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GroupVariable Number
1YC949 - YC951
1YC977 - YC978
1YD006 - YD007
1YD054 - YD057
1YD108 - YD110
2YD111 - YD117
1YD153 - YD159
1YD208 - YD209
1YD216 - YD219
1YD252 - YD254
1YD256 - YD257
1YD261
1YD317 - YD334
1YD391
1YD408 - YD410
1YD412 - YD416
2YD417 - YD422
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
2YF008 - YF011
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GroupVariable Number
1YF021 - YF040
2YF041 - YF045
1YF046 - YF047
2YF048 - YF049
1YF051 - YF060
2YF061 - YF080
1YF086
2YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF117
2YF118 - YF119
1YF121 - YF124
2YF125 - YF132
1YF176 - YF178
1YF191 - YF192
1YF201 - YF251
2YF252 - YF276
1YF401 - YF402
2YF431 - YF432
2YF436 - YF437
1YF441
2YF442
1YF451 - YF455
2YF456 - YF460
1YF501 - YF585
2YF586 - YF599
2YF601 - YF677
1YF701 - YF706
2YF707
1YF801 - YF803
2YF804 - YF805
1YF831 - YF832
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GroupVariable Number
1YF836 - YF837
2YF838
2YF871 - YF872
1YF901 - YF903
2YF904 - YF905
1YF921 - YF922
2YF923 - YF928
2YF951 - YF954
1YG043 - YG044
1YG083 - YG089
1YG091 - YG099
1YG101 - YG103
2YG104
1YG111 - YG114
1YG116 - YG125
2YG126 - YG143
1YG201 - YG205
1YG211 - YG214
1YG221 - YG223
2YG224
1YG251 - YG252
1YG505 - YG509
2YG510 - YG514
1YG701
1YG711
1YH001 - YH012
1YH031 - YH049
2YH050
1YH051 - YH055
2YH071 - YH080
1YH101 - YH130
2YH131 - YH132
1YH201 - YH202
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GroupVariable Number
1YH206 - YH207
1YH301 - YH305
2YH306
1YH321 - YH322
2YH501 - YH542
2YH551 - YH594
2YH601 - YH606
2YH611 - YH620
2YH631 - YH632
2YH636 - YH637
2YH641
2YH681 - YH682
2YH701 - YH725
2YH751 - YH754
2YH801 - YH840
2YH901 - YH905
2YH911 - YH914
2YH951 - YH952
1YJ001 - YJ013
1YJ021
1YJ472 - YJ480
1YJ514 - YJ517
1YJ531 - YJ578
2YJ579
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
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GroupVariable Number
2YJ961
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
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK466
2YK467
1YK471
2YK472 - YK473
1YK476
1YK480 - YK487
2YK491 - YK493
1YK495 - YK497
2YK498 - YK499
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GroupVariable Number
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
2YK695 - YK699
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK782
2YK783 - YK785
1YK791 - YK792
1YK796 - YK797
1YK801 - YK899
1YK901 - YK912
1YK918 - YK919
1YK921 - YK927
2YK928 - YK929
1YK941 - YK956
2YK957 - YK960
1YK961 - YK992
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GroupVariable Number
2YK993 - YK999
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL133
2YL134 - YL137
1YL201 - YL219
2YL220 - YL237
2YL241 - YL242
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL312
2YL313 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL544
2YL545 - YL551
1YL561 - YL568
2YL569 - YL579
1YL591 - YL594
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GroupVariable Number
2YL595 - YL598
1YL601 - YL606
1YL611 - YL612
1YL616 - YL617
1YL621
1YL626
1YL631 - YL634
2YL636 - YL637
1YL661 - YL664
1YL676 - YL681
2YL682 - YL690
1YL691
2YL696 - YL697
1YL701 - YL704
2YL705 - YL707
1YL731
1YL751 - YL752
2YL756 - YL757
1YL761 - YL772
2YL773 - YL780
2YL796 - YL797
1YL801 - YL809
2YL810 - YL815
1YL901 - YL910
1YL921 - YL937
2YL938 - YL940
1YL951 - YL963
2YL964 - YL968
1YM101 - YM103
1YM201 - YM242
2YM243 - YM244
1YM251 - YM299
1YM301 - YM393
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GroupVariable Number
2YM394 - YM399
2YM401 - YM415
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
1YM641 - YM652
1YM671 - YM674
1YM691 - YM697
2YM698 - YM699
1YM701 - YM710
1YM761 - YM763
2YM764 - YM765
2YM771 - YM779
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
2YN126
1YN201 - YN202
1YN211 - YN219
1YN231 - YN235
2YN236
1YN261
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GroupVariable Number
2YN501
2YN531 - YN534
2YN551 - YN563
2YN581 - YN585
2YN591 - YN592
2YN601 - YN606
2YN651 - YN653
2YN701 - YN702
2YN741 - YN746
2YN756
1YQ001 - YQ003
1YQ011
2YQ012 - YQ021
1YQ026
2YQ027 - YQ029
2YQ036 - YQ045
2YQ201 - YQ207
2YQ231
2YQ241 - YQ251
2YQ281 - YQ284
2YQ291 - YQ296
2YQ301 - YQ302
2YQ321 - YQ324
2YQ331 - YQ334
2YQ346 - YQ347
2YQ351
2YQ401 - YQ403
2YQ451 - YQ454
2YQ456
2YQ461
2YQ471
2YQ501 - YQ519
2YR001 - YR041
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GroupVariable Number
2YR051 - YR087
2YR091 - YR098
2YR101 - YR105
2YR111 - YR124
2YR126 - YR144
2YR166 - YR182
2YR186 - YR198
2YR201 - YR204
2YR231 - YR294
2YR296 - YR297
2YR301 - YR334
2YR338 - YR341
2YR361 - YR366
2YR371 - YR373
2YR376
2YR381 - YR382
2YR386 - YR388
2YR391
2YR396 - YR398
2YR401 - YR405
2YR411 - YR413
2YR416 - YR418
2YR421 - YR424
2YR426 - YR439
2YR441 - YR455
2YR457 - YR499
2YR501 - YR506
2YR511 - YR520
2YR526 - YR544
2YR546 - YR551
2YR556 - YR562
2YR571 - YR582
2YR591 - YR592
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GroupVariable Number
2YR601 - YR605
2YR616 - YR658
2YR661 - YR663
2YR671 - YR672
2YR676 - YR678
2YR681
2YR701 - YR769
2YR771 - YR799
2YR801 - YR816
2YR831 - YR838
2YR841 - YR891
2YR901 - YR903
2YR931 - YR934
2YR938 - YR944
2YR951 - YR970
2YR981 - YR996
2YS001 - YS002
2YS006 - YS009
2YS031 - YS032
2YS051 - YS073
2YS101 - YS120
2YS126 - YS135
2YS151 - YS160
2YS166 - YS194
2YS196 - YS197
2YS201 - YS209
2YS221 - YS225
2YS231 - YS236
2YS271 - YS286
2YS301 - YS333
2YS351 - YS365
2YS371 - YS374
2YS381 - YS383
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GroupVariable Number
2YS401
2YS451
2YS456 - YS457
2YS462
2YS467
2YS501 - YS502
2YS506
2YS511 - YS513
2YS551 - YS553
2YS561 - YS578
2YS581 - YS595
2YS601 - YS690
2YS701 - YS708
2YS721 - YS755
2YS761 - YS762
2YS771 - YS780
2YS806 - YS810
2YS816 - YS818
2YS823 - YS825
2YS851 - YS860
2YS876
2YS881 - YS883
2YS901 - YS909
2YS911 - YS925
2YS961 - YS965
2YS981 - YS983
2YS991 - YS996
2YT001 - YT004
2YT006
2YT026 - YT027
2YT031 - YT032
2YT036 - YT038
2YT061 - YT068
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GroupVariable Number
2YT101 - YT109
2YT126 - YT129
2YT136 - YT138
2YT176 - YT181
2YT196 - YT197
2YT201
2YT206 - YT207
2YT211 - YT212
2YT251 - YT270
2YT301 - YT303
2YT306 - YT307
2YT311 - YT312
2YT321 - YT323
2YT401 - YT403
2YT411 - YT415
2YT427
2YT461 - YT471
2YT491 - YT492
2YT501
2YT551
2YT556
2YT561
2YT601 - YT606
2YT761 - YT776
2YT796
2YT801 - YT803
2YT811
2YT831
2YT891 - YT894
2YT901 - YT906
2YU001 - YU042
2YU201 - YU211
2YV101 - YV104
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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 and W8122
caused by insufficient separation from a hydraulic tube in the Main Landing Gear (MLG) wheel well. If
this service bulletin is not done, wire chafing between the wire bundle and hydraulic tube could cause
arcing and a loss of hydraulic fluid, which may result in a wheel well fire.
Boeing has received a report of damage to wire W6128-0506-10. The wire had chafed and arced to
an adjacent hydraulic tube located in the forward bulkhead of the MLG wheel well. The chafing and
electrical arc created a small hole in the System B hydraulic tube and also caused damage to the wire
bundle, which resulted in a ground fault detection on the System A Electrical Motor-Driven Pump
(EMDP). The small hole led to a total loss of System B hydraulic fluid and the ground fault resulted in
removal of power from the System A EMDP and illumination of the System A EMDP low power light.
Boeing investigated this problem and found that there was not sufficient separation between the wire
bundles W6128 and W8122 and the adjacent hydraulic tube at that location. As a result, Boeing is
issuing this service bulletin to add clamps to separate the wire bundles from the hydraulic tube on
airplanes from line number 1060 and on. Airplanes before line number 1060 do not need this change
because of a configuration difference in the applicable area. This change will be incorporated on
in-production airplanes starting at line number 5432.
Boeing Service Related Problem (SRP) 737NG-SRP-29-0112 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737NG FTD 29-15001 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane YM346 by
Service Bulletin 737-29A1119 Original Issue before the release of Revision 1 of this service bulletin.
The change completed on airplane YM346 by Service Bulletin 737-29A1119 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane YM346 has the configuration of a Group
1 airplane.
Revision 1 is sent to incorporate changes identified during validation of the Original Issue. Also, the
work instructions have been rewritten to improve operator usability..
D. Description
In the right side of the Main Landing Gear wheel well, do a Detailed Inspection for damage of wire
bundles and a hydraulic tube. If the wire bundles are found to be damaged, repair as necessary. If the
hydraulic tube is found to be damaged, replace or repair as necessary. Install clamps and an optional
spacer between the wire bundle and hydraulic tube. Service the hydraulic system if the hydraulic tube
was replaced or repaired. Do a test of applicable electrical systems if the wire bundle was repaired.
Effects of this Revision on airplanes on which the Original Issue was previously done:
None.
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The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
134737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
Group 2:
Affected Maintenance Zones
ZoneModel
134737-700, 737-700C, 737-800,
737-900ER
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2015-NM-144-AD, is
related to this service bulletin.
Boeing recommends that the inspection and change given in this service bulletin be done within 24
months after the original issue date of this service bulletin. If any wire bundle or hydraulic tube damage
is found, repair or replace as given in this service bulletin before further flight.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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.
For 737-700C and BBJ models that have APB winglets installed by STC number ST00830SE, the
operator is responsible for obtaining appropriate regulatory agency approval before incorporating this
service bulletin if the bulletin is in the area affected by blended winglets.
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.
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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 make the parts
• Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.250.251FIGURE 1
0.350.351FIGURE 3
0.500.501Close Access
1.601.60TOTAL FOR EACH AIRPLANE (a)
(a) Estimate assumes no damage is found on wire bundles or hydraulic tube. If
damage is found, more time is necessary.
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.250.251FIGURE 2
0.350.351FIGURE 4
0.500.501Close Access
1.601.60TOTAL FOR EACH AIRPLANE (a)
(a) Estimate assumes no damage is found on wire bundles or hydraulic tube. If
damage is found, more time is necessary.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 737NG-SRP-29-0112
b. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2015-NM-144-AD
c. Service Bulletin Index D6-19567
d. Standard Overhaul Practices Manual (SOPM) 20-50-01
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 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,
27-09-31, 27-09-61, 27-61-12, 27-81-00, 28-21-00, 29-09-00, 29-11-00, 29-11-21, 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) 27-23-11, 27-23-14, 27-61-11, 27-81-51,
28-21-11, 29-11-12, 29-23-11, 29-25-11, 29-34-11, 31-31-15, 31-53-11, 33-42-11
h. 737NG Fleet Team Digest (FTD) 29-15001
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
HYDRAULIC PLUMBING INSTL - MAIN WHEEL WELL, REAR
SPAR
272A4401
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
29-11737 Aircraft Maintenance Manual
29-32737 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
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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.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are
encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The
kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
36.002251September 15,
2015
Top Kit - Wire Bun-
dle/Hydraulic Tube
Clamp Installation
002A0014-116
25December 10,
2015
25December 17,
2015
25January 4,
2016
25January 11,
2016
25January 18,
2016
25January 25,
2016
25February 1,
2016
25February 8,
2016
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.
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B. Industry Support Information
Boeing warranty remedies are not available for the (configuration changes, inspection, and/or repair
procedures) given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
ALL
Kit 002A0014
NotesExisting Part
Number
NameQtyNew Part Number
-116
Top Kit - Wire Bun-
dle/Hydraulic Tube
Clamp Installation
-002A0014-116
CLAMP,LOOP1AS21919WCE10
(a)WIRE BUNDLE
CLAMP
1BACC10JU104
(BACC10GU104 or
BACC10JU104P
optional)
(a)WIRE BUNDLE
CLAMP
1BACC10JU105
(BACC10GU105 or
BACC10JU105P
optional)
(a)WIRE BUNDLE
CLAMP
1BACC10JU106
(BACC10GU106 or
BACC10JU106P
optional)
NUT1BACN10JC3CD
(a) (b)SCREW1BACS12GU3K12
(a) (b)SCREW1BACS12GU3K16
(a) (b)SCREW1BACS12GU3K20
(a) (b)SCREW1BACS12GU3K24
(a) (b)SCREW1BACS12GU3K28
(a) (b)SCREW1BACS12GU3K32
(a) (b)SCREW1BACS12GU3K36
(a) (b)SCREW1BACS12GU3K8
WASHER1NAS1149D0316J
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-112FC
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ALERTALERT

### Page 35

ALL
Kit 002A0014
NotesExisting Part
Number
NameQtyNew Part Number
-116
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-128FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-16FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-32FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-48FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-64FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-80FC
(a) (b)SPACERS FOR
RIVETS
1NAS42DD6-96FC
(a) There are more parts than are necessary.
(b) If grip length shown is not available at Boeing, fasteners supplied in kits
may be one grip length longer than indicated. Also, if any fastener part
numbers listed are not available or have been superseded, substitute
fasteners may be supplied in kits.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 1:
NotesNameQTYPart Number/
Specification
(a)HYDRAULIC TUBE1272A4451-56
(a) This part is only necessary if the existing hydraulic tube is found to be damaged, and is replaced. The
existing hydraulic tube can also be repaired.
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### Page 36

Group 2:
NotesNameQTYPart Number/
Specification
(a)HYDRAULIC TUBE1272A4451-1044
(a) This part is only necessary if the existing hydraulic tube is found to be damaged, and is replaced. The
existing hydraulic tube can also be repaired.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
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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### Page 37

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:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 737
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. 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.
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7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
8. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
9. 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.
10. 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.
11. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
12. 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.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
15. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC. This is provided that the RC steps, including
sub-steps and identified figures, can still be done as specified, and the airplane can
be put back in an airworthy condition.
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.
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### Page 39

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 side of the Main Landing Gear wheel well in the forward bulkhead area.
5. RC - Do a Detailed Inspection of the wire bundles and hydraulic tube for damage, in accordance
with the applicable figure below.
a. Group 1:
FIGURE 1
b. Group 2:
FIGURE 2
6. RC - If any wire bundles are found to be damaged, repair them. Refer to SWPM 20-10-13 as an
accepted procedure.
7. If any of the wire bundles were repaired, record all wire numbers repaired to refer to for system
tests.
8. If the hydraulic tube is found to be damaged:
a. Remove pressure from hydraulic systems A, B and Standby. Refer to 737-600/700/800/900
AMM 29-09-00 as an accepted procedure.
b. RC - Replace or repair the damaged hydraulic tube. Refer to 737-600/700/800/900 AMM
20-10-51 as an accepted procedure.
9. RC - Install clamps and an optional spacer between the wire bundles and hydraulic tube in
accordance with the applicable figure below.
a. Group 1:
FIGURE 3
b. Group 2:
FIGURE 4
10. If you replaced or repaired the hydraulic tube, service the hydraulic reservoir. Refer to
737-600/700/800/900 AMM 12-12-00 as an accepted procedure.
11. Restore the electrical power to the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as an
accepted procedure.
12. If you replaced or repaired the hydraulic tube. restore pressure to hydraulic systems A, B and
Standby. Refer to 737-600/700/800/900 AMM 29-11-00 for systems A and B, and
737-600/700/800/900 AMM 29-21-00 for the standby hydraulic system as accepted procedures.
13. If you replaced or repaired the hydraulic tube, check for leaks at the hydraulic tube connections.
Refer to 737-600/700/800/900 AMM 20-10-51 as an accepted procedure.
14. If any of the wire bundles were repaired, do the tests that follow.
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### Page 40

NOTE: The table that follows includes tests for all wires in W6128 and W8122. Operators only
need to test the systems that were disturbed as a result of wire repairs.
a. If wire bundle W6128 was repaired, do the tests that follow.
Test - Refer to AMM
Chapter as an Accepted
Procedure
Refer to WDM ChapterSystem NameApplicable Wire Repaired
737-600/700/800/900
AMM 33-42-02  Re-
tractable Landing Light
Assembly Replacement.
(a)
737-600/700/800/900
WDM 33-42-11
Retractable Landing Lights0001 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 W8122 was repaired, do the tests that follow.
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
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### Page 41

Test - Refer to AMM
Chapter as an Accept-
ed Procedure
Refer to WDM ChapterSystem NameApplicable Wire Re-
paired
737-600/700/800/900
AMM 27-81-00 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
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) Refer to the Wiring Diagram Manual for the applicability of Wire 0530.
15. Remove the downlock pins from all landing gears, Refer to 737-600/700/800/900 AMM 32-00-01
as an accepted procedure.
16. Remove chocks from around the tires of all landing gears.
17. Put the airplane back to a serviceable condition.
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
This Figure applies only to: Group 1.
MAIN LANDING GEAR WHEEL WELL
FORWARD BULKHEAD, RIGHT SIDE
INBD  2432732
FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION
(SHEET 1 OF 2)
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### Page 43

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 shown,
do a Detailed Inspec-
tion for damage. Re-
fer to SWPM 20-10-
13  as an accepted
procedure.
1W6128 AND W8122WIRE BUNDLESInspect1
In the area shown,
do a Detailed Inspec-
tion for damage. Re-
fer to 737-
600/700/800/900
AMM 20-10-51 as
an accepted proce-
dure.
1272A4451-56HYDRAULIC TUBEInspect2
FIGURE 1: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION
(SHEET 2 OF 2)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
This Figure applies only to: Group 2.
MAIN LANDING GEAR WHEEL WELL
FORWARD BULKHEAD, RIGHT SIDE
INBD
2432925
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION
(SHEET 1 OF 2)
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### Page 45

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 shown,
do a Detailed Inspec-
tion for damage. Re-
fer to SWPM 20-10-
13  as an accepted
procedure.
1W6128 AND W8122WIRE BUNDLESInspect1
In the area shown,
do a Detailed Inspec-
tion for damage. Re-
fer to 737-
600/700/800/900
AMM 20-10-51 as
an accepted proce-
dure.
1272A4451-1044HYDRAULIC TUBEInspect2
FIGURE 2: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - HYDRAULIC
TUBE AND WIRE BUNDLES - INSPECTION
(SHEET 2 OF 2)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
This Figure applies only to: Group 1.
B
A
TAIN LANDING GEAR WHEEL WEL
ORWARD BULKHEAD. RIGHT SID
A-A
NBD
2436368
FIGURE 3: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 1 OF 3)
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### Page 47

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
2-CLAMPSLoosen1
(a)1W6128 AND W8122WIRE BUNDLESAdjust2
On wire bundles
W6128 and W8122
as shown. (b)
1BACC10JU105
(BACC10GU105 or
BACC10JU105P option-
al)
WIRE BUNDLE
CLAMP
Install (New)3
On hydraulic tube
P/N 272A4451-56 as
shown.
1AS21919WCE10CLAMP,LOOPInstall (New)4
(c)1NAS42DD6-16FCSPACERS FOR RIV-
ETS
Install (New)5
(d)1BACS12GU3K8SCREWInstall (New)6
1NAS1149D0316JWASHERInstall (New)
Loosely to let wire
bundles be adjusted.
1BACN10JC3CDNUTInstall (New)
35 in-lb.1BACN10JC3CDNUTTorque7
2-CLAMPSTighten8
(a) Adjust wire bundle slack outboard, towards the hydraulic tube, to install new clamps, if necessary.
(b) If the listed wire bundle clamp does not fit correctly, use wire bundle clamp BACC10JU104 (BACC10GU104
or BACC10JU104P optional) or BACC10JU106 (BACC10GU106 or BACC10JU106P optional).
(c) Installation of a spacer is optional. As an alternative, make a selection of a spacer from the extra parts
table below. Make sure that the distance between the wire bundles and hydraulic tube is 0.5 inch (1.3
cm) minimum.
(d) As an alternative, make a selection of a screw from the extra parts table below.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACC10JU104
(BACC10GU104 or
BACC10JU104P optional)
WIRE BUNDLE CLAMP
1BACC10JU106
(BACC10GU106 or
BACC10JU106P optional)
WIRE BUNDLE CLAMP
1BACS12GU3K12SCREW
FIGURE 3: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 2 OF 3)
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### Page 48

More DataQtyIdentificationName
1BACS12GU3K16SCREW
1BACS12GU3K20SCREW
1BACS12GU3K24SCREW
1BACS12GU3K28SCREW
1BACS12GU3K32SCREW
1BACS12GU3K36SCREW
1NAS42DD6-32FCSPACERS FOR RIVETS
1NAS42DD6-48FCSPACERS FOR RIVETS
1NAS42DD6-64FCSPACERS FOR RIVETS
1NAS42DD6-80FCSPACERS FOR RIVETS
1NAS42DD6-96FCSPACERS FOR RIVETS
1NAS42DD6-112FCSPACERS FOR RIVETS
1NAS42DD6-128FCSPACERS FOR RIVETS
FIGURE 3: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 3 OF 3)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
This Figure applies only to: Group 2.
MAIN LANDING GEAR WHEEL WELL
FORWARD BULKHEAD, RIGHT SIDE
A-A
NBD
2436369
FIGURE 4: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 1 OF 3)
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### Page 50

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
2-CLAMPSLoosen1
(a)1W6128 AND W8122WIRE BUNDLESAdjust2
On wire bundles
W6128 and W8122
as shown. (b)
1BACC10JU105
(BACC10GU105 or
BACC10JU105P option-
al)
WIRE BUNDLE
CLAMP
Install (New)3
On hydraulic tube
P/N 272A4451-1044
as shown.
1AS21919WCE10CLAMP,LOOPInstall (New)4
(c)1NAS42DD6-16FCSPACERS FOR RIV-
ETS
Install (New)5
(d)1BACS12GU3K8SCREWInstall (New)6
1NAS1149D0316JWASHERInstall (New)
Loosely to let wire
bundles be adjusted.
1BACN10JC3CDNUTInstall (New)
35 in-lb.1BACN10JC3CDNUTTorque7
2-CLAMPSTighten8
(a) Adjust wire bundle slack outboard, towards the hydraulic tube, to install new clamps, if necessary.
(b) If the listed wire bundle clamp does not fit correctly, use wire bundle clamp BACC10JU104 (BACC10GU104
or BACC10JU104P optional) or BACC10JU106 (BACC10GU106 or BACC10JU106P optional).
(c) Installation of a spacer is optional. As an alternative, make a selection of a spacer from the extra parts
table below. Make sure that the distance between the wire bundles and hydraulic tube is 0.5 inch (1.3
cm) minimum.
(d) As an alternative, make a selection of a screw from the extra parts table below.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACC10JU104
(BACC10GU104 or
BACC10JU104P optional)
WIRE BUNDLE CLAMP
1BACC10JU106
(BACC10GU106 or
BACC10JU106P optional)
WIRE BUNDLE CLAMP
1BACS12GU3K12SCREW
FIGURE 4: RIGHT MAIN WHEEL WELL - BELOW ELECTRIC MOTOR DRIVEN PUMP 'B' - CLAMPS -
INSTALLATION
(SHEET 2 OF 3)
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### Page 51

More DataQtyIdentificationName
1BACS12GU3K16SCREW
1BACS12GU3K20SCREW
1BACS12GU3K24SCREW
1BACS12GU3K28SCREW
1BACS12GU3K32SCREW
1BACS12GU3K36SCREW
1NAS42DD6-32FCSPACERS FOR RIVETS
1NAS42DD6-48FCSPACERS FOR RIVETS
1NAS42DD6-64FCSPACERS FOR RIVETS
1NAS42DD6-80FCSPACERS FOR RIVETS
1NAS42DD6-96FCSPACERS FOR RIVETS
1NAS42DD6-112FCSPACERS FOR RIVETS
1NAS42DD6-128FCSPACERS FOR RIVETS
FIGURE 4: 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: August 04, 2015
737-29A1119Revision 1 June 23, 2016
51 of 52
BOEING SERVICE BULLETIN 737-29A1119
ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-29A1119
ALERT  ALERT
Boeing Part Demand Intent
After review of this service bulletin (SB), Boeing asks that the primary engineer fill out this survey to
help Boeing predict the quantity and timing of the Boeing supplied kits.
Airline:
Contact Name:
Date:
Contact E-mail:
• Yes  - No Have/will you recommend to your airline to accomplish this SB?
• Yes  • No Would issuance of an Airworthiness Directive change this decision?
When would you likely be starting this SB incorporation? Month/ Year_
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes
For inspection related SBs, are you planning to replace on condition, or a teet campaign to replace on
all airplanes regardless of condition?
- On Condition  Campaign
If you are not incorporating this SB at this time will you please help us understand the reason(s) why?
Your input will help us provide better customer support.
- Cost Prohibitive  - Continue Inspections  - Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to:
sbsolutions@boeing.com
constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute  Disclaimer: The data provided in this survey will be used for planning purposes only and does not  2406498
a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
APPENDIX A: PART DEMAND INTENT
(SHEET 1 OF 1)
Original Issue: August 04, 2015
Revision 1 June 23, 2016  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-29A1119
Work - See page 1 for details.  52 of 52

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