# Boeing Alert Service Bulletin 737-52A1167: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0637; AD 2013-15-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-52A1167](https://openairdocs.org/service-documents/boeing/737-52a1167.md)
- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 59
- PDF: https://openairdocs.org/files/sha256/f7/c8/f7c83496206d09a47a8c62c479b566481e01d83d4fcdcdf509e33ee260bba3dd
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-52A1167
Original Issue: December 01, 2011
ATA System: 5280
SUBJECT: DOORS - Landing Gear Doors - Inboard Main Landing Gear Door Hinge Fittings -
Inspection and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 2 2
B. Concurrent Requirements ...................................... 2 2
C. Reason ................................................ 2 2
D. Description .............................................. 2 2
E. Compliance .............................................. 2 3
F. Approval ............................................... 2 4
G. Manpower .............................................. 2 5
H. Weight and Balance Changes .................................... 2 5
I. Electrical Load Data ......................................... 2 5
J. References .............................................. 2 5
1. Existing Data .......................................... 2 5
2. Data supplied with this Service Bulletin ............................ 2 6
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 6
K. Publications Affected ........................................ 2 6
L. Interchangeability and Intermixability of Parts ........................... 2 6
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 7
C. Parts Necessary For Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 2 9
3. Parts Modified and Reidentified ................................ 2 9
4. Parts Removed and Not Replaced .............................. 2 9
D. Parts Necessary to Change Spares ................................. 3 0
E. Special Tooling - Price and Availability ............................... 3 0
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 0
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 1
A. GENERAL INFORMATION ..................................... 3 1
B. WORK INSTRUCTIONS ....................................... 3 2
FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE .... 3 4
FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE . . . 37
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE . . 40
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE . 50
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-52A1167Original Issue: December 01, 2011
ATA System: 5280
SUBJECT: DOORS - Landing Gear Doors - Inboard Main Landing Gear Door Hinge Fittings -
Inspection and Replacement
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to inspect the inboard main landing gear (MLG) door hinge fittings for
any cracks. Undetected cracks in the inboard MLG door hinge fittings can lead to hinge fitting failures, which
can cause departure of the inboard MLG door assemblies to occur. The inboard MLG door assembly departure
may impact and damage control surfaces, which could lead to reduced controllability of the airplane.
One operator reported an inboard MLG door assembly departure on a 737-700 airplane with 24,114 flight cycles.
This was the first reported instance of inboard MLG door assembly departure that Boeing has received on this
particular model.
Boeing has conducted an analysis on the inboard MLG door assembly and found that the cracks in the inboard
MLG door hinge fittings are caused by fatigue due to vibration when the landing gears are deployed. The analysis
confirmed that the premature fatigue failure of the inboard MLG door hinge fittings resulted in the departure of
the inboard MLG door assembly.
A new and improved inboard MLG door hinge fitting has been designed to have a better durability. Production
incorporation of the new and improved inboard MLG door hinge fitting affects airplanes line number 3829 and
on.
This service bulletin gives instructions to inspect the existing inboard MLG door hinge fittings for any cracks.
Boeing Service Related Problem (SRP) 737NG-SRP-52-0097 is related to this service bulletin.
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ACTION (PRR 38275-176S)
Install safety equipment for the access of the MLG door. Do a detailed inspection or surface high frequency
eddy current (HFEC) inspection of the inboard MLG door hinge fittings. If no crack is found, repeat the inspection
or do the modification of the inboard MLG door hinge fitting assemblies as a preventative modification. If any
crack is found, do the modification of the inboard MLG door hinge fitting assemblies. The modification installs
new and improved inboard MLG door hinge fitting assemblies and terminates the repeat inspection requirements
of this service bulletin. Put the airplane back to a serviceable condition.
EFFECTIVITY
737-600/-700/-700C/-800/-900/-900ER airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for 737 airplanes in warranty as of July 6, 2010. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
6.5012.00All airplanes(a)
(a) More time is needed if the MLG door adjustment is
needed.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 7 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
LEFT MLG DOOR ASSEMBLY
SHOWN (RIGHT SIDE OPPOSITE
OUTBOARD MLG DOOR
CENTER MLG DOOR
INSTALL SAFETY EQUIPMENT FOR THE
ACCESS OF THE MAIN LANDING GEAR (MLG)
DOOR. DO A DETAILED OR SURFACE HIGH
FREQUENCY EDDY CURRENT (HFEC)
INSPECTION OF THE INBOARD MLG DOOR
HINGE FI  INGS.  - NO CRACK IS FOUND,
REPEAT  ION OR DO THE
MODIFICATION OF  THE INBOARD MLG DOOR
HINGE FITTING ASSEMBLIES AS A
PREVENTATIVE MODIFICATION. IF ANY CRACK
IS FOUND, DO THE MODIFICATION OF THE  INBOARD MLG
INBOARD MLG DOOR HINGE FITTING  DOOR
ASSEMBLIES. THE MODIFICATION TERMINATES
THE REPEAT INSPECTION REQUIREMENTS. PUT
THE AIRPLANE BACK TO A SERVICEABLE
CONDITION.
ONLY MLG DOOR ASSEMBLY SHOWN FOR CLARITY
(TYPICAL LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE)
2081163
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### Page 9

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-52A1167
Original Issue: December 01, 2011
ATA System: 5280
SUBJECT: DOORS - Landing Gear Doors - Inboard Main Landing Gear Door Hinge Fittings -
Inspection and Replacement
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
DESCRIPTIONCONFIGURATIONGROUP
737-600/-700/-700C/-800/-900/-900ER airplanes line number 1
through 3828.
-1
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
1YA201 - YA211
1YA221
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
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GroupVariable Number
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
1YA501 - YA536
1YA541 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
1YA809
1YA811 - YA814
1YA831 - YA835
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
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GroupVariable Number
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
1YB561 - YB598
1YB601 - YB635
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB975
1YB981
1YB986 - YB998
1YC001 - YC030
1YC051 - YC084
1YC091 - YC095
1YC101 - YC104
1YC111 - YC113
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GroupVariable Number
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC387
1YC391 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC752
1YC761 - YC770
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GroupVariable Number
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD117
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412 - YD417
1YD481 - YD485
1YD491 - YD499
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
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GroupVariable Number
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF011
1YF021 - YF049
1YF051 - YF067
1YF086 - YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF119
1YF121 - YF131
1YF176 - YF178
1YF191 - YF192
1YF201 - YF276
1YF401 - YF402
1YF431 - YF432
1YF436 - YF437
1YF441 - YF442
1YF451 - YF460
1YF501 - YF599
1YF601 - YF632
1YF701 - YF707
1YF801 - YF805
1YF831 - YF832
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GroupVariable Number
1YF836 - YF838
1YF901 - YF905
1YF921 - YF928
1YF951 - YF954
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG133
1YG201 - YG205
1YG211 - YG214
1YG221 - YG224
1YG251 - YG252
1YG501 - YG512
1YG601 - YG602
1YG701
1YG711
1YH001 - YH012
1YH031 - YH055
1YH071 - YH080
1YH101 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301 - YH306
1YH321 - YH322
1YH501 - YH510
1YH551
1YH601 - YH602
1YH611 - YH612
1YH631
1YJ001 - YJ013
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GroupVariable Number
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ579
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
1YJ961
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
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GroupVariable Number
1YK361 - YK378
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK467
1YK471 - YK473
1YK476
1YK480 - YK487
1YK491 - YK492
1YK495 - YK498
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 - YK785
1YK791 - YK792
1YK796 - YK797
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GroupVariable Number
1YK801 - YK899
1YK901 - YK912
1YK918 - YK919
1YK921 - YK929
1YK941 - YK998
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL137
1YL201 - YL230
1YL241 - YL242
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL551
1YL561 - YL579
1YL591 - YL598
1YL601 - YL606
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GroupVariable Number
1YL611 - YL612
1YL616 - YL617
1YL621
1YL626
1YL631 - YL634
1YL636 - YL637
1YL661 - YL664
1YL676 - YL691
1YL696 - YL697
1YL701 - YL707
1YL731
1YL751 - YL752
1YL756 - YL757
1YL761 - YL780
1YL796 - YL797
1YL801 - YL815
1YL901 - YL910
1YL921 - YL940
1YL951 - YL968
1YM101 - YM103
1YM201 - YM244
1YM251 - YM299
1YM301 - YM399
1YM401 - YM413
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
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GroupVariable Number
1YM631 - YM634
1YM641 - YM652
1YM671 - YM674
1YM691 - YM699
1YM701 - YM710
1YM761 - YM765
1YM771 - YM779
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YN531 - YN534
1YN551
1YN601
1YN701 - YN702
1YQ001 - YQ003
1YQ011 - YQ019
1YQ026 - YQ029
1YQ036 - YQ044
1YQ201 - YQ202
1YQ231
1YQ241 - YQ251
1YQ281
1YQ291 - YQ296
1YQ301 - YQ302
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GroupVariable Number
1YQ401 - YQ403
1YQ451 - YQ454
1YR001 - YR013
1YR051 - YR056
1YR101 - YR102
1YR111 - YR116
1YR126 - YR129
1YR141 - YR142
1YR166 - YR172
1YR201 - YR204
1YR231 - YR245
1YR271 - YR278
1YR286
1YR291 - YR294
1YR296 - YR297
1YR301 - YR311
1YR361 - YR362
1YR381
1YR401 - YR405
1YR421 - YR422
1YR431
1YR451 - YR453
1YR501 - YR503
1YR511 - YR512
1YR516 - YR518
1YR526
1YR601 - YR605
1YR616 - YR617
1YR651 - YR652
1YR656
1YR701 - YR712
1YR801 - YR805
1YR851 - YR853
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GroupVariable Number
1YR951
1YS001
1YS051 - YS052
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect the inboard main landing gear (MLG) door hinge
fittings for any cracks. Undetected cracks in the inboard MLG door hinge fittings can lead to hinge fitting
failures, which can cause departure of the inboard MLG door assemblies to occur. The inboard MLG
door assembly departure may impact and damage control surfaces, which could lead to reduced
controllability of the airplane.
One operator reported an inboard MLG door assembly departure on a 737-700 airplane with 24,114
flight cycles. This was the first reported instance of inboard MLG door assembly departure that Boeing
has received on this particular model.
Boeing has conducted an analysis on the inboard MLG door assembly and found that the cracks in
the inboard MLG door hinge fittings are caused by fatigue due to vibration when the landing gears are
deployed. The analysis confirmed that the premature fatigue failure of the inboard MLG door hinge
fittings resulted in the departure of the inboard MLG door assembly.
A new and improved inboard MLG door hinge fitting has been designed to have a better durability.
Production incorporation of the new and improved inboard MLG door hinge fitting affects airplanes line
number 3829 and on.
This service bulletin gives instructions to inspect the existing inboard MLG door hinge fittings for any
cracks.
Boeing Service Related Problem (SRP) 737NG-SRP-52-0097 is related to this service bulletin.
D. Description
Install safety equipment for the access of the MLG door. Do a detailed inspection or surface high
frequency eddy current (HFEC) inspection of the inboard MLG door hinge fittings. If no crack is found,
repeat the inspection or do the modification of the inboard MLG door hinge fitting assemblies as a
preventative modification. If any crack is found, do the modification of the inboard MLG door hinge
fitting assemblies. The modification installs new and improved inboard MLG door hinge fitting assemblies
and terminates the repeat inspection requirements of this service bulletin. Put the airplane back to a
serviceable condition.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Affected Maintenance Zones
ZoneModel
732, 733, 742, 743737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
For airplanes which have incorporated Boeing Business Jet (BBJ) Lower Cabin Altitude Supplemental
Type Certificate (STC) ST01697SE (6500 feet maximum cabin altitude in lieu of 8000 feet) as referenced
in Boeing Service Bulletin 737-21-1149, the airplane parts addressed in this service bulletin are not
affected by those increased cabin pressures.
Table 1: Inboard MLG Door Hinge Fitting Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 600 flight
cycles after the
original issue
date of this ser-
vice bulletin.
Before 10,000
total flight cy-
cles.
Do a detailed inspection
of the inboard MLG door
hinge fittings for cracks in
accordance with Part 2 in
Paragraph 3.B., Work In-
structions, (a)
Airplanes that have not re-
placed the inboard MLG
door hinge fitting assem-
blies with part numbers
113A8341-1 and/or -2.
OR
Do a surface HFEC in-
spection of the inboard
MLG door hinge fittings
for cracks in accordance
with Part 2 in Paragraph
3.B., Work Instructions.
(a)
-Within 600 flight
cycles after the
original issue
date of this ser-
vice bulletin.
Within 10,000
flight cycles af-
ter the replace-
ment.
Do a detailed inspection
of the inboard MLG door
hinge fittings for cracks in
accordance with Part 2 in
Paragraph 3.B., Work In-
structions, (a)
Airplanes that have re-
placed the inboard MLG
door hinge fitting assem-
blies with new fittings with
part numbers 113A8341-1
and/or -2.
OR
Do a surface HFEC in-
spection of the inboard
MLG door hinge fittings
for cracks in accordance
with Part 2 in Paragraph
3.B., Work Instructions.
(a)
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Table 1: Inboard MLG Door Hinge Fitting Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
- 600 flight cycles
after previous de-
tailed inspection.
(a)
Within 600 flight cycles after the
previous inspection.
Do a detailed inspection
of the inboard MLG door
hinge fittings for cracks in
accordance with Part 2 in
Paragraph 3.B., Work In-
structions, (a)
No crack is found after a
detailed inspection.
- 5,500 flight cycles
after previous sur-
face HFEC inspec-
tion. (a)
OR
Do a surface HFEC in-
spection of the inboard
MLG door hinge fittings
for cracks in accordance
with Part 2 in Paragraph
3.B., Work Instructions.
(a)
- 600 flight cycles
after previous de-
tailed inspection.
(a)
Within 5,500 flight cycles after the
previous inspection.
Do a detailed inspection
of the inboard MLG door
hinge fittings for cracks in
accordance with Part 2 in
Paragraph 3.B., Work In-
structions, (a)
No crack is found after a
surface HFEC inspection.
- 5,500 flight cycles
after previous sur-
face HFEC inspec-
tion. (a)
OR
Do a surface HFEC in-
spection of the inboard
MLG door hinge fittings
for cracks in accordance
with Part 2 in Paragraph
3.B., Work Instructions.
(a)
-Before further flight.Do the modification of the
inboard MLG door hinge
fitting assemblies in accor-
dance with Part 3 in
Paragraph 3.B., Work In-
structions. (a)
Any crack is found.
(a) Modification of the inboard MLG door hinge fitting assemblies in accordance with Part 3 in Paragraph
3.B., Work Instructions, terminates the inspection requirements of this service bulletin. The modification
installs new and improved MLG door hinge fitting assemblies.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
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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
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Access
0.500.501FIGURE 1
0.500.501FIGURE 2
1.753.502FIGURE 3
1.753.502FIGURE 4
1.002.002Restoration - Close
Access
6.5012.00TOTAL FOR EACH AIRPLANE(a)
(a) More time is needed if the MLG door adjustment is needed.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR 38275-176S
b. Boeing Service Related Problem (SRP) 737NG-SRP-52-0097
c. Standard Overhaul Practices Manual (SOPM) 20-00-00, 20-41-02, 20-43-03, 20-50-11,
20-50-19
d. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Figure 4 or 23
e. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 32-00-01, 32-13-11
f. 737-600 Structural Repair Manual (SRM) 51-40-05
g. 737-700 Structural Repair Manual (SRM) 51-40-05
h. 737-700CONV Structural Repair Manual (SRM) 51-40-05
i. 737-700IGW (BBJ) Structural Repair Manual (SRM) 51-40-05
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j. 737-800 Structural Repair Manual (SRM) 51-40-05
k. 737-900 Structural Repair Manual (SRM) 51-40-05
l. 737-900ER Structural Repair Manual (SRM) 51-40-05
m. Airplane Flight Manual (D631A001), Appendix Configuration Deviation List (CDL)
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
MLG Inboard Door Assembly113A8331
MLG Inboard Door Assembly113A8335
Inboard MLG Door Hing Fitting Assembly113A8341
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
32-13737 Illustrated Parts Catalog
32-13-23Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits 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
$6,550.00175(a)7/27/2011 thru
10/06/2011
TOP KIT - MLG DOOR
INBOARD HINGE FIT-
TING ASSEMBLY
002A0003-147
$6,550.00175(b)9/28/2011 thru
11/26/2013
(a) A quantity of 15 per every two weeks is available for the dates specified.
(b) A quantity of 32 per month is available for the dates specified.
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane if needed. 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 July 6, 2010. For task hour
reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty &
Product Assurance Contracts. The kits/parts for airplanes in warranty as of that date will be supplied
at no charge. Send a purchase order for the kits/parts to Boeing Spares. Please refer to this service
bulletin number and reference the airplane variable number(s) in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
Figure Kit
43Top Kit
11002A0003-147
ALL
KIT 002A0003-147
NOTES
Existing Part
NumberName
Figure
New Part Number
43
QTY
(a) (b)113A8341-2HINGE FITTING
ASSY
11113A8341-10
(a) (b)113A8341-1HINGE FITTING
ASSY
11113A8341-9
(c)HEX DRIVE BOLT22BACB30NX8K10
(c)BOLT, PROTRUD-
ING HD
22BACB30NX8K12
(c)BOLT, PROTRUD-
ING HD
11BACB30NX8K22
(c)BOLT, PROTRUD-
ING HD
11BACB30NX8K23
(c)BOLT22BACB30NX8K27
-COLLAR88BACC30BH8
-WASHER88BACW10BP4DP
(a) Discard the existing part.
(b) You can use the existing part to replace the new or changed part. If you use
the existing, you cancel the effect of the change given in this service bulletin.
(c) If grip length shown is not available at Boeing, fasteners supplied in kits may
be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in kits.
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2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD4BACB30NX8K10X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD4BACB30NX8K12X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD2BACB30NX8K22X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD2BACB30NX8K23X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD2BACB30NX8K24X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD4BACB30NX8K27X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD4BACB30NX8K28X
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD2BACB30NX8K24
This is an optional part. In-
stall this part as necessary.
BOLT, PROTRUDING HD4BACB30NX8K28
This is an optional part. In-
stall this part as necessary.
WASHER, PLAIN22BACW10BP41DP
This is an optional part. In-
stall this part as necessary.
WASHER, PLAIN6BACW10BP4DP
(a)CHEMICAL CONVERSION COAT-
ING
2 OzALODINE
(b)PRIMER2 OzBMS 10-11, TYPE
I
(b)SEALANT4 OzBMS 5-95
(a) Refer to SOPM 20-43-03 for material alternatives and SOPM 20-00-00 for supplier data.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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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:
– 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 limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. 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.
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. 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.
9. 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.
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10. The use of an inspection putty on the pushrods on the inboard main landing gear
(MLG) doors is recommended to make sure that there are no adjustments made to
the pushrods during the removal and installation of the inboard MLG doors.
B. WORK INSTRUCTIONS
Part 1 - Access
1. Install MLG downlock pins. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted procedure.
2. Do Part 2 - Inspection.
Part 2 - Inspection
1. Do a detailed inspection or surface high frequency eddy current (HFEC) inspection of the left side
inboard MLG door hinge fittings for cracks in accordance with FIGURE 1.
2. Do a detailed inspection or surface HFEC inspection of the right side inboard MLG door hinge
fittings for cracks in accordance with FIGURE 2.
3. If no crack is found, repeat the inspections at the time given in Paragraph 1.E., Compliance.
NOTE: As an alternative, it is acceptable to do Part 3 - Modification of Inboard MLG Door Hinge
Fitting Assemblies as a preventative modification. The modification of the inboard MLG
door hinge fitting assemblies terminates the inspection requirements of this service bulletin.
The modification installs new and improved inboard MLG door hinge fitting assemblies.
4. If any crack is found, do Part 3 - Modification of Inboard MLG Door Hinge Fitting Assemblies.
Part 3 - Modification of Inboard MLG Door Hinge Fitting Assemblies
CAUTION: BE CAREFUL NOT TO DAMAGE THE LOCKWIRES ON THE PUSHRODS OF THE
INBOARD MLG DOORS. DAMAGE TO THE LOCKWIRE MAY CAUSE AN ADJUSTMENT
OF THE PUSHRODS.
1. Remove the inboard MLG doors. Refer to 737-600/700/800/900 AMM 32-13-11 as an accepted
procedure.
NOTE: MLG door adjustment is necessary if the pushrods need a replacement or any adjustment
is made on the existing pushrods.
2. Modify the inboard MLG door hinge fitting assemblies in accordance with FIGURE 3 and FIGURE
4.
NOTE: The modification of the inboard MLG door hinge fitting assemblies terminates the inspection
requirements of this service bulletin. The modification installs new and improved inboard
MLG door hinge fitting assemblies.
3. Install the inboard MLG doors. Refer to 737-600/700/800/900 AMM 32-13-11 as an accepted
procedure.
4. If no adjustment was made on the existing pushrods, MLG door adjustment is not necessary.
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5. If any adjustment was made on the existing pushrods or the pushrods need a replacement, do the
MLG door adjustment. Refer to 737-600/700/800/900 AMM 32-13-11 as an accepted procedure.
Part 4 - Restoration
1. Remove the MLG downlock pins. Refer to 737-600/700/800/900 AMM 32-00-01 as an accepted
procedure.
2. Put the airplane back to a serviceable condition.
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
A LEFT MLG DOOR ASSEMBLY
OUTBOARD MLG DOOR
CENTER MLG DOOR
INBOARD MLG
DOOR
ONLY MLG DOOR ASSEMBLY SHOWN FOR CLARITY
2023361
FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE
(SHEET 1 OF 3)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
TYPICAL
CRACK
LOCATIONS
TYPICAL CRACK
LOCATIONS
TYPICAL MLG DOORS SHOWN
FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE
(SHEET 2 OF 3)
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### 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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b) (c)1113A8341-1HINGE FITTING AS-
SEMBLY
Inspect1
(a) (b) (c)1113A8341-2HINGE FITTING AS-
SEMBLY
Inspect2
(a) Do a detailed inspection or surface HFEC inspection in accordance with 737 NDT Part 6, 51-00-00, Figure
4 or 23, of the inboard MLG door hinge fittings for a crack.
(b) Inboard MLG door hinge fitting assembly includes inboard MLG door hinge fitting and bushings. Only the
Inspection of the inboard MLG door hinge fitting is necessary.
(c) Inspect the visible and accessible areas of the inboard MLG door hinge fitting. Removal of the part is not
necessary.
FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE
(SHEET 3 OF 3)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
RIGHT MLG DOOR ASSEMBLY
OUTBOARD MLG DOOR
CENTER MLG DOOR
INBOARD MLG DOOR
ONLY MLG DOOR ASSEMBLY SHOWN FOR CLARITY
(TYPICAL)
2081377
FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE
(SHEET 1 OF 3)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
TYPICAL CRACK
LOCATIONS  TYPICAL CRACK
LOCATIONS
TYPICAL MLG DOORS SHOWN
2081312
FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE
(SHEET 2 OF 3)
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### Page 39

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 this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b) (c)1113A8341-1HINGE FITTING AS-
SEMBLY
Inspect1
(a) (b) (c)1113A8341-2HINGE FITTING AS-
SEMBLY
Inspect2
(a) Do a detailed inspection or surface HFEC inspection in accordance with 737 NDT Part 6, 51-00-00, Figure
4 or 23, of the inboard MLG door hinge fittings for a crack.
(b) Inboard MLG door hinge fitting assembly includes inboard MLG door hinge fitting and bushings. Only the
Inspection of the inboard MLG door hinge fitting is necessary.
(c) Inspect the visible and accessible areas of the inboard MLG door hinge fitting. Removal of the part is not
necessary.
FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE
(SHEET 3 OF 3)
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ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
A LEFT MLG DOOR ASSEMBLY
B AND C
TYPICAL INBOARD MLG DOOR
2081546
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 1 OF 10)
Original Issue: December 01, 2011
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Copyright © Unpublished Work - See page 1 for details.  40 of 59

### Page 41 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
B  2081618
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 2 OF 10)
Original Issue: December 01, 2011
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Copyright © Unpublished Work - See page 1 for details.  41 of 59

### Page 42 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
Đ130
AF
478)  (6) 8 LOCATIONS
9/13
TYPICAL  2081704
A-A
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 3 OF 10)
Original Issue: December 01, 2011
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.

### 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 this figure.
More DataQtyIdentificationNameTaskStep
Locate the position
of the part by mak-
ing an outline of the
part on the inboard
MLG door. The new
part will be installed
by aligning the part
against the out-
line.(a)
1113A8341-1HINGE FITTING AS-
SEMBLY
Locate1
Locate the position
of the part by mak-
ing an outline of the
part on the inboard
MLG door. The new
part will be installed
by aligning the part
against the out-
line.(a)
1113A8341-2HINGE FITTING AS-
SEMBLY
Locate
-8-FASTENERSRemove2
-1113A8341-1HINGE FITTING AS-
SEMBLY
Remove
-1113A8341-2HINGE FITTING AS-
SEMBLY
Remove
Clean any sealant
on the door where
the inboard MLG
door hinge fitting as-
sembly was re-
moved.
1-INBOARD MLG DOORClean3
Align the new part
within +/- 0.01 inch
against the marked
outline of the old
part.
1113A8341-9HINGE FITTING ASSYAlign4
Use a clamping de-
vice to hold the part
in place.
1113A8341-9HINGE FITTING ASSYPut / Hold
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 4 OF 10)
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737-52A1167
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BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 44

More DataQtyIdentificationNameTaskStep
Align the new part
within +/- 0.01 inch
against the marked
outline of the old
part.
1113A8341-10HINGE FITTING ASSYAlign5
Use a clamping de-
vice to hold the part
in place.
1113A8341-10HINGE FITTING ASSYPut / Hold
Backdrill to existing
diameter at the exist-
ing fastener hole lo-
cations on the in-
board MLG door. It
is recommended to
install temporary
fasteners as fasten-
ers holes are drilled
to avoid any move-
ment of the part.(b)
8-FASTENER HOLESDrill / Ream6
-1113A8341-9HINGE FITTING ASSYRemove / Keep7
-1113A8341-10HINGE FITTING ASSYRemove / Keep
-1113A8341-9HINGE FITTING ASSYClean/Deburr8
-1113A8341-10HINGE FITTING ASSYClean/Deburr
-1-INBOARD MLG DOORClean/Deburr
Apply chemical con-
version coating to
bare aluminum on
the inboard MLG
door hinge fitting as-
semblies and in-
board MLG door as
necessary. Refer to
SOPM 20-43-03 as
an accepted proce-
dure.
-ALODINECHEMICAL CONVER-
SION COATING
Apply9
Refer to SOPM 20-
41-02 as an accept-
ed procedure.
-BMS 10-11, TYPE IPRIMERApply
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 5 OF 10)
BOEING PROPRIETARY -
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Original Issue: December 01, 2011
737-52A1167
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BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 45

More DataQtyIdentificationNameTaskStep
Apply faying surface
sealant between the
inboard MLG door
hinge fitting assem-
blies and inboard
MLG door. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS 5-95SEALANTApply10
(c)1113A8341-9HINGE FITTING ASSYInstall (New)11
(c)1113A8341-10HINGE FITTING ASSYInstall (New)12
Apply sealant to fill
the counterbores
and aerodynamically
fair to the outer sur-
face of the inboard
MLG door. Refer to
SOPM 20-50-11 as
an accepted proce-
dure.
-BMS 5-95SEALANTApply13
(a) Making an outline of the part can be done by, but not limited to, installing temporary brackets or having
a trace around the inboard MLG door hinge fitting assemblies.
(b) Make sure the existing fastener hole surface meets the requirements in accordance with 737-600 SRM
51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM 51-40-05,
737-800 SRM 51-40-05, 737-900 SRM 51-40-05, or 737-900ER SRM 51-40-05. If the fastener hole surface
does not meet the requirements of the SRM, drill to the full size fastener holes as shown in the optional
fastener table.
(c) Install the part with standard diameter size fasteners or optional over size fasteners as shown in the fas-
tener tables.
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 6 OF 10)
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Original Issue: December 01, 2011
737-52A1167
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BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 46

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K10HEX DRIVE BOLTA
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K12BOLT, PROTRUDING
HD
B
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K22BOLT, PROTRUDING
HD
C
Install the part under the
collar.
-1BACW10BP4DPWASHER
--1BACC30BH8COLLAR
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 7 OF 10)
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Original Issue: December 01, 2011
737-52A1167
46 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 47

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K23BOLT, PROTRUDING
HD
D
Install the part under the
collar.
-1BACW10BP4DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K27BOLTE
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
The codes shown below are optional fasteners for each fastener symbols in the figure. The QTY numbers shown
below are the number of optional fasteners necessary for this figure. It is not necessary to install all of the optional
fasteners as shown in this figure.
More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K10XHEX DRIVE BOLTA (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K12XBOLT, PROTRUDING
HD
B (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 8 OF 10)
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737-52A1167
47 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 48

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K22XBOLT, PROTRUDING
HD
C (Op-
tion 1)
Install the part under the
collar.
-1BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K23XBOLT, PROTRUDING
HD
D (Op-
tion 1)
Install the part under the
collar.
-1BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K24XBOLT, PROTRUDING
HD
D (Op-
tion 2)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-2BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K24BOLT, PROTRUDING
HD
D (Op-
tion 3)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-2BACW10BP4DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K27XBOLTE (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 9 OF 10)
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Original Issue: December 01, 2011
737-52A1167
48 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 49

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K28XBOLTE (Op-
tion 2)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-4BACW10BP41DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K28BOLTE (Op-
tion 3)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-4BACW10BP4DPWASHER
--2BACC30BH8COLLAR
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE
(SHEET 10 OF 10)
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737-52A1167
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BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
RIGHT MLG DOOR ASSEMBLY A
AND C
TYPICAL INBOARD MLG DOOR
2081790
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 1 OF 10)
Original Issue: December 01, 2011
737-52A1167
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  50 of 59

### Page 51 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
2081791
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 2 OF 10)
Original Issue: December 01, 2011
BOEING PROPRIETARY -  737-52A1167
Copyright © Unpublished Work - See page 1 for details.  51 of 59

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-52A1167
ALERT  ALERT
39(11
8 LOCATIONS (6  DE  578012
(8 9 13
LAND
TYPICAL  2081792
A-A
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 3 OF 10)
Original Issue: December 01, 2011
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  52 of 59

### Page 53

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 this figure.
More DataQtyIdentificationNameTaskStep
Locate the position
of the part by mak-
ing an outline of the
part on the inboard
MLG door. The new
part will be installed
by aligning the part
against the out-
line.(a)
1113A8341-1HINGE FITTING AS-
SEMBLY
Locate1
Locate the position
of the part by mak-
ing an outline of the
part on the inboard
MLG door. The new
part will be installed
by aligning the part
against the out-
line.(a)
1113A8341-2HINGE FITTING AS-
SEMBLY
Locate
-8-FASTENERSRemove2
-1113A8341-1HINGE FITTING AS-
SEMBLY
Remove
-1113A8341-2HINGE FITTING AS-
SEMBLY
Remove
Clean any sealant
on the door where
the inboard MLG
door hinge fitting as-
sembly was re-
moved.
1-INBOARD MLG DOORClean3
Align the new part
within +/- 0.01 inch
against the marked
outline of the old
part.
1113A8341-9HINGE FITTING ASSYAlign4
Use a clamping de-
vice to hold the part
in place.
1113A8341-9HINGE FITTING ASSYPut / Hold
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 4 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
53 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 54

More DataQtyIdentificationNameTaskStep
Align the new part
within +/- 0.01 inch
against the marked
outline of the old
part.
1113A8341-10HINGE FITTING ASSYAlign5
Use a clamping de-
vice to hold the part
in place.
1113A8341-10HINGE FITTING ASSYPut / Hold
Backdrill to existing
diameter at the exist-
ing fastener hole lo-
cations on the in-
board MLG door. It
is recommended to
install temporary
fasteners as fasten-
ers holes are drilled
to avoid any move-
ment of the part.(b)
8-FASTENER HOLESDrill / Ream6
-1113A8341-9HINGE FITTING ASSYRemove / Keep7
-1113A8341-10HINGE FITTING ASSYRemove / Keep
-1113A8341-9HINGE FITTING ASSYClean/Deburr8
-1113A8341-10HINGE FITTING ASSYClean/Deburr
-1-INBOARD MLG DOORClean/Deburr
Apply chemical con-
version coating to
bare aluminum on
the inboard MLG
door hinge fitting as-
semblies and in-
board MLG door as
necessary. Refer to
SOPM 20-43-03 as
an accepted proce-
dure.
-ALODINECHEMICAL CONVER-
SION COATING
Apply9
Refer to SOPM 20-
41-02 as an accept-
ed procedure.
-BMS 10-11, TYPE IPRIMERApply
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 5 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
54 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 55

More DataQtyIdentificationNameTaskStep
Apply faying surface
sealant between the
inboard MLG door
hinge fitting assem-
blies and inboard
MLG door. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS 5-95SEALANTApply10
(c)1113A8341-9HINGE FITTING ASSYInstall (New)11
(c)1113A8341-10HINGE FITTING ASSYInstall (New)12
Apply sealant to fill
the counterbores
and aerodynamically
fair to the outer sur-
face of the inboard
MLG door. Refer to
SOPM 20-50-11 as
an accepted proce-
dure.
-BMS 5-95SEALANTApply13
(a) Making an outline of the part can be done by, but not limited to, installing temporary brackets or having
a trace around the inboard MLG door hinge fitting assemblies.
(b) Make sure the existing fastener hole surface meets the requirements in accordance with 737-600 SRM
51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM 51-40-05,
737-800 SRM 51-40-05, 737-900 SRM 51-40-05, or 737-900ER SRM 51-40-05. If the fastener hole surface
does not meet the requirements of the SRM, drill to the full size fastener holes as shown in the optional
fastener table.
(c) Install the part with standard diameter size fasteners or optional over size fasteners as shown in the fas-
tener tables.
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 6 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
55 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 56

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K10HEX DRIVE BOLTA
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K12BOLT, PROTRUDING
HD
B
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K22BOLT, PROTRUDING
HD
C
Install the part under the
collar.
-1BACW10BP4DPWASHER
--1BACC30BH8COLLAR
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 7 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
56 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 57

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K23BOLT, PROTRUDING
HD
D
Install the part under the
collar.
-1BACW10BP4DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K27BOLTE
Install the part under the
collar.
-2BACW10BP4DPWASHER
--2BACC30BH8COLLAR
The codes shown below are optional fasteners for each fastener symbols in the figure. The QTY numbers shown
below are the number of optional fasteners necessary for this figure. It is not necessary to install all of the optional
fasteners as shown in this figure.
More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K10XHEX DRIVE BOLTA (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K12XBOLT, PROTRUDING
HD
B (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 8 OF 10)
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Original Issue: December 01, 2011
737-52A1167
57 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 58

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K22XBOLT, PROTRUDING
HD
C (Op-
tion 1)
Install the part under the
collar.
-1BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K23XBOLT, PROTRUDING
HD
D (Op-
tion 1)
Install the part under the
collar.
-1BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2661BACB30NX8K24XBOLT, PROTRUDING
HD
D (Op-
tion 2)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-2BACW10BP41DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2501BACB30NX8K24BOLT, PROTRUDING
HD
D (Op-
tion 3)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-2BACW10BP4DPWASHER
--1BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K27XBOLTE (Op-
tion 1)
Install the part under the
collar.
-2BACW10BP41DPWASHER
--2BACC30BH8COLLAR
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 9 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
58 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

### Page 59

More DataHole DiaQtyIdentificationNameCode
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.263 - 0.2662BACB30NX8K28XBOLTE (Op-
tion 2)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-4BACW10BP41DPWASHER
--2BACC30BH8COLLAR
Wet install with BMS 5-95
sealant. Refer to SOPM
20-50-19 as an accepted
procedure.
0.247 - 0.2502BACB30NX8K28BOLTE (Op-
tion 3)
Install the part under the
collar. Adjust the quantity,
no more than 2, for the
grip length.
-4BACW10BP4DPWASHER
--2BACC30BH8COLLAR
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE
(SHEET 10 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 01, 2011
737-52A1167
59 of 59
BOEING SERVICE BULLETIN 737-52A1167
ALERTALERT

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