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.

ECCN: 9E991

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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Unpublished Work - All Rights Reserved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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4.0
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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 26

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 30

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE . . . . 34

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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BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary 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.

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

Airplanes Total Task Hours Elapsed Hours

All airplanes(a) 12.00 6.50

(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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ALERT ALERT
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BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT

BLANK PAGE
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

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

YA001 - YA099 1

YA101 - YA199 1

YA201 - YA211 1

YA221 1

YA231 - YA242 1

YA251 - YA256 1

YA271 - YA272 1

YA291 1

YA301 - YA302 1

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Variable Number Group

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA536 1

YA541 - YA552 1

YA571 - YA578 1

YA601 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA710 1

YA721 - YA722 1

YA731 - YA734 1

YA751 - YA756 1

YA801 - YA803 1

YA809 1

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA978 1

YB001 - YB006 1

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BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Variable Number Group

YB101 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

YB181 - YB184 1

YB201 - YB208 1

YB271 1

YB276 1

YB301 - YB310 1

YB371 - YB392 1

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB598 1

YB601 - YB635 1

YB651 1

YB656 1

YB671 - YB672 1

YB851 - YB863 1

YB871 - YB874 1

YB881 - YB893 1

YB901 - YB903 1

YB911 1

YB961 - YB975 1

YB981 1

YB986 - YB998 1

YC001 - YC030 1

YC051 - YC084 1

YC091 - YC095 1

YC101 - YC104 1

YC111 - YC113 1

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Variable Number Group

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC179 1

YC186 - YC190 1

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC387 1

YC391 - YC394 1

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC439 1

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC499 1

YC501 - YC526 1

YC571 - YC583 1

YC587 - YC589 1

YC591 - YC593 1

YC601 - YC655 1

YC681 - YC696 1

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC752 1

YC761 - YC770 1

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Variable Number Group

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

YC941 - YC951 1

YC971 - YC978 1

YC981 - YC983 1

YD001 - YD007 1

YD021 - YD025 1

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD117 1

YD121 - YD126 1

YD151 - YD159 1

YD171 - YD172 1

YD201 - YD203 1

YD206 - YD209 1

YD216 - YD219 1

YD251 - YD254 1

YD256 - YD257 1

YD261 1

YD301 - YD334 1

YD391 1

YD401 - YD410 1

YD412 - YD417 1

YD481 - YD485 1

YD491 - YD499 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

YD571 - YD572 1

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BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Variable Number Group

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE157 1

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE383 1

YF001 - YF011 1

YF021 - YF049 1

YF051 - YF067 1

YF086 - YF087 1

YF106 - YF107 1

YF111 - YF114 1

YF116 - YF119 1

YF121 - YF131 1

YF176 - YF178 1

YF191 - YF192 1

YF201 - YF276 1

YF401 - YF402 1

YF431 - YF432 1

YF436 - YF437 1

YF441 - YF442 1

YF451 - YF460 1

YF501 - YF599 1

YF601 - YF632 1

YF701 - YF707 1

YF801 - YF805 1

YF831 - YF832 1

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Variable Number Group

YF836 - YF838 1

YF901 - YF905 1

YF921 - YF928 1

YF951 - YF954 1

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG133 1

YG201 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG501 - YG512 1

YG601 - YG602 1

YG701 1

YG711 1

YH001 - YH012 1

YH031 - YH055 1

YH071 - YH080 1

YH101 - YH132 1

YH201 - YH202 1

YH206 - YH207 1

YH301 - YH306 1

YH321 - YH322 1

YH501 - YH510 1

YH551 1

YH601 - YH602 1

YH611 - YH612 1

YH631 1

YJ001 - YJ013 1

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Variable Number Group

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ579 1

YJ591 - YJ599 1

YJ631 - YJ632 1

YJ671 - YJ694 1

YJ801 - YJ867 1

YJ871 - YJ880 1

YJ901 - YJ904 1

YJ908 - YJ929 1

YJ931 - YJ937 1

YJ941 - YJ956 1

YJ961 1

YJ976 - YJ977 1

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

YK131 - YK133 1

YK136 - YK139 1

YK141 - YK142 1

YK146 - YK148 1

YK151 - YK154 1

YK161 - YK167 1

YK171 1

YK176 - YK177 1

YK186 1

YK191 1

YK196 1

YK201 - YK202 1

YK301 - YK314 1

YK321 - YK340 1

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ALERT ALERT
Variable Number Group

YK361 - YK378 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK450 1

YK456 - YK467 1

YK471 - YK473 1

YK476 1

YK480 - YK487 1

YK491 - YK492 1

YK495 - YK498 1

YK511 - YK516 1

YK521 - YK530 1

YK551 - YK571 1

YK576 - YK577 1

YK580 - YK585 1

YK601 - YK602 1

YK606 - YK607 1

YK611 - YK616 1

YK621 - YK634 1

YK641 - YK644 1

YK651 - YK665 1

YK671 - YK672 1

YK676 - YK677 1

YK681 - YK686 1

YK691 1

YK701 - YK713 1

YK716 - YK719 1

YK721 - YK741 1

YK751 - YK770 1

YK776 - YK778 1

YK781 - YK785 1

YK791 - YK792 1

YK796 - YK797 1

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ALERT ALERT
Variable Number Group

YK801 - YK899 1

YK901 - YK912 1

YK918 - YK919 1

YK921 - YK929 1

YK941 - YK998 1

YL001 - YL005 1

YL011 - YL016 1

YL021 - YL024 1

YL051 - YL052 1

YL056 - YL057 1

YL061 1

YL066 - YL069 1

YL076 - YL077 1

YL101 - YL137 1

YL201 - YL230 1

YL241 - YL242 1

YL271 - YL272 1

YL281 - YL284 1

YL301 - YL303 1

YL311 - YL314 1

YL316 - YL321 1

YL351 - YL353 1

YL371 - YL374 1

YL401 1

YL421 - YL429 1

YL431 - YL444 1

YL461 - YL478 1

YL501 - YL509 1

YL531 - YL534 1

YL541 - YL551 1

YL561 - YL579 1

YL591 - YL598 1

YL601 - YL606 1

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ALERT ALERT
Variable Number Group

YL611 - YL612 1

YL616 - YL617 1

YL621 1

YL626 1

YL631 - YL634 1

YL636 - YL637 1

YL661 - YL664 1

YL676 - YL691 1

YL696 - YL697 1

YL701 - YL707 1

YL731 1

YL751 - YL752 1

YL756 - YL757 1

YL761 - YL780 1

YL796 - YL797 1

YL801 - YL815 1

YL901 - YL910 1

YL921 - YL940 1

YL951 - YL968 1

YM101 - YM103 1

YM201 - YM244 1

YM251 - YM299 1

YM301 - YM399 1

YM401 - YM413 1

YM471 1

YM481 - YM484 1

YM501 - YM515 1

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 1

YM591 - YM599 1

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Variable Number Group

YM631 - YM634 1

YM641 - YM652 1

YM671 - YM674 1

YM691 - YM699 1

YM701 - YM710 1

YM761 - YM765 1

YM771 - YM779 1

YN001 - YN016 1

YN021 - YN024 1

YN061 1

YN071 - YN082 1

YN091 - YN092 1

YN101 - YN112 1

YN121 1

YN201 - YN202 1

YN211 - YN219 1

YN231 - YN236 1

YN261 1

YN501 1

YN531 - YN534 1

YN551 1

YN601 1

YN701 - YN702 1

YQ001 - YQ003 1

YQ011 - YQ019 1

YQ026 - YQ029 1

YQ036 - YQ044 1

YQ201 - YQ202 1

YQ231 1

YQ241 - YQ251 1

YQ281 1

YQ291 - YQ296 1

YQ301 - YQ302 1

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Variable Number Group

YQ401 - YQ403 1

YQ451 - YQ454 1

YR001 - YR013 1

YR051 - YR056 1

YR101 - YR102 1

YR111 - YR116 1

YR126 - YR129 1

YR141 - YR142 1

YR166 - YR172 1

YR201 - YR204 1

YR231 - YR245 1

YR271 - YR278 1

YR286 1

YR291 - YR294 1

YR296 - YR297 1

YR301 - YR311 1

YR361 - YR362 1

YR381 1

YR401 - YR405 1

YR421 - YR422 1

YR431 1

YR451 - YR453 1

YR501 - YR503 1

YR511 - YR512 1

YR516 - YR518 1

YR526 1

YR601 - YR605 1

YR616 - YR617 1

YR651 - YR652 1

YR656 1

YR701 - YR712 1

YR801 - YR805 1

YR851 - YR853 1

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ALERT ALERT
Variable Number Group

YR951 1

YS001 1

YS051 - YS052 1

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

Model Zone

737-600, 737-700, 737-700C, 732, 733, 742, 743

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)

Condition Action

Within 600 flight -

cycles after the

original issue

date of this service bulletin.

Before 10,000

total flight cycles.

Do a detailed inspection

of the inboard MLG door

hinge fittings for cracks in

accordance with Part 2 in

Paragraph 3.B., Work Instructions, (a)

Airplanes that have not replaced the inboard MLG

door hinge fitting assemblies with part numbers

113A8341-1 and/or -2.

OR

Do a surface HFEC inspection 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 service bulletin.

Within 10,000

flight cycles after the replacement.

Do a detailed inspection

of the inboard MLG door

hinge fittings for cracks in

accordance with Part 2 in

Paragraph 3.B., Work Instructions, (a)

Airplanes that have replaced the inboard MLG

door hinge fitting assemblies with new fittings with

part numbers 113A8341-1

and/or -2.

OR

Do a surface HFEC inspection 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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ALERT ALERT
Table 1: Inboard MLG Door Hinge Fitting Inspection and Replacement

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

- 600 flight cycles

after previous detailed 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 Instructions, (a)

No crack is found after a

detailed inspection.

- 5,500 flight cycles

after previous surface HFEC inspection. (a)

OR

Do a surface HFEC inspection 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 detailed 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 Instructions, (a)

No crack is found after a

surface HFEC inspection.

- 5,500 flight cycles

after previous surface HFEC inspection. (a)

OR

Do a surface HFEC inspection of the inboard

MLG door hinge fittings

for cracks in accordance

with Part 2 in Paragraph

3.B., Work Instructions.

(a)

Do the modification of the Before further flight. -

inboard MLG door hinge

fitting assemblies in accordance with Part 3 in

Paragraph 3.B., Work Instructions. (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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ALERT ALERT
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

Task Number of Persons Task Hours Elapsed Hours

Access 2 2.00 1.00

FIGURE 1 1 0.50 0.50

FIGURE 2 1 0.50 0.50

FIGURE 3 2 3.50 1.75

FIGURE 4 2 3.50 1.75

Restoration - Close 2 2.00 1.00

Access

TOTAL FOR EACH AIRPLANE(a) 12.00 6.50

(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

Drawing Number Title

113A8331 MLG Inboard Door Assembly

113A8335 MLG Inboard Door Assembly

113A8341 Inboard MLG Door Hing Fitting Assembly

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:

Publication Chapter-Section

737 Illustrated Parts Catalog 32-13

Component Maintenance Manual 32-13-23

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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ALERT ALERT
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 Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

7/27/2011 thru (a) 175 $6,550.00

10/06/2011

TOP KIT - MLG DOOR

INBOARD HINGE FITTING ASSEMBLY

002A0003-147

9/28/2011 thru (b) 175 $6,550.00

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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ALERT ALERT
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

Top Kit 3 4

002A0003-147 1 1

ALL

KIT 002A0003-147

NOTES

Existing Part

Name Number

Figure

New Part Number

3 4

QTY

HINGE FITTING 113A8341-2 (a) (b)

ASSY

113A8341-10 1 1

HINGE FITTING 113A8341-1 (a) (b)

ASSY

113A8341-9 1 1

BACB30NX8K10 2 2 HEX DRIVE BOLT (c)

BOLT, PROTRUD- (c)

ING HD

BACB30NX8K12 2 2

BOLT, PROTRUD- (c)

ING HD

BACB30NX8K22 1 1

BOLT, PROTRUD- (c)

ING HD

BACB30NX8K23 1 1

BACB30NX8K27 2 2 BOLT (c)

BACC30BH8 8 8 COLLAR -

BACW10BP4DP 8 8 WASHER -

(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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ALERT ALERT
2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

This is an optional part. Install this part as necessary.BACB30NX8K10X 4 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K12X 4 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K22X 2 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K23X 2 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K24X 2 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K27X 4 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K28X 4 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K24 2 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACB30NX8K28 4 BOLT, PROTRUDING HD

This is an optional part. Install this part as necessary.BACW10BP41DP 22 WASHER, PLAIN

This is an optional part. Install this part as necessary.BACW10BP4DP 6 WASHER, PLAIN

CHEMICAL CONVERSION COAT- (a)

ING

ALODINE 2 Oz

BMS 10-11, TYPE 2 Oz PRIMER (b)

I

BMS 5-95 4 Oz SEALANT (b)

(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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ALERT ALERT
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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ALERT ALERT
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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FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 1: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - LEFT SIDE

(SHEET 2 OF 3)

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ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

HINGE FITTING AS- 113A8341-1 1 (a) (b) (c)

SEMBLY

1 Inspect

HINGE FITTING AS- 113A8341-2 1 (a) (b) (c)

SEMBLY

2 Inspect

(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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FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE

(SHEET 1 OF 3)

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FIGURE 2: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - INSPECTION - RIGHT SIDE

(SHEET 2 OF 3)

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ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

HINGE FITTING AS- 113A8341-1 1 (a) (b) (c)

SEMBLY

1 Inspect

HINGE FITTING AS- 113A8341-2 1 (a) (b) (c)

SEMBLY

2 Inspect

(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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FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 1 OF 10)

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FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 2 OF 10)

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737-52A1167

41 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 3 OF 10)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

42 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Locate the position

of the part by making an outline of the

part on the inboard

MLG door. The new

part will be installed

by aligning the part

against the outline.(a)

HINGE FITTING AS- 113A8341-1 1

SEMBLY

1 Locate

Locate the position

of the part by making an outline of the

part on the inboard

MLG door. The new

part will be installed

by aligning the part

against the outline.(a)

HINGE FITTING AS- 113A8341-2 1

SEMBLY

Locate

2 Remove FASTENERS - 8 -

HINGE FITTING AS- 113A8341-1 1 -

SEMBLY

Remove

HINGE FITTING AS- 113A8341-2 1 -

SEMBLY

Remove

Clean any sealant

on the door where

the inboard MLG

door hinge fitting assembly was removed.

3 Clean INBOARD MLG DOOR - 1

Align the new part

within +/- 0.01 inch

against the marked

outline of the old

part.

4 Align HINGE FITTING ASSY 113A8341-9 1

Use a clamping device to hold the part

in place.

Put / Hold HINGE FITTING ASSY 113A8341-9 1

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 4 OF 10)

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Original Issue: December 01, 2011

737-52A1167

43 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Step Task Name Identification Qty More Data

Align the new part

within +/- 0.01 inch

against the marked

outline of the old

part.

5 Align HINGE FITTING ASSY 113A8341-10 1

Use a clamping device to hold the part

in place.

Put / Hold HINGE FITTING ASSY 113A8341-10 1

Backdrill to existing

diameter at the existing fastener hole locations on the inboard MLG door. It

is recommended to

install temporary

fasteners as fasteners holes are drilled

to avoid any movement of the part.(b)

6 Drill / Ream FASTENER HOLES - 8

7 Remove / Keep HINGE FITTING ASSY 113A8341-9 1 -

Remove / Keep HINGE FITTING ASSY 113A8341-10 1 -

8 Clean/Deburr HINGE FITTING ASSY 113A8341-9 1 -

Clean/Deburr HINGE FITTING ASSY 113A8341-10 1 -

Clean/Deburr INBOARD MLG DOOR - 1 -

Apply chemical conversion coating to

bare aluminum on

the inboard MLG

door hinge fitting assemblies and inboard MLG door as

necessary. Refer to

SOPM 20-43-03 as

an accepted procedure.

CHEMICAL CONVER- ALODINE -

SION COATING

9 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE I -

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 5 OF 10)

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Original Issue: December 01, 2011

737-52A1167

44 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Step Task Name Identification Qty More Data

Apply faying surface

sealant between the

inboard MLG door

hinge fitting assemblies and inboard

MLG door. Refer to

SOPM 20-50-19 as

an accepted procedure.

10 Apply SEALANT BMS 5-95 -

11 Install (New) HINGE FITTING ASSY 113A8341-9 1 (c)

12 Install (New) HINGE FITTING ASSY 113A8341-10 1 (c)

Apply sealant to fill

the counterbores

and aerodynamically

fair to the outer surface of the inboard

MLG door. Refer to

SOPM 20-50-11 as

an accepted procedure.

13 Apply SEALANT BMS 5-95 -

(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 fastener tables.

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 6 OF 10)

BOEING PROPRIETARY -

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Original Issue: December 01, 2011

737-52A1167

45 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
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.

Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

A HEX DRIVE BOLT BACB30NX8K10 2 0.247 - 0.250

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K12 2 0.247 - 0.250

HD

B

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K22 1 0.247 - 0.250

HD

C

Install the part under the

collar.

WASHER BACW10BP4DP 1 -

COLLAR BACC30BH8 1 - -

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 7 OF 10)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

46 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K23 1 0.247 - 0.250

HD

D

Install the part under the

collar.

WASHER BACW10BP4DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E BOLT BACB30NX8K27 2 0.247 - 0.250

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

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.

Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

A (Op- HEX DRIVE BOLT BACB30NX8K10X 2 0.263 - 0.266

tion 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K12X 2 0.263 - 0.266

HD

B (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 8 OF 10)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

47 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K22X 1 0.263 - 0.266

HD

C (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K23X 1 0.263 - 0.266

HD

D (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K24X 1 0.263 - 0.266

HD

D (Option 2)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K24 1 0.247 - 0.250

HD

D (Option 3)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K27X 2 0.263 - 0.266

tion 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

FIGURE 3: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - LEFT SIDE

(SHEET 9 OF 10)

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737-52A1167

48 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K28X 2 0.263 - 0.266

tion 2)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP41DP 4 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K28 2 0.247 - 0.250

tion 3)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP4DP 4 -

COLLAR BACC30BH8 2 - -

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

ALERT ALERT
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 1 OF 10)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

50 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 2 OF 10)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

51 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 3 OF 10)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

52 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Locate the position

of the part by making an outline of the

part on the inboard

MLG door. The new

part will be installed

by aligning the part

against the outline.(a)

HINGE FITTING AS- 113A8341-1 1

SEMBLY

1 Locate

Locate the position

of the part by making an outline of the

part on the inboard

MLG door. The new

part will be installed

by aligning the part

against the outline.(a)

HINGE FITTING AS- 113A8341-2 1

SEMBLY

Locate

2 Remove FASTENERS - 8 -

HINGE FITTING AS- 113A8341-1 1 -

SEMBLY

Remove

HINGE FITTING AS- 113A8341-2 1 -

SEMBLY

Remove

Clean any sealant

on the door where

the inboard MLG

door hinge fitting assembly was removed.

3 Clean INBOARD MLG DOOR - 1

Align the new part

within +/- 0.01 inch

against the marked

outline of the old

part.

4 Align HINGE FITTING ASSY 113A8341-9 1

Use a clamping device to hold the part

in place.

Put / Hold HINGE FITTING ASSY 113A8341-9 1

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

ALERT ALERT
Step Task Name Identification Qty More Data

Align the new part

within +/- 0.01 inch

against the marked

outline of the old

part.

5 Align HINGE FITTING ASSY 113A8341-10 1

Use a clamping device to hold the part

in place.

Put / Hold HINGE FITTING ASSY 113A8341-10 1

Backdrill to existing

diameter at the existing fastener hole locations on the inboard MLG door. It

is recommended to

install temporary

fasteners as fasteners holes are drilled

to avoid any movement of the part.(b)

6 Drill / Ream FASTENER HOLES - 8

7 Remove / Keep HINGE FITTING ASSY 113A8341-9 1 -

Remove / Keep HINGE FITTING ASSY 113A8341-10 1 -

8 Clean/Deburr HINGE FITTING ASSY 113A8341-9 1 -

Clean/Deburr HINGE FITTING ASSY 113A8341-10 1 -

Clean/Deburr INBOARD MLG DOOR - 1 -

Apply chemical conversion coating to

bare aluminum on

the inboard MLG

door hinge fitting assemblies and inboard MLG door as

necessary. Refer to

SOPM 20-43-03 as

an accepted procedure.

CHEMICAL CONVER- ALODINE -

SION COATING

9 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE I -

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

ALERT ALERT
Step Task Name Identification Qty More Data

Apply faying surface

sealant between the

inboard MLG door

hinge fitting assemblies and inboard

MLG door. Refer to

SOPM 20-50-19 as

an accepted procedure.

10 Apply SEALANT BMS 5-95 -

11 Install (New) HINGE FITTING ASSY 113A8341-9 1 (c)

12 Install (New) HINGE FITTING ASSY 113A8341-10 1 (c)

Apply sealant to fill

the counterbores

and aerodynamically

fair to the outer surface of the inboard

MLG door. Refer to

SOPM 20-50-11 as

an accepted procedure.

13 Apply SEALANT BMS 5-95 -

(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 fastener 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

ALERT ALERT
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.

Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

A HEX DRIVE BOLT BACB30NX8K10 2 0.247 - 0.250

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K12 2 0.247 - 0.250

HD

B

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K22 1 0.247 - 0.250

HD

C

Install the part under the

collar.

WASHER BACW10BP4DP 1 -

COLLAR BACC30BH8 1 - -

FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 7 OF 10)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

56 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K23 1 0.247 - 0.250

HD

D

Install the part under the

collar.

WASHER BACW10BP4DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E BOLT BACB30NX8K27 2 0.247 - 0.250

Install the part under the

collar.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 2 - -

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.

Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

A (Op- HEX DRIVE BOLT BACB30NX8K10X 2 0.263 - 0.266

tion 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K12X 2 0.263 - 0.266

HD

B (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 8 OF 10)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

57 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K22X 1 0.263 - 0.266

HD

C (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K23X 1 0.263 - 0.266

HD

D (Option 1)

Install the part under the

collar.

WASHER BACW10BP41DP 1 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K24X 1 0.263 - 0.266

HD

D (Option 2)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

BOLT, PROTRUDING BACB30NX8K24 1 0.247 - 0.250

HD

D (Option 3)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP4DP 2 -

COLLAR BACC30BH8 1 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K27X 2 0.263 - 0.266

tion 1)

Install the part under the

collar.

WASHER BACW10BP41DP 2 -

COLLAR BACC30BH8 2 - -

FIGURE 4: INBOARD MLG DOOR HINGE FITTING ASSEMBLY - MODIFICATION - RIGHT SIDE

(SHEET 9 OF 10)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 01, 2011

737-52A1167

58 of 59

BOEING SERVICE BULLETIN 737-52A1167

ALERT ALERT
Code Name Identification Qty Hole Dia More Data

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K28X 2 0.263 - 0.266

tion 2)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP41DP 4 -

COLLAR BACC30BH8 2 - -

Wet install with BMS 5-95

sealant. Refer to SOPM

20-50-19 as an accepted

procedure.

E (Op- BOLT BACB30NX8K28 2 0.247 - 0.250

tion 3)

Install the part under the

collar. Adjust the quantity,

no more than 2, for the

grip length.

WASHER BACW10BP4DP 4 -

COLLAR BACC30BH8 2 - -

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

ALERT ALERT