Commercial 

Airplanes 737

Service Bulletin

Number: 737-27-1300

Original Issue: April 16, 2012

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach

Lug Modification

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, DreamlinerTM,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing

liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

Company.

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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

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

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

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 32

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 34

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION . . . . . . . . 42

FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION . . . . . . . . . 49

FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION . . . . . . . . 56

FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION . . . . . . . . . 58

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BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

Summary Number: 737-27-1300

Original Issue: April 16, 2012

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach

Lug Modification

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing has received 2 reports from operators where the failure of the aft attach lugs on the left elevator tab

control mechanism resulted in unwanted elevator freeplay vibration during flight. Investigation revealed that the

bearings installed in the elevator tab control mechanism aft attach lugs were likely installed such that they may

become loose and migrate. This service bulletin installs a new or modified elevator tab control mechanism with

a new improved machined lug with a new bearing that has an improved retention swage. A secondary retention

feature was also added to the lug assemblies to ensure the bearings remain in the load path in the event of a

swage failure. This new improved machined lug is more robust than the original and will increase the service

life of the lugs and bearings of the elevator tab control mechanism. A loose bearing in the aft attach lug of the

elevator tab control mechanism that is allowed to migrate out of the load path could lead to unwanted elevator

freeplay and then tab vibration which could lead to structural failure of the elevator or the horizontal stabilizer,

which can result in unsafe flight conditions.

The related Elevator Tab service bulletins are 737-27A1299 and 737-27A1297.

Boeing Service Related Problem (SRP) 737NG-SRP-27-0211 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

AD Related Yes Paragraph 1.F., Approval

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected No Paragraph 1.K., Publications Affected

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

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Planning Data Affected Reference

Paragraph 2.C.2., Parts and Materials Supplied by the

Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to do this

Service Bulletin

Special Tooling Required Yes

ACTION (PRR 38964)

Airplane Work

1. Gain access to the elevator tab control mechanism. Remove and replace with a new or previously

modified elevator tab control mechanism or remove and modify the elevator tab control mechanism by

installing the new machined lug assemblies to the existing frames and applying the part mark, as

indicated under Component Work. Perform functional tests, a power-off (manual reversion) flight test

and return the airplane to a serviceable condition.

Component Work

1. Disassemble the elevator tab control mechanism and remove the lugs (bracket) from the frame.

2. Replace the sheet metal lug assemblies with the new machined lug assemblies.

3. Reassemble the elevator tab control mechanism and part mark with the new dash number.

EFFECTIVITY

737-600, -700, -700C, -800, -900 and -900ER Airplane(s). Refer to Paragraph 1.A., Effectivity, Airplanes, for

the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-17-19 is related to this service bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of March 11, 2010. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Refer to Paragraph 1.G., Manpower.

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BOEING SERVICE BULLETIN 737-27-1300
Airplanes Total Task Hours Elapsed Hours

TOTAL FOR 12.00 11.00

EACH INSTALLED ELEVATOR TAB

CONTROL

MECHANISM

TOTAL FOR 6.00 6.00

SPARE COMPONENT - ELEVATOR TAB CONTROL MECHANISM

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 737-27-1300
Commercial 

Airplanes 737

Service Bulletin

Number: 737-27-1300

Original Issue: April 16, 2012

ATA System: 2731

SUBJECT: FLIGHT CONTROLS - Elevator and Tab - Elevator Tab Control Mechanism - Aft Attach

Lug Modification

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

GROUP CONFIGURATION DESCRIPTION

1 - Line numbers 1 through 3909

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

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

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Variable Number Group

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

YB101 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

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Variable Number Group

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 - YD418 1

YD481 - YD485 1

YD491 - YD499 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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 - YF132 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 - YF638 1

YF701 - YF707 1

YF801 - YF805 1

YF831 - YF832 1

YF836 - YF838 1

YF901 - YF905 1

YF921 - YF928 1

YF951 - YF954 1

YG001 - YG044 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG134 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 - YH515 1

YH551 - YH552 1

YH601 - YH602 1

YH611 - YH612 1

YH631 - YH632 1

YH641 1

YJ001 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ579 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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

YK361 - YK378 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK450 1

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Variable Number Group

YK456 - YK467 1

YK471 - YK473 1

YK476 1

YK480 - YK487 1

YK491 - YK492 1

YK495 - YK499 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

YK801 - YK899 1

YK901 - YK912 1

YK918 - YK919 1

YK921 - YK929 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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 - YL232 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

YL611 - YL612 1

YL616 - YL617 1

YL621 1

YL626 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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 - YM415 1

YM471 1

YM481 - YM484 1

YM501 - YM515 1

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 1

YM591 - YM599 1

YM631 - YM634 1

YM641 - YM652 1

YM671 - YM674 1

YM691 - YM699 1

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BOEING SERVICE BULLETIN 737-27-1300
Variable Number Group

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 - YN552 1

YN601 - YN602 1

YN701 - YN702 1

YQ001 - YQ003 1

YQ011 - YQ019 1

YQ026 - YQ029 1

YQ036 - YQ045 1

YQ201 - YQ202 1

YQ231 1

YQ241 - YQ251 1

YQ281 - YQ282 1

YQ291 - YQ296 1

YQ301 - YQ302 1

YQ401 - YQ403 1

YQ451 - YQ454 1

YQ461 1

YQ471 1

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Variable Number Group

YR001 - YR015 1

YR051 - YR057 1

YR091 1

YR101 - YR102 1

YR111 - YR116 1

YR126 - YR132 1

YR141 - YR142 1

YR166 - YR174 1

YR201 - YR204 1

YR231 - YR248 1

YR271 - YR278 1

YR286 - YR287 1

YR291 - YR294 1

YR296 - YR297 1

YR301 - YR314 1

YR361 - YR363 1

YR381 - YR382 1

YR401 - YR405 1

YR421 - YR422 1

YR431 1

YR441 1

YR451 - YR455 1

YR501 - YR504 1

YR511 - YR514 1

YR516 - YR520 1

YR526 - YR527 1

YR601 - YR605 1

YR616 - YR617 1

YR651 - YR653 1

YR656 1

YR701 - YR717 1

YR801 - YR808 1

YR831 - YR833 1

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Variable Number Group

YR851 - YR855 1

YR901 1

YR951 - YR952 1

YR981 - YR984 1

YS001 - YS002 1

YS051 - YS054 1

YS101 1

YS151 1

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

None.

C. Reason

Boeing has received 2 reports from operators where the failure of the aft attach lugs on the left elevator

tab control mechanism resulted in unwanted elevator freeplay vibration during flight. Investigation

revealed that the bearings installed in the elevator tab control mechanism aft attach lugs were likely

installed such that they may become loose and migrate. This service bulletin installs a new or modified

elevator tab control mechanism with a new improved machined lug with a new bearing that has an

improved retention swage. A secondary retention feature was also added to the lug assemblies to

ensure the bearings remain in the load path in the event of a swage failure. This new improved machined

lug is more robust than the original and will increase the service life of the lugs and bearings of the

elevator tab control mechanism. A loose bearing in the aft attach lug of the elevator tab control

mechanism that is allowed to migrate out of the load path could lead to unwanted elevator freeplay

and then tab vibration which could lead to structural failure of the elevator or the horizontal stabilizer,

which can result in unsafe flight conditions.

Boeing Service Related Problem (SRP) 737NG-SRP-27-0211 is related to this service bulletin.

Fleet Team Digest 737NG FTD 27-10005 is related to this service bulletin.

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D. Description

Airplane Work

1. Gain access to the elevator tab control mechanism. Remove and replace with a new or previously

modified elevator tab control mechanism or remove and modify the elevator tab control mechanism

by installing the new machined lug assemblies to the existing frames and applying the part mark,

as indicated under Component Work. Perform functional tests, a power-off (manual reversion)

flight test and return the airplane to a serviceable condition..

Component Work

1. Disassemble the elevator tab control mechanism and remove the lugs (bracket) from the frame.

2. Replace the sheet metal lug assemblies with the new machined lug assemblies.

3. Reassemble the elevator tab control mechanism and part mark with the new dash number.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 333, 334, 343, 344

737-800, 737-900, 737-900ER

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-17-19 is related to this service

bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Table 1: Elevator Tab Control Mechanism Aft Attach Lug Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within five years -

after the date of

the original issue of

this service bulletin

Replace the elevator tab

control mechanisms that

have sheet metal aft attach lugs with elevator

tab control mechanisms

that have the new machined aft attach lugs in

accordance with work instruction 3.B.

All Airplanes

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BOEING SERVICE BULLETIN 737-27-1300
F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection

or modification) defined in this service bulletin as an alternative method of compliance to the requirements

of paragraph (g), (h), (i), (j), (k), (l), (m), (n), (o), (p), (q), (r), (s), (t) of AD 2010-17-19. All provisions of

AD 2010-17-19 that are not specifically referenced in the above statement remain fully applicable and

must be complied with.

G. Manpower

The table below shows an estimate of the task hours necessary to do tasks required in this service

bulletin for one elevator tab control mechanism, there are two on the airplane. This estimate is for direct

labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary.

The estimate does not include lost time. These are some examples of lost time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Airplane Work

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Remove the elevator 1 1.50 1.50

tab control mechanism

Install the elevator 1 1.50 1.50

tab control mechanism

Close Access 1 0.50 0.50

Test 2 2.00 1.00

Flight Test 2 (a) (a)

(a) Flight test hours are not included in estimate.

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Airplane Work

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH INSTALLED ELEVATOR 6.00 5.00

TAB CONTROL MECHANISM

Component Work

Task Number of Persons Task Hours Elapsed Hours

Disassemble the ele- 1 1.60 1.60

vator tab control

mechanism

Modify the elevator 1 2.80 2.80

tab control mechanism

Reassemble the ele- 1 1.60 1.60

vator tab control

mechanism

TOTAL FOR EACH COMPONENT 6.00 6.00

H. Weight and Balance Changes

Change in Moment

(Inches-Pound)

Change in Weight

Airplane (Pounds)

+ 1,812.0 InchesPounds737-600 + 1.5 Pounds

+ 1,872.0 InchesPounds737-700, -700C + 1.5 Pounds

+ 2,040.0 InchesPounds737-800 + 1.5 Pounds

+ 2,103.0 InchesPounds737-900, -900ER + 1.5 Pounds

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 38964

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BOEING SERVICE BULLETIN 737-27-1300
b. Service Related Problem (SRP) 737NG-SRP-27-0211

c. Fleet Team Digest 737NG FTD 27-10005

d. Boeing Program Letter BPL 6-1151-737-PGM-196, dated July 15, 2011

e. 737 Maintenance Manual (AMM) Subject737-600/700/800/900 AMM 27-31-00 ,

737-600/700/800/900 AMM 27-31-34,

f. Component Maintenance Manual (CMM) CMM 27-34-03

g. Boeing Standard Wiring Practices Manual (SWPM) SWPM 20-10-11, SWPM 20-10-12, SWPM

20-10-19

h. Boeing Standard Overhaul Practices Manual (SOPM) SOPM 20-43-03, SOPM 20-50-07,

SOPM 20-50-10, SOPM 20-50-19

i. Boeing Service Bulletin 737-27A1297, 737-27A1299

j. FAA Airworthiness Directive AD 2010-17-19

k. Boeing Parts Standards Document D-590

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

251A2430 Tab Mechanism Assy - Elevator Control

251A2431 Frame Assy - Tab Mechanism, Elevator Control

251A2401 Tab Mechanism instl - Elevator Control

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 Aircraft Maintenance Manual 27-31

737 Structural Repair Manual -

737 Illustrated Parts Catalog 27-31

737 Weight and Balance Manual -

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Publication Chapter-Section

Component Maintenance Manual 27-34

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.

M. Software Accomplishment Summary

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BOEING SERVICE BULLETIN 737-27-1300

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane, and

Paragraph 2.D., Parts Necessary to Change Spares. Operators are encouraged to share schedule

requirements with Boeing for incorporation of the service bulletin. The kits/parts 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/Part Number Name Date QTY

002A0001-107 Top Kit - - 222 days $2,359.00

002A0001-109 Top Kit - - 242 days $570.00

B. Industry Support Information

Boeing warranty remedies are available for 737 NG airplanes in warranty as of March 11, 2010. For

man-hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Warranty & Product Assurance Contracts. The parts for airplanes in warranty as of that date will be

supplied at no charge. Send a purchase order for the parts to Boeing Spares. Please refer to this

service bulletin number and reference the airplane variable number(s) in your purchase order. Also

see Program Letter BPL 6-1151-737-PGM-196, dated July 15,2011 for out of warranty parts support.

Additional copies of program letters are available from Boeing Commercial Airplanes Group - Warranties.

QTY (1) MIT002A0001-107 will be supplied for each operator with 737NG airplanes in warranty as of

March 11, 2010, and are not planning to accomplish modifications at Boeing or a MRO. Please see

Program Letter BPL 6-1151-737-PGM-196-R1, for out of warranty tool support.

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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BOEING SERVICE BULLETIN 737-27-1300
NOTE: Two of each top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied

by the Operator, are necessary for each airplane. One of the 002A0001-107 kits is

necessary to modify each spare. As an option operators may exchange their elevator tab

control mechanism for one previously modified or send their elevator tab control

mechanism to be modified by a designated MRO. (c) (d)

Kit 002A0001

Existing Part Notes

Number

New Part Number QTY Name

-107 -109

Kit - Retrofit - Elev (c)

Tab Control Mech

Aft Attach Lug

002A0001-107 - .

Kit - Retrofit - Elev (d)

Tab Instl

002A0001-109 . -

PIN ASSY - DUAL

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

251A2445-4 . 1

PIN ASSY - DUAL

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

251A2445-5 . 1

LUG ASSY - TAB (a)

MECHANISM, ELEVATOR CONTROLS

251A2455-1 1 .

DOUBLER - TAB

MECHANISM, ELEVATOR CONTROLS

251A2455-10 2 .

RADIUS FILLER,

UPPER - TAB

MECHANISM, ELEVATOR CONTROLS

251A2455-11 2 .

LUG ASSY - TAB (a)

MECHANISM, ELEVATOR CONTROLS

251A2455-2 1 .

MACHINED SPACER - TAB MECHANISM, ELEVATOR

CONTROLS

251A2455-7 2 .

RETAINER - TAB

MECHANISM, ELEVATOR CONTROL

251A2455-8 2 .

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Kit 002A0001

Existing Part Notes

Number

New Part Number QTY Name

-107 -109

RADIUS FILLER,

LOWER - TAB

MECHANISM, ELEVATOR CONTROLS

251A2455-9 2 .

BACB30FM5AK7 4 . BOLT, HEX DRIVE (a) (b)

BOLT, PROTRUD- (a) (b)

ING HD

BACB30MB8A10 4 .

BACC30BH8 4 . COLLAR (a)

BACC30M5 4 . COLLAR (a)

BACN10HR5CD . 1 NUT (a)

SELF-LOCKING (a)

NUT

BACN10JC12CD 1 .

NUT,SELF-LOCK- (a)

ING

BACN10JC4CD . 1

SELF-LOCKING (a)

NUT

BACN10JC5CD 2 2

SELF-LOCKING (a)

NUT

BACN10JC7CD 3 .

BACN10YR3CD 2 4 NUT (a)

BACN10YR4CD . 4 NUT (a)

BACP18BC02A12P . 2 PIN, COTTER (a) (b)

BACR15FP5F3R 4 . RIVET, BLIND (a) (b)

BACR15GF5D11 2 . RIVET, 100 DEG (a) (b)

BACR15GF5D12 2 . RIVET, 100 DEG (a) (b)

BACR15GF5D9 2 . RIVET, 100 DEG (a) (b)

BACS12GU3K7 . 2 SCREW, CAP (a) (b)

SHIM, LAMINAT- (a)

ED

BACS40R007Y020P 4 .

BACW10BP5CD . 1 CSK WASHER (a)

BACW10P475CG . 4 WASHER, FLAT (a)

NAS1149D0332J . 2 WASHER (a)

NAS1149D0363J 2 4 WASHER, FLAT (a)

NAS1149D0463J . 1 WASHER (a)

NAS1149D0563J 2 3 WASHER (a)

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Kit 002A0001

Existing Part Notes

Number

New Part Number QTY Name

-107 -109

NAS1149D0763J 3 . WASHER (a)

NAS1149D1290J 1 . WASHER, PLAIN (a)

NAS75-5-021 . 2 BUSHING (a)

BACW10P220S 2 . WASHER (a)

(a) Discard the existing part{Keep the existing part if there are other uses for it}

(b) If grip length shown is not available at Boeing, fasteners supplied in kits may

be one grip length longer than indicated. Also, if any fasteners part numbers

listed are not available or have been superseded, substitute fasteners may be

supplied in kits. Boeing Document D-590 and Boeing Drawing 65-88700 are

used to determine the part numbers used as substitutes.

(c) One kit is required for each elevator tab control mechanism that the operator

plans to modify.

(d) One kit is required for each elevator tab control mechanism that is installed on

the airplane.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

As an option to modifying

your elevator tab control

mechanism, you may install

a new or previously modified elevator tab control

mechanism.

Elevator Tab Control Mechanism,

Left hand side

251A2430-25 1

As an option to modifying

your elevator tab control

mechanism, you may install

a new or previously modified elevator tab control

mechanism.

Elevator Tab Control Mechanism,

Right hand side

251A2430-26 1

BMS 3-28 1 oz Anti-seize Compound (a)

Type 41 1 oz Clear Skydrol-resistance Topcoating

Alodine 1 oz Chemical conversion coating

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

– Part Interchangeability

– Left hand side:

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BOEING SERVICE BULLETIN 737-27-1300
251A2430-23 is a replacement for a 251A2430-17 and -13 or -101 and -103

251A2430-25 is a replacement for a 251A2430-15

– Right hand side:

251A2430-24 is a replacement for a 251A2430-18 and -14 or -102 and -104

251A2430-26 is a replacement for a 251A2430-16

3. Parts Modified and Reidentified

Existing Part QTY Name New Part Number Notes

Number

- 4 Lug assembly 251A2455-1, -2 (a) (c)

251A2431-15, -17 (a) (b) (c)

& -16, -18

251A2431-11, -12 4 Frame assembly

Elevator tab control 251A2430-23, -24 (a) (b) (c)

mechanism

251A2430-13, -14, 2

-17, -18, -101, -

102, -103, -104

(a) Make the change in accordance with this service bulletin.

(b) This is the part number after the change is done in accordance with this service bulletin.

(c) This part is used in production.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability.

Part Number Name QTY

002A0001-107 Top Kit 1

E. Special Tooling - Price and Availability

Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service

Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of

the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase

order acknowledgement. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin number and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

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BOEING SERVICE BULLETIN 737-27-1300
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

Purchase Data:

Unit Price as of

the Original Issue

date of this Service Bulletin (US

Dollars)

Tool Kit Number Name

Miscellaneous Tool Tab Mecha- $2,145.00 (b)

nism Lug Locating Tool

MIT002A0001-107

Removal / Installation EQPT - - -

TAB Mechanism ASSY, Elevator Control. (a)

C27085

(a) This tool is not required to accomplish this service bulletin, but it is

listed as an option and recommended to help prevent damage to the elevator tab mechanism bearings when the aft pin assemblies are removed.

This tool is GSE (Ground Support Equipment), operators will have access

to the drawing, and they will be able to procure it from wherever they

want.

(b) The daily rate is $90.00

F. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

necessary. Examine operator tool supply to make sure all necessary tools are available.

Tool Kit Number Name

Miscellaneous Tool Tab Mechanism Lug Locating ToolMIT002A0001-107

Removal / Installation EQPT - -

TAB Mechanism ASSY, Elevator

Control (a)

C27085

(a) This tool is not required to accomplish this service

bulletin, but it is listed as an option and recommended

to help prevent damage to the elevator tab mechanism

bearings when the aft pin assemblies are removed. This

tool is GSE (Ground Support Equipment), operators will

have access to the drawing, and they will be able to

procure it from wherever they want.

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BOEING SERVICE BULLETIN 737-27-1300
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. The work instructions are divided into Airplane Work and Component Work. Task

Hours and Elapsed Hours for each section are given in Paragraph 1.G., Manpower.

4. 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

5. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

7. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

8. 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.

9. 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.

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BOEING SERVICE BULLETIN 737-27-1300
10. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

11. 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.

12. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

13. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

14. 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.

15. 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.

16. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

17. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

B. WORK INSTRUCTIONS

Airplane work, right elevator tab control mechanism

1. Gain access to the Horizontal Stabilizer and the Elevator as required. Refer to 737-600/700/800/900

AMM 27-31-34 as an accepted procedure.

2. Remove the elevator tab control mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an

accepted procedure.

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NOTE: As an option the actuator can be removed from the elevator tab control mechanism and

left on the airplane, prior to removing the elevator tab control mechanism.

3. Remove the actuator from the elevator tab control mechanism. Refer to CMM 27-34-03 or

737-600/700/800/900 AMM 27-31-34 as an accepted procedure.

NOTE: It is not required to remove the actuator from the airplane.

4. Modify your elevator tab control mechanism in accordance with the Component Work section.

NOTE: As an option to modifying your elevator tab control mechanism in accordance with the

Component Work section, you may install a new elevator tab control mechanism with the

machined lugs or elevator tab control mechanism previously modified in accordance to

the requirements of this service bulletin.

5. Install the 251A2430-24 elevator tab control mechanism onto the airplane. If the actuator was left

on the airplane install the 251A2430-26 elevator tab control mechanism onto the airplane. Refer

to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in

accordance with Figure 3 for the replacement fasteners, otherwise re-use the fasteners removed

from the airplane. Installation fasteners, that are to be replaced are provided in kit #002A0001-109.

6. This step is only required if the actuator has not been previously installed in the elevator tab control

mechanism.

Install the actuator onto the new 251A2430-26 elevator tab control mechanism. Refer to CMM

27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener

codes in accordance with Figure 3 for the replacement fasteners, otherwise reuse the existing

fasteners. Installation fasteners that are to be replaced are provided in kit #002A0001-109

7. Part mark the assembly with the actuator to 251A2430 -24 in accordance with Figure 1, if the

assembly has not been previously part marked.

8. Close access and restore airplane as required, refer to 737-600/700/800/900 AMM 27-31-34 as

an accepted procedure.

9. Perform functional tests and a power-off (manual reversion) flight test. Ref to 737-600/700/800/900

AMM 27-31-34, 737-600/700/800/900 AMM 27-31-00 as an accepted procedure.

10. Put the airplane back into a serviceable condition.

11. Report all tab mechanism retrofit completions to Boeing using the Service Requests application

on MyBoeingFleet. Include airplane identification and date the retrofit was completed.

Airplane work, left elevator tab control mechanism

1. Gain access to the Horizontal Stabilizer and the Elevator as required. Refer to 737-600/700/800/900

AMM 27-31-34 as an accepted procedure.

2. Remove the elevator tab control mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an

accepted procedure.

NOTE: As an option the actuator can be removed from the elevator tab control mechanism and

left on the airplane, prior to removing the elevator tab control mechanism.

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BOEING SERVICE BULLETIN 737-27-1300
3. Remove the actuator from the elevator tab control mechanism. Refer to CMM 27-34-03 or

737-600/700/800/900 AMM 27-31-34 as an accepted procedure.

NOTE: It is not required to remove the actuator from the airplane.

4. Modify your elevator tab control mechanism in accordance with the Component Work section.

NOTE: As an option to modifying your elevator tab control mechanism in accordance with the

Component Work section, you may install a new elevator tab control mechanism with the

machined lugs or elevator tab control mechanism previously modified in accordance to

the requirements of this service bulletin.

5. Install the 251A2430-23 elevator tab control mechanism onto the airplane. If the actuator was left

on the airplane install the 251A2430-25 elevator tab control mechanism onto the airplane. Refer

to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener codes in

accordance with Figure 3 for the replacement fasteners, otherwise re-use the fasteners removed

from the airplane. Installation fasteners, that are to be replaced are provided in kit #002A0001-109.

6. This step is only required if the actuator has not been previously installed in the elevator tab control

mechanism.

Install the actuator onto the new 251A2430-25 elevator tab control mechanism. Refer to CMM

27-34-03 or 737-600/700/800/900 AMM 27-31-34 as an accepted procedure. Use the fastener

codes in accordance with Figure 4 for the replacement fasteners, otherwise reuse the existing

fasteners. Installation fasteners and hardware that are to be replaced are provided in kit

#002A0001-109.

7. Part mark the assembly with the actuator to 251A2430-23 in accordance with Figure 2, if the

assembly has not been previously part marked.

8. Close access and restore airplane as required, refer to 737-600/700/800/900 AMM 27-31-34 as

an accepted procedure.

9. Perform functional tests and a power-off (manual reversion) flight test. Ref to 737-600/700/800/900

AMM 27-31-34, 737-600/700/800/900 AMM 27-31-00 as an accepted procedure.

10. Put the airplane back into a serviceable condition.

11. Report all tab mechanism retrofit completions to Boeing using the Service Requests application

on MyBoeingFleet. Include airplane identification and date the retrofit was completed.

Component work, right elevator tab control mechanism

1. Disassemble the elevator tab control mechanism as required to get access to the left and right

frame assemblies. Refer to CMM 27-34-03 as an accepted procedure.

2. Remove the sheet metal lug (bracket) assemblies from the left and right frame assemblies. Refer

to CMM 27-34-03 as an accepted procedure.

3. For each frame assembly: Locate the frame assembly on the tool, using the 2 indicated holes in

the frame and make the cutout. Refer to the MIT002A0001-107 tool use instructions as an accepted

procedure.

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4. For each frame assembly: Locate the new lug assembly onto the close tolerance pin. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

5. For each frame assembly: Locate the doubler at the lower flange and the shims at the upper and

lower flanges, between the lug assembly and the frame in accordance with Figure 1. Use the shims

to center the lug assemble in the frame.

6. For each frame assembly: Clamp the lug assembly against the web of the frame subassembly.

Refer to the MIT002A0001-107 tool use instructions as an accepted procedure.

7. For each frame assembly: Locate the upper and lower radius fillers flush with the end of the lug

assembly and clamp in place in accordance with Figure 1.

8. For each frame assembly: Match drill fastener holes in lower flange, upper flange and lower part

of the frame web through the stack-up using existing hole locations in the frame assemblies in

accordance with Figure 1.

NOTE: Take care not to oversize the existing hole.

9. For each frame assembly: Install 2 fasteners in lower flange and 1 in upper flange and 2 in the

lower part of the frame web in accordance with Figure 1. Note, there are two more existing holes

in the upper frame flange that will be used when the elevator tab control mechanism is reassembled.

10. For each frame assembly: Locate the spacers/retainers with the MIT002A0001-107 tool.

a. For the left frame assembly: Locate the retainers and clamp in place. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

b. For the right frame assembly: Locate the machined spacers and clamp in place. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

11. For each frame assembly: Drill holes through the spacer/retainer stack-up.

a. For the left frame assembly: Drill holes through the retainer stack-up. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners

in accordance with Figure 1.

b. For the right frame assembly: Drill holes through the machined spacer stack-up. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners

in accordance with Figure 1

12. Reassemble the elevator tab control mechanism. Refer to CMM 27-34-03 as an accepted procedure.

Use the fastener codes in accordance with Figure 1 for the replacement fasteners, otherwise reuse

the existing fasteners. Installation fasteners that are to be replaced are provided in kit

#002A0001-107.

13. Part mark the frame assemblies in accordance with Figure 1. On the right mechanism the

251A2431-11 frame becomes a 251A2431-18 frame and the 251A2431-12 becomes a

251A2431-16.

14. Part mark 251A2430-26 on the elevator tab control mechanism in accordance with Figure 1.

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NOTE: After installation of the actuator, part mark 251A2430-24 on the elevator tab control

mechanism in accordance with Figure 1

Component work, left elevator tab control mechanism

1. Disassemble the elevator tab control mechanism as required to get access to the left and right

frame assemblies. Refer to CMM 27-34-03 as an accepted procedure.

2. Remove the sheet metal lug (bracket) assemblies from the left and right frame assemblies. Refer

to CMM 27-34-03 as an accepted procedure.

3. For each frame assembly: Locate the frame assembly on the tool, using the 2 indicated holes in

the frame and make the cutout. Refer to the MIT002A0001-107 tool use instructions as an accepted

procedure.

4. For each frame assembly: Locate the new lug assembly onto the close tolerance pin. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

5. For each frame assembly: Locate the doubler at the lower flange and the shims at the upper and

lower flanges, between the lug assembly and the frame in accordance with Figure 2. Use the shims

to center the lug assemble in the frame.

6. For each frame assembly: Clamp the lug assembly against the web of the frame subassembly.

Refer to the MIT002A0001-107 tool use instructions as an accepted procedure.

7. For each frame assembly: Locate the upper and lower radius fillers flush with the end of the lug

assembly and clamp in place in accordance with Figure 2.

8. For each frame assembly: Match drill fastener holes in lower flange, upper flange and the lower

part of the frame web through the stack-up using existing hole locations in the frame assemblies

in accordance with Figure 2.

NOTE: Take care not to oversize the existing hole.

9. For each frame assembly: Install 2 fasteners in lower flange, 1 in upper flange and 2 in the lower

part of the frame web in accordance with Figure 2. Note, there are two more existing holes in the

upper frame flange that will be used when the elevator tab control mechanism is reassembled.

10. For each frame assembly: Locate the spacers/retainers with the MIT002A0001-107 tool.

a. For the left frame assembly: Locate the machined spacers and clamp in place. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

b. For the right frame assembly: Locate the retainers and clamp in place. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure.

11. For each frame assembly: Drill holes through the bearing retainer stack-up.

a. For the left frame assembly: Drill holes through the machined spacer stack-up. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners

in accordance with Figure 2.

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BOEING SERVICE BULLETIN 737-27-1300
b. For the right frame assembly: Drill holes through the retainer stack-up. Refer to the

MIT002A0001-107 tool use instructions as an accepted procedure. Install double flush fasteners

in accordance with Figure 2.

12. Reassemble the elevator tab control mechanism. Refer to CMM 27-34-03 as an accepted procedure.

Use the fastener codes in accordance with Figure 2 for the replacement fasteners, otherwise reuse

the existing fasteners. Installation fasteners that are to be replaced are provided in kit

#002A0001-107.

13. Part mark the frame assemblies in accordance with Figure 2. On the left mechanism the

251A2431-11 frame becomes a 251A2431-15 frame and the 251A2431-12 becomes a

251A2431-17.

14. Part mark 251A2430-25 on the elevator tab control mechanism in accordance with Figure 2.

NOTE: After installation of the actuator, part mark 251A2430-23 on the elevator tab control

mechanism in accordance with Figure 2.

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 1 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 2 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 3 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

Install flush with

edge of lug assembly. Shim

if/as required.

SHIM, LAMINAT- BACS40R007Y020P 4

ED

1 Install (New)

Install flush with

edge of lug assembly.

DOUBLER - TAB 251A2455-10 2

MECHANISM,

ELEVATOR

CONTROLS

2 Install (New)

Install flush with

edge of lug assembly.

RADIUS FILLER, 251A2455-11 2

UPPER - TAB

MECHANISM,

ELEVATOR

CONTROLS

3 Install (New)

Install flush with

edge of lug assembly.

RADIUS FILLER, 251A2455-9 2

LOWER - TAB

MECHANISM,

ELEVATOR

CONTROLS

Install (New)

Match drill 5

holes each side.

(a)

4 Drill Fastener Hole - 10

LUG ASSY - 251A2455-1 1 (b)

TAB MECHANISM, ELEVATOR CONTROLS

5 Install (New)

Left frame assembly

LUG ASSY - 251A2455-2 1 (b)

TAB MECHANISM, ELEVATOR CONTROLS

Install (New)

Right frame assembly

MACHINED 251A2455-7 2 (a)

SPACER - TAB

MECHANISM,

ELEVATOR

CONTROLS

6 Install (New)

Right frame assembly

RETAINER - 251A2455-8 2 (a)

TAB MECHANISM, ELEVATOR CONTROL

Install (New)

Left frame assembly

FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

On the top of the

frame assemblies Part mark

251A2431-16

(right frame assy)

& 251A2431-18

(left frame assy)

on the

251A2430-26 elevator tab control

mechanism. (c)

7 Identify Part Mark - 2

On the bottom of

the elevator tab

control mechanism part mark

251A2430-26. (c)

(d)

Identify Part Mark - 1

On the bottom of

the elevator tab

control mechanism with actuator installed part

mark 251A2430-

24. (c) (d)

Identify Part Mark - 1

(a) Touch-up fastener holes with Chemical Conversion Coating. Refer to SOPM 20-43-03 as an accepted

procedure.

(b) Wet install bolts with BMS 5-95. Refer to SOPM 20-50-19 as an accepted procedure.

(c) Rubber stamp part mark. Refer to SOPM 20-50-10 as an accepted procedure.

(d) Apply abrasive overcoat.

Code Name Identification Qty Hole Dia More Data

C BOLT, HEX DRIVE BACB30FM5AK7 4 - Head far side

BOLT, PROTRUDING BACB30MB8A10 4 -

HD

D

E COLLAR BACC30BH8 4 -

F COLLAR BACC30M5 4 -

H SELF-LOCKING NUT BACN10JC12CD 1 -

J SELF-LOCKING NUT BACN10JC5CD 2 -

K SELF-LOCKING NUT BACN10JC7CD 3 -

L NUT BACN10YR3CD 2 -

FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Code Name Identification Qty Hole Dia More Data

O RIVET, BLIND BACR15FP5F3R 4 - Head near side

Head near side. Grip

length may need to be

adjusted depending on the

amount of shimming, if

any.

P RIVET, 100 DEG BACR15GF5D11 2 -

Head near side, double

flush

Q RIVET, 100 DEG BACR15GF5D12 2 -

Head near side, double

flush

R RIVET, 100 DEG BACR15GF5D9 2 -

X WASHER, FLAT NAS1149D0363J 2 -

Z WASHER NAS1149D0563J 2 -

AA WASHER NAS1149D0763J 3 -

AB WASHER, PLAIN NAS1149D1290J 1 -

AD WASHER BACW10P220S 2 -

FIGURE 1: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 1 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 2 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 3 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 4 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

Install flush with

edge of lug assembly. Shim

if/as required.

SHIM, LAMINAT- BACS40R007Y020P 4

ED

1 Install (New)

Install flush with

edge of lug assembly.

DOUBLER - TAB 251A2455-10 2

MECHANISM,

ELEVATOR

CONTROLS

2 Install (New)

Install flush with

edge of lug assembly.

RADIUS FILLER, 251A2455-11 2

UPPER - TAB

MECHANISM,

ELEVATOR

CONTROLS

3 Install (New)

Install flush with

edge of lug assembly.

RADIUS FILLER, 251A2455-9 2

LOWER - TAB

MECHANISM,

ELEVATOR

CONTROLS

Install (New)

Match drill 5

holes each side.

(a)

4 Drill Fastener Hole - 10

LUG ASSY - 251A2455-1 1 (b)

TAB MECHANISM, ELEVATOR CONTROLS

5 Install (New)

Left frame assembly

LUG ASSY - 251A2455-2 1 (b)

TAB MECHANISM, ELEVATOR CONTROLS

Install (New)

Right frame assembly

MACHINED 251A2455-7 2 (a)

SPACER - TAB

MECHANISM,

ELEVATOR

CONTROLS

6 Install (New)

Left frame assembly

RETAINER - 251A2455-8 2 (a)

TAB MECHANISM, ELEVATOR CONTROL

Install (New)

Right frame assembly

FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

On the top of the

frame assemblies Part mark

251A2431-15

(left frame assy)

& 251A2431-17

(right frame assy)

on the

251A2430-25 elevator tab control

mechanism. (c)

7 Identify Part Mark - 2

On the bottom of

the elevator tab

control mechanism part mark

251A2430-25. (c)

(d)

Identify Part Mark - 1

On the bottom of

the elevator tab

control mechanism with actuator installed part

mark 251A2430-

23. (c) (d)

Identify Part Mark - 1

(a) Touch-up fastener holes with Chemical Conversion Coating. Refer to SOPM 20-43-03 as an accepted

procedure.

(b) Wet install bolts with BMS 5-95. Refer to SOPM 20-50-19 as an accepted procedure.

(c) Rubber stamp part mark. Refer to SOPM 20-50-10 as an accepted procedure.

(d) apply abrasive overcoat.

Code Name Identification Qty Hole Dia More Data

C BOLT, HEX DRIVE BACB30FM5AK7 4 - Head far side

BOLT, PROTRUDING BACB30MB8A10 4 -

HD

D

E COLLAR BACC30BH8 4 -

F COLLAR BACC30M5 4 -

H SELF-LOCKING NUT BACN10JC12CD 1 -

J SELF-LOCKING NUT BACN10JC5CD 2 -

K SELF-LOCKING NUT BACN10JC7CD 3 -

L NUT BACN10YR3CD 2 -

FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 6 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
Code Name Identification Qty Hole Dia More Data

O RIVET, BLIND BACR15FP5F3R 4 - Head near side

Head near side. Grip

length may need to be

adjusted depending on the

amount of shimming, if

any.

P RIVET, 100 DEG BACR15GF5D11 2 -

Head near side, double

flush

Q RIVET, 100 DEG BACR15GF5D12 2 -

Head near side, double

flush

R RIVET, 100 DEG BACR15GF5D9 2 -

X WASHER, FLAT NAS1149D0363J 2 -

Z WASHER NAS1149D0563J 2 -

AA WASHER NAS1149D0763J 3 -

AB WASHER, PLAIN NAS1149D1290J 1 -

AD WASHER BACW10P220S 2 -

FIGURE 2: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM MODIFICATION

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

Use the parts/fasteners at the locations

shown to replace the

existing parts/fasteners. All other

parts/fasteners are

to be reused for installation. (a)

Elevator Tab Control - 1

Mechanism

1 Install (Changed)

(a) Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.

Code Name Identification Qty Hole Dia More Data

PIN ASSY - DUAL 251A2445-4 1 - (a)

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

A

PIN ASSY - DUAL 251A2445-5 1 - (a)

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

B

G NUT BACN10HR5CD 1 -

I NUT,SELF-LOCKING BACN10JC4CD 1 -

J SELF-LOCKING NUT BACN10JC5CD 2 -

L NUT BACN10YR3CD 4 -

M NUT BACN10YR4CD 4 -

N PIN, COTTER BACP18BC02A12P 2 -

S SCREW, CAP BACS12GU3K7 2 -

U CSK WASHER BACW10BP5CD 1 -

V WASHER, FLAT BACW10P475CG 4 -

W WASHER NAS1149D0332J 2 -

X WASHER, FLAT NAS1149D0363J 4 -

Y WASHER NAS1149D0463J 1 -

Z WASHER NAS1149D0563J 3 -

AC BUSHING NAS75-5-021 2 - (a)

(a) Apply BMS3-28 anti-seize compound to the OD of the fastener or bushing prior to installation. Refer to

SOPM 20-50-07 as an acceptable procedure.

FIGURE 3: RIGHT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2012

737-27-1300

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BOEING SERVICE BULLETIN 737-27-1300
FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2012

737-27-1300

58 of 59

BOEING SERVICE BULLETIN 737-27-1300
Step Task Name Identification Qty More Data

Use the parts/fasteners at the locations

shown to replace the

existing parts/fasteners. All other

parts/fasteners are

to be reused for installation. (a)

Elevator Tab Control - 1

Mechanism

1 Install (Changed)

(a) Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.

Code Name Identification Qty Hole Dia More Data

PIN ASSY - DUAL 251A2445-4 1 - (a)

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

A

PIN ASSY - DUAL 251A2445-5 1 - (a)

LOAD PATH, TAB

MECHANISM, ELEVATOR CONTROL

B

G NUT BACN10HR5CD 1 -

I NUT,SELF-LOCKING BACN10JC4CD 1 -

J SELF-LOCKING NUT BACN10JC5CD 2 -

L NUT BACN10YR3CD 4 -

M NUT BACN10YR4CD 4 -

N PIN, COTTER BACP18BC02A12P 2 -

S SCREW, CAP BACS12GU3K7 2 -

U CSK WASHER BACW10BP5CD 1 -

V WASHER, FLAT BACW10P475CG 4 -

W WASHER NAS1149D0332J 2 -

X WASHER, FLAT NAS1149D0363J 4 -

Y WASHER NAS1149D0463J 1 -

Z WASHER NAS1149D0563J 3 -

AC BUSHING NAS75-5-021 2 - (a)

(a) Apply BMS3-28 anti-seize compound to the OD of the fastener or bushing prior to installation. Refer to

SOPM 20-50-07 as an acceptable procedure.

FIGURE 4: LEFT SIDE, ELEVATOR TAB CONTROL MECHANISM INSTALLATION

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 16, 2012

737-27-1300

59 of 59

BOEING SERVICE BULLETIN 737-27-1300