# Boeing Alert Service Bulletin 737-27A1297: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0798; AD 2010-17-19 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-27A1297](https://openairdocs.org/service-documents/boeing/737-27a1297.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin
- Pages: 68
- PDF: https://openairdocs.org/files/sha256/3d/be/3dbe00624e5507eed3457aabcac258508d4853c635bc53c810cb8c4245b719b9
- Page: https://openairdocs.org/service-documents/boeing/737-27a1297/file/3dbe00624e55

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-27A1297
Original Issue: April 16, 2010
Revision 1: August 02, 2010
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Tab Control Mechanism Detailed Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2010 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 6
B. Concurrent Requirements ...................................... 2 6
C. Reason ................................................ 2 6
D. Description .............................................. 2 7
E. Compliance .............................................. 2 8
F. Approval ............................................... 3 0
G. Manpower .............................................. 3 0
H. Weight and Balance Changes .................................... 3 2
I. Electrical Load Data ......................................... 3 2
J. References .............................................. 3 2
1. Existing Data .......................................... 3 2
2. Data supplied with this Service Bulletin ............................ 3 2
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 3 2
K. Publications Affected ........................................ 3 2
L. Interchangeability and Intermixability of Parts ........................... 3 2
2. MATERIAL INFORMATION ........................................ 3 3
A. Material - Price and Availability ................................... 3 3
B. Industry Support Information .................................... 3 3
C. Parts Necessary For Each Airplane ................................. 3 3
1. Kits/Parts ............................................ 3 3
2. Parts and Materials Supplied by the Operator ........................ 3 4
3. Parts Modified and Reidentified ................................ 3 4
4. Parts Removed and Not Replaced .............................. 3 4
D. Parts Necessary to Change Spares ................................. 3 4
E. Special Tooling - Price and Availability ............................... 3 4
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5
A. GENERAL INFORMATION ..................................... 3 5
B. WORK INSTRUCTIONS ....................................... 3 5
FIGURE 1: ACCESS PANEL REMOVAL & INSTALLATION - LEFT SIDE ................ 4 4
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE ....... 4 6
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE ...... 5 1
FIGURE 4: ACCESS PANEL REMOVAL & INSTALLATION - RIGHT SIDE ............... 5 6
FIGURE 5: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - RIGHT SIDE ...... 5 8
FIGURE 6: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - RIGHT SIDE ..... 6 3
FIGURE 7: DETERMINING IF REPLACEMENT MECHANISM IS NOT BOEING BUILT ........ 6 8
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-27A1297Original Issue: April 16, 2010
Revision 1: August 02, 2010
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Tab Control Mechanism Detailed Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
More work is necessary on airplanes inspected in accordance with the original issue of this service bulletin:
Group 2 airplanes now require repeat inspections.
Airplanes were added to new Group 3 of this service bulletin effectivity and airplanes were added to existing
Group 2 of this service bulletin effectivity.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-09-05, is related to this service bulletin.
REASON FOR REVISION
This revision is sent to: add new Group 3 airplanes to the effectivity and add an inspection and compliance for
Group 3 airplanes; add airplanes to existing Group 2 effectivity and change the compliance for Group 2 airplanes;
remove the terminating action from the compliance; change the inspection method; delete Figure 7, "Determining
if Replacement Mechanism is not Boeing Built" and all associated steps in the Work Instructions; provide
manpower estimates; add warranty information; add convenience kit information.
These sections were changed:
1. In paragraph 1.A., Effectivity, added Group 3 airplanes to the Group/Configuration table and to the effectivity.
2. In Paragraph 1.E., Compliance, changed the requirements for Group 2 airplanes, added Group 3 compliance,
removed terminating action,
3. In Paragraph 1.G., Manpower, added manpower tables.
4. In Paragraph 2.B., Industry Support Information, added warranty remedies.
5. In Paragraph 2.C., Parts Necessary For Each Airplane, added convenience kit information.
6. In Figures 2, 3, 5, and 6, clarified feeler gage requirements and changed allowable depths.
7. Deleted Figure 7.
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The data given in Information Notices 737-27A1297 IN 01, IN 02 and IN 03 is included in this revision, as
applicable.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
April 16, 2010Original Issue:
August 02, 2010Revision 1:
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-27A1297Original Issue: April 16, 2010
Revision 1: August 02, 2010
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Tab Control Mechanism Detailed Inspection
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
An operator experienced a vibration event 21 days after performing inspections on the swage ring and spacer
on the elevator tab control mechanism (mechanism) in accordance with Service Bulletin (SB) 737-27A1296.
Investigation revealed that the vibration was most likely caused by the same conditions that Service Bulletin
737-27A1296 was meant to detect, but did not. For the most critical group of airplanes, this service bulletin does
a more enhanced inspection than the inspection in SB 737-27A1296 and continues with repeat inspections. The
more enhanced inspection includes using a feeler gage at specific locations to check for gaps. The inspections
in this SB will detect a loose bearing in the aft attach lugs of the elevator tab control mechanism. A loose bearing
in the aft attach lug of the elevator tab control mechanism could lead to unwanted elevator tab freeplay and then
elevator tab vibration which could lead to structural failure of the elevator or the horizontal stabilizer.
Since the initial release of this service bulletin, several operators have reported gaps in Boeing-built mechanisms,
but no loose bearings. Also, additional analysis by Boeing has shown that non-Boeing built mechanisms built
after Line Number 2708 may have bearings which will come loose. Because of this, the effectivity of this service
bulletin is being increased to include airplanes beyond the effectivity of the initial release. Also, installing a
Boeing-built mechanism is no longer terminating action to the repeat inspections.
ACTION
Remove the seal plate and lower hinge cover to gain access to the elevator tab control mechanism (mechanism)
and do a detailed inspection of the aft attach lugs (lugs). Look for rotation of the spacer. Also, use a feeler gage
to check for any gaps at certain locations. If there is a gap or a loose spacer, then replace the mechanism per
the AMM and this SB. If there is no gap or a loose spacer, then return the airplane to a serviceable condition .
Do repeat inspections of the mechanism at the times shown in paragraph 1.E., compliance.
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EFFECTIVITY
737-600, -700, -700C, -800, -900, and -900ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of
affected airplanes.
COMPLIANCE
Refer to Paragraph 1.E., Compliance.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-09-05 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for 737 airplanes in warranty as of March 11, 2010. Please refer to
Paragraph 2.B., Industry Support Information.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
None.
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BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
FWO
DO A DETAILED
INSPECTION OF THE
ELEVATOR TAB
CONTROL MECHANISM
AFT LUGS
SURROUNDING STRUCTURE NOT SHOWN FOR CLARITY  1975845
Original Issue: April 16, 2010
Revision 1: August 02, 2010  737-27A1297
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-27A1297
Original Issue: April 16, 2010
Revision 1: August 02, 2010
ATA System: 2731
SUBJECT: FLIGHT CONTROLS - Elevator Tab Control Mechanism Detailed Inspection
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
NOTE: This service bulletin is for the airplanes identified below. The effectivity list shown below
is complete for airplanes through line number 3554. At least one airplane after line number
3554 is also affected by this service bulletin, and these airplanes are in Group(s) 2. These
airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) \"get effectivity\"
result when they are added to the MBF Fleet Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes Line Number 2508 to 2707-1
Airplanes Line Number 2708 and on-2
Airplanes Line Number 1 to 2507-3
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
3YA001 - YA099
3YA101 - YA199
3YA201 - YA211
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GroupVariable Number
3YA221
3YA231 - YA242
3YA251 - YA256
3YA271 - YA272
3YA291
3YA301 - YA302
3YA311 - YA314
3YA321 - YA323
3YA336 - YA345
3YA351
3YA356 - YA357
3YA366 - YA367
3YA371 - YA377
3YA501 - YA536
3YA541 - YA552
3YA571 - YA578
3YA601 - YA615
3YA621 - YA622
3YA626 - YA631
3YA635 - YA636
3YA641 - YA642
3YA645 - YA650
3YA656 - YA659
3YA666 - YA667
3YA671 - YA672
3YA681 - YA691
3YA701 - YA710
3YA721 - YA722
3YA731 - YA734
3YA751 - YA756
3YA801 - YA803
3YA809
3YA811 - YA814
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GroupVariable Number
3YA831 - YA835
3YA841 - YA862
3YA881 - YA882
3YA891 - YA892
3YA961 - YA978
3YB001 - YB006
3YB101 - YB132
3YB151 - YB153
3YB156 - YB158
3YB161 - YB164
3YB171 - YB172
3YB181 - YB184
3YB201 - YB208
3YB271
3YB276
3YB301 - YB310
3YB371 - YB392
3YB501 - YB502
3YB521 - YB526
3YB541 - YB544
3YB551
3YB561 - YB598
3YB601 - YB632
2YB633 - YB635
3YB651
3YB656
3YB671 - YB672
3YB851 - YB863
3YB871 - YB874
3YB881 - YB893
3YB901 - YB903
3YB911
3YB961 - YB973
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GroupVariable Number
1YB974
2YB975
2YB981
1YB986 - YB987
2YB988 - YB996
3YC001 - YC030
3YC051 - YC084
3YC091 - YC094
2YC095
3YC101 - YC104
3YC111 - YC113
3YC121
3YC126 - YC127
3YC136 - YC141
3YC146 - YC147
3YC151 - YC156
3YC166 - YC171
3YC176 - YC179
3YC186 - YC190
3YC201 - YC203
3YC206 - YC207
3YC301 - YC305
3YC321 - YC387
3YC391 - YC394
3YC396
3YC401 - YC417
3YC421 - YC422
3YC426 - YC428
3YC436 - YC439
3YC441 - YC448
3YC451 - YC455
3YC459
3YC461 - YC467
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GroupVariable Number
3YC471 - YC499
3YC501 - YC526
3YC571 - YC583
3YC587 - YC589
3YC591 - YC593
3YC601 - YC655
3YC681 - YC696
3YC701 - YC715
3YC720 - YC725
3YC727 - YC752
3YC761 - YC770
3YC781 - YC793
3YC801 - YC892
3YC901 - YC907
3YC921 - YC922
3YC931 - YC932
3YC941 - YC951
3YC971 - YC978
3YC981 - YC983
3YD001 - YD007
3YD021 - YD025
3YD041 - YD057
3YD081 - YD084
3YD101 - YD110
2YD111 - YD113
3YD121 - YD126
3YD151 - YD159
3YD171 - YD172
3YD201 - YD203
3YD206 - YD209
3YD216 - YD219
3YD251 - YD254
3YD256 - YD257
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GroupVariable Number
3YD261
3YD301 - YD334
3YD391
3YD401 - YD410
3YD412 - YD414
1YD415
2YD416 - YD417
3YD481 - YD485
3YD491 - YD499
3YD501 - YD512
3YD531 - YD535
3YD541 - YD547
3YD561 - YD564
3YD571 - YD572
3YD591 - YD595
3YD601 - YD612
3YD651 - YD655
3YE001 - YE020
3YE051
3YE101 - YE109
3YE151 - YE157
3YE171 - YE172
3YE201 - YE206
3YE301 - YE305
3YE321 - YE326
3YE371 - YE383
1YF001
2YF002 - YF011
1YF021 - YF026
2YF027 - YF049
1YF051 - YF052
2YF053 - YF065
1YF086
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GroupVariable Number
2YF087
3YF106 - YF107
3YF111
2YF112 - YF114
2YF116 - YF119
2YF121 - YF128
1YF176 - YF178
2YF191 - YF192
2YF201 - YF276
2YF401 - YF402
2YF431 - YF432
2YF441 - YF442
2YF451 - YF460
2YF501 - YF599
2YF601 - YF605
2YF701 - YF707
2YF801 - YF803
2YF831 - YF832
2YF836 - YF838
2YF901 - YF905
2YF921 - YF927
2YF951
3YG001 - YG044
3YG061 - YG064
3YG066 - YG089
3YG091 - YG099
3YG101 - YG103
2YG104
3YG111 - YG114
3YG116 - YG119
1YG120
2YG121 - YG128
3YG201 - YG205
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GroupVariable Number
3YG211 - YG214
2YG221 - YG224
3YG251 - YG252
3YG501 - YG509
2YG510 - YG511
3YG601 - YG602
3YG701
1YG711
3YH001 - YH010
1YH011 - YH012
2YH031 - YH050
3YH051 - YH052
1YH053 - YH054
2YH055
2YH071 - YH078
3YH101 - YH102
1YH103 - YH115
2YH116 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301
2YH302 - YH306
2YH321 - YH322
3YJ001 - YJ008
1YJ009 - YJ010
3YJ011 - YJ013
3YJ021
3YJ471 - YJ480
3YJ501 - YJ517
3YJ531 - YJ559
1YJ560 - YJ566
2YJ567 - YJ579
3YJ591 - YJ596
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GroupVariable Number
1YJ597
2YJ598 - YJ599
3YJ631 - YJ632
3YJ671 - YJ694
3YJ801 - YJ867
3YJ871 - YJ873
1YJ874 - YJ875
2YJ876 - YJ880
3YJ901 - YJ903
1YJ904
1YJ908
2YJ909 - YJ910
3YJ911 - YJ929
3YJ931 - YJ937
3YJ941 - YJ956
2YJ961
3YJ976 - YJ977
3YK001 - YK007
3YK101 - YK104
3YK111 - YK112
3YK121 - YK122
3YK131 - YK132
1YK133
3YK136 - YK139
3YK141 - YK142
3YK146 - YK148
3YK151 - YK154
3YK161 - YK166
1YK167
3YK171
1YK176
2YK177
2YK186
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GroupVariable Number
2YK191
2YK196
2YK201 - YK202
3YK301 - YK308
1YK309
2YK310 - YK314
3YK321 - YK336
1YK337 - YK338
2YK339 - YK340
3YK361 - YK372
1YK373 - YK375
2YK376 - YK378
3YK401 - YK406
3YK426 - YK427
3YK431 - YK450
3YK456 - YK460
2YK461 - YK467
2YK471 - YK473
3YK476
3YK480 - YK485
2YK486 - YK487
2YK491
1YK495
2YK496 - YK498
3YK511 - YK516
1YK521 - YK523
2YK524 - YK530
3YK551 - YK565
1YK566 - YK569
2YK570
3YK571
3YK576 - YK577
3YK580 - YK585
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GroupVariable Number
3YK601 - YK602
3YK606 - YK607
3YK611 - YK614
1YK615 - YK616
3YK621 - YK625
1YK626 - YK627
2YK628 - YK630
3YK631 - YK634
3YK641 - YK644
3YK651 - YK660
1YK661
2YK662 - YK665
1YK671
2YK672
2YK676 - YK677
2YK681 - YK686
2YK691
3YK701 - YK709
1YK710 - YK712
2YK713
3YK716 - YK719
3YK721 - YK741
3YK751 - YK756
1YK757 - YK760
2YK761 - YK770
2YK776 - YK778
2YK781 - YK785
3YK791 - YK792
3YK796 - YK797
3YK801 - YK870
1YK871 - YK887
2YK888 - YK899
3YK901 - YK910
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GroupVariable Number
1YK911
2YK912
3YK918
2YK919
3YK921 - YK923
1YK924 - YK927
2YK928
3YK941 - YK950
1YK951 - YK952
2YK953 - YK959
3YK961 - YK971
2YK972 - YK980
3YK981 - YK984
1YK985
2YK986 - YK996
3YL001 - YL005
3YL011 - YL016
3YL021 - YL024
3YL051 - YL052
3YL056 - YL057
3YL061
3YL066 - YL069
3YL076 - YL077
3YL101 - YL109
1YL110 - YL116
2YL117 - YL136
3YL201 - YL205
1YL206 - YL209
2YL210 - YL226
3YL271 - YL272
3YL281 - YL282
2YL283 - YL284
3YL301 - YL303
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GroupVariable Number
3YL311 - YL312
2YL313 - YL314
1YL316 - YL319
2YL320 - YL321
2YL351 - YL353
1YL371 - YL373
2YL374
2YL401
3YL421 - YL425
1YL426
2YL427 - YL429
3YL431 - YL437
2YL438 - YL444
3YL461 - YL471
1YL472 - YL473
2YL474 - YL478
3YL501 - YL503
1YL504 - YL505
2YL506 - YL509
3YL531
1YL532 - YL533
2YL534
2YL541 - YL544
3YL561
1YL562 - YL565
2YL566 - YL569
1YL591 - YL592
2YL593 - YL598
3YL601 - YL604
1YL605 - YL606
1YL611
2YL612
1YL616
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GroupVariable Number
2YL617
1YL621
2YL626
2YL631 - YL634
2YL636 - YL637
1YL661 - YL664
2YL676 - YL681
2YL691
2YL696 - YL697
2YL701 - YL706
2YL731
2YL751 - YL752
2YL756 - YL757
2YL761 - YL779
2YL796 - YL797
2YL801 - YL815
3YL901 - YL903
1YL904 - YL907
2YL908 - YL910
2YL921 - YL930
3YL931 - YL932
2YL933 - YL940
1YL951 - YL952
2YL953 - YL968
3YM101 - YM103
3YM201 - YM231
1YM232 - YM238
2YM239 - YM242
3YM251 - YM299
3YM301 - YM353
1YM354 - YM374
2YM375 - YM398
3YM471
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GroupVariable Number
3YM481 - YM484
3YM501 - YM515
3YM521 - YM522
3YM541
3YM551 - YM553
3YM571 - YM572
3YM581 - YM582
3YM591 - YM593
2YM594 - YM599
3YM631 - YM634
3YM641 - YM646
1YM647 - YM651
2YM652
3YM671 - YM672
2YM673 - YM674
1YM691 - YM692
2YM693 - YM698
1YM701 - YM702
2YM703 - YM710
2YM761 - YM765
3YN001 - YN014
1YN015 - YN016
3YN021 - YN023
1YN024
3YN061
3YN071 - YN079
2YN080 - YN082
3YN091 - YN092
3YN101 - YN112
3YN121
3YN201
2YN202
3YN211 - YN214
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GroupVariable Number
1YN215 - YN216
2YN217 - YN219
3YN231
1YN232
2YN233 - YN236
2YN261
2YQ001 - YQ003
2YQ011 - YQ018
2YQ026 - YQ027
2YQ036 - YQ042
2YQ201
2YQ231
2YQ241 - YQ242
2YQ291 - YQ295
2YQ401 - YQ403
2YR001 - YR005
2YR051 - YR053
2YR101
2YR111 - YR113
2YR126
2YR166
2YR201 - YR203
2YR231 - YR233
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
An operator experienced a vibration event 21 days after performing inspections on the swage ring and
spacer on the elevator tab control mechanism (mechanism) in accordance with Service Bulletin (SB)
737-27A1296. Investigation revealed that the vibration was most likely caused by the same conditions
that Service Bulletin 737-27A1296 was meant to detect, but did not. For the most critical group of
airplanes, this service bulletin does a more enhanced inspection than the inspection in SB 737-27A1296
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and continues with repeat inspections. The more enhanced inspection includes using a feeler gage at
specific locations to check for gaps. The inspections in this SB will detect a loose bearing in the aft
attach lugs of the elevator tab control mechanism. A loose bearing in the aft attach lug of the elevator
tab control mechanism could lead to unwanted elevator tab freeplay and then elevator tab vibration
which could lead to structural failure of the elevator or the horizontal stabilizer.
Since the initial release of this service bulletin, several operators have reported gaps in Boeing-built
mechanisms, but no loose bearings. Also, additional analysis by Boeing has shown that non-Boeing
built mechanisms built after Line Number 2708 may have bearings which will come loose. Because of
this, the effectivity of this service bulletin is being increased to include airplanes beyond the effectivity
of the initial release. Also, installing a Boeing-built mechanism is no longer terminating action to the
repeat inspections.
This revision is sent to: add new Group 3 airplanes to the effectivity and add an inspection and
compliance for Group 3 airplanes; add airplanes to existing Group 2 effectivity and change the
compliance for Group 2 airplanes; remove the terminating action from the compliance; change the
inspection method; delete Figure 7, "Determining if Replacement Mechanism is not Boeing Built" and
all associated steps in the Work Instructions; provide manpower estimates; add warranty information;
add convenience kit information.
The data given in Information Notices 737-27A1297 IN 01, IN 02 and IN 03 is included in this revision,
as applicable.
D. Description
Remove the seal plate and lower hinge cover to gain access to the elevator tab control mechanism
(mechanism) and do a detailed inspection of the aft attach lugs (lugs). Look for rotation of the spacer.
Also, use a feeler gage to check for any gaps at certain locations. If there is a gap or a loose spacer,
then replace the mechanism per the AMM and this SB. If there is no gap or a loose spacer, then return
the airplane to a serviceable condition .
Do repeat inspections of the mechanism at the times shown in paragraph 1.E., compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1-2:
Affected Maintenance Zones
ZoneModel
333, 334, 343, 344737-700, 737-700C, 737-800,
737-900ER
Group 3:
Affected Maintenance Zones
ZoneModel
333, 334, 343, 344737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
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E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2010-09-05 is related to this service
bulletin.
Table 1: ELEVATOR TAB CONTROL MECHANISM INSPECTION - LEFT SIDE
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
300 flight hours-Within 30 days
after the Revi-
sion 1 date of
this service bul-
letin or within
300 flight hours
from the previ-
ous repeat in-
spection per-
formed in accor-
dance with the
original issue of
the service bul-
letin, whichever
occurs later.
Do a detailed inspection
of the mechanism in ac-
cordance with Step 2 of
paragraph 3.B., Work In-
structions. (a)
Group 1
300 flight hoursWithin 14 days
after the Revi-
sion 1 date of
this service bul-
letin.
Within 2,000 To-
tal Flight Cycles
or 4,000 Total
Flight Hours,
whichever oc-
curs first.
Do a detailed inspection
of the elevator tab control
mechanism in accor-
dance with Step 2 of
paragraph 3.B., Work In-
structions
Group 2
1,800 flight hours.-Within 180 days
or 1,800 flight
hours after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs first.
Do a detailed inspection
of the elevator tab control
mechanism in accor-
dance with Step 2 of
paragraph 3.B., Work In-
structions
Group 3
300 flight hours if
mechanism is re-
placed due to a
finding of a dis-
crepant mecha-
nism.
-Before further flightReplace the elevator tab
control mechanism and
do detailed inspection
before and after installing
it, in accordance with
Step 7 of paragraph 3.B.,
Work Instructions
All:
Elevator tab control mecha-
nism is found to be dis-
crepant
OR
Replacement elevator tab
control mechanism is found
to be discrepant.
(a) For Group 1 airplanes doing repeat inspection in accordance with the original issue of this service bulletin:
It is acceptable to do the initial inspection using the inspection in the original issue of this service bulletin.
However, the first repeat inspection and all following repeat inspections must use the Revision 1 inspection.
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Table 2: ELEVATOR TAB CONTROL MECHANISM INSPECTION - RIGHT SIDE
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
300 flight hours-Within 30 days
after the Revi-
sion 1 date of
this service bul-
letin or within
300 flight hours
from the previ-
ous repeat in-
spection per-
formed in accor-
dance with the
original issue of
the service bul-
letin, whichever
occurs later.
Do a detailed inspection
of the mechanism in ac-
cordance with Step 5 of
paragraph 3.B., Work In-
structions. (a)
Group 1
300 flight hoursWithin 14 days
after the Revi-
sion 1 date of
this service bul-
letin.
Within 2,000 To-
tal Flight Cycles
or 4,000 Total
Flight Hours,
whichever oc-
curs first.
Do a detailed inspection
of the elevator tab control
mechanism in accor-
dance with Step 5 of
paragraph 3.B., Work In-
structions
Group 2
1,800 flight hours.-Within 180 days
or 1,800 flight
hours after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs first.
Do a detailed inspection
of the elevator tab control
mechanism in accor-
dance with Step 5 of
paragraph 3.B., Work In-
structions
Group 3
300 flight hours if
mechanism is re-
placed due to a
finding of a dis-
crepant mecha-
nism.
-Before further flightReplace the elevator tab
control mechanism and
do detailed inspection
before and after installing
it, in accordance with
Step 8 of paragraph 3.B.,
Work Instructions
All:
Elevator tab control mecha-
nism is found to be dis-
crepant
OR
Replacement elevator tab
control mechanism is found
to be discrepant.
(a) For Group 1 airplanes doing repeat inspection in accordance with the original issue of this service bulletin:
It is acceptable to do the initial inspection using the inspection in the original issue of this service bulletin.
However, the first repeat inspection and all following repeat inspections must use the Revision 1 inspection.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
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), (m), (n), (o), (p), and (q) of AD 2010-09-05. All provisions of AD 2010-09-05 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 this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
INSPECT LEFT SIDE
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
1.001.001Figure 1
0.750.751Figure 2
0.750.751Figure 3
0.500.501Close Access
3.503.50TOTAL FOR EACH AIR-
PLANE
INSPECT RIGHT SIDE
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
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INSPECT RIGHT SIDE
Elapsed HoursTask HoursNumber of PersonsTask
1.001.001Figure 4
0.750.751Figure 5
0.750.751Figure 6
0.500.501Close Access
3.503.50TOTAL FOR EACH AIR-
PLANE
REPLACE MECHANISM LEFT SIDE
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Remove Mechanism
0.750.751Figure 2
0.750.751Figure 3
1.501.501Install Mechanism
1.501.501Inspect
0.250.251Part Mark
1.002.002Functional Test
(a)(a)2Flight Test
7.258.25TOTAL FOR EACH AIR-
PLANE
(a) Flight test hours not included in estimate.
REPLACE MECHANISM RIGHT SIDE
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Remove Mechanism
0.750.751Figure 5
0.750.751Figure 6
1.501.501Install Mechanism
1.501.501Inspect
0.250.251Part Mark
1.002.002Functional Test
(a)(a)2Flight Test
7.258.25TOTAL FOR EACH AIR-
PLANE
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REPLACE MECHANISM RIGHT SIDE
(a) Flight test hours not included in estimate.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Boeing Service Bulletin 737-27A1296
b. Federal Aviation Administration (FAA) Airworthiness Directive 2010-09-05
c. Standard Overhaul Practices Manual (SOPM) 20-50-10
d. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 27-31-00, 27-31-34
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
No kit is necessary to do this service bulletin. However, a convenience topkit is available from Boeing
that contains the hardware required to install an elevator tab control mechanism on the left and right
side of the airplane. Refer to paragraph 2.C., Parts Necessary For Each Airplane.
The Boeing price data shown below is given for planning purposes. Supply data can be given if
requested.
Unit Price thru 31-
Jul-2011
NameKit Number
$7,285.00Kit - Elevator Tab Mechanism002A0001-100
The kit is 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
B. Industry Support Information
Boeing warranty remedies are available for 737 NG airplanes in warranty as of March 11, 2010. For
inspection labor hours reimbursement for airplanes in warranty as of that date, send a warranty claim
to Boeing Product Assurance Contracts. If the condition described in this service bulletin is found during
the inspection for airplanes in warranty as of that date, send parts to Boeing in accordance with the
Service Bulletin and associated FAA AD. If needed, exchange units are available for purchase through
Boeing Spares. Please send claims for airplanes in warranty as of March 11, 2010, to Boeing Warranty
& Product Assurance Contracts.
C. Parts Necessary For Each Airplane
1. Kits/Parts
None, however a convenience topkit is available from Boeing that contains the hardware required
to install an elevator tab control mechanism on the left and right side of the airplane:
002A0001-100 KIT - ELEVATOR TAB MECHANISM
QTY
KIT - ELEVATOR TAB MECHANISM - HANGAR JOINT002A0001-1012
KIT - ELEVATOR TAB MECHANISM - LUG ATTACH JOINT002A0001-1022
KIT - ELEVATOR TAB MECHANISM - FWD TAB ROD ATTACH
JOINT
002A0001-1032
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KIT - ELEVATOR TAB MECHANISM - AFT TAB ROD ATTACH
JOINT
002A0001-1042
2. Parts and Materials Supplied by the Operator
NotesExisting Part NumberNameQTYPart Number /
Specification
-251A2430-15 or -17Elevator Tab Control Mechanism -
Left
1251A2430-15 or -
17
-251A2430-16 or -18Elevator Tab Control Mechanism -
Right
1251A2430-16 or -
18
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
.
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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. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. Use the approved fastener and process material substitutions in accordance with
737 SRM 51. Alternate fasteners are listed in 737 SRM 51 and Boeing Drawing
65-88700.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in 737 SRM 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards in 737
SRM 51 may be used.
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 access procedures may be required.
7. 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.
8. 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.
B. WORK INSTRUCTIONS
1. OPEN ACCESS - LEFT SIDE:
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a. Remove pressure from the elevator hydraulic systems A and B. Refer to 737-600/700/800/900
AMM 27-31-00 as an accepted procedure.
b. Gain access by removing the seal plate and hinge lower cover in accordance with Figure 1.
c. Put the horizontal stabilizer in a neutral position:
(1) Supply electrical power. Refer to 737-600/700/800/900 AMM 24-22-00 as an accepted
procedure.
(2) Make sure that these circuit breakers are closed:
F/O Electrical System Panel, P6-2
NameNumberColRow
FLIGHT CONTROL STAB TRIM CONTC0020710B
FLIGHT CONTROL STAB TRIM ACTUATORC0084010D
(3) Make sure that the main cutout switch, S272 is in the NORMAL position.
(4) Make sure that the STAB TRIM switch on the stab trim and cabin door panel, P8-47 is
in the NORMAL position.
(5) Make sure that the flaps are in the full up position.
(6) Move the stabilizer to 4 units +/- .5
d. Put the elevator into a neutral position:
(1) Using hand pressure, move the elevator until it is within 2 inches of the index mark
mounted on the side of the tailcone.
2. DETAILED INSPECTION - LEFT SIDE:
a. For the inboard aft attach lug of the elevator tab control mechanism (mechanism), use a feeler
gage and finger pressure to do a detailed inspection in accordance with Figure 2 and determine
if the elevator tab control mechanism is discrepant. While doing the inspection, apply inboard
and outboard hand pressure to the elevator tab control mechanism in accordance with Figure
2.
For the outboard aft attach lug of the elevator tab control mechanism, use a feeler gage and
finger pressure to do a detailed inspection in accordance with Figure 3 and determine if the
elevator tab control mechanism is discrepant. While doing the inspection, apply inboard and
outboard hand pressure to the elevator tab control mechanism in accordance with Figure 3.
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(1) Spacer: If the spacer moves or rotates, then the mechanism is discrepant
(2) Swage Ring to Lug interface: Make sure that there is no gap between the swage ring and
the outer face of the aft attach lug such that a 0.005 inch feeler gage can be inserted
more than 0.025 inch. If there is such a gap, then then the elevator tab control mechanism
is discrepant.
(3) Lug to Lug interface: Make sure that there is no gap between the two nested lugs such
that a 0.005 inch feeler gage can be inserted more than 0.16 inch. If there is such a gap,
then the elevator tab control mechanism is discrepant.
(4) Lug to Spacer interface: Make sure that there is no gap between the inner face of the aft
attach lug and the spacer such that a 0.005 inch feeler gage can be inserted more than
0.16 inch. If there is such a gap, then the elevator tab control mechanism is discrepant.
b. If the elevator tab control mechanism is discrepant, then replace it in accordance with Step
3.B.7.
3. CLOSE ACCESS - LEFT SIDE:
a. Reinstall the hinge lower cover and the seal plate in accordance with Figure 1.
b. Restore pressure to the elevator hydraulic systems A and B. Refer to 737-600/700/800/900
AMM 27-31-00 as an accepted procedure. If continuing with inspection of the right side, this
step can be skipped.
4. OPEN ACCESS - RIGHT SIDE
a. If not already done, remove pressure from the elevator hydraulic systems A and B. Refer to
737-600/700/800/900 AMM 27-31-00 as an accepted procedure.
b. Gain access by removing the seal plate and hinge lower cover in accordance with Figure 4.
c. If not already done, put the horizontal stabilizer in a neutral position:
(1) Supply electrical power. Refer to 737-600/700/800/900 AMM 24-22-00 as an accepted
procedure.
(2) Make sure that these circuit breakers are closed:
F/O Electrical System Panel, P6-2
NameNumberColRow
FLIGHT CONTROL STAB TRIM CONTC0020710B
FLIGHT CONTROL STAB TRIM ACTUATORC0084010D
(3) Make sure that the main cutout switch, S272 is in the NORMAL position.
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### Page 38

(4) Make sure that the STAB TRIM switch on the stab trim and cabin door panel, P8-47 is
in the NORMAL position.
(5) Make sure that the flaps are in the full up position.
(6) Move the stabilizer to 4 units +/- 0 .5
d. If not already done, put the elevator in a neutral position:
(1) Using hand pressure, move the elevator until it is within 2 inches of the index mark
mounted on the side of the tailcone.
5. DETAILED INSPECTION - RIGHT SIDE:
a. For the inboard aft attach lug of the elevator tab control mechanism (mechanism), use a feeler
gage and finger pressure to do a detailed inspection in accordance with Figure 5 and determine
if the elevator tab control mechanism is discrepant. While doing the inspection, apply inboard
and outboard hand pressure to the elevator tab control mechanism in accordance with Figure
5.
For the outboard aft attach lug of the elevator tab control mechanism, use a feeler gage and
finger pressure to do a detailed inspection in accordance with Figure 6 and determine if the
elevator tab control mechanism is discrepant. While doing the inspection, apply inboard and
outboard hand pressure to the elevator tab control mechanism in accordance with Figure 6.
(1) Spacer: If the spacer moves or rotates, then the mechanism is discrepant
(2) Swage Ring to Lug interface: Make sure that there is no gap between the swage ring and
the outer face of the aft attach lug such that a 0.005 inch feeler gage can be inserted
more than 0.025 inch. If there is such a gap, then then the elevator tab control mechanism
is discrepant.
(3) Lug to Lug interface: Make sure that there is no gap between the two nested lugs such
that a 0.005 inch feeler gage can be inserted more than 0.16 inch. If there is such a gap,
then the elevator tab control mechanism is discrepant.
(4) Lug to Spacer interface: Make sure that there is no gap between the inner face of the aft
attach lug and the spacer such that a 0.005 inch feeler gage can be inserted more than
0.16 inch. If there is such a gap, then the elevator tab control mechanism is discrepant.
b. If the elevator tab control mechanism is discrepant, then replace it in accordance with Step
3.B.8.
6. CLOSE ACCESS - RIGHT SIDE
a. Reinstall the hinge lower cover and the seal plate in accordance with Figure 4.
b. Restore pressure to the elevator hydraulic systems A and B. Refer to 737-600/700/800/900
AMM 27-31-00 as an accepted procedure.
7. REPLACEMENT OF A MECHANISM- LEFT SIDE
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### Page 39

WARNING: WHEN INSTALLING THE PINS TO CONNECT THE ELEVATOR TAB CONTROL
MECHANISM TO THE ELEVATOR, MAKE SURE YOU DON'T DAMAGE THE LUGS
OR THE BEARINGS. IF A LUG OR BEARING IS DAMAGED, THEN IT COULD
LEAD TO UNWANTED ELEVATOR TAB FREEPLAY AND THEN ELEVATOR TAB
VIBRATION WHICH COULD LEAD TO STRUCTURAL FAILURE OF THE
ELEVATOR OR THE HORIZONTAL STABILIZER.
a. Gain access as required and remove the elevator tab control mechanism (mechanism). Refer
to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
b. Replace the elevator tab control mechanism as follows:
(1) Before you install the replacement mechanism, do the following inspection:
(a) For the inboard attach lug of the elevator tab control mechanism, use a feeler gage
and finger pressure to do a detailed inspection in accordance with Figure 2, except
as noted below, and determine if the replacement mechanism is discrepant.
For the outboard attach lug of the elevator tab control mechanism, use a feeler gage
and finger pressure to do a detailed inspection in accordance with Figure 3, except
as noted below, and determine if the replacement mechanism is discrepant.
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### Page 40

NOTE: Figures 2 and 3 show the detailed inspection being done on an elevator
tab control mechanism that is installed. If a replacement mechanism is being
inspected before it is installed, then:
– Do not apply force as shown in the figures or as discussed in the figure
notes,
– These figures will not show what the mechanic will see when doing the
inspection, but this is OK.
1) Spacer: If the spacer moves or rotates, then the replacement mechanism is
discrepant
2) Swage Ring to Lug interface: Make sure that there is no gap between the swage
ring and the outer face of the aft attach lug such that a 0.005 inch feeler gage
can be inserted more than 0.025 inch. If there is such a gap, then then the
replacement mechanism is discrepant.
3) Lug to Lug interface: Make sure that there is no gap between the two nested
lugs such that a 0.005 inch feeler gage can be inserted more than 0.16 inch. If
there is such a gap, then the replacement mechanism is discrepant.
4) Lug to Spacer interface: Make sure that there is no gap between the inner face
of the aft attach lug and the spacer such that a 0.005 inch feeler gage can be
inserted more than 0.16 inch. If there is such a gap, then the replacement
mechanism is discrepant.
(b) If the replacement mechanism is discrepant, then it cannot be installed.
(2) Install the replacement mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an
accepted procedure.
(3) After you install the replacement mechanism, do a detailed inspection of the elevator tab
control mechanism in accordance with Step 3.B.2.
c. Close access as required. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted
procedure.
d. Functional tests and a manual reversion flight test of the airplane are required when an elevator
tab control mechanism is replaced. Refer to 737-600/700/800/900 AMM 27-31-00 and
737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
8. REPLACEMENT OF A MECHANISM - RIGHT SIDE
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ALERTALERT

### Page 41

WARNING: WHEN INSTALLING THE PINS TO CONNECT THE ELEVATOR TAB CONTROL
MECHANISM TO THE ELEVATOR, MAKE SURE YOU DON'T DAMAGE THE LUGS
OR THE BEARINGS. IF A LUG OR BEARING IS DAMAGED, THEN IT COULD
LEAD TO UNWANTED ELEVATOR TAB FREEPLAY AND THEN ELEVATOR TAB
VIBRATION WHICH COULD LEAD TO STRUCTURAL FAILURE OF THE
ELEVATOR OR THE HORIZONTAL STABILIZER.
a. Gain access as required and remove the elevator tab control mechanism (mechanism). Refer
to 737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
b. Replace the elevator tab control mechanism as follows:
(1) Before you install the replacement mechanism, do the following inspection:
(a) For the inboard attach lug of the elevator tab control mechanism, use a feeler gage
and finger pressure to do a detailed inspection in accordance with Figure 5, except
as noted below, and determine if the replacement mechanism is discrepant.
For the outboard attach lug of the elevator tab control mechanism, use a feeler gage
and finger pressure to do a detailed inspection in accordance with Figure 6, except
as noted below, and determine if the replacement mechanism is discrepant.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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ALERTALERT

### Page 42

NOTE: Figures 5 and 6 show the detailed inspection being done on an elevator
tab control mechanism that is installed. If a replacement mechanism is being
inspected before it is installed, then:
– Do not apply force as shown in the figures or as discussed in the figure
notes,
– These figures will not show what the mechanic will see when doing the
inspection, but this is OK.
1) Spacer: If the spacer moves or rotates, then the replacement mechanism is
discrepant
2) Swage Ring to Lug interface: Make sure that there is no gap between the swage
ring and the outer face of the aft attach lug such that a 0.005 inch feeler gage
can be inserted more than 0.025 inch. If there is such a gap, then then the
replacement mechanism is discrepant.
3) Lug to Lug interface: Make sure that there is no gap between the two nested
lugs such that a 0.005 inch feeler gage can be inserted more than 0.16 inch. If
there is such a gap, then the replacement mechanism is discrepant.
4) Lug to Spacer interface: Make sure that there is no gap between the inner face
of the aft attach lug and the spacer such that a 0.005 inch feeler gage can be
inserted more than 0.16 inch. If there is such a gap, then the replacement
mechanism is discrepant.
(b) If the replacement mechanism is discrepant, then it cannot be installed.
(2) Install the replacement mechanism. Refer to 737-600/700/800/900 AMM 27-31-34 as an
accepted procedure.
(3) After you install the replacement mechanism, do a detailed inspection of the elevator tab
control mechanism in accordance with Step 3.B.5.
c. Close access as required. Refer to 737-600/700/800/900 AMM 27-31-34 as an accepted
procedure.
d. Functional tests and a manual reversion flight test of the airplane are required when an elevator
tab control mechanism is replaced. Refer to 737-600/700/800/900 AMM 27-31-00 and
737-600/700/800/900 AMM 27-31-34 as an accepted procedure.
9. Report all initial inspection findings to Boeing and report all discrepant mechanism findings from
a repeat inspection to Boeing. Identify the airplane and give the total flight hours and flight cycles
of the airplane. If there is damage, give the extent of the damage. Send your report to:
BOEING COMMERCIAL AIRPLANES GROUP
ATTENTION: MANAGER, AIRLINE SUPPORT
Email: rse.boecom@boeing.com
10. Send all removed elevator tab control mechanisms to:
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### Page 43

Spares Distribution Center
Repair Overhaul and Exchange Services, SSA 111
Boeing Commercial Airplane Group
2201 South 142nd, Door W10
Seatac, Washington USA 98168
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
1000004
a
ELEVATOR
HINGE LOWER  FWD
COVER
SEAL PLATE U
LEFT SHOWN
(ELEVATOR TAB CONTROL MECHANISM NOT SHOWN FOR CLARITY)
1972937
FIGURE 1: ACCESS PANEL REMOVAL & INSTALLATION - LEFT SIDE
(SHEET 1 OF 2)
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### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-seal plateRemove / Keep1
1-elevator hinge lower
cover
Remove / Keep2
1-elevator hinge lower
cover
Install (Kept)3
1-seal plateInstall (Kept)4
FIGURE 1: ACCESS PANEL REMOVAL & INSTALLATION - LEFT SIDE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
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ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
OUTER FACE OF LUG
FWD
INNER FACE OF LUG
PANEL 333ВВ SHOWN REMOVED FOR CLARITY  1972940
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE
(SHEET 1 OF 5)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
(2) SPACER
5) LUG/SPACER
INTERFACE
D
(4) LUG/LUG INTERFACE
FWD  3) SWAGE RING/LUG  INTERFACE
OUTER FACE OF LUG  1975812
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE
(SHEET 2 OF 5)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
SPACER (2
LUG/LUG
INTERFACE
LUG/SPACER
INTERFACE
FWD
INNER FACE OF LUG  1975811
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE
(SHEET 3 OF 5)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
CENTER OF BEARING
CENTER OF  20°-
BEARING  ALLOWABLE
OUTER LIMITS OF
CENTERLINE OF
FEELER GAGE
DEPTH OF
FEELER
GAGE
SWAGE
RING
LUG
CENTER OF FEELER GAGE,
RADIAL TO CENTER OF THE
BEARING
FEELER GAGE DEPTH MEASUREMENT  2006152
FOR SWAGE RING/LUG INTERFACE SHOWN, OTHER
INTERFACES SIMILAR
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE
(SHEET 4 OF 5)
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### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
CAUTION: DO NOT APPLY FORCE WITH ANYTHING OTHER THAN YOUR HAND. DO NOT APPLY
EXCESSIVE FORCE OR YOU MAY DAMAGE THE ELEVATOR TAB CONTROL MECHANISM
LUGS OR BEARINGS. A BENT LUG OR LOOSE BEARING COULD LEAD TO UNWANTED
ELEVATOR TAB FREEPLAY AND THEN TAB VIBRATION WHICH COULD LEAD TO
STRUCTURAL FAILURE OF THE ELEVATOR OR THE HORIZONTAL STABILIZER.
Using hand pres-
sure, apply force to
the mechanism alter-
nating between the
inboard and out-
board direction while
doing the inspec-
tions in the following
steps. The force can
be applied at any lo-
cation on the mecha-
nism, but no more
than four inches for-
ward of the elevator
front spar.
--forceApply1
(b)1-spacerInspect2
(a) If there is sealant
in the interface, do
not remove it.
1-swage ring/lug interfaceInspect3
(c) If there is sealant
in the interface, do
not remove it.
1-lug/lug interfaceInspect4
(c) If there is sealant
in the interface, do
not remove it.
1-lug/spacer interfaceInspect5
(a) Using a feeler gage, make sure that there is no gap between the swage ring and the outer face of the lug
such that a 0.005 inch feeler gage can be inserted more than 0.025 inch. Do the inspection at a single
location between the allowable outer limits defined in Detail D.  Apply force to the mechanism alternating
between the inboard and outboard direction as you use the feeler gage.
(b) As you apply force to the mechanism alternating between the inboard and outboard direction, use finger
pressure and try to rotate the spacer.
(c) Using a feeler gage, Make sure that there is no gap between the two nested lugs or between the inner
face of the lug and the spacer such that a 0.005 inch feeler gage can be inserted more than 0.16 inch.
Do the inspection at a single location between the allowable outer limits defined in Detail D.  Apply force
to the mechanism alternating between the inboard and outboard direction as you use the feeler gage.
FIGURE 2: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - LEFT SIDE
(SHEET 5 OF 5)
BOEING PROPRIETARY -
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Original Issue: April 16, 2010
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BOEING SERVICE BULLETIN 737-27A1297
ALERTALERT

### Page 51 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
INNER FACE OF LUG
FWD  • OUTER FACE OF LUG
PANEL 333ВВ SHOWN REMOVED FOR CLARITY  1975822
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE
(SHEET 1 OF 5)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
2) SPACER
LUG/LUG
INTERFACE
LUG/SPACER
INTERFACE
FWD
INNER FACE OF LUG  1975656
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE
(SHEET 2 OF 5)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
3 SWAGE RING/LUG
SPACER 2  INTERFACE
LUG/SPACER  LUG/LUG
INTERFACE  INTERFACE
FWD
OUTER FACE OF LUG  1975825
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE
(SHEET 3 OF 5)
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### Page 54 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
CENTER OF BEARING
90°
- 20°*  CENTER OF
OUTER LIMITS OF  ALLOWABLE  BEARING
CENTERLINE OF
FEELER GAGE
DEPTH OF
FEELER
GAGE
SWAGE
RING
LUG
CENTER OF FEELER GAGE
RADIAL TO CENTER OF THE
BEARING
FOR SWAGE RING/LUG INTERFACE SHOWN, OTHER  _ FEELER GAGE DEPTH MEASUREMENT  2006248
INTERFACES SIMILAR
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE
(SHEET 4 OF 5)
Original Issue: April 16, 2010
Revision 1 August 02, 2010  737-27A1297
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  54 of 68

### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
CAUTION: DO NOT APPLY FORCE WITH ANYTHING OTHER THAN YOUR HAND. DO NOT APPLY
EXCESSIVE FORCE OR YOU MAY DAMAGE THE ELEVATOR TAB CONTROL MECHANISM
LUGS OR BEARINGS. A BENT LUG OR LOOSE BEARING COULD LEAD TO UNWANTED
ELEVATOR TAB FREEPLAY AND THEN TAB VIBRATION WHICH COULD LEAD TO
STRUCTURAL FAILURE OF THE ELEVATOR OR THE HORIZONTAL STABILIZER.
Using hand pres-
sure, apply force to
the mechanism alter-
nating between the
inboard and out-
board direction while
doing the inspec-
tions in the following
steps. The force can
be applied at any lo-
cation on the mecha-
nism, but no more
than four inches for-
ward of the elevator
front spar.
--forceApply1
(b)1-spacerInspect2
(a) If there is sealant
in the interface, do
not remove it.
1-swage ring/lug interfaceInspect3
(c) If there is sealant
in the interface, do
not remove it.
1-lug/lug interfaceInspect4
(c) If there is sealant
in the interface, do
not remove it.
1-lug/spacer interfaceInspect5
(a) Using a feeler gage, make sure that there is no gap between the swage ring and the outer face of the lug
such that a 0.005 inch feeler gage can be inserted more than 0.025 inch. Do the inspection at a single
location between the allowable outer limits defined in Detail D.  Apply force to the mechanism alternating
between the inboard and outboard direction as you use the feeler gage.
(b) As you apply force to the mechanism alternating between the inboard and outboard direction, use finger
pressure and try to rotate the spacer.
(c) Using a feeler gage, Make sure that there is no gap between the two nested lugs or between the inner
face of the lug and the spacer such that a 0.005 inch feeler gage can be inserted more than 0.16 inch.
Do the inspection at a single location between the allowable outer limits defined in Detail D. Apply force
to the mechanism alternating between the inboard and outboard direction as you use the feeler gage.
FIGURE 3: AFT ATTACH LUG DETAILED INSPECTION - OUTBOARD LUG - LEFT SIDE
(SHEET 5 OF 5)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 16, 2010
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55 of 68
BOEING SERVICE BULLETIN 737-27A1297
ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
00000
FWD
ELEVATOR
HINGE LOWER  COVER  OA SEAL PLATE
RIGHT SHOWN
(ELEVATOR TAB CONTROL MECHANISM NOT SHOWN FOR CLARITY)
1973291
FIGURE 4: ACCESS PANEL REMOVAL & INSTALLATION - RIGHT SIDE
(SHEET 1 OF 2)
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### Page 57

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 one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-seal plateRemove / Keep1
1-elevator hinge lower
cover
Remove / Keep2
1-elevator hinge lower
cover
Install (Kept)3
1-seal plateInstall (Kept)4
FIGURE 4: ACCESS PANEL REMOVAL & INSTALLATION - RIGHT SIDE
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 16, 2010
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BOEING SERVICE BULLETIN 737-27A1297
ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
B
INNER FACE OF LUG
FWD
PANEL 343BB SHOWN REMOVED FOR CLARITY  1975847
FIGURE 5: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - RIGHT SIDE
(SHEET 1 OF 5)
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Revision 1 August 02, 2010  BOEING PROPRIETARY -
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### Page 59 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
SPACER 2)
LUG/SPACER 5
INTERFACE
LUG/LUG
INTERFACE
FWD
1975848
FIGURE 5: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - RIGHT SIDE
Original Issue: April 16, 2010
Revision 1 August 02, 2010  L681LZ-L8L
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### Page 60 (OCR)

BOEING SERVICE BULLETIN 737-27A1297
ALERT  ALERT
(2) SPACER
LUG/LUG
INTERFACE
FWD
INNER FACE OF LUG  1975849
FIGURE 5: AFT ATTACH LUG DETAILED INSPECTION - INBOARD LUG - RIGHT SIDE
(SHEET 3 OF 5)
Original Issue: April 16, 2010
Revision 1 August 02, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  89 10 09

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