# Boeing Alert Service Bulletin 737-55A1097: Revision 1

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- Document: [Boeing Alert Service Bulletin 737-55A1097](https://openairdocs.org/service-documents/boeing/737-55a1097.md)
- Title as filed: SB-737-55A1097-01-- BOEING
- Pages: 101
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-55A1097
Original Issue: July 01, 2015
Revision 1: September 20, 2017
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord Inspection
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2015 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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737-55A1097Revision 1: September 20, 2017
1 of 101
4.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
S u m m a r y  ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A . E f f e c t i v i t y  ............................................... 1 1
1. Airplanes ............................................ 1 1
2 . S p a r e s  A f f e c t e d  ........................................ 3 6
B. Concurrent Requirements ...................................... 3 6
C. Reason ................................................ 3 6
D. Description .............................................. 3 7
E. Compliance .............................................. 3 7
F . A p p r o v a l  ............................................... 5 0
G. Manpower .............................................. 5 1
H. Weight and Balance Changes .................................... 5 2
I. Electrical Load Data ......................................... 5 2
J . R e f e r e n c e s  .............................................. 5 2
1. Existing Data: ......................................... 5 2
2. Data Supplied with this Service Bulletin: ........................... 5 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 5 3
K. Publications Affected ........................................ 5 3
L. Interchangeability and Intermixability of Parts ........................... 5 3
M. Software Accomplishment Summary ................................ 5 3
2. MATERIAL INFORMATION ........................................ 5 5
A. Material - Price and Availability ................................... 5 5
B. Industry Support Information .................................... 5 5
C. Parts Necessary for Each Airplane ................................. 5 5
1 . K i t s / P a r t s  ............................................ 5 5
2. Parts and Materials Supplied by the Operator ........................ 5 5
3. Parts Modified and Reidentified ................................ 5 5
4. Parts Removed and Not Replaced .............................. 5 5
D. Parts Necessary to Change Spares ................................. 5 5
E. Special Tooling - Price and Availability ............................... 5 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 5 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 5 7
A. GENERAL INFORMATION ..................................... 5 7
B. WORK INSTRUCTIONS ....................................... 5 8
FIGURE 1: LEFT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION ..... 6 4
FIGURE 2: RIGHT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION .... 6 7
FIGURE 3: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION
TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT
.................................................. 7 0
FIGURE 4: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION
TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT
.................................................. 7 3
FIGURE 5: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION
TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT
.................................................. 7 6
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FIGURE 6: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION
TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT
.................................................. 7 9
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: HORIZONTAL
STABILIZER IDENTIFICATION [Group 1, Configuration 1] ................. 8 2
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: HORIZONTAL
STABILIZER IDENTIFICATION [Group 1, Configuration 2] ................. 8 7
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: HORIZONTAL
STABILIZER IDENTIFICATION [Group 2, Configuration 1] ................. 9 2
APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 4: HORIZONTAL
STABILIZER IDENTIFICATION [Group 2, Configuration 2] ................. 9 7
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-55A1097Original Issue: July 01, 2015
Revision 1: September 20, 2017
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-13-16 is related to this service bulletin.
Effects of this Revision on airplanes on which Original Issue was previously done and the horizontal stabilizers
were determined to be not affected:
ActionConditionGroup
Determine if any horizontal stabilizer
is affected by this bulletin and do the
required inspections and related
corrective actions.
Airplane horizontal stabilizers deter-
mined not to be affected by the
original issue of this service bulletin.
Group 1-2, Configuration 2
REASON FOR REVISION
Revision 1 is sent to clarify the areas of inspection and serial number information and to make sure that operators
who have previously determined their horizontal stabilizer not to be affected by the original issue of this service
bulletin, determine again if any horizontal stabilizer is affected by this bulletin and do the required inspections
and related corrective actions.
These sections were changed:
1. Summary, Background; revised the serial number information to more accurately describe the affected
serial numbers.
2. Summary, Compliance; added new airworthiness directive.
3. Summary, Industry Support Information; revised the warranty statement.
4. Summary, Illustration; revised to more accurately express the area of work.
5. Paragraph 1.A.2., Spares Affected; revised the serial number information to more accurately describe
the affected serial numbers.
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6. Paragraph 1.C., Reason; revised the serial number information to more accurately describe the affected
serial numbers, included the reason for revision paragraph, and included the paragraph stating that
IN01 was incorporated into this revision.
7. Paragraph 1.D., Description; included the effects of this revision paragraph.
8. Paragraph 1.E., Compliance; added new airworthiness directive, revised the compliance times to the
effective date of the airworthiness directive and revised the serial number information to more accurately
describe the affected serial numbers. Added new compliance tables for airplanes that completed the
original issue of this service bulletin.
9. Paragraph 1.F., Approval; revised the approval paragraphs and added an AMOC paragraph for the
new airworthiness directive.
10. Paragraph 1.J., References; added the new airworthiness directive.
11. Paragraph 2.B., Industry Support Information; revised the warranty statement.
12. Paragraph 3.B., Work Instructions; revised the serial number information to more accurately describe
the affected serial numbers.
13. Figures 1-2; revised the illustrations to clarify the area of work and revised the serial number information
to more accurately describe the affected serial numbers.
14. Figures 3-6; revised the illustrations to clarify the area of work.
15. Appendices B and D added for airplanes that completed the original issue of this service bulletin.
Appendix A and C; revised to incorporate changes made in Paragraph 1.E., Compliance and add
flagnote tables.
The data given in Information Notice 737-55A1097 IN 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
July 01, 2015Original Issue:
September 20, 2017Revision 1:
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-55A1097Original Issue: July 01, 2015
Revision 1: September 20, 2017
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to inspect for cracking in the horizontal stabilizer rear spar upper chord
on horizontal stabilizers with affected serial numbers. If the work in this service bulletin is not done, corrosion
damage may lead to cracking in the horizontal stabilizer rear spar upper chord. Fracture of the upper chord of
the horizontal stabilizer will compromise the structural integrity which could lead to departure of the horizontal
stabilizer from the airplane. This will lead to loss of continued safe flight and landing.
Due to a manufacturing oversight, discovered after production of the affected stabilizers, supplier SAMC (Shanghai
Aviation Manufacturing Corporation, formally SAIC, Shanghai Aviation Industrial Corporation) omitted the required
protective finish (zinc-nickel alloy plate or cadmium plate) on the 182A1508-4/-5/-6 bushings (in line with the
terminal fitting holes) installed in the rear spar upper chord on horizontal stabilizers with the following serial
numbers:
Serial Number (a)Manufacturer (MFR) Code
1 to 143, 145 to 625, 627 to 1144, 1146 to 1601SAIC
1602 to 2639SAMC
(a) Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
The 182A1508-4/-5/-6 bushings are made from aluminum-nickel-bronze. When these bushings are installed,
without the required protective finish, into the 2024-T3511 aluminum horizontal stabilizer rear spar upper chord,
this can lead to galvanic corrosion between the dissimilar metals. This corrosion can lead to cracking of the rear
spar upper chord, which can result in the failure of the upper chord.
Boeing Fleet Team Digest (FTD) 737NG FTD 55-14001 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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Boeing Service Related Problem (SRP) 737NG-SRP-55-0056 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedYesSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
NoOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
To determine if the left and right horizontal stabilizers are affected, do one of the following:
- OPTION 1: Do a check of delivery and maintenance records to find the serial number of the horizontal stabilizer
installed on the airplane during production and to determine if the horizontal stabilizer has been exchanged.
- OPTION 2: Gain access to the horizontal stabilizer identification plate and do an inspection of the identification
plate to find the serial numbers of the horizontal stabilizers.
If any affected horizontal stabilizer is installed on the airplane, do one of the following:
- OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER): Do a High Frequency Eddy Current (HFEC)
inspection of the horizontal stabilizer rear spar upper chord for any crack using a 0.050 inch scan increment.
- OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER): Do an HFEC inspection of the horizontal
stabilizer rear spar upper chord for any crack using a 0.100 inch scan increment.
If no crack is found, repeat the OPTION 1 or OPTION 2 HFEC inspection at the repeat interval given in Paragraph
1.E., Compliance.
If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do the work
instructed by Boeing. Repeat the inspection for any crack at the unrepaired areas.
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EFFECTIVITY
737-600, -700, -700C, -800, -900, -900ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
Refer to Paragraph 1.A.2., Spares Affected for the list of affected components.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-13-16 is related to this service bulletin.
The effective date of AD 2016-13-16 is August 12, 2016.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for 737 airplanes in warranty as of December 20, 2012. 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 737-55A1097
ALERT  ALERT
INSPECT  DO A HFEC INSPECTION OF THE
IDENTIFICATION  HORIZONTAL STABILIZER REAR
PLATE  SPAR UPPER CHORD FOR ANY
CRACK  2389661
Original Issue: July 01, 2015
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Work - See page 1 for details.  10 of 101

### Page 11

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-55A1097
Original Issue: July 01, 2015
Revision 1: September 20, 2017
ATA System: 5510
SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord Inspection
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 737-600, -700, -700C, -800, -900, -900ER airplanes in 2
Groups. The Variable Numbers and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
NOTE: The Variable Number table below includes all affected airplanes up to Line Number 7107.
Affected airplanes after Line Number 7107 will be added to the service bulletin's
MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet
Profile Page.
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DESCRIPTIONCONFIGURATIONGROUP
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
379-1117, 1119-1782, 1784-2504, 2506-4484. These airplanes were
possibly delivered with affected stabilizers installed.
-1
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
379-1117, 1119-1782, 1784-2504, 2506-4484. These airplanes were
possibly delivered with affected stabilizers installed, on which the
original issue of this service bulletin was not previously done, or the
original issue was done and it was determined the horizontal
stabilizers are affected.
1
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
379-1117, 1119-1782, 1784-2504, 2506-4484. These airplanes were
possibly delivered with affected stabilizers installed, on which the
original issue of this service bulletin was previously done and it was
determined the horizontal stabilizers are not affected.
2
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
1-378, 1118, 1783, 2505, 4485 and on. These airplanes were not
delivered with any affected stabilizer installed.
-2
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
1-378, 1118, 1783, 2505, 4485 and on. These airplanes were not
delivered with any affected stabilizer installed, on which the original
issue of this service bulletin was not previously done, or the original
issue was done and it was determined the horizontal stabilizers are
affected.
1
737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers
1-378, 1118, 1783, 2505, 4485 and on. These airplanes were not
delivered with any affected stabilizer installed, on which the original
issue of this service bulletin was previously done and it was
determined the horizontal stabilizers are not affected.
2
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
2YA001 - YA049
1YA050 - YA099
1YA101 - YA199
2YA201 - YA206
1YA207 - YA211
1YA221
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GroupVariable Number
2YA231 - YA242
2YA251 - YA254
1YA255 - YA256
2YA271 - YA272
2YA291
2YA301 - YA302
2YA311 - YA314
2YA321 - YA322
1YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
2YA501 - YA535
1YA536
2YA541 - YA546
1YA547 - YA552
2YA571 - YA577
1YA578
2YA601 - YA608
1YA609 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
2YA701 - YA704
1YA705 - YA710
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GroupVariable Number
2YA721 - YA722
2YA731
1YA732 - YA734
2YA751 - YA756
1YA801 - YA803
1YA809
2YA811 - YA814
2YA831 - YA832
1YA833 - YA835
2YA841 - YA842
1YA843 - YA862
2YA881
1YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
1YB101 - YB112
2YB113
1YB114 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
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GroupVariable Number
1YB561 - YB598
1YB601 - YB636
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB975
1YB981
1YB986 - YB998
2YC001 - YC011
1YC012 - YC030
2YC051 - YC058
1YC059 - YC070
2YC071 - YC076
1YC077 - YC084
1YC091 - YC095
2YC101 - YC103
1YC104
2YC111 - YC112
1YC113
2YC121
2YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
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GroupVariable Number
1YC206 - YC207
2YC301 - YC302
1YC303 - YC305
2YC321 - YC348
1YC349 - YC380
2YC381 - YC382
1YC383 - YC387
2YC391
1YC392 - YC394
1YC396
2YC401 - YC408
1YC409 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
2YC471 - YC475
1YC476 - YC499
2YC501 - YC515
1YC516 - YC526
2YC571 - YC580
1YC581 - YC583
1YC587 - YC589
2YC591 - YC593
2YC601 - YC611
1YC612 - YC655
1YC681 - YC696
2YC701 - YC706
1YC707 - YC715
1YC720 - YC725
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GroupVariable Number
1YC727 - YC730
2YC731 - YC734
1YC735 - YC750
2YC751 - YC752
2YC761 - YC763
1YC764 - YC770
2YC781 - YC784
1YC785 - YC793
2YC801 - YC819
1YC820 - YC892
1YC901 - YC907
1YC921 - YC922
2YC931 - YC932
2YC941 - YC942
1YC943 - YC951
2YC971
1YC972 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD117
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
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### Page 18

GroupVariable Number
1YD391
1YD401 - YD410
1YD412 - YD419
2YD420 - YD422
1YD481 - YD485
1YD491 - YD499
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
2YE001 - YE017
1YE018 - YE020
1YE051
2YE101 - YE109
2YE151 - YE153
1YE154 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF011
1YF021 - YF049
1YF051 - YF072
2YF073 - YF080
1YF086 - YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF119
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### Page 19

GroupVariable Number
1YF121 - YF132
1YF176 - YF178
1YF191 - YF192
1YF201 - YF276
1YF401 - YF402
1YF431 - YF432
1YF436 - YF437
1YF441 - YF442
1YF451 - YF460
1YF501 - YF599
1YF601 - YF661
2YF662 - YF685
2YF691 - YF695
1YF701 - YF707
1YF801 - YF805
1YF831 - YF832
1YF836 - YF838
1YF871 - YF872
1YF901 - YF905
1YF921 - YF928
1YF951 - YF954
2YG001 - YG018
1YG019
2YG020 - YG023
1YG024 - YG026
2YG027 - YG032
1YG033 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG138
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### Page 20

GroupVariable Number
2YG139 - YG148
1YG201 - YG205
1YG211 - YG214
1YG221 - YG224
1YG251 - YG252
1YG501 - YG512
2YG513 - YG515
1YG601 - YG602
1YG701
1YG711
2YG721 - YG722
1YH001 - YH012
1YH031 - YH055
1YH071 - YH080
1YH101 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301 - YH306
2YH307
1YH321 - YH322
1YH501 - YH525
2YH526 - YH530
1YH531 - YH537
2YH538 - YH542
1YH551 - YH581
2YH582 - YH594
1YH601 - YH606
1YH611 - YH620
1YH631 - YH632
2YH636 - YH637
1YH641
2YH681 - YH685
1YH701 - YH708
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### Page 21

GroupVariable Number
2YH709 - YH755
2YH801 - YH899
2YH901 - YH908
2YH911 - YH915
2YH951 - YH952
1YJ001 - YJ013
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ579
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
1YJ961
1YJ976 - YJ977
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK133
1YK136 - YK139
1YK141 - YK142
1YK146 - YK148
1YK151 - YK154
1YK161 - YK167
1YK171
1YK176 - YK177
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GroupVariable Number
1YK186
1YK191
1YK196
1YK201 - YK202
1YK301 - YK314
1YK321 - YK340
1YK361 - YK378
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK467
1YK471 - YK473
1YK476
2YK478
1YK480 - YK487
1YK491 - YK493
1YK495 - YK499
1YK511 - YK516
1YK521 - YK530
1YK551 - YK571
1YK576 - YK577
1YK580 - YK585
1YK601 - YK602
1YK606 - YK607
1YK611 - YK616
1YK621 - YK634
1YK641 - YK644
1YK651 - YK665
1YK671 - YK672
1YK676 - YK677
1YK681 - YK686
1YK691
1YK695 - YK699
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GroupVariable Number
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK785
1YK791 - YK792
1YK796 - YK797
1YK801 - YK899
1YK901 - YK912
1YK918 - YK919
1YK921 - YK929
1YK941 - YK999
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL137
1YL201 - YL237
1YL241 - YL242
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
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GroupVariable Number
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL551
1YL561 - YL579
1YL591 - YL598
1YL601 - YL606
1YL611 - YL612
1YL616 - YL617
1YL621
1YL626
1YL631 - YL634
1YL636 - YL637
1YL661 - YL664
1YL676 - YL691
1YL696 - YL697
1YL701 - YL707
1YL731
1YL751 - YL752
1YL756 - YL757
1YL761 - YL780
1YL796 - YL797
1YL801 - YL815
1YL901 - YL910
1YL921 - YL940
1YL951 - YL968
1YM101 - YM103
1YM201 - YM230
2YM231
1YM232 - YM244
1YM251 - YM299
1YM301 - YM399
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GroupVariable Number
1YM401 - YM415
1YM471
1YM481 - YM484
1YM501 - YM502
2YM503
1YM504 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
1YM641 - YM652
1YM671 - YM674
1YM691 - YM699
1YM701 - YM710
1YM761 - YM765
1YM771 - YM779
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN126
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YN531 - YN534
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GroupVariable Number
1YN551 - YN555
2YN556 - YN566
2YN581 - YN585
2YN591 - YN593
1YN601 - YN606
1YN651 - YN652
2YN653
2YN661 - YN663
2YN666 - YN667
2YN671 - YN674
1YN701 - YN702
1YN741 - YN743
2YN744 - YN746
2YN756 - YN758
1YQ001 - YQ003
1YQ011 - YQ021
1YQ026 - YQ029
1YQ036 - YQ045
1YQ201 - YQ203
2YQ204 - YQ207
1YQ231
1YQ241 - YQ251
1YQ281 - YQ284
1YQ291 - YQ296
1YQ301 - YQ302
1YQ321 - YQ323
2YQ324
1YQ331 - YQ332
2YQ333 - YQ334
1YQ346
2YQ347
2YQ351 - YQ367
2YQ371
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GroupVariable Number
1YQ401 - YQ403
1YQ451 - YQ454
1YQ456
1YQ461
1YQ471
1YQ501 - YQ505
2YQ506 - YQ520
2YQ601 - YQ606
2YQ610 - YQ614
1YR001 - YR023
2YR024 - YR050
1YR051 - YR069
2YR070 - YR090
1YR091 - YR096
2YR097 - YR098
1YR101 - YR104
2YR105
1YR111 - YR118
2YR119 - YR124
1YR126 - YR143
2YR144
1YR166 - YR182
1YR186 - YR188
2YR189 - YR198
1YR201 - YR204
2YR205 - YR215
1YR231 - YR266
2YR267 - YR270
1YR271 - YR289
2YR290
1YR291 - YR294
1YR296 - YR297
1YR301 - YR327
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GroupVariable Number
2YR328 - YR334
2YR338 - YR341
1YR361 - YR366
1YR371 - YR372
2YR373
2YR376 - YR377
1YR381 - YR382
1YR386
2YR387 - YR388
2YR391
1YR396 - YR397
2YR398 - YR399
1YR401 - YR405
1YR411 - YR413
1YR416 - YR417
2YR418
1YR421 - YR422
2YR423 - YR424
1YR426
2YR427 - YR430
1YR431 - YR436
2YR437 - YR440
1YR441 - YR446
2YR447 - YR450
1YR451 - YR455
1YR457 - YR481
2YR482 - YR499
1YR501 - YR506
1YR511 - YR520
1YR526 - YR534
2YR535
1YR536 - YR541
2YR542 - YR544
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GroupVariable Number
1YR546
2YR547 - YR551
2YR556 - YR562
2YR571 - YR582
2YR591 - YR592
1YR601 - YR605
1YR616 - YR630
2YR631 - YR650
1YR651 - YR658
1YR661 - YR663
2YR671 - YR673
2YR676 - YR678
2YR681 - YR682
1YR701 - YR759
2YR760 - YR769
2YR771 - YR799
1YR801 - YR814
2YR815 - YR827
1YR831 - YR838
1YR841 - YR845
2YR846 - YR850
1YR851 - YR866
2YR867 - YR899
1YR901 - YR903
1YR931 - YR933
2YR934
2YR938 - YR940
1YR941 - YR944
1YR951 - YR960
2YR961 - YR980
1YR981 - YR991
2YR992 - YR998
1YS001 - YS002
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GroupVariable Number
2YS006 - YS009
1YS031 - YS032
1YS051 - YS064
2YS065 - YS073
1YS101 - YS112
2YS113 - YS120
2YS126 - YS142
2YS146 - YS150
1YS151 - YS160
1YS166 - YS173
2YS174 - YS194
1YS196
2YS197
1YS201 - YS207
2YS208 - YS209
1YS221 - YS225
2YS231 - YS236
1YS271 - YS273
2YS274 - YS288
2YS295 - YS296
1YS301 - YS316
2YS317 - YS348
1YS351 - YS352
2YS353 - YS370
1YS371 - YS374
2YS375 - YS378
2YS381 - YS384
2YS401
1YS451
2YS456 - YS457
2YS462 - YS465
2YS467
1YS501 - YS502
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GroupVariable Number
2YS506
2YS511 - YS518
2YS531
2YS536 - YS538
2YS541 - YS542
2YS546
1YS551 - YS553
2YS554 - YS556
1YS561 - YS562
2YS563 - YS578
2YS581 - YS590
1YS591
2YS592 - YS595
1YS601 - YS638
2YS639 - YS685
1YS686 - YS690
1YS701 - YS705
2YS706 - YS715
1YS721 - YS727
2YS728 - YS762
1YS771 - YS775
2YS776 - YS780
2YS806 - YS810
2YS816 - YS818
2YS823 - YS825
2YS851 - YS863
2YS876
2YS881 - YS883
2YS891
2YS896 - YS897
2YS901 - YS909
2YS911 - YS957
2YS961 - YS974
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GroupVariable Number
2YS976 - YS977
2YS981 - YS987
2YS991 - YS998
1YT001
2YT002 - YT004
2YT006
2YT026 - YT027
2YT031 - YT032
2YT036 - YT038
2YT061 - YT068
2YT101 - YT138
2YT176 - YT185
2YT191
2YT196 - YT199
2YT201
2YT206 - YT207
2YT211 - YT213
2YT251 - YT299
2YT301 - YT307
2YT311 - YT312
2YT321 - YT355
2YT371 - YT372
2YT381
2YT391 - YT396
2YT401 - YT403
2YT411 - YT417
2YT427
2YT461 - YT477
2YT491 - YT492
2YT501 - YT521
2YT551 - YT552
2YT556 - YT563
2YT565
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GroupVariable Number
2YT571 - YT576
2YT601 - YT606
2YT701 - YT708
2YT723
2YT761 - YT781
2YT791 - YT794
2YT796 - YT797
2YT801 - YT804
2YT811 - YT813
2YT826 - YT827
2YT831 - YT832
2YT841 - YT852
2YT856 - YT863
2YT885 - YT887
2YT891 - YT895
2YT901 - YT998
2YU001 - YU060
2YU201 - YU216
2YU301 - YU320
2YU901
2YV001 - YV004
2YV006 - YV012
2YV021 - YV023
2YV030 - YV034
2YV037 - YV042
2YV045 - YV047
2YV051 - YV059
2YV081
2YV083 - YV084
2YV097 - YV099
2YV101 - YV154
2YV201 - YV203
2YV251 - YV252
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GroupVariable Number
2YV256 - YV257
2YV301 - YV312
2YV351 - YV368
2YV381 - YV388
2YV391 - YV394
2YV401
2YV411 - YV413
2YV431 - YV433
2YV441 - YV454
2YV461 - YV462
2YV467 - YV470
2YV501 - YV508
2YV521
2YV571 - YV585
2YV601 - YV605
2YV651 - YV669
2YV695 - YV696
2YV711
2YV722 - YV731
2YV741 - YV779
2YV781 - YV791
2YV801 - YV817
2YV831 - YV836
2YV881 - YV883
2YV901 - YV915
2YV923 - YV926
2YV971 - YV982
2YW001
2YW011 - YW099
2YW101 - YW149
2YW201 - YW206
2YW226 - YW240
2YW245 - YW261
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GroupVariable Number
2YW263
2YW267 - YW281
2YW283 - YW285
2YW292 - YW299
2YW351
2YW356 - YW358
2YW361 - YW366
2YW371 - YW399
2YW401 - YW421
2YW441 - YW445
2YW451 - YW452
2YW471 - YW472
2YW491 - YW495
2YW531 - YW533
2YW541
2YW551 - YW566
2YW585 - YW591
2YW595 - YW596
2YW601
2YW610
2YW616 - YW623
2YW666
2YW696 - YW699
2YW701 - YW710
2YW726 - YW728
2YW766
2YW881
2YW891 - YW893
2YW906 - YW907
2YW916 - YW918
2YW921 - YW923
2YW971 - YW976
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### Page 36

2. Spares Affected
Examine your spares supply for the parts or components identified below. If any parts or components
are found, refer to Paragraph 3.B., Work Instructions for the recommended action.
Serial Number (a)Manufacturer (MFR) Code
1 to 143, 145 to 625, 627 to 1144, 1146 to 1601SAIC
1602 to 2639SAMC
(a) Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect for cracking in the horizontal stabilizer rear spar upper
chord on horizontal stabilizers with affected serial numbers. If the work in this service bulletin is not
done, corrosion damage may lead to cracking in the horizontal stabilizer rear spar upper chord. Fracture
of the upper chord of the horizontal stabilizer will compromise the structural integrity which could lead
to departure of the horizontal stabilizer from the airplane. This will lead to loss of continued safe flight
and landing.
Due to a manufacturing oversight, discovered after production of the affected stabilizers, supplier SAMC
(Shanghai Aviation Manufacturing Corporation, formally SAIC, Shanghai Aviation Industrial Corporation)
omitted the required protective finish (zinc-nickel alloy plate or cadmium plate) on the 182A1508-4/-5/-6
bushings (in line with the terminal fitting holes) installed in the rear spar upper chord on horizontal
stabilizers with the following serial numbers:
Serial Number (a)Manufacturer (MFR) Code
1 to 143, 145 to 625, 627 to 1144, 1146 to 1601SAIC
1602 to 2639SAMC
(a) Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
The 182A1508-4/-5/-6 bushings are made from aluminum-nickel-bronze. When these bushings are
installed, without the required protective finish, into the 2024-T3511 aluminum horizontal stabilizer rear
spar upper chord, this can lead to galvanic corrosion between the dissimilar metals. This corrosion can
lead to cracking of the rear spar upper chord, which can result in the failure of the upper chord.
Boeing Fleet Team Digest (FTD) 737NG FTD 55-14001 is related to this service bulletin.
Boeing Service Related Problem (SRP) 737NG-SRP-55-0056 is related to this service bulletin.
Revision 1 is sent to clarify the areas of inspection and serial number information.
The data given in Information Notice 737-55A1097 IN 01 is included in this revision.
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### Page 37

D. Description
To determine if the left and right horizontal stabilizers are affected, do one of the following:
- OPTION 1: Do a check of delivery and maintenance records to find the serial number of the horizontal
stabilizer installed on the airplane during production and to determine if the horizontal stabilizer has
been exchanged.
- OPTION 2: Gain access to the horizontal stabilizer identification plate and do an inspection of the
identification plate to find the serial numbers of the horizontal stabilizers.
If any affected horizontal stabilizer is installed on the airplane, do one of the following:
- OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER): Do a High Frequency Eddy
Current (HFEC) inspection of the horizontal stabilizer rear spar upper chord for any crack using a 0.050
inch scan increment.
- OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER): Do an HFEC inspection of the
horizontal stabilizer rear spar upper chord for any crack using a 0.100 inch scan increment.
If no crack is found, repeat the OPTION 1 or OPTION 2 HFEC inspection at the repeat interval given
in Paragraph 1.E., Compliance.
If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do
the work instructed by Boeing. Repeat the inspection for any crack at the unrepaired areas.
Effects of this Revision on airplanes on which Original Issue was previously done and the horizontal
stabilizers were determined to be not affected:
ActionConditionGroup
Determine if any horizontal stabilizer
is affected by this bulletin and do the
required inspections and related
corrective actions.
Airplane horizontal stabilizers deter-
mined not to be affected by the
original issue of this service bulletin.
Group 1-2, Configuration 2
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
332, 342737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-13-16 is related to this service
bulletin. The effective date of AD 2016-13-16 is August 12, 2016.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 38

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Logic diagrams showing compliance tasks and compliance times are included as aids in APPENDIX
A, APPENDIX B, APPENDIX C and APPENDIX D.
Group 1, Configuration 1:
Table 1: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Do PART 1:
RECORDS CHECK.
All airplanes
OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 1: CURRENT-
LY INSTALLED HORIZON-
TAL STABILIZER NOT
AFFECTED (a)
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
CONDITION 2: CURRENT-
LY INSTALLED HORIZON-
TAL STABILIZER AFFECT-
ED (a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 39

Group 1, Configuration 1:
Table 1: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 3: PRODUC-
TION HORIZONTAL STA-
BILIZER NOT EX-
CHANGED AND SERIAL
NUMBER UNKNOWN
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Check mainte-
nance records to find the
original delivered airplane
for the horizontal stabiliz-
er.
CONDITION 4: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND IN-
STALLED HORIZONTAL
STABILIZER SERIAL
NUMBER UNKNOWN OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 8: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 1-378, 1118,
1783, 2505, OR 4485-5388
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 40

Group 1, Configuration 1:
Table 1: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 9: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 379-1117, 1119-
1782, 1784-2504, OR
2506-4484 OR IS FROM
UNKNOWN AIRPLANE
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) Refer to Table 5 for resulting conditions and corrective actions.
(c) Refer to Table 6 for resulting conditions and corrective actions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 41

Group 1, Configuration 2:
Table 2: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Do PART 1:
RECORDS CHECK.
All airplanes
OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 1: CURRENT-
LY INSTALLED HORIZON-
TAL STABILIZER NOT
AFFECTED (a)
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
CONDITION 2: CURRENT-
LY INSTALLED HORIZON-
TAL STABILIZER AFFECT-
ED (a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 01, 2015
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41 of 101
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ALERTALERT

### Page 42

Group 1, Configuration 2:
Table 2: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 3: PRODUC-
TION HORIZONTAL STA-
BILIZER NOT EX-
CHANGED AND SERIAL
NUMBER UNKNOWN
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Check mainte-
nance records to find the
original delivered airplane
for the horizontal stabiliz-
er.
CONDITION 4: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND IN-
STALLED HORIZONTAL
STABILIZER SERIAL
NUMBER UNKNOWN OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 8: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 1-378, 1118,
1783, 2505, OR 4485-5388
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 43

Group 1, Configuration 2:
Table 2: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 9: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 379-1117, 1119-
1782, 1784-2504, OR
2506-4484 OR IS FROM
UNKNOWN AIRPLANE
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) Refer to Table 7 for resulting conditions and corrective actions.
(c) Refer to Table 6 for resulting conditions and corrective actions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 44

Group 2, Configuration 1:
Table 3: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Do PART 1:
RECORDS CHECK.
All airplanes
OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 5: NO HORI-
ZONTAL STABILIZER EX-
CHANGED OR ANY HOR-
IZONTAL STABILIZER
EXCHANGED WITH AN
UNAFFECTED HORIZON-
TAL STABILIZER (a)
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
CONDITION 6: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND AF-
FECTED HORIZONTAL
STABILIZER INSTALLED
(a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 01, 2015
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44 of 101
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ALERTALERT

### Page 45

Group 2, Configuration 1:
Table 3: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Check mainte-
nance records to find the
original delivered airplane
for the horizontal stabiliz-
er.
CONDITION 7: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND IN-
STALLED HORIZONTAL
STABILIZER SERIAL
NUMBER UNKNOWN OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 8: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 1-378, 1118,
1783, 2505, OR 4485-5388
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 9: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 379-1117, 1119-
1782, 1784-2504, OR
2506-4484 OR IS FROM
UNKNOWN AIRPLANE
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) Refer to Table 5 for resulting conditions and corrective actions.
(c) Refer to Table 6 for resulting conditions and corrective actions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 46

Group 2, Configuration 2:
Table 4: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Do PART 1:
RECORDS CHECK.
All airplanes
OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 5: NO HORI-
ZONTAL STABILIZER EX-
CHANGED OR ANY HOR-
IZONTAL STABILIZER
EXCHANGED WITH AN
UNAFFECTED HORIZON-
TAL STABILIZER (a)
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
CONDITION 6: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND AF-
FECTED HORIZONTAL
STABILIZER INSTALLED
(a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (c)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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ALERTALERT

### Page 47

Group 2, Configuration 2:
Table 4: Horizontal Stabilizer Identification
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1: Check mainte-
nance records to find the
original delivered airplane
for the horizontal stabiliz-
er.
CONDITION 7: ANY HOR-
IZONTAL STABILIZER
EXCHANGED AND IN-
STALLED HORIZONTAL
STABILIZER SERIAL
NUMBER UNKNOWN OPTION 2: Do PART 2:
HORIZONTAL STABILIZ-
ER IDENTIFICATION
PLATE INSPECTION. (b)
---No more work is required.CONDITION 8: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 1-378, 1118,
1783, 2505, OR 4485-5388
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
Do PART 2: HORIZON-
TAL STABILIZER IDENTI-
FICATION PLATE IN-
SPECTION. (b)
CONDITION 9: HORIZON-
TAL STABILIZER IS
FROM AIRPLANE LINE
NUMBER 379-1117, 1119-
1782, 1784-2504, OR
2506-4484 OR IS FROM
UNKNOWN AIRPLANE
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) Refer to Table 7 for resulting conditions and corrective actions.
(c) Refer to Table 6 for resulting conditions and corrective actions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 01, 2015
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47 of 101
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ALERTALERT

### Page 48

Group 1-2, Configuration 1:
Table 5: PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION - Corrective Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
---No more work is required.CONDITION 10: NO AF-
FECTED HORIZONTAL
STABILIZER FOUND (a)
-Within 12
months after the
effective date of
AD 2016-13-16
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (b)
CONDITION 11: ANY AF-
FECTED HORIZONTAL
STABILIZER FOUND (a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (b)
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) See Table 6 for resulting conditions and corrective actions.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 01, 2015
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ALERTALERT

### Page 49

Table 6: Horizontal Stabilizer Rear Spar Upper Chord HFEC Inspection - Corrective Actions
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--Do one of the following:CONDITION 12: NO
CRACK FOUND 3,000 horizontal
stabilizer flight cy-
cles
-Repeat OPTION 1 (TO
DETECT ANY CRACK
0.100 INCH OR
GREATER) HFEC inspec-
tion of the horizontal sta-
bilizer rear spar upper
chord.
2,000 horizontal
stabilizer flight cy-
cles
-Repeat OPTION 2 (TO
DETECT ANY CRACK
0.200 INCH OR
GREATER) HFEC inspec-
tion of the horizontal sta-
bilizer rear spar upper
chord.
-Before further flightACTION 1: Contact Boe-
ing to get instructions for
the repair for this service
bulletin, and do the work
instructed by Boeing.
CONDITION 13: ANY
CRACK FOUND
--ACTION 2: Do one of the
following:
3,000 horizontal
stabilizer flight cy-
cles
-Repeat OPTION 1 (TO
DETECT ANY CRACK
0.100 INCH OR
GREATER) HFEC inspec-
tion of the horizontal sta-
bilizer rear spar upper
chord, for any crack of
the unrepaired area.
2,000 horizontal
stabilizer flight cy-
cles
-Repeat OPTION 2 (TO
DETECT ANY CRACK
0.200 INCH OR
GREATER) HFEC inspec-
tion of the horizontal sta-
bilizer rear spar upper
chord, for any crack of
the unrepaired area.
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Group 1-2, Configuration 2:
Table 7: PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION - Corrective Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
---No more work is required.CONDITION 10: NO AF-
FECTED HORIZONTAL
STABILIZER FOUND (a)
-Within 12
months after the
Revision 1 date
of this service
bulletin.
Before 20,000
total horizontal
stabilizer flight
cycles or within
10 years from
the date of is-
suance of the
original certifi-
cate of airworthi-
ness or the origi-
nal export certifi-
cate of airworthi-
ness, whichever
occurs first
OPTION 1 (TO DETECT
ANY CRACK 0.100 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (b)
CONDITION 11: ANY AF-
FECTED HORIZONTAL
STABILIZER FOUND (a)
OPTION 2 (TO DETECT
ANY CRACK 0.200 INCH
OR GREATER): Do an
HFEC inspection of the
horizontal stabilizer rear
spar upper chord for any
crack. (b)
(a) Affected horizontal stabilizers have one of the conditions that follow:
1. Manufacturer (MFR) code SAIC and serial numbers from 1 to 143, or 145 to 625, or 627 to
1144, or 1146 to 1601.
2. MFR code SAMC and a serial number in the range 1602 to 2639.
Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
(b) See Table 6 for resulting conditions and corrective actions.
F. Approval
NOTE: The approval statement that follows is valid for all affected airplanes, except 737-700C
airplanes.
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.
NOTE: The approval statement that follows is valid for 737-700C airplanes.
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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 for all 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.
This service bulletin is also approved for airplanes having FAA Aviation Partners Boeing (APB)
Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas affected
by the split scimitar winglet configuration).
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.
The Manager of the Seattle ACO Branch approves the incorporation of the inspection threshold, interval,
and methods for the high frequency eddy current (HFEC) inspection defined in Paragraph 1.E.,
Compliance of Service Bulletin 737-55A-1097, as an Alternative Method of Compliance (AMOC) to the
incorporation of the corresponding HFEC inspections in the area of Principal Structural Elements
55-10-04-10A, 55-10-04-10B, and 55-10-04-10C, specified in Subsection B of Section 9 of Boeing
Model 737-600/-700/-700C/-800/-900/-900ER MPD, Document D626A001-CMR, Revision July 2011,
December 2011, or August 2012, required by paragraphs (g) and (h) of AD 2013-19-23.
In addition, the Manager of the Seattle ACO Branch approves accomplishment of the records check,
horizontal stabilizer identification plate inspection, and HFEC inspection with the corresponding
compliance times and repeat intervals specified in Paragraph 1.E., Compliance of Service Bulletin
737-55A1097 R01, as an AMOC to the records check or inspection and HFEC inspection required by
paragraphs (g)(1), (g)(2), (i)(1), and (i)(2) of AD 2016-13-16.
G. Manpower
The tables below show an estimate of the task hours necessary to do this inspection for each airplane
or component. 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.
1. Airplane-Level Work
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HORIZONTAL STABILIZER - REAR SPAR UPPER CHORD - INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
1.501.501Preparation and
Open Access
0.050.051FIGURE 1
0.050.051FIGURE 2
1.001.001FIGURE 3 or FIG-
URE 5
1.001.001FIGURE 4 or FIG-
URE 6
1.501.501Restoration and
Close Access
5.105.10TOTAL FOR EACH AIRPLANE
2. Component-Level Work
HORIZONTAL STABILIZER - REAR SPAR UPPER CHORD - INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
0.050.051FIGURE 1
0.050.051FIGURE 2
1.001.001FIGURE 3 or FIG-
URE 5
1.001.001FIGURE 4 or FIG-
URE 6
2.102.10TOTAL FOR LEFT SIDE OF AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 737NG-SRP-55-0056
b. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-19-23, 2016-13-16
c. Service Bulletin Index D6-19567
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d. Standard Overhaul Practices Manual (SOPM) 20-50-01
e. 737 Non-Destructive Testing (NDT) Manual Part 6, 55-10-27, Part 6
f. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 06-42-00, 27-31-00, 27-41-11
g. 737NG Fleet Team Digest (FTD) 55-14001
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:
Chapter-SectionPublication
55-10-27737 NDT Manual Part 6
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 affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 55

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are available for 737 airplanes in warranty as of December 20, 2012. For
inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty
claim to Boeing Fleet Support Contracts - Warranty. If the condition described in this service bulletin
is found during the inspection for airplanes in warranty as of that date and additional task hours, parts,
and/or special tools are required, send a warranty claim to Boeing Fleet Support Contracts - Warranty.
Please refer to this service bulletin number and reference the airplane variable number(s) in your
purchase order.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 57

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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.
CAUTION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 737 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 737
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. 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.
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7. Refer to APPENDIX A and APPENDIX C for logic diagram(s). Logic diagrams are
provided as an aid only. Information contained in Paragraph 1.E., Compliance is the
primary source for compliance times. Information in Paragraph 3.B., Work Instructions
is the primary source for tasks required for compliance.
8. 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.
9. 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.
10. 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.
11. 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.
12. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. An Alternative Method of
Compliance (AMOC) is required for any deviations to RC steps, including sub-steps
and identified figures. Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection program without
obtaining approval of an AMOC.
17. A check of the airplane maintenance and delivery records is an acceptable method
to determine if the left and right horizontal stabilizers are affected provided the installed
components can be conclusively determined from that check.
B. WORK INSTRUCTIONS
1. RC - To determine if the left and right horizontal stabilizers are affected, do one of the following
options:
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a. OPTION 1 : Do PART 1: RECORDS CHECK.
b. OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION.
PART 1: RECORDS CHECK
1. Group 1:
RC - Do a check of delivery and maintenance records to find the manufacturer (MFR) code and
serial numbers of the horizontal stabilizers installed on the airplane during production, and to
determine if any horizontal stabilizer has been exchanged. The following serial numbers are
affected:
Serial Number (a)Manufacturer (MFR) Code
1 to 143, 145 to 625, 627 to 1144, 1146 to 1601SAIC
1602 to 2639SAMC
(a) Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
a. CONDITION 1: CURRENTLY INSTALLED HORIZONTAL STABILIZER NOT AFFECTED
(1) No more work is required.
b. CONDITION 2: CURRENTLY INSTALLED HORIZONTAL STABILIZER AFFECTED
(1) Do PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC
INSPECTION.
c. CONDITION 3: PRODUCTION HORIZONTAL STABILIZER NOT EXCHANGED AND SERIAL
NUMBER UNKNOWN
(1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION.
d. CONDITION 4: ANY HORIZONTAL STABILIZER EXCHANGED AND INSTALLED
HORIZONTAL STABILIZER SERIAL NUMBER UNKNOWN
(1) OPTION 1: Check maintenance records to find the original delivered airplane for the
horizontal stabilizer.
(a) CONDITION 8: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER
1-378, 1118, 1783, 2505, OR 4485-5388
1) No more work is required.
(b) CONDITION 9: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER
379-1117, 1119-1782, 1784-2504, OR 2506-4484 OR IS FROM UNKNOWN
AIRPLANE
1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE
INSPECTION.
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(2) OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE
INSPECTION.
2. Group 2:
RC - Do a check of maintenance records to determine if any horizontal stabilizer has been
exchanged, and to find the manufacturer (MFR) code and serial number of the horizontal stabilizer
installed. The following serial numbers are affected:
Serial Number (a)Manufacturer (MFR) Code
1 to 143, 145 to 625, 627 to 1144, 1146 to 1601SAIC
1602 to 2639SAMC
(a) Horizontal stabilizer serial numbers may or may not have leading zeroes. In addition, all horizontal stabi-
lizer serial numbers can start with the MFR code.
a. CONDITION 5: NO HORIZONTAL STABILIZER EXCHANGED OR ANY HORIZONTAL
STABILIZER EXCHANGED WITH AN UNAFFECTED HORIZONTAL STABILIZER
(1) No more work is required.
b. CONDITION 6: ANY HORIZONTAL STABILIZER EXCHANGED AND AFFECTED
HORIZONTAL STABILIZER INSTALLED
(1) Do PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC
INSPECTION.
c. CONDITION 7: ANY HORIZONTAL STABILIZER EXCHANGED AND INSTALLED
HORIZONTAL STABILIZER SERIAL NUMBER UNKNOWN
(1) OPTION 1: Check maintenance records to find the original delivered airplane for the
installed horizontal stabilizer.
(a) CONDITION 8: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER
1-378, 1118, 1783, 2505, OR 4485-5388
1) No more work is required.
(b) CONDITION 9: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER
379-1117, 1119-1782, 1784-2504, OR 2506-4484 OR IS FROM UNKNOWN
AIRPLANE
1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE
INSPECTION.
(2) OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE
INSPECTION.
PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION
1. Do PART 3: PREPARATION AND ACCESS - AIRPLANE-LEVEL WORK ONLY.
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