# Boeing Alert Service Bulletin 737-25A1732: Revision 2

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2016-9506; AD 2017-14-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-25A1732](https://openairdocs.org/service-documents/boeing/737-25a1732.md)
- Title as filed: FAA-2016-9506_SB-737-25A1732-Rev 02
- Pages: 46
- PDF: https://openairdocs.org/files/sha256/1a/d2/1ad22255c4f28b6d00ffa19903e1fa95c0a1a5e9a646b0e403e2b491fb8670be
- Page: https://openairdocs.org/service-documents/boeing/737-25a1732/file/1ad22255c4f2

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-25A1732
Original Issue: April 12, 2016
Revision 2: April 13, 2017
ATA System: 2510
SUBJECT: EQUIPMENT / FURNISHINGS - Flight Compartment - Captain's and First Officer's
Rudder Pedal Heel Rest Cover Assembly Fastener Torque Check
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 © 2016 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Unpublished Work.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.
Original Issue: April 12, 2016
737-25A1732Revision 2: April 13, 2017
1 of 46
4.0

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
737-25A1732Revision 2: April 13, 2017
2 of 46
BOEING SERVICE BULLETIN 737-25A1732
ALERTALERT
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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 27
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 30
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
FIGURE 1: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - TORQUE CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
FIGURE 2: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER
ASSEMBLY SCREWS - TORQUE CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . 37
FIGURE 3: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
- SCREW AND NUTPLATE REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . 39
FIGURE 4: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER
ASSEMBLY - SCREW AND NUTPLATE REPLACEMENT . . . . . . . . . . . . . . . . . 41
FIGURE 5: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - PAINT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
737-25A1732Revision 2: April 13, 2017
3 of 46
BOEING SERVICE BULLETIN 737-25A1732
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FIGURE 6: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER
ASSEMBLY SCREWS - PAINT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
737-25A1732Revision 2: April 13, 2017
4 of 46
BOEING SERVICE BULLETIN 737-25A1732
ALERTALERT

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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-25A1732Original Issue: April 12, 2016
Revision 2: April 13, 2017
ATA System: 2510
SUBJECT: EQUIPMENT / FURNISHINGS - Flight Compartment - Captain's and First Officer's
Rudder Pedal Heel Rest Cover Assembly Fastener Torque Check
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2016-NM-090-AD, is related to
this service bulletin.
Effects of this Revision on airplanes on which the Original Issue or Revision 1 was previously done:
None.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
REASON FOR REVISION
This revision is sent to give information that lets an optional screw be installed if replacement is necessary. This
revision also has better described work instructions, where some instructions are moved to new Figures and to
make sure necessary tests are done.
These sections were changed:
1. Summary, Background: Added reference to Boeing Fleet Team Digest (FTD) 737NG FTD 25-15004.
Changed summary evaluation table.
2. Summary, Compliance: Added reference to Federal Aviation Administration (FAA) Notice of Proposed
Rule Making NPRM 2016-NM-090-AD.
3. Summary, Material Information: Added Operator Supplied Parts/Materials reference.
4. Summary, Illustration: Changed.
5. Paragraph 1.C., Reason: Added reference to Boeing Fleet Team Digest (FTD) 737NG FTD 25-15004.
Added Revision 2 information.
6. Paragraph 1.D., Description: Added Revision 2 information.
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737-25A1732Revision 2: April 13, 2017
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7. Paragraph 1.E., Compliance: Added reference to Federal Aviation Administration (FAA) Notice of
Proposed Rule Making NPRM 2016-NM-090-AD.
8. Paragraph 1.F., Approval: Changed.
9. Paragraph 1.G., Manpower: Changed paragraph. Changed manpower. Changed footnotes (a) and (b).
10. Paragraph 1.J.1., Existing Data: Changed and added references.
11. Paragraph 1.K.1., Publications: Added specific impacted section of Aircraft Maintenance Manual. Added
Illustrated Parts Catalog.
12. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Added table.
13. Paragraph 3.B., Work Instructions: Changed Steps 2.b., 3.a., 3.b., 4. and 5.. Added Steps 2.c., 2.d.,
3.c. and 3.d..
14. Figure 1 and Figure 2: Changed.
15. Figure 3, Figure 4, Figure 5 and Figure 6: Added.
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
April 12, 2016Original Issue:
August 15, 2016Revision 1:
April 13, 2017Revision 2:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
737-25A1732Revision 2: April 13, 2017
6 of 46
BOEING SERVICE BULLETIN 737-25A1732
ALERTALERT

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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-25A1732Original Issue: April 12, 2016
Revision 2: April 13, 2017
ATA System: 2510
SUBJECT: EQUIPMENT / FURNISHINGS - Flight Compartment - Captain's and First Officer's
Rudder Pedal Heel Rest Cover Assembly Fastener Torque Check
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
Accomplishment of this service bulletin will prevent the Captain's and First Officer's rudder pedals from operating
incorrectly because of any protruding screw in the rudder pedal heel rest cover assembly. If this Service Bulletin
is not accomplished, this condition could restrict rudder pedal motion and differential braking during takeoff or
landing potentially leading to a high speed runway excursion.
A pilot from an operator reported that a flight was aborted during takeoff because the rudder pedals were not
operating correctly. The airplane was returned to gate safely with normal tiller operation. The operator did further
investigation, and found a protruding screw at the outboard edge of the Captain's rudder pedal heel rest cover
assembly adjacent to the rudder pedal. Boeing has implemented a process of monitoring the screw installation
starting at Line Number 3556 to ensure conformance to engineering requirements.
This service bulletin gives instructions to do a one-time torque check of the Captain's and First Officer's rudder
pedal heel rest cover assembly screw locations adjacent to the rudder pedals.
Boeing Service Related Problem (SRP) 737NG-27-0274 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737NG FTD 25-15004 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 AffectedNoSpares Affected
Paragraph 1.E., ComplianceYesAD Related
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ReferenceAffectedPlanning Data
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
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Get access to the flight compartment and do a one-time torque check of the Captain's and First Officer's rudder
pedal heel rest cover assembly screw locations adjacent to the rudder pedals. If the torque requirement at all
screw locations is correct, no more work is necessary. If any screw does not hold a torque or is not fully seated
then replace the screw and nutplate. Do an operational check of the rudder pedals to make sure that motion is
not restricted.
EFFECTIVITY
737-600, -700, -700C, -800, -900, -900ER Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplane(s).
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2016-NM-090-AD, is related to
this service bulletin.
Boeing recommends that the torque check be done within 21 months after the Original Issue date of this service
bulletin and any necessary corrections given in this service bulletin be done before further flight.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the torque check and/or repair procedures given in this service
bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
CAPTAIN'S
FIRST OFFICER'S
FLIGHT COMPARTMENT
DO A ONE-TIME TORQUE
CHECK OF THE RUDDER
PEDAL HEEL REST COVER
ASSEMBLY SCREWS
(6 LOCATIONS)
TYPICAL
(2 LOCATIONS)
2479828
Original Issue: April 12, 2016
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737-25A1732Revision 2: April 13, 2017
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ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-25A1732
Original Issue: April 12, 2016
Revision 2: April 13, 2017
ATA System: 2510
SUBJECT: EQUIPMENT / FURNISHINGS - Flight Compartment - Captain's and First Officer's
Rudder Pedal Heel Rest Cover Assembly Fastener Torque Check
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
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is applicable to 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER,
line numbers 1-3555, in 1 Group. The Variable Numbers and Group Information for the applicable
airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP
737-600, -700, -700C, -800, -900, -900ER Airplanes with rudder pedal
heel rest cover assembly screws that may not have been installed
in conformance to engineering requirements.
-1
Airplane Models:
737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER
GroupVariable Number
1YA001 - YA099
1YA101 - YA199
1YA201 - YA211
1YA221
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GroupVariable Number
1YA231 - YA242
1YA251 - YA256
1YA271 - YA272
1YA291
1YA301 - YA302
1YA311 - YA314
1YA321 - YA323
1YA336 - YA345
1YA351
1YA356 - YA357
1YA366 - YA367
1YA371 - YA377
1YA501 - YA536
1YA541 - YA552
1YA571 - YA578
1YA601 - YA615
1YA621 - YA622
1YA626 - YA631
1YA635 - YA636
1YA641 - YA642
1YA645 - YA650
1YA656 - YA659
1YA666 - YA667
1YA671 - YA672
1YA681 - YA691
1YA701 - YA710
1YA721 - YA722
1YA731 - YA734
1YA751 - YA756
1YA801 - YA803
1YA809
1YA811 - YA814
1YA831 - YA835
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GroupVariable Number
1YA841 - YA862
1YA881 - YA882
1YA891 - YA892
1YA961 - YA978
1YB001 - YB006
1YB101 - YB132
1YB151 - YB153
1YB156 - YB158
1YB161 - YB164
1YB171 - YB172
1YB181 - YB184
1YB201 - YB208
1YB271
1YB276
1YB301 - YB310
1YB371 - YB392
1YB501 - YB502
1YB521 - YB526
1YB541 - YB544
1YB551
1YB561 - YB598
1YB601 - YB635
1YB651
1YB656
1YB671 - YB672
1YB851 - YB863
1YB871 - YB874
1YB881 - YB893
1YB901 - YB903
1YB911
1YB961 - YB975
1YB981
1YB986 - YB996
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GroupVariable Number
1YC001 - YC030
1YC051 - YC084
1YC091 - YC095
1YC101 - YC104
1YC111 - YC113
1YC121
1YC126 - YC127
1YC136 - YC141
1YC146 - YC147
1YC151 - YC156
1YC166 - YC171
1YC176 - YC179
1YC186 - YC190
1YC201 - YC203
1YC206 - YC207
1YC301 - YC305
1YC321 - YC387
1YC391 - YC394
1YC396
1YC401 - YC417
1YC421 - YC422
1YC426 - YC428
1YC436 - YC439
1YC441 - YC448
1YC451 - YC455
1YC459
1YC461 - YC467
1YC471 - YC499
1YC501 - YC526
1YC571 - YC583
1YC587 - YC589
1YC591 - YC593
1YC601 - YC655
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GroupVariable Number
1YC681 - YC696
1YC701 - YC715
1YC720 - YC725
1YC727 - YC752
1YC761 - YC770
1YC781 - YC793
1YC801 - YC892
1YC901 - YC907
1YC921 - YC922
1YC931 - YC932
1YC941 - YC951
1YC971 - YC978
1YC981 - YC983
1YD001 - YD007
1YD021 - YD025
1YD041 - YD057
1YD081 - YD084
1YD101 - YD113
1YD121 - YD126
1YD151 - YD159
1YD171 - YD172
1YD201 - YD203
1YD206 - YD209
1YD216 - YD219
1YD251 - YD254
1YD256 - YD257
1YD261
1YD301 - YD334
1YD391
1YD401 - YD410
1YD412 - YD417
1YD481 - YD485
1YD491 - YD499
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GroupVariable Number
1YD501 - YD512
1YD531 - YD535
1YD541 - YD547
1YD561 - YD564
1YD571 - YD572
1YD591 - YD595
1YD601 - YD612
1YD651 - YD655
1YE001 - YE020
1YE051
1YE101 - YE109
1YE151 - YE157
1YE171 - YE172
1YE201 - YE206
1YE301 - YE305
1YE321 - YE326
1YE371 - YE383
1YF001 - YF011
1YF021 - YF049
1YF051 - YF065
1YF086 - YF087
1YF106 - YF107
1YF111 - YF114
1YF116 - YF119
1YF121 - YF128
1YF176 - YF178
1YF191 - YF192
1YF201 - YF276
1YF401 - YF402
1YF431 - YF432
1YF441 - YF442
1YF451 - YF460
1YF501 - YF599
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GroupVariable Number
1YF601 - YF610
1YF701 - YF707
1YF801 - YF803
1YF831 - YF832
1YF836 - YF838
1YF901 - YF905
1YF921 - YF927
1YF951
1YG001 - YG044
1YG061 - YG064
1YG066 - YG089
1YG091 - YG099
1YG101 - YG104
1YG111 - YG114
1YG116 - YG128
1YG201 - YG205
1YG211 - YG214
1YG221 - YG224
1YG251 - YG252
1YG501 - YG511
1YG601 - YG602
1YG701
1YG711
1YH001 - YH012
1YH031 - YH055
1YH071 - YH079
1YH101 - YH132
1YH201 - YH202
1YH206 - YH207
1YH301 - YH306
1YH321 - YH322
1YH501
1YJ001 - YJ013
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GroupVariable Number
1YJ021
1YJ471 - YJ480
1YJ501 - YJ517
1YJ531 - YJ579
1YJ591 - YJ599
1YJ631 - YJ632
1YJ671 - YJ694
1YJ801 - YJ867
1YJ871 - YJ880
1YJ901 - YJ904
1YJ908 - YJ929
1YJ931 - YJ937
1YJ941 - YJ956
1YJ961
1YJ976 - YJ977
1YK001 - YK007
1YK101 - YK104
1YK111 - YK112
1YK121 - YK122
1YK131 - YK133
1YK136 - YK139
1YK141 - YK142
1YK146 - YK148
1YK151 - YK154
1YK161 - YK167
1YK171
1YK176 - YK177
1YK186
1YK191
1YK196
1YK201 - YK202
1YK301 - YK314
1YK321 - YK340
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GroupVariable Number
1YK361 - YK378
1YK401 - YK406
1YK426 - YK427
1YK431 - YK450
1YK456 - YK467
1YK471 - YK473
1YK476
1YK480 - YK487
1YK491
1YK495 - YK498
1YK511 - YK516
1YK521 - YK530
1YK551 - YK571
1YK576 - YK577
1YK580 - YK585
1YK601 - YK602
1YK606 - YK607
1YK611 - YK616
1YK621 - YK634
1YK641 - YK644
1YK651 - YK665
1YK671 - YK672
1YK676 - YK677
1YK681 - YK686
1YK691
1YK701 - YK713
1YK716 - YK719
1YK721 - YK741
1YK751 - YK770
1YK776 - YK778
1YK781 - YK785
1YK791 - YK792
1YK796 - YK797
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GroupVariable Number
1YK801 - YK899
1YK901 - YK912
1YK918 - YK919
1YK921 - YK928
1YK941 - YK996
1YL001 - YL005
1YL011 - YL016
1YL021 - YL024
1YL051 - YL052
1YL056 - YL057
1YL061
1YL066 - YL069
1YL076 - YL077
1YL101 - YL136
1YL201 - YL227
1YL271 - YL272
1YL281 - YL284
1YL301 - YL303
1YL311 - YL314
1YL316 - YL321
1YL351 - YL353
1YL371 - YL374
1YL401
1YL421 - YL429
1YL431 - YL444
1YL461 - YL478
1YL501 - YL509
1YL531 - YL534
1YL541 - YL545
1YL561 - YL571
1YL591 - YL598
1YL601 - YL606
1YL611 - YL612
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GroupVariable Number
1YL616 - YL617
1YL621
1YL626
1YL631 - YL634
1YL636 - YL637
1YL661 - YL664
1YL676 - YL681
1YL691
1YL696 - YL697
1YL701 - YL707
1YL731
1YL751 - YL752
1YL756 - YL757
1YL761 - YL779
1YL796 - YL797
1YL801 - YL815
1YL901 - YL910
1YL921 - YL940
1YL951 - YL968
1YM101 - YM103
1YM201 - YM242
1YM251 - YM299
1YM301 - YM399
1YM471
1YM481 - YM484
1YM501 - YM515
1YM521 - YM522
1YM541
1YM551 - YM553
1YM571 - YM572
1YM581 - YM582
1YM591 - YM599
1YM631 - YM634
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GroupVariable Number
1YM641 - YM652
1YM671 - YM674
1YM691 - YM698
1YM701 - YM710
1YM761 - YM765
1YN001 - YN016
1YN021 - YN024
1YN061
1YN071 - YN082
1YN091 - YN092
1YN101 - YN112
1YN121
1YN201 - YN202
1YN211 - YN219
1YN231 - YN236
1YN261
1YN501
1YQ001 - YQ003
1YQ011 - YQ018
1YQ026 - YQ027
1YQ036 - YQ042
1YQ201
1YQ231
1YQ241 - YQ242
1YQ291 - YQ295
1YQ401 - YQ403
1YR001 - YR006
1YR051 - YR053
1YR101
1YR111 - YR113
1YR126
1YR141
1YR166
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GroupVariable Number
1YR201 - YR204
1YR231 - YR233
1YR301
1YR401
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will prevent the Captain's and First Officer's rudder pedals from
operating incorrectly because of any protruding screw in the rudder pedal heel rest cover assembly. If
this Service Bulletin is not accomplished, this condition could restrict rudder pedal motion and differential
braking during takeoff or landing potentially leading to a high speed runway excursion.
A pilot from an operator reported that a flight was aborted during takeoff because the rudder pedals
were not operating correctly. The airplane was returned to gate safely with normal tiller operation. The
operator did further investigation, and found a protruding screw at the outboard edge of the Captain's
rudder pedal heel rest cover assembly adjacent to the rudder pedal. Boeing has implemented a process
of monitoring the screw installation starting at Line Number 3556 to ensure conformance to engineering
requirements.
This service bulletin gives instructions to do a one-time torque check of the captain and first officers
rudder pedal heel rest cover assembly screw locations adjacent to the rudder pedals.
Boeing Service Related Problem (SRP) 737NG-27-0274 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737NG FTD 25-15004 is related to this service bulletin.
Revision 1 was sent to remove the part numbers for the rudder pedal heel rest cover screw and nutplates.
Revision 2 is sent to give information that lets an optional screw be installed if replacement is necessary.
This revision also has better described work instructions, where some instructions are moved to new
Figures and to make sure necessary tests are done.
D. Description
Get access to the flight compartment and do a one-time torque check of the Captain's and First Officer's
rudder pedal heel rest cover assembly screw locations adjacent to the rudder pedals. If the torque
requirement at all screw locations is correct, no more work is necessary. If any screw does not hold a
torque or is not fully seated then replace the screw and nutplate. Do an operational check of the rudder
pedals to make sure that motion is not restricted.
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Effects of this Revision on airplanes on which the Orignal Issue or Revision 1 was previously done:
None.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
211, 212737-600, 737-700, 737-700C,
737-800, 737-900, 737-900ER
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2016-NM-090-AD, is
related to this service bulletin.
Boeing recommends that the torque check be done within 21 months after the Original Issue date of
this service bulletin and any necessary corrections given in this service bulletin be done before further
flight.
F. Approval
NOTE: The approval statement that follows is valid for 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 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.
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).
For 737-700C models that have APB winglets installed by STC number ST00830SE, the operator is
responsible for obtaining appropriate regulatory agency approval before incorporating this service
bulletin if the bulletin is in the area affected by blended winglets.
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.
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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.
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).
For BBJ models that have APB winglets installed by STC number ST00830SE, the operator is
responsible for obtaining appropriate regulatory agency approval before incorporating this service
bulletin if the bulletin is in the area affected by blended winglets.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this service bulletin 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
Elapsed HoursTask HoursNumber of PersonsTask
0.250.251Open Access
0.500.501FIGURE 1
0.500.501FIGURE 2
1.001.001FIGURE 3 (a)
1.001.001FIGURE 4 (a)
0.500.501FIGURE 5 (b)
0.500.501FIGURE 6 (b)
0.250.251Close Access
0.600.601Test
2.102.10TOTAL FOR EACH AIRPLANE
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Elapsed HoursTask HoursNumber of PersonsTask
(a) This task is not included in the total. This task is necessary if a screw and
mating nutplate does not hold the specified torque.
(b) This task is optional and is not included in the total. Time is for a quantity of
6 screws.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 737NG-27-0274
b. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2016-NM-090-AD
c. Service Bulletin Index D6-19567
d. Standard Overhaul Practices Manual (SOPM) 20-50-01
e. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 20-50-11, 27-21-31 , 51-21-73
f. 737-600 Structural Repair Manual (SRM) 51-40-01
g. 737-700 Structural Repair Manual (SRM) 51-40-01
h. 737-700CONV Structural Repair Manual (SRM) 51-40-01
i. 737-800 Structural Repair Manual (SRM) 51-40-01
j. 737-900 Structural Repair Manual (SRM) 51-40-01
k. 737-900ER Structural Repair Manual (SRM) 51-40-01
l. 737NG Fleet Team Digest (FTD) 25-15004
2. Data Supplied with this Service Bulletin:
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
HEEL REST INSTL - RUDDER PEDAL251A3120
SUPPORT INSTL - FORWARD PANEL233A2301
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
27-21737-600/700/800/900 Aircraft Maintenance
Manual - Practices and Procedures
27-21737-600/700/800/900 Illustrated Parts Cata-
log
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
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 29

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the torque check and/or repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesExisting Part NumberNameQTYPart Number /
Specification
(a) (b) (c) (f)
(g)
FH10F8TPKL10GY OR
BACS12ER3K8GR
SCREW, 100 DEG HEAD12FH10F8TP-
KL10GY OR
BACS12ER3K8GR
(BACS12ER3K8
optional)
(b) (c)BACN10JR3CFDNUTPLATE8BACN10JR3CFD
(b) (c) (d)BACN10KA3BCD OR
BACN10JY3CM
NUTPLATE4BACN10KA3BCD
OR
BACN10JY3CM
(e) (f)-ENAMEL, GLOSS2 OzBMS 10-60, Type
II
(a) BACS12ER3K8 screws do not have a painted head.
(b) Discard the existing part.
(c) Maximum quantity given. Refer to FIGURE 3 and FIGURE 4 for usage.
(d) Use a new nutplate that has the same part number as the removed nutplate.
(e) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
(f) Maximum quantity given. Enamel is optional to paint a screw head to match the color of adjacent rudder
pedal heel rest cover assembly.
(g) Use a new screw that has the same part number as the removed screw. BACS12ER3K8 can be used
as an option.
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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. 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.
— 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.
7. 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.
8. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
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9. 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.
10. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
12. 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. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub step. 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. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Get access to the flight compartment.
2. RC - Do the one-time torque check of the Captain's rudder pedal heel rest cover assembly screws
in accordance with FIGURE 1.
a. If the torque requirement at all locations is correct, continue to step 3.
b. Replace any screw and mating nutplate that does not hold the specified torque:
(1) RC Exempt - Refer to 737-600/700/800/900 AMM 27-21-31, Rudder Pedals Removal,
as an accepted procedure to get access to the nutplate(s).
(2) Replace the screw and mating nutplate in accordance with FIGURE 3.
NOTE: FIGURE 3 gives the quantity for the replacement of one screw and mating
nutplate. Make sure you replace all location of screws and mating nutplates that
do not hold the specified torque.
c. RC Exempt - OPTION: Apply paint to the screw head(s) in accordance with FIGURE 5.
NOTE: FIGURE 5 shows the maximum quantity of screws to paint. The quantity of screws
to paint is the choice of the operator.
d. RC Exempt - Close access to the nutplate(s). Refer to737-600/700/800/900 AMM 27-21-31,
Rudder Pedals Installation, as an accepted procedure.
3. RC - Do the one-time torque check of the First Officer's rudder pedal heel rest cover assembly
screws in accordance with FIGURE 2.
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a. If the torque requirement at all locations is correct, continue to step 4.
b. Replace any screw and mating nutplate that does not hold the specified torque:
(1) RC Exempt - Refer to 737-600/700/800/900 AMM 27-21-31, Rudder Pedals Removal,
as an accepted procedure to get access to the nutplate(s).
(2) Replace the screw and mating nutplate in accordance with FIGURE 4.
NOTE: FIGURE 4 gives the quantity for the replacement of one screw and mating
nutplate. Make sure you replace all location of screws and mating nutplates that
do not hold the specified torque.
c. RC Exempt - OPTION: Apply paint to the screw head(s) in accordance with FIGURE 6.
NOTE: FIGURE 6 shows the maximum quantity of screws to paint. The quantity of screws
to paint is the choice of the operator.
d. RC Exempt - Close access to the nutplate(s). Refer to737-600/700/800/900 AMM 27-21-31,
Rudder Pedals Installation, as an accepted procedure.
4. If one or more nutplate and screw was replaced on the Captain's side, do the Captain's rudder
pedal operation test.
a. Turn the rudder pedal adjustment crank to move the Captain's pedals full forward.
(1) Push the Captain's left pedal forward until it touches the stop and hold.
(2) Make sure that pedal travel is not restricted by surrounding screws.
(3) Push the Captain's right pedal forward until it touches the stop and hold.
(4) Make sure that pedal travel is not restricted by surrounding screws.
b. Turn the rudder pedal adjustment crank to move the Captain's pedals full aft.
(1) Push the Captain's left pedal forward until it touches the stop and hold.
(2) Make sure that pedal travel is not restricted by surrounding screws.
(3) Push the Captain's right pedal forward until it touches the stop and hold.
(4) Make sure that pedal travel is not restricted by surrounding screws.
5. If one or more nutplate and screw was replaced on the First Officer's side, do the First Officer's
rudder pedal operation test.
a. Turn the rudder pedal adjustment crank to move the First Officer's pedals full forward.
(1) Push the First Officer's left pedal forward until it touches the stop and hold.
(2) Make sure that pedal travel is not restricted by surrounding screws.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-25A1732
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### Page 34

(3) Push the First Officer's right pedal forward until it touches the stop and hold.
(4) Make sure that pedal travel is not restricted by surrounding screws.
b. Turn the rudder pedal adjustment crank to move the First Officer's pedals full aft.
(1) Push the First Officer's left pedal forward until it touches the stop and hold.
(2) Make sure that pedal travel is not restricted by surrounding screws.
(3) Push the First Officer's right pedal forward until it touches the stop and hold.
(4) Make sure that pedal travel is not restricted by surrounding screws.
6. If the rudder pedals operation test fails, do above corrective actions, repeat the test, and do
applicable corrective actions until the rudder pedals operation test passes.
7. Put the airplane back to a serviceable condition.
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
CAPTAIN'S
FLIGHT COMPARTMENT
TYPICAL
2479826
FIGURE 1: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - TORQUE CHECK
(SHEET 1 OF 2)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  35 of 46

### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
Torque to 34-36 inch
pounds. Refer to
737-
600/700/800/900
AMM 20-50-11 as
an accepted proce-
dure.
6-SCREWTorque1
FIGURE 1: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - TORQUE CHECK
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
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ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
FIRST OFFICER'S
FLIGHT COMPARTMENT
TYPICAL
2479827
FIGURE 2: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - TORQUE CHECK
(SHEET 1 OF 2)
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Revision 2 April 13, 2017  Export Controlled ECCN: 9E991 - BOEING  737-25A1732
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  37 of 46

### Page 38

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 each airplane.
More DataQtyIdentificationNameTaskStep
Torque to 34-36 inch
pounds. Refer to
737-
600/700/800/900
AMM 20-50-11 as
an accepted proce-
dure.
6-SCREWTorque1
FIGURE 2: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - TORQUE CHECK
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
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BOEING SERVICE BULLETIN 737-25A1732
ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
CAPTAIN'S
A
FLIGHT COMPARTMENT
TYPICAL
2560140
FIGURE 3: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY -
SCREW AND NUTPLATE REPLACEMENT
(SHEET 1 OF 2)
Original Issue: April 12, 2016
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  39 of 46

### Page 40

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 each nutplate/screw location that does not hold
the specified torque on the Captain's side.
More DataQtyIdentificationNameTaskStep
1-SCREWRemove1
1-NUTPLATERemove
(b)1BACN10JR3CFDNUTPLATEInstall (New)2
(c)1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWInstall (New)
Torque to 34-36 inch
pounds.
1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWTorque
(a) (b)1BACN10KA3BCD OR
BACN10JY3CM
NUTPLATEInstall (New)3
(c)1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWInstall (New)
Torque to 34-36 inch
pounds.
1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWTorque
(a) Use a new nutplate that has the same part number as the removed nutplate.
(b) Refer to 737-600 SRM 51-40-01 or 737-700 SRM 51-40-01 or 737-700CONV SRM 51-40-01 or 737-800
SRM 51-40-01 or 737-900 SRM 51-40-01 or 737-900ER SRM 51-40-01 as an accepted procedure.
(c) Use a new screw that has the same part number as the removed screw. BACS12ER3K8 can be used as
an option.
FIGURE 3: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY -
SCREW AND NUTPLATE REPLACEMENT
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
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ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
FIRST OFFICER'S
FLIGHT COMPARTMENT
TYPICAL
FIGURE 4: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
- SCREW AND NUTPLATE REPLACEMENT
(SHEET 1 OF 2)
Original Issue: April 12, 2016
Revision 2 April 13, 2017  Export Controlled ECCN: 9E991 - BOEING  737-25A1732
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  41 of 46

### Page 42

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 each nutplate/screw location that does not hold
the specified torque on the First Officer's side.
More DataQtyIdentificationNameTaskStep
1-SCREWRemove1
1-NUTPLATERemove
(b)1BACN10JR3CFDNUTPLATEInstall (New)2
(c)1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWInstall (New)
Torque to 34-36 inch
pounds.
1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWTorque
(a) (b)1BACN10KA3BCD OR
BACN10JY3CM
NUTPLATEInstall (New)3
(c)1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWInstall (New)
Torque to 34-36 inch
pounds.
1FH10F8TPKL10GY OR
BACS12ER3K8GR
(BACS12ER3K8 option-
al)
SCREWTorque
(a) Use a new nutplate that has the same part number as the removed nutplate.
(b) Refer to 737-600 SRM 51-40-01 or 737-700 SRM 51-40-01 or 737-700CONV SRM 51-40-01 or 737-800
SRM 51-40-01 or 737-900 SRM 51-40-01 or 737-900ER SRM 51-40-01 as an accepted procedure.
(c) Use a new screw that has the same part number as the removed screw. BACS12ER3K8 can be used as
an option.
FIGURE 4: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
- SCREW AND NUTPLATE REPLACEMENT
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
CAPTAIN'S
A
FLIGHT COMPARTMENT
TYPICAL
2565692
FIGURE 5: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - PAINT
(SHEET 1 OF 2)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 46

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)-BMS 10-60, TYPE IIENAMEL, GLOSSApply1
(a) Apply one layer to the screw head. Use the same color as the adjacent rudder pedal heel rest cover as-
sembly. Refer to 737-600/700/800/900 AMM 51-21-73 as an accepted procedure.
FIGURE 5: FLIGHT COMPARTMENT - CAPTAIN'S RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - PAINT
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 737-25A1732
ALERT  ALERT
FIRST OFFICER'S
FLIGHT COMPARTMENT
TYPICAL  2565693
FIGURE 6: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - PAINT
(SHEET 1 OF 2)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  45 of 46

### Page 46

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)-BMS 10-60, TYPE IIENAMEL, GLOSSApply1
(a) Apply one layer to the screw head. Use the same color as the adjacent rudder pedal heel rest cover as-
sembly. Refer to 737-600/700/800/900 AMM 51-21-73 as an accepted procedure.
FIGURE 6: FLIGHT COMPARTMENT - FIRST OFFICERS RUDDER PEDAL HEEL REST COVER ASSEMBLY
SCREWS - PAINT
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 12, 2016
737-25A1732Revision 2 April 13, 2017
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BOEING SERVICE BULLETIN 737-25A1732
ALERTALERT

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