# Boeing Alert Service Bulletin 747-27A2513: Revision 1

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- Document: [Boeing Alert Service Bulletin 747-27A2513](https://openairdocs.org/service-documents/boeing/747-27a2513.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 747-27A2513 Revision 01
- Pages: 108
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## Text

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### Page 1

Commercial
Airplanes
747
Service Bulletin
Number: 747-27A2513
Original Issue: February 04, 2014
Revision 1: July 18, 2014
ATA System: 2731 2900 5510
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator
Installation and Power Control Package Replacement
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 © 2014 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Unpublished Work.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
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connection with this document unless provided in writing by Boeing.
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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  ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 3
E. Compliance .............................................. 1 3
F . A p p r o v a l  ............................................... 1 3
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 4
J . R e f e r e n c e s  .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 9
C. Parts Necessary for Each Airplane ................................. 1 9
1 . K i t s / P a r t s  ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 2 4
3. Parts Modified and Reidentified ................................ 2 5
4. Parts Removed and Not Replaced .............................. 2 5
D. Parts Necessary to Change Spares ................................. 2 5
E. Special Tooling - Price and Availability ............................... 2 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES
R E M O V A L  -  L E F T  S I D E .................................... 3 0
FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE ............. 3 4
F I G U R E  3 : F A S T E N E R S  A N D  B R A C K E T S  R E M O V A L  -  L E F T  S I D E .................. 3 6
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE .... 3 9
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE . . 47
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE ....... 5 5
FIGURE 7: WIRE BUNDLE W1656 AND W4615 ROUTING - LEFT SIDE ................ 6 1
FIGURE 8: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - LEFT SIDE
.................................................. 6 4
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FIGURE 9: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES
R E M O V A L  -  R I G H T  S I D E ................................... 6 8
FIGURE 10: LOOSEN THE WIRE BUNDLE W1912 AND W4616 - RIGHT SIDE ............ 7 3
F I G U R E  1 1 : F A S T E N E R S  A N D  B R A C K E T S  R E M O V A L  -  R I G H T  S I D E ................. 7 5
FIGURE 12: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . . . 78
FIGURE 13: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - RIGHT SIDE . 85
FIGURE 14: BRACKET INSTALLATION - RIGHT SIDE .......................... 9 2
FIGURE 15: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - RIGHT SIDE ...... 9 5
FIGURE 16: WIRE BUNDLE W1912 AND W4616 ROUTING - RIGHT SIDE .............. 1 0 2
FIGURE 17: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) INSTALLATION - RIGHT SIDE
................................................. 1 0 5
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Commercial
Airplanes
747
Service Bulletin
Revision Transmittal SheetNumber: 747-27A2513Original Issue: February 04, 2014
Revision 1: July 18, 2014
ATA System: 2731 2900 5510
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator
Installation and Power Control Package Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
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.
No more work is necessary on the airplanes changed in accordance with the original issue of this service bulletin.
REASON FOR REVISION
This revision is sent to make corrections to fastener length and wire clamp size, revised the manpower as found
during the service bulletin validation.
As a part of a service bulletin validation program, this change was completed on airplane RC008 by Service
Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin. The change
completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group 1 airplane.
These sections were changed:
1. Paragraph 1.A.1., Airplanes: Removed the Notes paragraph.
2. Paragraph 1.G., Manpower: Changed the task hour table.
3. Paragraph 1.J.1., References: Revised Existing Data step h and i.
4. Paragraph 2.B., Industry Support Information: Changed the warranty statement
5. Paragraph 2.C.1., Kits/Parts: Changed the part numbers, added extra quantity to the kit, and added
the foot note (c).
6. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Changed the part number.
7. Figures 2 and 10: Revised the step table to add foot note (a).
8. Figures 4 and 7: Changed the step table and fastener table to correct the fastener length and clamp
size, and added extra quantity to the extra parts table.
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9. Figures 5: Changed sheet 2, step table, and added extra quantity to the extra parts table.
10. Figure 6: Changed sheet 2, step table, and added extra quantity to the extra parts table. Revised the
foot note (d).
11. Figure 8: Changed sheet 1.
12. Figures 9: Changed the step table.
13. Figures 12, 13, 14 and 16: Changed the step table and fastener table to correct the fastener length
and clamp size and added extra quantity to the extra parts table.
14. Figure 15: Changed sheet 3, step table and added extra quantity to the extra parts table. Revised the
foot note (d).
The data given in Information Notices 747-27A2513 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
February 04, 2014Original Issue:
July 18, 2014Revision 1:
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Commercial
Airplanes
747
Service Bulletin
SummaryNumber: 747-27A2513Original Issue: February 04, 2014
Revision 1: July 18, 2014
ATA System: 2731 2900 5510
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator
Installation and Power Control Package Replacement
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration that can
occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent flutter could
result in the possible loss of control of the airplane.
Boeing analysis found that the existing internal compensators to the two inboard elevator power control package
(PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface when two hydraulic
systems are not functional. This service bulletin installs two (2) larger external compensators for each of the two
(2) inboard elevator PCP. This replacement provides sufficient hydraulic capacity to prevent divergent flutter or
unacceptable vibration.
This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions to
rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator PCP
with internal compensators removed. This service bulletin gives instructions to replace the existing PCP internal
compensators with larger external compensators and new design of inboard elevator PCP. Replace existing
brackets and hydraulic tubing to accommodate the new external compensators.
Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 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 ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
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ReferenceAffectedPlanning Data
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/PartsYesKits/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 (PRR 86601-5)
Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic tubes and
associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing electrical brackets
and rivets. Install inboard and outboard compensator mounting brackets. Install inboard and outboard
compensators, and hydraulic tubes. Route the wire bundles. Install inboard elevator PCP. Bleed the hydraulic
systems. Do the operational test. Close access to the left and right inboard elevator PCP. Put the airplane back
to a serviceable condition.
EFFECTIVITY
747-8 and 747-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 60 months after the Original
Issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of January 28, 2013. Please refer to
Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original
issue date of this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-27A2513
REPLACE  SSTA
HYDRAULIC 172.4
TUBES
SSTA
210
SSTA
REPLACE HYDRAULIC  235
TUBE
SSTA
260
INSTALL NEW
BLEED VALVE  INSTALL TEE AND  BRACKET AND  COMPENSATOR
REPLACE
POWER
CONTROL
PACKAGE
INSTALL NEW BRACKET
COMPENSATOR AND TEE
REPLACE TEE, INSTALL
ELBOW AND BLEED VALVE  INBOARD ELEVATOR COMPENSATOR
LEFT SIDE SHOWN
RIGHT SIDE SIMILAR
2267309
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Commercial
Airplanes
747
Service Bulletin
Number: 747-27A2513
Original Issue: February 04, 2014
Revision 1: July 18, 2014
ATA System: 2731 2900 5510
SUBJECT: FLIGHT CONTROLS - Elevator Control System - Inboard Elevator Compensator
Installation and Power Control Package Replacement
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 86601-5 for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
747-8 and 747-8F airplanes line number 1420 through 1434, and
1436 through 1491.
-1
Airplane Models:
747-8, 747-8F
GroupVariable Number
1RC001 - RC008
1RC022 - RC030
1RC501 - RC511
1RC521 - RC528
1RC541
1RC546 - RC549
1RC551 - RC563
1RC571 - RC582
1RC601 - RC605
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2. Spares Affected
Examine your spares supply for the parts or components identified below . If any parts or
components are found, refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator
for the recommended action.
Serial NumberPart Number
N/A327400-1009
B. Concurrent Requirements
None.
C. Reason
The change given in this service bulletin will help to prevent divergent flutter or unacceptable vibration
that can occur in certain parts of the flight envelope if two hydraulic systems are not functional. Divergent
flutter could result in the possible loss of control of the airplane.
Boeing analysis found that the existing internal compensators to the two inboard elevator power control
package (PCP) provided insufficient hydraulic capacity for retained stiffness of the elevator surface
when two hydraulic systems are not functional. This service bulletin installs two (2) larger external
compensators for each of the two (2) inboard elevator PCP. This replacement provides sufficient
hydraulic capacity to prevent divergent flutter or unacceptable vibration.
This service bulletin also refers to a Parker service bulletin. The Parker service bulletin gives instructions
to rework the existing inboard elevator PCP that has internal compensators into the new inboard elevator
PCP with internal compensators removed. This service bulletin gives instructions to replace the existing
PCP internal compensators with larger external compensators and new design of inboard elevator
PCP. Replace existing brackets and hydraulic tubing to accommodate the new external compensators.
Boeing Service Related Problem (SRP) 747-SRP-27-0235 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 27-13004 is related to this service bulletin.
As a part of a service bulletin validation program, this change was completed on airplane RC008 by
Service Bulletin 747-27A2513, Original Issue, before the release of Revision 1 of this service bulletin.
The change completed on airplane RC008 by Service Bulletin 747-27A2513 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane RC008 has the configuration of a Group
1 airplane.
Revision 1 is sent to make corrections to fastener length and wire clamp size, revised the manpower
as found during the service bulletin validation.
The data given in Information Notices 747-27A2513 IN 01 is included in this revision.
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D. Description
Open access to the left and right inboard elevator PCP. Remove the inboard elevator PCP, hydraulic
tubes and associated hardware. Remove the clamps and loosen the wire bundles. Remove the existing
electrical brackets and rivets. Install inboard and outboard compensator mounting brackets. Install
inboard and outboard compensators, and hydraulic tubes. Route the wire bundles. Install inboard
elevator PCP. Bleed the hydraulic systems. Do the operational test. Close access to the left and right
inboard elevator PCP. Put the airplane back to a serviceable condition.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue
oft his service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
313, 314, 334, 335, 339, 344, 345, 349747-8, 747-8F
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.
Boeing recommends that the change given in this service bulletin be done within 60 months after the
Original Issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change 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
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• Time to make the parts
• Time to find the tools.
Elapsed HoursTask HoursNumber of PersonsTask
1.001.001Open Access
2.306.903Figure 1
1.001.001Figure 2
1.001.001Figure 3
2.004.002Figure 4
2.004.002Figure 5
2.004.002Figure 6
3.003.001Figure 7
3.009.003Figure 8
2.306.903Figure 9
1.001.001Figure 10
1.001.001Figure 11
2.004.002Figure 12
2.004.002Figure 13
0.500.501Figure 14
2.004.002Figure 15
3.003.001Figure 16
3.009.003Figure 17
4.008.002Test
1.001.001Close Access
39.1076.30TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 91650.4 lb-in+ 34.0 lbGroup 1
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Engineering Change Memo PRR 86601-5
b. Boeing Service Related Problem (SRP) 747-SRP-27-0235
c. Service Bulletin Index D6-30300
d. Standard Overhaul Practices Manual (SOPM) 20-41-01, 20-41-02, 20-43-03, 20-44-01,
20-50-01, 20-50-02, 20-50-05, 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00
f. 747 Fleet Team Digest (FTD) 27-13004
g. 747-8 Aircraft Maintenance Manual (AMM) 06-09-06, 20-11-05, 20-11-18, 20-51-01, 27-31-07,
29-11-00
h. 747-8F Structural Repair Manual (SRM) 51-40-02, 51-40-04
i. 747-8P Structural Repair Manual (SRM) 51-40-02, 51-40-04
j. Parker Service Bulletin 327400-27-001
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
WIRE BUNDLE INSTALLATION LH HORIZONTAL STABILIZER
AND HORIZONTAL FUEL
288U8267
WIRE BUNDLE INSTALLATION RH HORIZONTAL STABILIZER
AND HORIZONTAL FUEL
288U8268
POWER CONTROL ACTUATOR INSTL - INBOARD ELEVATOR251U2500
HYDRAULIC TUBING INSTL - SECTION 81272U8101
HYDRAULIC TUBING INSTL - SECTION 82272U8201
SPAR INSTL - REAR, HORIZONTAL STAB182U1000
TRAILING EDGE ASSY - FIXED HORIZONTAL STABILIZER183U1000
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.
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K. Publications Affected
1. Publications:
Chapter-SectionPublication
27-31747 Aircraft Maintenance Manual
27-31747 Fault Isolation Manual
11-32, 27-21, 27-31747 Illustrated Parts Catalog
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 but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
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REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameNumber
$51,789.005252December 20,
2013
Top Kit - 747-8 IN-
BOARD ELEVATOR
REMOTE COMPEN-
SATOR - REVISION
015U1960-1
1January 9,
2014
12March 7, 2014
2March 21,
2014
3April 4, 2014
2April 18, 2014
3May 5, 2014
2May 19, 2014
3Jun 5, 2014
2Jun 18, 2014
3July 7, 2014
2July 18, 2014
3August 4, 2014
2August 18,
2014
3September 5,
2014
2September 18,
2014
3October 3,
2014
3October 17,
2014
3November 4,
2014
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### Page 19

B. Industry Support Information
Boeing warranty remedies are available for 747 airplanes in warranty as of January 28, 2013. For labor
hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Fleet Support
Contracts - Warranty. The kits for airplanes in warranty as of that date will be supplied at no charge.
Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number and
reference the airplane variable number(s) in your purchase order. In addition, labor hour and material
reimbursement is available for the PCP modification included in this service bulletin for 747 airplanes
in warranty as of January 28, 2013. The warranty remedies will expire eight years after the original
release date of this service bulletin.
A limited number of seed unit PCPs are available to support incorporation of this service bulletin. To
inquire about availability and scheduling, please contact Boeing Retrofit and Modification via e-mail at
the following address: MMRetrofitMods@boeing.com. Please reference the service bulletin number in
your message
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
Figure Kit
1287654Top Kit
111111015U1960-1
Figure Kit
1716151413Top Kit
11111015U1960-1
ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1287654
Qty
MOUNTING
BRACKET, LEFT
OUTBD - COM-
PENSATOR, ELE-
VATOR PCU
....1.252U3102-11
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### Page 20

ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1287654
Qty
MOUNTING
BRACKET ASSY,
RIGHT INBD -
COMPENSATOR,
ELEVATOR PCU
1.....252U3102-12
MOUNTING
BRACKET ASSY,
LEFT INBD - COM-
PENSATOR, ELE-
VATOR PCU
.....1252U3102-13
(a), (b)272U8190-26TUBE ASSY...1..272U8190-32
(a), (b)272U8190-19TUBE ASSY...1..272U8190-34
TUBE ASSY...1..272U8190-35
TUBE ASSY...1..272U8190-36
(a), (b)272U8190-17TUBE ASSY...1..272U8190-37
BRACKET ASSEM-
BLY
...1..272U9405-25
BRACKET ASSEM-
BLY
....1.287U0037-33
VALVE ASSY...2..293W6132-1
REMOTE COM-
PENSATOR - UP-
PER RUDDER
...2..463430-1001
(a), (b)BACT16BM100810PTEE...1..AS1009W080810
CLAMP,LOOP...1..AS21919WCE08
CLAMP,LOOP...2..AS21919WCE10
TEE...1..AS4140V100808P
(BACT16BT100808P
optional)
NUT, TUBE,
BULKHEAD
...1..AS5178W10
MARKER.2....BAC27EHY242
BOLT, PROTRUD-
ING HD
3....3BACB30MY10K12X
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### Page 21

ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1287654
Qty
(c)BOLT, PROTRUD-
ING HD
8....8BACB30MY10K8X
(c)BOLT, PROTRUD-
ING HD
....3.BACB30MY8K11X
BOLT, PROTRUD-
ING HD
1....2BACB30MY8K12X
(c)BOLT, PROTRUD-
ING HD
....5.BACB30MY8K14X
(c)BOLT, PROTRUD-
ING HD
....3.BACB30MY8K6X
(c)BOLT, PROTRUD-
ING HD
....3.BACB30MY8K9X
(c)BOLT, HEX HEAD...9..BACB30NM4K11
CLAMP, WIRE
BUNDLE
..3...BACC10GU103
(c)COLLAR13....13BACC30M10
(c)COLLAR1...151BACC30M8
ELBOW, SWVL-
RDCR, 45
...1..BACE21AU1010W
FILLER, FLAT1....1BACF3F015X026NN
RADIUS FILLER....2.BACF3H10RF010HG
FILLER, RECTAN-
GULAR
2....2BACF3H10RF024HF
FILLER, RECTAN-
GULAR
....2.BACF3H10RF040HF
NUT...2..BACN10YR3CD
NUT...9..BACN11Z4CD
SCREW...5..BACS12GU3K10
SCREW..3...BACS12GU3K26
SCREW...1..BACS12GU3K8
SPACER...2..BACS18AF4
TEE, SWIVEL ON
RUN
...1..BACT16AY080808W
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ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1287654
Qty
WASHER...9..BACW10BP4AC
WASHER...6..NAS1149D0316J
WASHER..4...NAS1149D0332J
WASHER, PLAIN...1..NAS1149D1490J
WASHER, PLAIN...9..NAS1149E0432P
SPACERS FOR
RIVETS
..2...NAS42DD6-64FC
(a) This part is used in production.
(b) You cannot use the existing part to replace the new or changed part.
(c) There are more parts than are necessary.
ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1716151413
Qty
MOUNTING
BRACKET, RIGHT
OUTBD - COM-
PENSATOR, ELE-
VATOR PCU
....1252U3102-10
(a), (b)272U8290-7TUBE ASSY..1..272U8290-34
(a), (b)272U8290-9TUBE ASSY..1..272U8290-35
TUBE ASSY..1..272U8290-36
TUBE ASSY..1..272U8290-37
TUBE ASSY..1..272U8290-38
(a), (b)272U8290-10TUBE ASSY..1..272U8290-39
(a), (b)272U8290-20TUBE ASSY..1..272U8290-40
VALVE ASSY..2..293W6132-1
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### Page 23

ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1716151413
Qty
REMOTE COM-
PENSATOR - UP-
PER RUDDER
..2..463430-1001
BRACKET...1.69B80913-5
TEE, FLARELESS..1..AS1005W100808
CLAMP,LOOP..6..AS21919WCE08
(a), (b)BACT16BM100810PTEE..1..AS4134V100808P
(BACT16BN100808P
optional)
MARKER2....BAC27EHY242
BOLT, PROTRUD-
ING HD
....2BACB30MY8K11X
BOLT, PROTRUD-
ING HD
....4BACB30MY8K14X
BOLT, PROTRUD-
ING HD
....2BACB30MY8K9X
(c)BOLT, HEX HEAD..9..BACB30NM4K11
CLAMP, WIRE
BUNDLE
.2...BACC10GU103
(c)COLLAR....13BACC30M8
ELBOW, SWVL-
RDCR, 90
..4..BACE21AW0808W
RADIUS FILLER....2BACF3H10RF010HG
FILLER, RECTAN-
GULAR
....2BACF3H10RF040HF
NUT,CLIP-ON..1..BACN10YD1
NUT1.3..BACN10YR3CD
NUT..9..BACN11Z4CD
RIVET, UNIVER-
SAL HD
...4.BACR15BB5D8C
SCREW.2...BACS12GU3K26
SCREW..4..BACS12GU3K8
(c)SPACER..5..BACS18AF4
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### Page 24

ALL
KIT 015U1960-1
Notes
Existing Part
NumberName
Figure
New Part Number
1716151413
Qty
TEE, SWIVEL ON
RUN
..1..BACT16AY080808W
WASHER..9..BACW10BP4AC
WASHER..8..NAS1149D0316J
WASHER.4...NAS1149D0332J
WASHER, PLAIN..2..NAS1149D1432J
WASHER, PLAIN..9..NAS1149E0432P
SPACERS FOR
RIVETS
.2...NAS42DD6-64FC
(a) This part is used in production.
(b) You cannot use the existing part to replace the new or changed part.
(c) There are more parts than are necessary.
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 NumberNameQty
Part Number/
Specification
(b), (c), (d),
(e)
327400-1009POWER CONTROL PACKAGE -
INBOARD ELEVATOR
2327400-1011
(a)Chemical Conversion Coating5 OzALODINE 600
(f)Clear Skydrol Resistant Topcoating2 OzBAC5710, TYPE
41
(a)Primer2 OzBMS 10-11, TYPE
1
(a)Gloss Enamel2 OzBMS10-60, TYPE
1
(a)Sealant10 OzBMS5-142, TYPE
II
(a)Sealant20 OzBMS5-45
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### Page 25

NotesExisting Part NumberNameQty
Part Number/
Specification
Lockwire3 ftMS20995NC40
(MS20995C41 op-
tional)
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
(b) This part is used in production.
(c) You cannot use the existing part to replace the new or changed part.
(d) Parker service bulletin 327400-27-001 gives instructions to change the existing part to the new part.
(e) The Boeing part specification for the new part is S252U201-4. The Boeing part specification for the ex-
isting part is S252U201-3.
(f) This is a two part protective coating available from Akzo Nobel Aerospace Coatings 1 East Water Street,
Waukegan, IL 60085. Refer to SOPM 20-44-01 for the recommended materials.
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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BLANK PAGE

### Page 27

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 747-8 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747-8
Airplane 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 747-8
Airplane Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
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7. 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.
8. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
9. 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.
10. 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.
11. 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.
12. 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.
13. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
15. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
1. Open access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side.
Refer to 747-8 AMM 06-09-06.
2. Open access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KBL, left side.
Refer to 747-8 AMM 06-09-06.
3. Open access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06.
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### Page 29

4. Horizontal stabilizer rear spar rework - left side. Do these steps:
a. RC - Remove the inboard elevator power control package (PCP) and hydraulic tubes in
accordance with FIGURE 1.
b. Loosen the wire bundles W1656 and W4615 in accordance with FIGURE 2.
c. Remove the fasteners and brackets in accordance with FIGURE 3.
d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 4.
e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 5.
f. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 6.
g. Route the wire bundles W1656 and W4615 in accordance with FIGURE 7.
h. RC - Install the inboard elevator PCP in accordance with FIGURE 8.
5. Horizontal stabilizer rear spar rework - right side. Do these steps:
a. RC - Remove inboard elevator PCP and hydraulic tubes in accordance with FIGURE 9.
b. Loosen the wire bundles W1912 and W4616 in accordance with FIGURE 10.
c. Remove the fasteners and brackets in accordance with FIGURE 11.
d. RC - Install the inboard compensator mounting bracket in accordance with FIGURE 12.
e. RC - Install the outboard compensator mounting bracket in accordance with FIGURE 13.
f. RC - Install the bracket in accordance with FIGURE 14.
g. RC - Install the compensators and hydraulic tubes in accordance with FIGURE 15.
h. Route the wire bundles W1912 and W4616 in accordance with FIGURE 16.
i. RC - Install the inboard elevator PCP in accordance with FIGURE 17.
6. Bleed the hydraulic system 1, 2, 3 and 4. Refer to 747-8 AMM 29-11-00 as an accepted procedure.
7. RC - Do an Operational Test of each inboard elevator PCP. Refer to 747-8 AMM 27-31-07 as an
accepted procedure.
8. Close access door panels 344HBR, 345DBR, 344AT, 344GBR, 344JBR, and 344KBR, right side.
Refer to 747-8 AMM 06-09-06.
9. Close access door panels 334HBL, 335DBL, 334AT, 334GBL, 334JBL, and 334KB, left side. Refer
to 747-8 AMM 06-09-06.
10. Close access door panels 338AZ, 339AZ and 349AZ. Refer to 747-8 AMM 06-09-06.
11. Put the airplane back to serviceable condition.
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
172.4
SSTA
210
SSTA
235
SSTA
260
SSTA
285
SSTA
360
FWD
2277016
FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL
- LEFT SIDE
(SHEET 1 OF 4)
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### Page 31

FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL
- LEFT SIDE
(SHEET 2 OF 4)
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### Page 32

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
Keep all the screw,
washers and nut.
2-ClampRemove / Keep1
(a)4-Hose AssyRemove / Keep2
Refer to 747-8 AMM
27-31-07 as an ac-
cepted procedure.
1327400-1009Power Control Package
Inboard Elevator
Remove3
Keep all the screws,
washers and clip
nuts.
2-ClampRemove4
(b)1272U8190-19Tube AssyRemove
FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL
- LEFT SIDE
(SHEET 3 OF 4)
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### Page 33

More DataQtyIdentificationNameTaskStep
Keep all the fasten-
ers and hardware.
1-Clamp Block AssyRemove / Keep5
Keep all the screws,
washers and five (5)
clip nuts.
6-ClampRemove / Keep6
(b)1272U8190-26Tube AssyRemove
Keep all the screws,
washers and clip
nuts.
6-ClampRemove / Keep7
(b)1272U8190-17Tube AssyRemove
1-Lock NutRemove8
1-WasherRemove
1BACT16BM100810PTeeRemove
1-ScrewRemove9
1-ClampRemove / Keep
1-WasherRemove / Keep
1-Clip NutRemove
(a) Refer to 747-8 AMM 20-11-18 as an accepted procedure.
(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.
FIGURE 1: INBOARD ELEVATOR POWER CONTROL PACKAGE (PCP) AND HYDRAULIC TUBES REMOVAL
- LEFT SIDE
(SHEET 4 OF 4)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
W1656
W4615
SSTA
172.4
SSTA
210.0
VISS
235.0
SSTA
260.0
SSTA  2275497
285.0
FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE
(SHEET 1 OF 2)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2-ScrewRemove1
2-ClampRemove
2-WasherRemove
12-ScrewRemove / Keep2
12-WasherRemove / Keep
12-ClampRemove / Keep
(a)-W1656, W4615Wire BundleLoosen3
(a) Make sure cover wire bundle with plastic and tape to protect them from the chips.
FIGURE 2: LOOSEN THE WIRE BUNDLE W1656 AND W4615 - LEFT SIDE
(SHEET 2 OF 2)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
285.0
SSTA
260.0
SSITA
210.0
SSTA
172.
2275811
FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE
(SHEET 1 OF 3)
Original Issue: February 04, 2014
Revision 1 July 18, 2014  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
962
SSTA
FWD  184.8
SSTA
172.4
SSTA
270.0
SSTA  2275778
FWD  260.0
FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE
(SHEET 2 OF 3)
Original Issue: February 04, 2014
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Work - See page 1 for details.  37 of 108

### 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 this figure.
More DataQtyIdentificationNameTaskStep
4-BoltRemove1
2287U0037-17BracketRemove
5-RivetRemove2
1-BoltRemove3
2-RivetRemove4
1287U0037-33BracketRemove
8-RivetRemove5
FIGURE 3: FASTENERS AND BRACKETS REMOVAL - LEFT SIDE
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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38 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
285.0
VISS
0092
SSTA
210.0
SSTA
172.4
2275997
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 8)
Original Issue: February 04, 2014
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Work - See page 1 for details.  39 of 108

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
23 AN
3 LOCATIONS
AN OU  3 U14
12) (13
SSTA
196.2  SSTI
84
SSTA
184.8
FWD  2276016
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 8)
Original Issue: February 04, 2014
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Work - See page 1 for details.  40 of 108

### Page 41 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
184.8
EXISTING
BRACKET
0.07
BRACKET
INBD
A-A
EXISTING
CRANK
BRACKET
0.64
FILLER
• BRACKET
FWD
B-B  2277193
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 8)
Original Issue: February 04, 2014
Revision 1 July 18, 2014  Export Controlled ECCN: 9E991 - BOEING  747-27A2513
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  41 of 108

### 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 this figure.
More DataQtyIdentificationNameTaskStep
On the fwd side, the
fillers are under the
collars.
2BACF3H10RF024HFFILLER, RECTANGU-
LAR
Put / Hold1
Two (2) holes for
each location. Back
drill the holes
through radius filler.
Refer to Fastener
Code table for the
hole diameter.
4-HoleDrill / Ream2
--HoleClean/Deburr
On mating surfaces
of filler, web. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-45SealantApply3
On the fwd side, un-
der the collar. One
(1) for each location.
2BACF3H10RF024HFFILLER, RECTANGU-
LAR
Install (New)
Refer to Fastener
Code table for fasten-
er part number.
--FastenerInstall (New)
(d)1-RivetMicroshave4
--SurfaceClean
(a)-ALODINE 600Chemical Conversion
Coating
Apply
(b)-BMS 10-11, TYPE 1PrimerApply
Optional, (e)-BMS10-60, TYPE 1Gloss EnamelApply
As shown in figure.1252U3102-13MOUNTING BRACKET
ASSY, LEFT INBD -
COMPENSATOR, ELE-
VATOR PCU
Put / Hold5
As shown in figure,
the filler is between
the bracket and the
spar.
1BACF3F015X026NNFILLER, FLATPut / Hold
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-27A2513

### Page 43

More DataQtyIdentificationNameTaskStep
Back drill the holes
through the filler and
bracket. Refer to
Fastener Code table
for the hole diame-
ter.
5-HoleDrill / Ream6
Back drill the holes
through the bracket.
Minimum edge mar-
gin of 0.30 is accept-
able at this location.
Refer to Fastener
Code table for the
hole diameter.
1-HoleDrill / Ream7
-252U3102-13MOUNTING BRACKET
ASSY, LEFT INBD -
COMPENSATOR, ELE-
VATOR PCU
Disassemble8
-BACF3F015X026NNFILLER, FLATDisassemble
To the bracket, filler
and the web
--HoleClean/Deburr
Non-designated
bond. Refer to SW-
PM 20-20-00,
Cleaning Procedure
1, as an accepted
procedure.
--SurfaceClean9
(a)-ALODINE 600Chemical Conversion
Coating
Apply
To mating surface of
bracket and web.
Refer to SWPM 20-
20-00, Category 2
fay surface bond, as
an accepted proce-
dure.
-BMS5-45SealantApply
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 5 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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43 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 44

More DataQtyIdentificationNameTaskStep
Refer to SWPM 20-
20-00, Procedure 5,
as an accepted pro-
cedure.
--SurfaceClean10
To mating surface of
bracket, filler, web.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply
1252U3102-13MOUNTING BRACKET
ASSY, LEFT INBD -
COMPENSATOR, ELE-
VATOR PCU
Install (New)11
The filler is between
the bracket and the
spar.
1BACF3F015X026NNFILLER, FLATInstall (New)
Refer to Fastener
Code table for fasten-
er part number.
--FastenerInstall (New)
(c)--ResistanceMeasure12
Apply a fillet seal
around the bracket
where it connects to
the structure. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-142, TYPE IISealantApply13
(a)-ALODINE 600Chemical Conversion
Coating
Apply14
(b)-BMS 10-11, TYPE 1PrimerApply
(a) Apply to bare metal. Refer to SOPM 20-43-03, as an accepted procedure.
(b) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an ac-
cepted procedure.
(c) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as
an accepted procedure.
(d) Microshave the bucked tail of the existing rivet as necessary to allow the clearance for the bracket instal-
lation. Complete removal of bucked tail is acceptable.
(e) Refer to SOPM 20-41-01 code F-14.9812, as an accepted procedure.
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 6 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
747-27A2513Revision 1 July 18, 2014
44 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 45

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
Install the fastener wet
with sealant BMS5-45. (a)
0.325 - 0.3287BACB30MY10K8XBOLT, PROTRUDING
HD
A
(b)-7BACC30M10COLLAR
Install the fastener wet
with sealant BMS5-45. (a)
0.325 - 0.3282BACB30MY10K12XBOLT, PROTRUDING
HD
B
(b)-2BACC30M10COLLAR
Install the fastener wet
with sealant BMS5-45. (a)
0.263 - 0.2661BACB30MY8K12XBOLT, PROTRUDING
HD
C
(b)-1BACC30M8COLLAR
(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02
(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to
SOPM 20-50-19 as an accepted procedure.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
4BACC30M10COLLAR
1BACB30MY10K12XBOLT, PROTRUDING
HD
1BACB30MY8K12XBOLT, PROTRUDING
HD
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 7 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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45 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 46

More DataQtyIdentificationName
1BACB30MY10K8XBOLT, PROTRUDING
HD
FIGURE 4: INBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 8 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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46 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 47 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
285.0
VISS
260.0
SSTA
210.0
SSTA
172.4
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 8)
Original Issue: February 04, 2014
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Work - See page 1 for details.  47 of 108

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
D6 14
FN 26
2G'N
SSTA
270.0
SSTA
260.0
0.090
0.610 -
A-A  2276785
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 8)
Original Issue: February 04, 2014
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Work - See page 1 for details.  48 of 108

### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
260
FILLER
- EXISTING
ANGLE
0.04
BRACKET-
B-B  INBD
BRACKET
-0.43  EXISTING
RIB
FWD
C-C  2278819
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 8)
Original Issue: February 04, 2014
Revision 1 July 18, 2014  Export Controlled ECCN: 9E991 - BOEING  747-27A2513
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  49 of 108

### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
As shown in figure.1252U3102-11MOUNTING BRACK-
ET, LEFT OUTBD -
COMPENSATOR, ELE-
VATOR PCU
Put / Hold1
On the fwd side, the
fillers are under the
collars.
2BACF3H10RF040HFFILLER, RECTANGU-
LAR
Put / Hold
The radius fillers are
between the head of
fasteners and brack-
et.
2BACF3H10RF010HGRADIUS FILLERPut / Hold
Back drill the holes
through bracket and
radius fillers. Refer
to Fastener Code ta-
ble for the hole diam-
eter.
8-HoleDrill / Ream2
To the bracket, fillers
and web.
--HoleDeburr
Non-designated
bond. Refer to SW-
PM 20-20-00,
Cleaning Procedure
1, as an accepted
procedure.
--SurfaceClean3
(b)-ALODINE 600Chemical Conversion
Coating
Apply
To mating surface of
bracket, fillers. Refer
to SWPM 20-20-00,
Category 2 fay sur-
face bond, as an ac-
cepted procedure.
-BMS5-45SealantApply
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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50 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 51

More DataQtyIdentificationNameTaskStep
Refer to SWPM 20-
20-00, Procedure 5,
as an accepted pro-
cedure.
--SurfaceClean4
To mating surface of
bracket, fillers, web.
Refer to SOPM 20-
50-19 as an accept-
ed procedure.
-BMS5-45SealantApply
1252U3102-11MOUNTING BRACK-
ET, LEFT OUTBD -
COMPENSATOR, ELE-
VATOR PCU
Install (New)5
On the fwd side, un-
der the collars.
2BACF3H10RF040HFFILLER, RECTANGU-
LAR
Install (New)
Refer to Fastener
Code table for fasten-
er part number.
--FastenerInstall (New)
To mating surface of
fillers. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS5-45SealantApply6
Under the head of
fasteners.
2BACF3H10RF010HGRADIUS FILLERInstall (New)
Refer to Fastener
Code table for fasten-
er part number.
--FastenerInstall (New)
(a)--ResistanceMeasure7
As shown in figure.1287U0037-33BRACKET ASSEMBLYPut / Hold8
Back drill the holes
through bracket. Re-
fer to Fastener Code
table for the hole di-
ameter.
2-HoleDrill / Ream9
--HoleDeburr
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 5 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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51 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 52

More DataQtyIdentificationNameTaskStep
Non-designated
bond. Refer to SW-
PM 20-20-00,
Cleaning Procedure
1, as an accepted
procedure.
--SurfaceClean10
(b)-ALODINE 600Chemical Conversion
Coating
Apply
To mating surface of
bracket. Refer to
SWPM 20-20-00,
Category 2 fay sur-
face bond, as an ac-
cepted procedure.
-BMS5-45SealantApply
1287U0037-33BRACKET ASSEMBLYInstall (New)11
Refer to Fastener
Code table for fasten-
er part number.
--FastenerInstall (New)
(a)--ResistanceMeasure12
Apply a fillet seal
around the bracket
where it connects to
the structure. Refer
to SOPM 20-50-19
as an accepted pro-
cedure.
-BMS5-142, TYPE IISealantApply13
(b)-ALODINE 600Chemical Conversion
Coating
Apply14
(c)-BMS 10-11, TYPE 1PrimerApply
(a) Between the bracket and structure. Maximum resistance is 0.0005 ohms. Refer to SWPM 20-20-00 as
an accepted procedure.
(b) Apply to bare metal surfaces. Refer to SOPM 20-43-03, as an accepted procedure.
(c) Apply 2 layers of the primer over the chemical conversion coating. Refer to SOPM 20-41-02, as an ac-
cepted procedure.
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 6 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
747-27A2513Revision 1 July 18, 2014
52 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 53

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
Install the fastener wet
with sealant BMS5-45. (a)
0.263 - 0.2664BACB30MY8K14XBOLT, PROTRUDING
HD
D
(b)-4BACC30M8COLLAR
Install the fastener wet
with sealant BMS5-45. (a)
0.263 - 0.2662BACB30MY8K9XBOLT, PROTRUDING
HD
E
(b)-2BACC30M8COLLAR
Install the fastener wet
with sealant BMS5-45. (a)
0.263 - 0.2662BACB30MY8K11XBOLT, PROTRUDING
HD
F
(b)-2BACC30M8COLLAR
Install the fastener wet
with sealant BMS5-45. (a)
0.263 - 0.2662BACB30MY8K6XBOLT, PROTRUDING
HD
G
(b)-2BACC30M8COLLAR
(a) Install fasteners in accordance with 747-8P SRM 51-40-02 or 747-8F SRM 51-40-02
(b) Cap seal over the fastener threaded ends and collars inside the tank with sealant BMS5-45. Refer to
SOPM 20-50-19 as an accepted procedure.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
5BACC30M8COLLAR
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 7 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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53 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 54

More DataQtyIdentificationName
1BACB30MY8K14XBOLT, PROTRUDING
HD
1BACB30MY8K9XBOLT, PROTRUDING
HD
1BACB30MY8K11XBOLT, PROTRUDING
HD
1BACB30MY8K6XBOLT, PROTRUDING
HD
FIGURE 5: OUTBOARD COMPENSATOR MOUNTING BRACKET INSTALLATION - LEFT SIDE
(SHEET 8 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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54 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
172.4
SSTA
210
SSTA
235
SSTA
260
SSTA
285
SSTA
360
FWD
2277589
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 1 OF 6)
Original Issue: February 04, 2014
Revision 1 July 18, 2014  Export Controlled ECCN: 9E991 - BOEING  747-27A2513
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  55 of 108

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
235
SSTA
260
EXISTING
BRACKET
SSTA
285
FWD
6 LOCATIONS
2) 2 LOCATIONS
C-C
A-A  2) 2 LOCATIONS  2277606
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 2 OF 6)
Original Issue: February 04, 2014
Revision 1 July 18, 2014  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-27A2513
Work - See page 1 for details.  56 of 108

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-27A2513
SSTA
172.4
SSTA 5 LOCATIONS 6
210
FWD
C
(2) 2 LOCATIONS
2 LOCATIONS (2  2277600
B-B
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 3 OF 6)
Original Issue: February 04, 2014
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### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2463430-1001REMOTE COMPEN-
SATOR - UPPER
RUDDER
Install (New)1
Under the head of
fastener. Four (4)
per Compensator
8BACW10BP4ACWASHERInstall (New)2
Four (4) per Com-
pensator
8BACB30NM4K11BOLT, HEX HEADInstall (New)
Four (4) per Com-
pensator
8NAS1149E0432PWASHER, PLAINInstall (New)
Four (4) per Com-
pensator. Refer to
747-8P SRM 51-40-
04 and 747-8F SRM
51-40-04 as an ac-
cepted procedure for
the torque value.
8BACN11Z4CDNUTInstall (New)
Onto back of exist-
ing bracket
272U9405-10
1272U9405-25BRACKET ASSEMBLYInstall (New)3
To the tube assem-
bly 272U8190-10.
1-ClampInstall (Kept)4
1-WasherInstall (Kept)
1BACS12GU3K10SCREWInstall (New)
Connect the TEE to
the Compensator,
(b), (c)
1AS4140V100808P
(BACT16BT100808P
optional)
TEEInstall (New)5
(b), (c)1272U8190-32TUBE ASSYInstall (New)6
Use the kept screws,
washers and clip
nuts for the installa-
tion.
5-ClampInstall (Kept)
Use the kept fasten-
ers and hardware.
1-Clamp Block AssyInstall (Kept)7
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
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58 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 59

More DataQtyIdentificationNameTaskStep
(d)1BACS18AF4SPACERInstall (New)8
1AS21919WCE10CLAMP,LOOPInstall (New)
1NAS1149D0316JWASHERInstall (New)
1BACS12GU3K10SCREWInstall (New)
(b), (c)1272U8190-37TUBE ASSYInstall (New)9
Use all kept screws,
washers and clip
nuts for the installa-
tion.
6-ClampInstall (New)
(b), (c)1AS1009W080810TEEInstall (New)10
1NAS1149D1490JWASHER, PLAINInstall (New)
1AS5178W10NUT, TUBE, BULK-
HEAD
Install (New)
(b), (c). Torque the
valve to 40-80 inch-
pounds to make
sure the valve is
seated.
1293W6132-1VALVE ASSYInstall (New)11
(a)-MS20995NC40
(MS20995C41 optional)
LockwireInstall (New)
Connect the tube
assy to the tee and
compensator, (b), (c)
1272U8190-36TUBE ASSYInstall (New)12
1-ClampInstall (Kept)
1-WasherInstall (Kept)
1BACS12GU3K10SCREWInstall (New)
Connect the elbow
to the tee. (b), (c)
1BACE21AU1010WELBOW, SWVL-RDCR,
45
Install (New)13
Connect the tube
assy to the Compen-
sator, (b), (c)
1272U8190-34TUBE ASSYInstall (New)14
Use all kept screw,
washer and clip nut
for the installation.
1-ClampInstall (Kept)
(b), (c)1BACT16AY080808WTEE, SWIVEL ON RUNInstall (New)15
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
747-27A2513Revision 1 July 18, 2014
59 of 108
BOEING SERVICE BULLETIN 747-27A2513

### Page 60

More DataQtyIdentificationNameTaskStep
(b), (c). Torque the
valve to 40-80 inch-
pounds to make
sure the valve is
seated.
1293W6132-1VALVE ASSYInstall (New)16
(a)-MS20995NC40
(MS20995C41 optional)
LockwireInstall (New)
Connect the tube
assy to the Compen-
sator and Tee. (b),
(c)
1272U8190-35TUBE ASSYInstall (New)17
Use all kept screw,
washer and clip nut
for the installation.
1-ClampInstall (Kept)
1AS21919WCE08CLAMP,LOOPInstall (New)18
(d)1BACS18AF4SPACERInstall (New)
2NAS1149D0316JWASHERInstall (New)
1BACS12GU3K8SCREWInstall (New)
1BACN10YR3CDNUTInstall (New)
(a) Double-twist method. Refer to SOPM 20-50-02 as an accepted procedure.
(b) Refer to 747-8 AMM 20-11-05 as an accepted procedure.
(c) Refer to 747-8 AMM 20-51-01 as an accepted procedure for the torque value.
(d) Use spacers as necessary to make sure that the clamp holds the tube with minimum force. The maximum
permitted quantity of spacers for each clamp is 4.
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
1BACW10BP4ACWASHER
1NAS1149E0432PWASHER, PLAIN
1BACN11Z4CDNUT
3NAS1149D0316JWASHER
2BACS12GU3K10SCREW
1BACN10YR3CDNUT
1AS21919WCE10CLAMP,LOOP
1BACB30NM4K11BOLT, HEX HEAD
FIGURE 6: COMPENSATORS AND HYDRAULIC TUBES INSTALLATION - LEFT SIDE
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 04, 2014
747-27A2513Revision 1 July 18, 2014
60 of 108
BOEING SERVICE BULLETIN 747-27A2513

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