# Boeing Alert Service Bulletin 747-54A2238: No revision named

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- Document: [Boeing Alert Service Bulletin 747-54A2238](https://openairdocs.org/service-documents/boeing/747-54a2238.md)
- Title as filed: U.S. DOT/FAA - SB-747-54A2238-00
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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2238
Original Issue: January 31, 2014
ATA System: 5451
SUBJECT: NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse
Pin 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Unpublished Work.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
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 1
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 1
G. Manpower .............................................. 1 1
H. Weight and Balance Changes .................................... 1 2
I. Electrical Load Data ......................................... 1 2
J. References .............................................. 1 3
1. Existing Data: ......................................... 1 3
2. Data Supplied with this Service Bulletin: ........................... 1 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 3
K. Publications Affected ........................................ 1 3
L. Interchangeability and Intermixability of Parts ........................... 1 4
M. Software Accomplishment Summary ................................ 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 6
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL ................. 2 3
FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL ................. 2 5
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT . . 27
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT .... 3 5
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT .... 4 0
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT . . 48
FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION .............. 5 3
FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION .............. 5 5
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-54A2238Original Issue: January 31, 2014
ATA System: 5451
SUBJECT: NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse
Pin Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will prevent outboard migration of the outboard aft upper spar strut-to-wing
attachment fuse pins on struts No. 1 and No. 4 that could result in the complete disconnect and loss of the
outboard aft upper spar strut-to-wing attachment load path. The complete loss of the No. 1 or No. 4 outboard
aft upper spar strut-to-wing attachment load path could result in divergent flutter in certain parts of the flight
envelope, which can result in loss of control of the airplane.
Boeing analysis determined that the existing outboard aft upper spar strut-to-wing attachment fuse pins on struts
No. 1 and No. 4 are susceptible to migration in the event of a failed fuse pin through bolt. To prevent the outboard
aft upper spar strut-to-wing attachment fuse pins migrating outboard, the outboard aft upper spar strut-to-wing
attachment fuse pin design was changed to add a flange. The outboard fuse pin access cover assemblies were
changed to add interference ribs to only allow the fuse pin to be installed with the flanged end of the fuse pin
on the inboard side of the outboard aft upper spar fitting. To prevent incorrect installation of the outboard aft
upper spar strut-to-wing attachment fuse pins, the inboard aft upper spar strut-to-wing attachment fuse pin
incorporated the same flanged fuse pin design.
This service bulletin provides instructions to replace the outboard aft upper spar strut-to-wing attachment fuse
pins and access covers on struts No. 1 and No. 4 with the new flanged fuse pins and ribbed access cover
assemblies. Installation of the new flanged fuse pins at the outboard aft upper spar strut-to-wing attachment will
prevent outboard migration of the fuse pins and possible loss of the outboard aft upper spar strut-to-wing attach
load path. Installation of the new ribbed fuse pin access cover assembly will prevent incorrect installation of the
outboard aft upper spar strut-to-wing attachment fuse pins.
This service bulletin also provides instructions to replace the inboard aft upper spar strut-to-wing attachment
fuse pins on struts No. 1 and No. 4 with the new flanged fuse pins. Installation of the new flanged fuse pins at
the inboard aft upper spar strut-to-wing attachment will prevent incorrect installation of the non-flanged fuse pins
at the outboard and inboard aft upper spar strut-to-wing attachment.
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Boeing Service Related Problem (SRP) 747-8-SRP-51-0016 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., 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
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
YesSpecial Tooling Required
ACTION (PRR 86601-4)
Get access to the Aft Upper Spar Fuse Pins and remove Access Cover Assemblies. Depressurize hydraulic
system. Remove Air Drive Units and replace Fuse Pins. Install Air Drive Units and pressurize hydraulic system.
Install new Access Cover Assemblies and close access to the Aft Upper Spar Fuse Pins.
EFFECTIVITY
747-8 and 747-8F Airplanes. 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.
Boeing recommends that the change given in this service bulletin be done within 48 months after the Original
Issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of July 25, 2012. 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.
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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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### Page 8 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 1 OUTBOARD
STRUT
GET ACCESS TO THE AFT UPPER SPAR FUSE PINS
AND REMOVE ACCESS COVER ASSEMBLIES.
DEPRESSURIZE HYDRAULIC SYSTEM.
REMOVE AIR DRIVE UNITS AND REPLACE FUSE PINS
INSTALL AIR DRIVE UNITS AND PRESSURIZE
HYDRAULIC SYSTEM. INSTALL NEW ACCESS COVER
ASSEMBLIES AND CLOSE ACCESS TO THE AFT
UPPER SPAR FUSE PINS.
UPPER LINK
AFT UPPER
SPAR FITTINGS
SIDE LINKS
DIAGONAL
DIAGONAL  BRACE
BRACE
NO. 1 OUTBOARD STRUT SHOWN
(NO. 4 OUTBOARD STRUT IS SIMILAR)
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### Page 9

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2238
Original Issue: January 31, 2014
ATA System: 5451
SUBJECT: NACELLES/PYLONS - Nacelle Strut Attach Pin - Outboard Struts Aft Upper Spar Fuse
Pin Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 86601-4 for data about this change.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
NOTE: Variable numbers for airplanes scheduled to be delivered more than a year after the
Original Issue date of this service bulletin are not listed in the table below. MyBoeingFleet
(MBF) will show current listing of the affected airplanes.
NOTE: This service bulletin is for the airplanes shown in the effectivity list below. The effectivity
list includes all affected airplanes scheduled to be delivered before DEC 02, 2014. In
addition, at least one airplane scheduled to be delivered after DEC 02, 2014 is affected
by this service bulletin and is in Group(s) 1 as described in the Group Configuration table.
Affected airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) "get
effectivity" result when they are added to the MBF Fleet Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
747-8 and 747-8F Airplanes line number 1420 through 1434, 1436
through 1491
-1
Airplane Models:
747-8, 747-8F
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GroupVariable Number
1RC001 - RC008
1RC022 - RC030
1RC501 - RC511
1RC521 - RC528
1RC541
1RC546 - RC549
1RC551 - RC563
1RC571 - RC572
1RC574 - RC582
1RC601 - RC605
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will prevent outboard migration of the outboard aft upper spar
strut-to-wing attachment fuse pins on struts No. 1 and No. 4 that could result in the complete disconnect
and loss of the outboard aft upper spar strut-to-wing attachment load path. The complete loss of the
No. 1 or No. 4 outboard aft upper spar strut-to-wing attachment load path could result in divergent
flutter in certain parts of the flight envelope, which can result in loss of control of the airplane.
Boeing analysis determined that the existing outboard aft upper spar strut-to-wing attachment fuse
pins on struts No. 1 and No. 4 are susceptible to migration in the event of a failed fuse pin through bolt.
To prevent the outboard aft upper spar strut-to-wing attachment fuse pins migrating outboard, the
outboard aft upper spar strut-to-wing attachment fuse pin design was changed to add a flange. The
outboard fuse pin access cover assemblies were changed to add interference ribs to only allow the
fuse pin to be installed with the flanged end of the fuse pin on the inboard side of the outboard aft upper
spar fitting. To prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment
fuse pins, the inboard aft upper spar strut-to-wing attachment fuse pin incorporated the same flanged
fuse pin design.
This service bulletin provides instructions to replace the outboard aft upper spar strut-to-wing attachment
fuse pins and access covers on struts No. 1 and No. 4 with the new flanged fuse pins and ribbed access
cover assemblies. Installation of the new flanged fuse pins at the outboard aft upper spar strut-to-wing
attachment will prevent outboard migration of the fuse pins and possible loss of the outboard aft upper
spar strut-to-wing attach load path. Installation of the new ribbed fuse pin access cover assembly will
prevent incorrect installation of the outboard aft upper spar strut-to-wing attachment fuse pins.
Export Controlled ECCN: 9E991 - BOEING
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### Page 11

This service bulletin also provides instructions to replace the inboard aft upper spar strut-to-wing
attachment fuse pins on struts No. 1 and No. 4 with the new flanged fuse pins. Installation of the new
flanged fuse pins at the inboard aft upper spar strut-to-wing attachment will prevent incorrect installation
of the non-flanged fuse pins at the outboard and inboard aft upper spar strut-to-wing attachment.
Boeing Service Related Problem (SRP) 747-8-SRP-51-0016 is related to this service bulletin.
D. Description
Get access to the Aft Upper Spar Fuse Pins and remove Access Cover Assemblies. Depressurize
hydraulic system. Remove Air Drive Units and replace Fuse Pins. Install Air Drive Units and pressurize
hydraulic system. Install new Access Cover Assemblies and close access to the Aft Upper Spar Fuse
Pins.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
451, 452, 481, 482747-8, 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 48 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 replacement 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
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 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Elapsed
Hours
Task HoursNumber of
Persons
Task
3.2513.004Open Access
Remove Access Panels
1.001.001...FIGURE 1: Strut No. 1
1.001.001...FIGURE 2: Strut No. 4
0.150.151Depressurize hydraulic system
4.5018.004Remove Air Drive Unit
Replace Fuse Pins
4.008.002...FIGURE 3: Strut No. 1, Outboard Side
2.755.502...FIGURE 4: Strut No. 1, Inboard Side
2.755.502...FIGURE 5: Strut No. 4, Inboard Side
4.008.002...FIGURE 6: Strut No. 4, Outboard Side
4.5018.004Install Air Drive Unit
0.150.151Pressurize hydraulic system
Install Access Panels
1.001.001...FIGURE 7: Strut No. 1
1.001.001...FIGURE 8: Strut No. 4
3.2513.004Close Access
1.004.004Test
34.3097.30TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+8320.9 lb.-in.+5.2 lb.All
I. Electrical Load Data
Not changed.
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### Page 13

J. References
1. Existing Data:
a. Engineering Change Memo PRR 86601-4
b. Boeing Service Related Problem (SRP) 747-8-SRP-51-0016
c. Service Bulletin Index D6-30300
d. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-00, 20-50-01, 20-50-01,
20-50-02, 20-50-07, 20-60-03
e. 747-8 Aircraft Maintenance Manual (AMM) 27-81-00, 29-11-00, 29-11-08, 54-51-02, 54-62-04,
71-11-04
2. Data Supplied with this Service Bulletin:
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
--1747 Hydraulic Bracket Trim ToolMIT321U8047
--2
--3
---747 Hydraulic Bracket Trim ToolMIT321U8047_-
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
REWORK - BRACKET INSTL, TRAS, HYD, FUEL321U8046
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
54-51747 Aircraft Maintenance Manual
54-51747 Illustrated Parts Catalog
54-00Component Maintenance Manual
1. Damage Tolerance Based Structural Inspections:
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### Page 14

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
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 15

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 kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the Original Issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
Original Issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$31,036.005782December 13,
2013
TOP KIT - OUTBOARD
STRUT R3 FUSE PIN
AND ACCESS DOOR
- REPLACEMENT
015U1954-1
10January 24,
2014
18February 27,
2014
B. Industry Support Information
Boeing warranty remedies are available for 747 airplanes in warranty as of July 25, 2012. For task hour
reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty &
Product Assurance Contracts. 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 Material Management. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order. The warranty
remedies will expire eight years from the original issue date of this service bulletin.
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.
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### Page 16

Figure Kit
876543Top Kit
111111015U1954-1
ALL
KIT 015U1954-1
Notes
Existing Part
NumberName
Figure
New Part Number
876543
Qty
(a) (b)
(c)
311U8092-2FUSE PIN - AFT
UPPER SPAR NA-
CELLE STRUT
..1111311U8092-3
(a) (b)
(c)
311U8098-9THROUGH BOLT
- AFT UPPER
SPAR NACELLE
STRUT
..1111311U8098-10
(a) (b)
(c)
323U8215-3ACCESS COVER
ASSY, OUTBD
SIDE, LH OUTBD
ENGINE
.1....323U8215-5
(a) (b)
(c)
323U8215-4ACCESS COVER
ASSY, OUTBD
SIDE, RH OUTBD
ENGINE
1.....323U8215-6
(d)BOLT1515....BACB30NN4K11
(BACB30NN4K11G
optional)
SELF-LOCKING
NUT
..1111BACN10HR14CS
NUT..1111BACN11N114CS
PIN..1111BACP18BC04A14P
(a) Discard the existing part. Keep the existing part if there are other uses for it.
(b) This part is used in production.
(c) You cannot use the existing part to replace the new or changed part.
(d) 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.
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NotesNameQTYPart Number /
Specification
(a)PRIMER8
ounces
BMS 10-11, TYPE
1
(a) (e)GREASE1
quart
AEROSHELL
GREASE 33MS
(a)HYDRAULIC FLUID8
ounces
BMS 3-11
(MCS0352 option-
al)
(a)GREASE1
quart
BMS 3-33, TYPE I
(b)ANTI-SEIZE THREAD COMPOUND8
ounces
-
(c)CABLE ASSEMBLY, SAFETY4BACC13AT4K18
(d)MARKING LACQUER2
ounces
-
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(b) Refer to SOPM 20-60-03 for a list of applicable anti-seize thread compounds.
(c) Part is used when installing Side Link Assembly.
(d) F-925, Skydrol Resistant Torque Seal, Organic Products Company, PO Box 560625,
Dallas, TX 75356-0625 (MSDS41617).
(e) Aeroshell Grease 33MS is qualified to MIL-G-21164.
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
Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of
the service bulletin. The tool(s) are subject to the terms and conditions of the Boeing standard purchase
order acknowledgement. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin number and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
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### Page 18

2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST
RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT)
AND PRICE INFORMATION
Purchase Data:
Unit Price as of
the Original Issue
date of this Ser-
vice Bulletin (US
Dollars)
NameTool Kit Number
$53,760.00747 Hydraulic Bracket Trim ToolMIT321U8047
Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of
the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject
to the terms and conditions of the Boeing standard purchase order acknowledgement. Prices are in
United States dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (425) 965-8237
Rental Data:
Daily Price as of
the Original Issue
date of this ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$360.00747 Hydraulic Bracket Trim ToolMIT321U8047
F. Special Tooling Necessary to do this Service Bulletin
To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.
Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be
necessary. Examine operator tool supply to make sure all necessary tools are available.
NameTool Kit Number
747 Hydraulic Bracket Trim ToolMIT321U8047
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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 747-8F or 747-8P 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. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
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7. 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.
8. 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.
9. 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.
10. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
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 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. Retract leading edge flaps and install leading edge flap drive unit lock. Refer to 747-8 AMM 27-81-00
as an accepted procedure.
2. Remove and keep Forward Fairing Access Panels shown below from Strut No. 1 and No. 4. Refer
to 747-8 AMM 54-62-04 as an accepted procedure.
No. 4 Engine StrutNo. 1 Engine StrutForward Fairing Ac-cess Panel No.
481AT451AT1
481BT451BT2
481DL and 481DR451DL and 451DR3
481EL and 481ER451EL and 451ER4
3. Remove and keep Fan Cowl Panels from Engine No. 1 and No. 4. Refer to 747-8 AMM 71-11-04
as an accepted procedure.
4. Prepare for the removal of the Strut No. 1 and No. 4 Aft Upper Spar Fuse Pins. Refer to 747-8
AMM 54-51-02, Prepare for the Removal (Engine Removed) or 747-8 AMM 54-51-02, Prepare for
Removal (Engine Supported) as accepted procedures.
5. Remove Access Cover Assemblies in accordance with the figures below.
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FigureEngine Strut
FIGURE 1Strut No. 1
FIGURE 2Strut No. 4
6. Depressurize the hydraulic system. Refer to 747-8 AMM 29-11-00 as an accepted procedure.
7. Remove Air Drive Unit (ADU) on Strut No. 1 and No. 4. Refer to 747-8 AMM 29-11-08 as an
accepted procedure.
8. RC - Replace Aft Upper Spar Fuse Pins in accordance with the figures below.
FigureEngine Strut Location
FIGURE 3Strut No. 1, Outboard Side
FIGURE 4Strut No. 1, Inboard Side
FIGURE 5Strut No. 4, Inboard Side
FIGURE 6Strut No. 4, Outboard Side
9. Install and test ADU on Strut No. 1 and No. 4. Refer to 747-8 AMM 29-11-08 as an accepted
procedure.
10. Pressurize the hydraulic system. Refer to 747-8 AMM 29-11-00 as an accepted procedure.
11. RC - Install Access Cover Assemblies in accordance with the figures below
FigureEngine Strut
FIGURE 7Strut No. 1
FIGURE 8Strut No. 4
12. Restore access to the Strut No. 1 and No. 4 Aft Upper Spar Fuse Pins. Refer to 747-8 AMM
54-51-02, Restore the Airplane to Normal (Engine Removed) or 747-8 AMM 54-51-02, Restore
the Airplane to Normal (Engine Supported) as accepted procedures.
13. Install kept Fan Cowl Panels from Strut No. 1 and No. 4. Refer to 747-8 AMM 71-11-04 as an
accepted procedure.
14. Install kept Forward Fairing Access Panels shown below on to Strut No. 1 and No. 4. Refer to
747-8 AMM 54-62-04 as an accepted procedure.
No. 4 Engine StrutNo. 1 Engine StrutForward Fairing Ac-cess Panel No.
481AT451AT1
481BT451BT2
481DL and 481DR451DL and 451DR3
481EL and 481ER451EL and 451ER4
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15. Remove safety locks from leading edge flaps. Refer to 747-8 AMM 27-81-00 as an accepted
procedure.
16. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 1 OUTBOARD STRUT
2264537
FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL
(SHEET 1 OF 2)
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### Page 24

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut.
More DataQtyIdentificationNameTaskStep
(a)13-BOLTRemove / Keep1
1323U8215-3ACCESS COVER AS-
SY, OUTBD SIDE, LH
OUTBD ENGINE
Remove
(a)11-BOLTRemove / Keep2
1323U8225-3ACCESS COVER AS-
SY, INBD SIDE, LH
OUTBD ENGINE
Remove / Keep
(a) Make note of Bolt location for Access Cover Assembly installation.
FIGURE 1: STRUT NO. 1 - ACCESS COVER ASSEMBLY REMOVAL
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 4 OUTBOARD STRUT
2264666
FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL
(SHEET 1 OF 2)
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### Page 26

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut.
More DataQtyIdentificationNameTaskStep
(a)13-BOLTRemove / Keep1
1323U8215-4ACCESS COVER AS-
SY, OUTBD SIDE, RH
OUTBD ENGINE
Remove
(a)11-BOLTRemove / Keep2
1323U8225-4ACCESS COVER AS-
SY, INBD SIDE, RH
OUTBD ENGINE
Remove / Keep
(a) Make note of Bolt location for Access Cover Assembly installation.
FIGURE 2: STRUT NO. 4 - ACCESS COVER ASSEMBLY REMOVAL
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 1 OUTBOARD STRUT
STRUT -
BEFORE  INBD  2264689
A-A
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT OPPER SPAR FUSE PIN REPLACEMENT
(SHEET 1 OF 8)
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### Page 28

FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 2 OF 8)
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BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
2265191
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT OPPER SPAR FUSE PIN REPLACEMENT
(SHEET 3 OF 8)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
4.77  2.38
4.67  2.28
•R= 2.30
2.20
B-B
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 4 OF 8)
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### Page 31

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut outboard side.
More DataQtyIdentificationNameTaskStep
and attach fuse pins.
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2321U8740-1SIDE LINK ASSEMBLYRemove / Keep1
1-CABLE ASSEMBLY,
SAFETY
Remove
and fasteners.1-CLAMPBLOCK - HY-
DRAULIC TUBE SUP-
PRT BRACKET
Remove / Keep2
and lift hydraulic
tube to provide
clearance for installa-
tion of new fuse pin.
1-HYDRAULIC TUBEDisconnect3
by loosening or re-
moving clamp
screws, as required,
to move the conduit.
Keep all clamp
screws, if removed.
--CONDUITMove4
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
1-PINRemove5
1-NUTRemove
1-SELF-LOCKING NUTRemove
1311U8098-9THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Remove
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Remove / Keep6
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 5 OF 8)
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### Page 32

More DataQtyIdentificationNameTaskStep
to provide clearance
for new fuse pin.
Refer to tool
MIT321U8047 in-
structions.
1321U8047-40BRACKET ASSYMachine7
two coats to bare
metal areas. Refer
to SOPM 20-41-02
as an accepted pro-
cedure.
-BMS 10-11, TYPE 1PRIMERApply
Refer to tool
MIT321U8047 in-
structions.
1-FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Remove8
with the flanged end
on the inboard side.
Apply thin film of
Aeroshell Grease
33MS to outer diam-
eter of the fuse pin.
Fuse pin may need
to be rotated up to
40 degrees in order
to clear Side Link
lug. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
1311U8092-3FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Install (New)
After installation, in-
ject grease into
grease fitting until
grease appears at
other side of the
joint. Refer to SOPM
20-50-07 as accept-
ed procedure.
-AEROSHELL GREASE
33MS
GREASEApply
One End Cap is in-
stalled on the
Through Bolt head
side and one End
Cap is installed on
the Through Bolt
thread side.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Install (Kept)9
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 6 OF 8)
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### Page 33

More DataQtyIdentificationNameTaskStep
with bolt head facing
the outboard side.
(a)
1311U8098-10THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Install (New)10
(a) (c)1BACN10HR14CSSELF-LOCKING NUTInstall (New)
Apply a torque stripe
to End Cap and Self-
Locking Nut on in-
board side. Refer to
Paragraph 2.C.2.,
Parts and Materials
Supplied by the Op-
erator for acceptable
material.
--MARKING LACQUERApply11
Tighten Nut 70 to
750 inch-pounds.
Replace Nut if Nut
cannot be tighten
between 70 to 750
inch-pounds. In-
crease torque, to
align with Pin hole in
Through Bolt, to not
exceed 1500 inch-
pounds. (a)
1BACN11N114CSNUTInstall (New)12
(b) (d)1BACP18BC04A14PPINInstall (New)
back to previous po-
sition. Install clamp
screws, if removed.
--CONDUITMove13
1-HYDRAULIC TUBEConnect14
to seal surface of
sleeve before seat-
ing B-nut, to external
fitting threads, and
to shoulder of
sleeve. Torque B-nut
to 855 to 945 inch-
pounds. Refer to
SOPM 20-50-00 as
an accepted proce-
dure.
-BMS 3-11  (MCS-352
optional)
HYDRAULIC FLUIDApply
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 7 OF 8)
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### Page 34

More DataQtyIdentificationNameTaskStep
and fasteners.
Torque nut to 3.5 to
30.0 inch-pounds.
Refer to SOPM 20-
50-01 as an accept-
ed procedure.
1-CLAMPBLOCK - HY-
DRAULIC TUBE SUP-
PRT BRACKET
Install (Kept)15
and attach fuse pins.
Torque nuts on
through bolts to
1500 to 2500 inch-
pounds. Ensure that
all parts are firmly
seated. Refer to
747-8 AMM 54-51-
02 as an accepted
procedure.
2321U8740-1SIDE LINK ASSEMBLYInstall (Kept)16
Refer to SOPM 20-
50-02 as an accept-
ed procedure.
1BACC13AT4K18CABLE ASSEMBLY,
SAFETY
Install (New)
(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20-
60-03 as accepted procedures.
(b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt.
(c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged.
Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed
on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking
Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do
a check to make sure that the torque vale is correct.
(d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly.
Make sure that the joint is not clamped.
FIGURE 3: STRUT NO. 1 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 8 OF 8)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 1 OUTBOARD STRUT
• STRUT
INBD
BEFORE
A-A
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 1 OF 5)
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### 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 one engine strut inboard side.
More DataQtyIdentificationNameTaskStep
and attach fuse pins.
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2321U8740-1SIDE LINK ASSEMBLYRemove / Keep1
1-CABLE ASSEMBLY,
SAFETY
Remove
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 2 OF 5)
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### Page 37

More DataQtyIdentificationNameTaskStep
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
1-PINRemove2
1-NUTRemove
1-SELF-LOCKING NUTRemove
1311U8098-9THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Remove
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Remove / Keep3
Refer to tool
MIT321U8047 in-
structions.
1-FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Remove4
with the flanged end
on the outboard
side. Apply thin film
of Aeroshell Grease
33MS to outer diam-
eter of the fuse pin.
Fuse pin may need
to be rotated up to
40 degrees in order
to clear Side Link
lug. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
1311U8092-3FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Install (New)
After installation, in-
ject grease into
grease fitting until
grease appears at
other side of the
joint. Refer to SOPM
20-50-07 as accept-
ed procedure.
-AEROSHELL GREASE
33MS
GREASEApply
One End Cap is in-
stalled on the
Through Bolt head
side and one End
Cap is installed on
the Through Bolt
thread side.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Install (Kept)5
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 3 OF 5)
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
37 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 38

More DataQtyIdentificationNameTaskStep
with bolt head facing
the inboard side. (a)
1311U8098-10THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Install (New)6
(a) (c)1BACN10HR14CSSELF-LOCKING NUTInstall (New)
Apply a torque stripe
to End Cap and Self-
Locking Nut on out-
board side. Refer to
Paragraph 2.C.2.,
Parts and Materials
Supplied by the Op-
erator for acceptable
material.
--MARKING LACQUERApply7
Tighten Nut 70 to
750 inch-pounds.
Replace Nut if Nut
cannot be tighten
between 70 to 750
inch-pounds. In-
crease torque, to
align with Pin hole in
Through Bolt, to not
exceed 1500 inch-
pounds. (a)
1BACN11N114CSNUTInstall (New)8
(b) (d)1BACP18BC04A14PPINInstall (New)
and attach fuse pins.
Torque nuts on
through bolts to
1500 to 2500 inch-
pounds. Ensure that
all parts are firmly
seated. Refer to
747-8 AMM 54-51-
02 as an accepted
procedure.
2321U8740-1SIDE LINK ASSEMBLYInstall (Kept)9
Refer to SOPM 20-
50-02 as an accept-
ed procedure.
1BACC13AT4K18CABLE ASSEMBLY,
SAFETY
Install (New)
(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20-
60-03 as accepted procedures.
(b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt.
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
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38 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 39

More DataQtyIdentificationNameTaskStep
(c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged.
Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed
on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking
Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do
a check to make sure that the torque vale is correct.
(d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly.
Make sure that the joint is not clamped.
FIGURE 4: STRUT NO. 1 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
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BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 4 OUTBOARD STRUT
STRUT
INBD
BEFORE  A-A  2265404
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 1 OF 8)
Original Issue: January 31, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2238
Work - See page 1 for details.  40 of 56

### Page 41

FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 2 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
41 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
2265583
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 3 OF 8)
Original Issue: January 31, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2238
Work - See page 1 for details.  42 of 56

### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
₴ 15
B
413
4.77  2.38
4.67  2.28
• R= 2.30
2.20
B-B  2265584
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 4 OF 8)
Original Issue: January 31, 2014
Export Controlled ECCN: 9E991 - BOEING  747-54A2238
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  43 of 56

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut outboard side.
More DataQtyIdentificationNameTaskStep
and attach fuse pins.
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2321U8740-1SIDE LINK ASSEMBLYRemove / Keep1
1-CABLE ASSEMBLY,
SAFETY
Remove
and fasteners.1-CLAMPBLOCK - HY-
DRAULIC TUBE SUP-
PRT BRACKET
Remove / Keep2
and lift hydraulic
tube to provide
clearance for installa-
tion of new fuse pin.
1-HYDRAULIC TUBEDisconnect3
by loosening or re-
moving clamp
screws, as required,
to move the conduit.
Keep all clamp
screws, if removed.
--CONDUITMove4
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
1-PINRemove5
1-NUTRemove
1-SELF-LOCKING NUTRemove
1311U8098-9THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Remove
One End Cap is in-
stalled on the
Through Bolt head
side and one End
Cap is installed on
the Through Bold
thread side.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Remove / Keep6
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 5 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
44 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 45

More DataQtyIdentificationNameTaskStep
to provide clearance
for new fuse pin.
Refer to tool
MIT321U8047 in-
structions.
1321U8047-40BRACKET ASSYMachine7
two coats to bare
metal areas. Refer
to SOPM 20-41-02
as an accepted pro-
cedure.
-BMS 10-11, TYPE 1PRIMERApply
Refer to tool
MIT321U8047 in-
structions.
1-FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Remove8
with the flanged end
on the outboard
side. Apply thin film
of Aeroshell Grease
33MS to outer diam-
eter of the fuse pin.
Fuse pin may need
to be rotated up to
40 degrees in order
to clear Side Link
lug. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
1311U8092-3FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Install (New)
After installation, in-
ject grease into
grease fitting until
grease appears at
other side of the
joint. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
-AEROSHELL GREASE
33MS
GREASEApply
One End Cap is in-
stalled on the
Through Bolt head
side and one End
Cap is installed on
the Through Bolt
thread side.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Install (Kept)9
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 6 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
45 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 46

More DataQtyIdentificationNameTaskStep
with bolt head facing
the inboard side. (a)
1311U8098-10THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Install (New)10
(a) (c)1BACN10HR14CSSELF-LOCKING NUTInstall (New)
Apply a torque stripe
to End Cap and Self-
Locking Nut on out-
board side. Refer to
Paragraph 2.C.2.,
Parts and Materials
Supplied by the Op-
erator for acceptable
material.
--MARKING LACQUERApply11
Tighten Nut 70 to
750 inch-pounds.
Replace Nut if Nut
cannot be tighten
between 70 to 750
inch-pounds. In-
crease torque, to
align with Pin hole in
Through Bolt, to not
exceed 1500 inch-
pounds. (a)
1BACN11N114CSNUTInstall (New)12
(b) (d)1BACP18BC04A14PPINInstall (New)
back to previous po-
sition. Install clamp
screws, if removed.
--CONDUITMove13
1-HYDRAULIC TUBEConnect14
to seal surface of
sleeve before seat-
ing B-nut, to external
fitting threads, and
to shoulder of
sleeve. Torque B-nut
to 855 to 945 inch-
pounds. Refer to
SOPM 20-50-00 as
an accepted proce-
dure.
-BMS 3-11  (MCS-352
optional)
HYDRAULIC FLUIDApply
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 7 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
46 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 47

More DataQtyIdentificationNameTaskStep
and fasteners.
Torque nut to 3.5 to
30.0 inch-pounds.
Refer to SOPM 20-
50-01 as an accept-
ed procedure.
1-CLAMPBLOCK - HY-
DRAULIC TUBE SUP-
PRT BRACKET
Install (Kept)15
and attach fuse pins.
Torque nuts on
through bolts to
1500 to 2500 inch-
pounds. Ensure that
all parts are firmly
seated. Refer to
747-8 AMM 54-51-
02 as an accepted
procedure.
2321U8740-1SIDE LINK ASSEMBLYInstall (Kept)16
Refer to SOPM 20-
50-02 as an accept-
ed procedure.
1BACC13AT4K18CABLE ASSEMBLY,
SAFETY
Install (New)
(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20-
60-03 as accepted procedures.
(b) If Pin can not be installed, then back off the Nut a minimum amount to align pin hole in Through Bolt.
(c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged.
Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed
on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking
Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do
a check to make sure that the torque vale is correct.
(d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly.
Make sure that the joint is not clamped.
FIGURE 5: STRUT NO. 4 - INBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 8 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
47 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
NO. 4 OUTBOARD STRUT
~ STRUT
INBD  BEFORE  2265660
A-A
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 1 OF 5)
Original Issue: January 31, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2238
Work - See page 1 for details.  48 of 56

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut inboard side.
More DataQtyIdentificationNameTaskStep
and attach fuse pins.
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
2321U8740-1SIDE LINK ASSEMBLYRemove / Keep1
1-CABLE ASSEMBLY,
SAFETY
Remove
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 2 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
49 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 50

More DataQtyIdentificationNameTaskStep
Refer to 747-8 AMM
54-51-02 as an ac-
cepted procedure.
1-PINRemove2
1-NUTRemove
1-SELF-LOCKING NUTRemove
1311U8098-9THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Remove
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Remove / Keep3
Refer to tool
MIT321U8047 in-
structions.
1-FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Remove4
with the flanged end
on the inboard side.
Apply thin film of
Aeroshell Grease
33MS to outer diam-
eter of the fuse pin.
Fuse pin may need
to be rotated up to
40 degrees in order
to clear Side Link
lug. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
1311U8092-3FUSE PIN - AFT UP-
PER SPAR NACELLE
STRUT
Install (New)
After installation, in-
ject grease into
grease fitting until
grease appears at
other side of the
joint. Refer to SOPM
20-50-07 as an ac-
cepted procedure.
-AEROSHELL GREASE
33MS
GREASEApply
One End Cap is in-
stalled on the
Through Bolt head
side and one End
Cap is installed on
the Through Bolt
thread side.
2311U8095-9END CAP - AFT UP-
PER SPAR NACELLE
STRUT
Install (Kept)5
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
50 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 51

More DataQtyIdentificationNameTaskStep
with bolt head facing
the outboard side.
(a)
1311U8098-10THROUGH BOLT -
AFT UPPER SPAR
NACELLE STRUT
Install (New)6
(a) (c)1BACN10HR14CSSELF-LOCKING NUTInstall (New)
Apply a torque stripe
to End Cap and Self-
Locking Nut on in-
board side. Refer to
Paragraph 2.C.2.,
Parts and Materials
Supplied by the Op-
erator for acceptable
material.
--MARKING LACQUERApply7
Tighten Nut 70 to
750 inch-pounds.
Replace Nut if Nut
cannot be tighten
between 70 to 750
inch-pounds. In-
crease torque, to
align with Pin hole in
Through Bolt, to not
exceed 1500 inch-
pounds. (a)
1BACN11N114CSNUTInstall (New)8
(b) (d)1BACP18BC04A14PPINInstall (New)
and attach fuse pins.
Torque nuts on
through bolts to
1500 to 2500 inch-
pounds. Ensure that
all parts are firmly
seated. Refer to
747-8 AMM 54-51-
02 as an accepted
procedure.
2321U8740-1SIDE LINK ASSEMBLYInstall (Kept)9
Refer to SOPM 20-
50-02 as an accept-
ed procedure.
1BACC13AT4K18CABLE ASSEMBLY,
SAFETY
Install (New)
(a) Apply anti-seize thread compound to threads before installation. Refer to SOPM 20-50-07 and SOPM 20-
60-03 as accepted procedures.
(b) If Pin can not be installed, then back off the Nut minimum amount to align pin hole in Through Bolt.
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
51 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 52

More DataQtyIdentificationNameTaskStep
(c) To install Self-Locking Nut, use the following procedure. Tighten until the Self-Locking Nut is fully engaged.
Tighten Self-Locking Nut to run-on torque of 70 to 600 inch-pounds. The torque wrench must be installed
on the Self-Locking Nut and not the head of the Through Bolt. Replace Self-Locking Nut if Self-Locking
Nut cannot be tighten to run-on torque range. Tighten Self-Locking Nut to 2800 to 3200 inch-pounds. Do
a check to make sure that the torque vale is correct.
(d) Make sure to check that the Through Bolt, End Caps, Self Locking Nut, Nut, and Pin are installed correctly.
Make sure that the joint is not clamped.
FIGURE 6: STRUT NO. 4 - OUTBOARD SIDE - AFT UPPER SPAR FUSE PIN REPLACEMENT
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
52 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
¡ A
NO. 1 OUTBOARD STRUT
2265666
FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION
(SHEET 1 OF 2)
Original Issue: January 31, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-54A2238
Work - See page 1 for details.  53 of 56

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut.
More DataQtyIdentificationNameTaskStep
1323U8215-5ACCESS COVER AS-
SY, OUTBD SIDE, LH
OUTBD ENGINE
Install (New)1
with BMS 3-33, Type
1 grease on bolt
shank. Torque to 60
to 80 inch-pounds.
13-BOLTInstall (Kept)
1323U8225-3ACCESS COVER AS-
SY, INBD SIDE, LH
OUTBD ENGINE
Install (Kept)2
with BMS 3-33, Type
I grease on bolt
shank. Torque to 60
to 80 inch-pounds.
11-BOLTInstall (Kept)
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
These parts are not required for
installing Access Cover Assem-
blies. These parts can be used to
replace kept parts if grip length
meets installation requirements.
15BACB30NN4K11
(BACB30NN4K11G op-
tional)
BOLT
FIGURE 7: STRUT NO. 1 - ACCESS COVER ASSEMBLY INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
54 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-54A2238
ALERT  ALERT
¡ A
NO. 4 OUTBOARD STRUT
2265667
FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION
(SHEET 1 OF 2)
Original Issue: January 31, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-54A2238
Work - See page 1 for details.  55 of 56

### Page 56

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one engine strut.
More DataQtyIdentificationNameTaskStep
1323U8215-6ACCESS COVER AS-
SY, OUTBD SIDE, RH
OUTBD ENGINE
Install (New)1
with BMS 3-33, Type
1 grease on bolt
shank. Torque to 60
to 80 inch-pounds.
13-BOLTInstall (Kept)
1323U8225-4ACCESS COVER AS-
SY, INBD SIDE, RH
OUTBD ENGINE
Install (Kept)2
with BMS 3-33, Type
I grease on bolt
shank. Torque to 60
to 80 inch-pounds.
11-BOLTInstall (Kept)
The parts shown in the table below are provided as extra parts for this figure.
More DataQtyIdentificationName
These parts are not required for
installing Access Cover Assem-
blies. These parts can be used to
replace kept parts if grip length
meets installation requirements.
15BACB30NN4K11
(BACB30NN4K11G op-
tional)
BOLT
FIGURE 8: STRUT NO. 4 - ACCESS COVER ASSEMBLY INSTALLATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 31, 2014
747-54A2238
56 of 56
BOEING SERVICE BULLETIN 747-54A2238
ALERTALERT

---
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