# Boeing Alert Service Bulletin 747-54A2247: No revision named

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- Document: [Boeing Alert Service Bulletin 747-54A2247](https://openairdocs.org/service-documents/boeing/747-54a2247.md)
- Title as filed: SB-747-54A2247-00--
- Pages: 50
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2247
Original Issue: August 03, 2017
ATA System: 5461
SUBJECT: NACELLES/PYLONS - No.1 and No.4 Engines Strut Aft Fairings - Vapor Seal, Block
Seal, Heat Shield Seal and Seal Retainer Change
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 © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: August 03, 2017
747-54A2247
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Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 14
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 20
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
FIGURE 1: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL . 26
FIGURE 2: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL . 28
FIGURE 3: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30
FIGURE 4: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
FIGURE 5: NO.1 STRUT - AFT FAIRING NEW PART MARK . . . . . . . . . . . . . . . . . . . . . . 36
FIGURE 6: NO.4 STRUT - AFT FAIRING NEW PART MARK . . . . . . . . . . . . . . . . . . . . . . 39
FIGURE 7: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION  [Group 1] . . . 42
FIGURE 8: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION  [Group 1] . . . 44
FIGURE 9: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION  [Group 2] . . . 46
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FIGURE 10: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION  [Group 2] . . . 48
APPENDIX A: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-54A2247Original Issue: August 03, 2017
ATA System: 5461
SUBJECT: NACELLES/PYLONS - No.1 and No.4 Engines Strut Aft Fairings - Vapor Seal, Block
Seal, Heat Shield Seal and Seal Retainer Change
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
Accomplishment of this service bulletin will prevent heat damage on the vapor seal between the strut and aft
fairing of the number 1 and number 4 engines. In the event of a flammable fluid leakage in the aft fairing structure,
damaged vapor seals could result in an uncontained engine strut fire.
Boeing has received reports from operators of damaged vapor seals, block seals, and heat shield seals on
number 1 and number 4 engines aft strut fairings. As a result, Boeing has issued Service Bulletin 747-54A2246
to inspect for heat damage and replace heat damaged parts.
Since the release of Boeing Service Bulletin 747-54A2246, Boeing has designed new and improved heat shield
seal and retainer, block seals and access panels to prevent hot exhaust gases from entering the aft fairing. This
new and improved design includes the following improvements:
– The new heat shield seal prevents hot exhaust gas flowing into the aft fairing with redesigned seal and
retainer
– The new block seals seal the edges of the aft fairing between the heat shield seal and vapor seal
– The new access panels allow external airflow into the space between strut and aft fairing
This service bulletin gives instructions to modify the heat shield seal and retainer, block seals, and replace the
existing vapor seal and access panel. Accomplishment of this replacement is terminating action for the inspection
requirements in SAFETY RELATED - INITIAL AND REPEAT INSPECTIONS AND REPLACEMENT OF SEALS
in accordance with SB 747-54A2246. In addition, a final one-time accomplishment of ECONOMIC RELATED -
STRUCTURAL INSPECTION AND REPAIR FOR HEAT DAMAGE in accordance with SB 747-54A2246 and
accomplishment of this service bulletin is the terminating action to the economic related inspections of SB
747-54A2246.
Boeing Service Related Problem (SRP) 747-8-SRP-54-0153 is related to this service bulletin.
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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 ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/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 85901-156S)
Deactivate the trailing edge flaps. Remove and keep the aft fairings at the number 1 and number 4 engine strut.
Remove vapor seals. Remove block seals. Remove heat shield seals and heat shield seal retainer. Install new
vapor seal. Install new block seals. Install new heat shield seal and heat shield seal retainer. Install the kept aft
fairings at the number 1 and number 4 engine strut. Remove lateral restraint access panels. Install new lateral
restraint access panels. Activate the trailing edge flaps.
EFFECTIVITY
747-8/8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-04-13 is related to this service bulletin.
The effective date of AD 2017-04-13 is April 3, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional 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 modification given in this service bulletin be done within 4 years or 4,800 flight
cycles after the original issue date of this service bulletin, whichever occurs first.
NOTE: Accomplishment of this modification is terminating action for the inspection requirements in SAFETY
RELATED - INITIAL AND REPEAT INSPECTIONS AND REPLACEMENT OF SEALS in accordance
with Boeing Service Bulletin 747-54A2246.
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Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of February 12, 2015. 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.
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
NACELLE
STRUT
ASSEMBLY
ENGINE
COWLING
- G
NO.1 OUTBOARD NACELLE
(NO.4 OUTBOARD NACELLE OPPOSITE)
DO THE MODIFICATION TO INSTALL
NEW AND IMPROVED HEAT SHIELD
SEAL, SEAL RETAINER, BLOCK
SEALS, AND LATERAL RESTRAINT
ACCESS PANEL
WD
NO. 1 AND NO. 4 STRUT AFT FAIRING
(NO. 4 OPPOSITE OUTBOARD STRUT)
2554562
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### Page 9

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2247
Original Issue: August 03, 2017
ATA System: 5461
SUBJECT: NACELLES/PYLONS - No.1 and No.4 Engines Strut Aft Fairings - Vapor Seal, Block
Seal, Heat Shield Seal and Seal Retainer Change
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 747-8/8F Airplanes, line numbers 1420-1540 in 2 Groups.
The Variable Numbers and Group Information for the applicable airplanes is given below. An
equivalent change is on subsequent production airplanes. Refer to PRR 85901-156S for data
about this change.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
Airplane line numbers 1420 - 1453 that have the 321U8595-1/-2
lateral restraint access panels installed.
-1
Airplane line numbers 1454 - 1540 that have the 321U8595-3/-4
lateral restraint access panels installed.
-2
Airplane Models:
747-8, 747-8F
GroupVariable Number
1RC001 - RC005
2RC006 - RC009
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GroupVariable Number
1RC021 - RC024
2RC025 - RC040
2RC051 - RC060
2RC066 - RC072
2RC076 - RC077
1RC501 - RC504
2RC505 - RC514
1RC521 - RC523
2RC524 - RC528
1RC541
1RC546
2RC547 - RC550
1RC551 - RC557
2RC558 - RC566
1RC571 - RC576
2RC577 - RC582
1RC601 - RC603
2RC604 - RC606
2RC641 - RC644
2RC651 - RC652
2RC661
2RC671 - RC674
2. Spares Affected
None.
B. Concurrent Requirements
The service bulletins listed below must be done at the same time as this service bulletin:
DescriptionService BulletinCompany
A final one time ECONOMIC RELATED -
STRUCTURAL INSPECTION AND REPAIR
FOR HEAT DAMAGE on the strut aft fairing.
(a)
747-54A2246 Original Issue or Revision 1The Boeing Compa-
ny
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DescriptionService BulletinCompany
(a) Accomplishment of a final, one-time ECONOMIC RELATED - STRUCTURAL INSPECTION AND REPAIR
FOR HEAT DAMAGE in accordance with 747-54A2246 and accomplishment of this service bulletin is the
terminating action to the economic related inspections of 747-54A2246.
C. Reason
Accomplishment of this service bulletin will prevent heat damage on the vapor seal between the strut
and aft fairing of the number 1 and number 4 engines. In the event of a flammable fluid leakage in the
aft fairing structure, damaged vapor seals could result in an uncontained engine strut fire.
Boeing has received reports from operators of damaged vapor seals, block seals, and heat shield seals
on number 1 and number 4 engines aft strut fairings. As a result, Boeing has issued Service Bulletin
747-54A2246 to inspect for heat damage and replace heat damaged parts.
Since the release of Boeing Service Bulletin 747-54A2246, Boeing has designed new and improved
heat shield seal and retainer, block seals and access panels to prevent hot exhaust gases from entering
the aft fairing. This new and improved design includes the following improvements:
– The new heat shield seal prevents hot exhaust gas flowing into the aft fairing with redesigned seal
and retainer
– The new block seals seal the edges of the aft fairing between the heat shield seal and vapor seal
– The new access panels allow external airflow into the space between strut and aft fairing
This service bulletin gives instructions to modify the heat shield seal and retainer, block seals, and
replace the existing vapor seal and access panel. Accomplishment of this replacement is terminating
action for the inspection requirements in SAFETY RELATED - INITIAL AND REPEAT INSPECTIONS
AND REPLACEMENT OF SEALS in accordance with SB 747-54A2246. In addition, a final one-time
accomplishment of ECONOMIC RELATED - STRUCTURAL INSPECTION AND REPAIR FOR HEAT
DAMAGE in accordance with SB 747-54A2246 and accomplishment of this service bulletin is the
terminating action to the economic related inspections of SB 747-54A2246.
Boeing Service Related Problem (SRP) 747-8-SRP-54-0153 is related to this service bulletin.
D. Description
Deactivate the trailing edge flaps. Remove and keep the aft fairings at the number 1 and number 4
engine strut. Remove vapor seals. Remove block seals. Remove heat shield seals and heat shield
seal retainer. Install new vapor seal. Install new block seals. Install new heat shield seal and heat shield
seal retainer. Install the kept aft fairings at the number 1 and number 4 engine strut. Remove lateral
restraint access panels. Install new lateral restraint access panels. Activate the trailing edge flaps.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
452, 454, 482, 484747-8, 747-8F
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E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-04-13 is related to this service
bulletin. The effective date of AD 2017-04-13 is April 3, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional 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 modification given in this service bulletin be done within 4 years or 4,800
flight cycles after the original issue date of this service bulletin, whichever occurs first.
NOTE: Accomplishment of this modification is terminating action for the inspection requirements in
SAFETY RELATED - INITIAL AND REPEAT INSPECTIONS AND REPLACEMENT OF SEALS
in accordance with Boeing Service Bulletin 747-54A2246.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Seattle approves the action (i.e. inspection or modification) defined
in this service bulletin as an alternative method of compliance to the requirements of paragraphs (g)
and (h) of AD 2017-04-13. All provisions of AD 2017-04-13 that are not specifically referenced in the
above statement remain fully applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplanes.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
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Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
8.1064.808Open Access
0.500.501FIGURE 1
0.500.501FIGURE 2
1.401.401FIGURE 3
1.401.401FIGURE 4
0.250.251FIGURE 5
0.250.251FIGURE 6
1.001.001FIGURE 7
1.001.001FIGURE 8
8.1064.808Close Access
22.50135.90TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
8.1064.808Open Access
0.500.501FIGURE 1
0.500.501FIGURE 2
1.401.401FIGURE 3
1.401.401FIGURE 4
0.250.251FIGURE 5
0.250.251FIGURE 6
1.001.001FIGURE 9
1.001.001FIGURE 10
8.1064.808Close Access
22.50135.90TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-156S
b. Boeing Service Bulletin 747-54A2246
c. Boeing Service Related Problem (SRP) 747-8-SRP-54-0153
d. Component Maintenance Manual (CMM) 54-52-06
e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2017-04-13
f. Service Bulletin Index D6-30300
g. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-01, 20-50-10, 20-50-12,
20-50-19
h. 747-8 Aircraft Maintenance Manual (AMM) 27-51-00, 54-61-02
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
AFT FAIRING INSTL - OUTBD323U8300
SEAL INSTALLATION - OUTBD AFT FAIRING323U8450
AFT FAIRING INSTL - OUTBD323U8300
FWD HEATSHIELD INSTL - OUTBD AFT FAIRING323U8801
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
54-52, 54-61, 54-62747 Illustrated Parts Catalog
54-52Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
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Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
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### Page 17

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
Group 1:
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
$21,910.00229 days5July 31, 2017KIT - RETROFIT- AFT
FAIRING HEAT
SHIELD SEALS
CHANGE
015U2192-1
$21,910.00229 days5August 31,
2017
$21,910.00229 days5October 16,
2017
$21,910.00229 days2November 13,
2017
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Group 2:
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
$21,910.00229 days5July 31, 2017KIT - RETROFIT- AFT
FAIRING HEAT
SHIELD SEALS
CHANGE
015U2192-2
$21,910.00229 days5August 31,
2017
$21,910.00229 days5October 16,
2017
$21,910.00229 days5November 13,
2017
$21,910.00229 days5December 13,
2017
$21,910.00229 days5January 19,
2018
$21,910.00229 days5February 16,
2018
$21,910.00229 days5March 16,
2018
$21,910.00229 days5April 18, 2018
Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Kits.
B. Industry Support Information
Boeing warranty remedies are available for 747 airplanes in warranty as of February 12, 2015. For
task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to BCA
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 Material Management. Please refer to this service bulletin
number and reference the airplane variable number 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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Figure Kit
1098743Top Kit
--1111015U2192-1
11--11015U2192-2
Group 1:
KIT 015U2192-1
Notes
Existing Part
NumberName
Figure
New Part Number
8743
Qty
(a)(b)321U8595-1ACCESS PANEL -
LATERAL RE-
STRAINT, LH
.1..321U8595-9
(a)(b)321U8595-2ACCESS PANEL -
LATERAL RE-
STRAINT, RH
1...321U8595-10
(a)323U8452-3VAPOR SEAL -
OUTBD AFT FAIR-
ING
..11323U8452-3
(a)(b)323U8452-2SEAL BLOCK -
OUTBD AFT FAIR-
ING
..22323U8452-4
(a)(b)323U8852-1HEATSHIELD
SEAL FWD - OUT-
BOARD AFT FAIR-
ING
..11323U8852-5
(a)(b)323U8852-2HEATSHIELD
SEAL RETAINER
FWD - OUT-
BOARD AFT FAIR-
ING
..11323U8852-6
(a) Discard the existing part.
(b) You cannot use the existing part to replace the new or changed part.
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Group 2:
KIT 015U2192-2
Notes
Existing Part
NumberName
Figure
New Part Number
10943
Qty
(a)(b)321U8595-3ACCESS PANEL -
LATERAL RE-
STRAINT, LH
.1..321U8595-7
(a)(b)321U8595-4ACCESS PANEL -
LATERAL RE-
STRAINT, RH
1...321U8595-8
(a)323U8452-3VAPOR SEAL -
OUTBD AFT FAIR-
ING
..11323U8452-3
(a)(b)323U8452-2SEAL BLOCK -
OUTBD AFT FAIR-
ING
..22323U8452-4
(a)(b)323U8852-1HEATSHIELD
SEAL FWD - OUT-
BOARD AFT FAIR-
ING
..11323U8852-5
(a)(b)323U8852-2HEATSHIELD
SEAL RETAINER
FWD - OUT-
BOARD AFT FAIR-
ING
..11323U8852-6
(a) Discard the existing part.
(b) You cannot use the existing part to replace the new or changed part.
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.
NotesNameQTYPart Number /
Specification
(a)FIREWALL SEALANT4 Oz.BMS 5-63, TYPE I
(b)ADHESIVE4 Oz.SOPM 20-50-12,
TYPE 60
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
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NotesNameQTYPart Number /
Specification
(b) Refer to the Boeing Standard Overhaul Practices Manual (SOPM) for material information
and supplier data.
3. Parts Modified and Reidentified
NotesNew Part NumberNameQTYExisting Part
Number
(a)323U8400-13 (b)SAF GE P1 AFT FAIR-
ING ASSY - OUTBD
1323U8400-11
(a)323U8400-14 (b)SAF GE P4 AFT FAIR-
ING ASSY - OUTBD
1323U8400-12
(a) Make the change in accordance with this service bulletin.
(b) This is the part number after the change is done in accordance with this service bulletin.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

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 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
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7. 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. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
12. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
1. Deactivate the trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted procedure.
2. Remove and keep the aft fairings at the number 1 and number 4 engine strut. Refer to 747-8 AMM
54-61-02 as an accepted procedure.
3. Remove the aft fairing vapor seal, heat shield seal, heat shield seal retainer, and block seals in
accordance with the figures in the following table:
No.4 StrutNo.1 Strut
FIGURE 2FIGURE 1
4. RC - Install the aft fairing vapor seal, heat shield seal, heat shield seal retainer, and block seals
in accordance with the figures in the following table:
No.4 StrutNo.1 Strut
FIGURE 4FIGURE 3
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### Page 25

5. Identify the aft fairing with the new part number in accordance with the figures in the following
table:
No.4 StrutNo.1 Strut
FIGURE 6FIGURE 5
6. Install the kept aft fairings. Refer to 747-8 AMM 54-61-02 as an accepted procedure.
7. RC - Remove and install the outboard lateral restraint access panel in accordance with the figures
below:
Group 1:
No.4 StrutNo.1 Strut
FIGURE 8FIGURE 7
Group 2:
No.4 StrutNo.1 Strut
FIGURE 10FIGURE 9
8. Activate the trailing edge flaps. Refer to 747-8 AMM 27-51-00 as an accepted procedure.
9. Put the airplane back to a serviceable condition.
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### Page 26 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
VAPOR SEAL
HEATSHIELD SEAL
SEAL RETAINER
NO. 1 STRUT AFT FAIRING
2554730
FIGURE 1: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL
(SHEET 1 OF 2)
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### Page 27

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
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
1323U8452-3VAPOR SEALRemove1
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
2323U8452-2BLOCK SEALRemove2
-2BACB30LM4U6BOLTRemove / Keep3
-2BACW10BP4ACUWASHERRemove / Keep
-1323U8852-2SEAL RETAINERRemove
-1323U8852-1HEAT SHIELD SEALRemove
FIGURE 1: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL
(SHEET 2 OF 2)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
1 VAPOR SEAL
) HEATSHIELD
SEAL
BLOCK SEAL
(2 LOCATIONS)
NO. 4 STRUT AFT FAIRING  2554748
FIGURE 2: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL
(SHEET 1 OF 2)
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### Page 29

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
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
1323U8452-3VAPOR SEALRemove1
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
2323U8452-2BLOCK SEALRemove2
-2BACB30LM4U6BOLTRemove / Keep3
-2BACW10BP4ACUWASHERRemove / Keep
-1323U8852-2SEAL RETAINERRemove
-1323U8852-1HEAT SHIELD SEALRemove
FIGURE 2: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS REMOVAL
(SHEET 2 OF 2)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
VAPOR SEAL
HEATSHIELD SEAL
SEAL RETAINER
NO. 1 STRUT AFT FAIRING
2554749
FIGURE 3: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 1 OF 3)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
A-A
2557958
FIGURE 3: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 2 OF 3)
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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
(a)-BMS 5-63, TYPE IFIREWALL SEALANTApply1
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
1323U8452-3VAPOR SEAL -
OUTBD AFT FAIRING
Install (New)
-1323U8852-5HEATSHIELD SEAL
FWD - OUTBOARD
AFT FAIRING
Install (New)2
-1323U8852-6HEATSHIELD SEAL
RETAINER FWD -
OUTBOARD AFT
FAIRING
Install (New)
Torque to 20-82 in-
lbs. Make sure the
seal retainer is not
permanently de-
formed.
2BACB30LM4U6BOLTInstall (Kept)
-2BACW10BP4ACUWASHERInstall (Kept)
(b)-323U8701-()AFT FAIRING, FRAME
1 ASSY
Clean3
(c)--SILICONE ADHESIVE,
TYPE 60
Apply4
(d)2323U8452-4SEAL BLOCK - OUTBD
AFT FAIRING
Install (New)5
(e)-BMS 5-63, TYPE IFIREWALL SEALANTApply6
(a) Fay surface seal between the aft fairing frame and the vapor seal to areas not common with the vapor
seal retainer. Refer to SOPM 20-50-19 as an accepted procedure.
(b) Clean the fay surface area on the frame at the location of the block seal installation. Refer to SOPM 20-
30-03 as an accepted procedure.
(c) Apply adhesive to the block seals. Refer to CMM 54-52-06, Repair 2-1, or SOPM 20-50-12 as an accepted
procedure.
(d) Bond the seals to the frame. Refer to CMM 54-52-06, Repair 2-1, or SOPM 20-50-12 as an accepted
procedure.
(e) Fill the gaps between the block seals and vapor seal. Refer to CMM 54-52-06, Repair 2-1, or SOPM 20-
50-19 as an accepted procedure.
FIGURE 3: NO.1 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 3 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
1 VAPOR SEAL
(2) HEATSHIELD SEAL
SEAL RETAINER
NO. 4 STRUT AFT FAIRING
2554750
FIGURE 4: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 1 OF 3)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
A-A
2557972
FIGURE 4: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 2 OF 3)
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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
(a)-BMS 5-63, TYPE IFIREWALL SEALANTApply1
Refer to CMM 54-
52-06, Repair 2-1,
as an accepted pro-
cedure.
1323U8452-3VAPOR SEAL -
OUTBD AFT FAIRING
Install (New)
-1323U8852-5HEATSHIELD SEAL
FWD - OUTBOARD
AFT FAIRING
Install (New)2
-1323U8852-6HEATSHIELD SEAL
RETAINER FWD -
OUTBOARD AFT
FAIRING
Install (New)
Torque to 20-82 in-
lbs. Make sure the
seal retainer is not
permanently de-
formed.
2BACB30LM4U6BOLTInstall (Kept)
-2BACW10BP4ACUWASHERInstall (Kept)
(b)-323U8701-()AFT FAIRING, FRAME
1 ASSY
Clean3
(c)--SILICONE ADHESIVE,
TYPE 60
Apply4
(d)2323U8452-4SEAL BLOCK - OUTBD
AFT FAIRING
Install (New)5
(e)-BMS 5-63, TYPE IFIREWALL SEALANTApply6
(a) Fay surface seal between the aft fairing frame and the vapor seal to areas not common with the vapor
seal retainer. Refer to SOPM 20-50-19 as an accepted procedure.
(b) Clean the fay surface area on the frame at the location of the block seal installation. Refer to SOPM 20-
30-03 as an accepted procedure.
(c) Apply adhesive to the block seals. Refer to CMM 54-52-06, Repair 2-1, or SOPM 20-50-12 as an accepted
procedure.
(d) Bond the seals to the frame. Refer to CMM 54-52-06, Repair 2-1, or SOPM 20-50-12 as an accepted
procedure.
(e) Fill the gaps between the block seals, vapor seal and heat shield seal. Refer to CMM 54-52-06, Repair
2-1, or SOPM 20-50-19 as an accepted procedure.
FIGURE 4: NO.4 STRUT - VAPOR SEALS, BLOCK SEALS AND HEAT SHIELD SEALS INSTALLATION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
35 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
NO. 1 STRUT AFT FAIRING
2558022
FIGURE 5: NO.1 STRUT - AFT FAIRING NEW PART MARK
(SHEET 1 OF 3)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2247
Work - See page 1 for details.  36 of 50

### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
P
INBD
(VIEW LOOKING DOWN)
A-A  2562292
FIGURE 5: NO.1 STRUT - AFT FAIRING NEW PART MARK
(SHEET 2 OF 3)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  747-54A2247
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  37 of 50

### 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
(a)-323U8400-11SAF GE P1 AFT FAIR-
ING ASSY - OUTBD
Identify1
(a) Mark the new part number. Refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator.
Refer to SOPM 20-50-10, Part Mark RH, as an accepted procedure.
FIGURE 5: NO.1 STRUT - AFT FAIRING NEW PART MARK
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
38 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
NO. 4 STRUT AFT FAIRING
2558031
FIGURE 6: NO.4 STRUT - AFT FAIRING NEW PART MARK
(SHEET 1 OF 3)
Original Issue: August 03, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-54A2247
Work - See page 1 for details.  39 of 50

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
(VIEW LOOKING DOWN)
A-A
FIGURE 6: NO.4 STRUT - AFT FAIRING NEW PART MARK
(SHEET 2 OF 3)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2247
Work - See page 1 for details.  40 of 50

### Page 41

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
(a)-323U8400-12SAF GE P4 AFT FAIR-
ING ASSY - OUTBD
Identify1
(a) Mark the new part number. Refer to Paragraph 2.C.2., Parts and Materials Supplied by the Operator.
Refer to SOPM 20-50-10, Part Mark RH, as an accepted procedure.
FIGURE 6: NO.4 STRUT - AFT FAIRING NEW PART MARK
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
41 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
This Figure applies only to: Group 1.
NACELLE
STRUT
ASSEMBLY
ENGINE
COWLING  • 9t
￾- €
NO.1 OUTBOARD NACELLE
2558012
FIGURE 7: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 1 OF 2)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  747-54A2247
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  42 of 50

### Page 43

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
-10-FASTENERRemove / Keep1
-1321U8595-1ACCESS PANEL, LAT-
ERAL RESTRAINT, LH
Remove
-1321U8595-9ACCESS PANEL -
LATERAL RE-
STRAINT, LH
Install (New)2
(a)10-FASTENERInstall (Kept)
(a) Torque fasteners to 25-35 in-lbs.
FIGURE 7: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
43 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
This Figure applies only to: Group 1.
NACELLE
STRUT
ASSEMBLY
ENGINE
— COWLING
FWD
NO.4 OUTBOARD NACELLE
2558015
FIGURE 8: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 1 OF 2)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure:
More DataQtyIdentificationNameTaskStep
-10-FASTENERRemove / Keep1
-1321U8595-2ACCESS PANEL, LAT-
ERAL RESTRAINT, RH
Remove
-1321U8595-10ACCESS PANEL -
LATERAL RE-
STRAINT, RH
Install (New)2
(a)10-FASTENERInstall (Kept)
(a) Torque fasteners to 25-35 in-lbs.
FIGURE 8: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
45 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
This Figure applies only to: Group 2.
NACELLE
STRUT
ASSEMBLY
ENGINE
COWLING  • 9t
￾- €
NO.1 OUTBOARD NACELLE
2560416
FIGURE 9: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 1 OF 2)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  747-54A2247
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  46 of 50

### Page 47

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
-9-FASTENERRemove / Keep1
-1321U8595-3ACCESS PANEL, LAT-
ERAL RESTRAINT, LH
Remove
-1321U8595-7ACCESS PANEL -
LATERAL RE-
STRAINT, LH
Install (New)2
(a)9-FASTENERInstall (Kept)
(a) Torque fasteners to 25-35 in-lbs.
FIGURE 9: NO.1 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
47 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
This Figure applies only to: Group 2.
NACELLE
STRUT
ASSEMBLY
ENGINE
— COWLING
FWD
NO.4 OUTBOARD NACELLE
2560407
FIGURE 10: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 1 OF 2)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  48 of 50

### 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 this figure:
More DataQtyIdentificationNameTaskStep
-9-FASTENERRemove / Keep1
-1321U8595-4ACCESS PANEL, LAT-
ERAL RESTRAINT, RH
Remove
-1321U8595-8ACCESS PANEL -
LATERAL RE-
STRAINT, RH
Install (New)2
(a)9-FASTENERInstall (Kept)
(a) Torque fasteners to 25-35 in-lbs.
FIGURE 10: NO.4 STRUT - LATERAL RESTRAINT ACCESS PANEL MODIFICATION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 03, 2017
747-54A2247
49 of 50
BOEING SERVICE BULLETIN 747-54A2247
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-54A2247
ALERT  ALERT
Boeing Part Demand Intent
After review of this service bulletin (SB), Boeing asks that the primary engineer fill out this survey to
elp Boeing predict the quantity and timing of the Boeing supplied kits
Airline:
Contact Name:
Date:
Contact E-mail:
_ Yes  Have/will you recommend to your airline to accomplish this SB?
_ Yes  _ No Would issuance of an Airworthiness Directive change this decision?
When would you likely be starting this SB incorporation? Month/ Year
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes.
For inspection related SBs, are you planning to replace on condition, or a tleet campaign to replace on
all airplanes regardless of condition?
On Condition  _ Campaign
If you are not incorporating this SB at this time will you please help us understand the reason(s) why?
Your input will help us provide better customer support.
- Cost Prohibitive  Continue Inspections  • Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to:
sbsolutions@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not
constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute
a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
2406495
APPENDIX A: PART DEMAND INTENT
(SHEET 1 OF 1)
Original Issue: August 03, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-54A2247
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