# Boeing Alert Service Bulletin 747-54A2232: No revision named

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- Document: [Boeing Alert Service Bulletin 747-54A2232](https://openairdocs.org/service-documents/boeing/747-54a2232.md)
- Title as filed: U.S. DOT/FAA - Service Bullentin
- Pages: 99
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## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2232
Original Issue: April 15, 2010
ATA System: 5410 5451 5432 5462 1113
SUBJECT: NACELLES/PYLONS - Nacelle Strut Spring Beam - Spring Beam Mid Pivot Bolt
Assembly - Access Door Inspection and Replacement, Marker Installation, and Bolt
Assembly Inspection and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2010 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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### Page 3

Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 3
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 7
H. Weight and Balance Changes .................................... 1 9
I. Electrical Load Data ......................................... 2 0
J. References .............................................. 2 0
1. Existing Data .......................................... 2 0
2. Data supplied with this Service Bulletin ............................ 2 0
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 0
K. Publications Affected ........................................ 2 0
L. Interchangeability and Intermixability of Parts ........................... 2 1
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts ............................................ 2 3
2. Parts and Materials Supplied by the Operator ........................ 2 5
3. Parts Modified and Reidentified ................................ 2 6
4. Parts Removed and Not Replaced .............................. 2 6
D. Parts Necessary to Change Spares ................................. 2 6
E. Special Tooling - Price and Availability ............................... 2 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION .... 3 4
FIGURE 2: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION ...... 3 6
FIGURE 3: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION ...... 3 8
FIGURE 4: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION .... 4 0
FIGURE 5: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 1] ............................................ 4 2
FIGURE 6: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 1] ............................................ 4 4
FIGURE 7: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 1] ............................................ 4 6
FIGURE 8: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 1] ............................................ 4 8
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FIGURE 9: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 2] ............................................ 5 0
FIGURE 10: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 2] ............................................ 5 2
FIGURE 11: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 2] ............................................ 5 4
FIGURE 12: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 2] ............................................ 5 6
FIGURE 13: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 3] ............................................ 5 8
FIGURE 14: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 3] ............................................ 6 0
FIGURE 15: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 3] ............................................ 6 2
FIGURE 16: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
[Group 3] ............................................ 6 4
FIGURE 17: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT BOLT ASSEMBLY - REPLACEMENT . 66
FIGURE 18: STRUT NO. 1 - INBOARD SIDE - MID PIVOT BOLT ASSEMBLY - REPLACEMENT . . . 68
FIGURE 19: STRUT NO. 4 - INBOARD SIDE - MID PIVOT BOLT ASSEMBLY - REPLACEMENT . . . 70
FIGURE 20: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT BOLT ASSEMBLY - REPLACEMENT . 72
FIGURE 21: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - REPLACEMENT . . . 74
FIGURE 22: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - REPLACEMENT .... 7 6
FIGURE 23: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - REPLACEMENT .... 7 8
FIGURE 24: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - REPLACEMENT . . . 80
FIGURE 25: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT BOLT ASSEMBLY - INSPECTION . . . 82
FIGURE 26: STRUT NO. 1 - INBOARD SIDE - MID PIVOT BOLT ASSEMBLY - INSPECTION ..... 8 4
FIGURE 27: STRUT NO. 4 - INBOARD SIDE - MID PIVOT BOLT ASSEMBLY - INSPECTION ..... 8 6
FIGURE 28: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT BOLT ASSEMBLY - INSPECTION . . . 88
APPENDIX A: MID PIVOT ACCESS DOOR IDENTIFICATION ....................... 9 0
APPENDIX B: MID PIVOT BOLT ASSEMBLY ULTRASONIC INSPECTION ................ 9 1
APPENDIX C: SCOPE OF CHANGE ..................................... 9 9
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-54A2232Original Issue: April 15, 2010
ATA System: 5410 5451 5432 5462 1113
SUBJECT: NACELLES/PYLONS - Nacelle Strut Spring Beam - Spring Beam Mid Pivot Bolt
Assembly - Access Door Inspection and Replacement, Marker Installation, and Bolt
Assembly Inspection and 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 make sure both spring beam mid pivot bolt assemblies on the outboard
struts are correctly installed. If the mid pivot bolt assembly is not correctly installed the internal lubrication channel
of the bolt assembly will not be in the correct orientation. When the lubrication channel is not in the correct
orientation, the mid pivot bolt assembly could fatigue and eventually crack or fracture. A cracked or fractured
mid pivot bolt assembly could result in the loss of the spring beam load path. Loss of the spring beam load path
could result in the separation of a strut and engine from the airplane during flight.
An operator reported that the left and right spring beam mid pivot bolt assembly access doors for the no. 1 strut
were inadvertently installed in the incorrect position. It is believed that the doors were installed on the wrong
side of the strut during strut modification. The design of the access doors can allow the doors to be installed on
either side of the strut. The mid pivot access door has machined tabs that fit the slots in the head of the mid
pivot bolt assembly. The machined tabs correctly orient the mid pivot bolt assembly and prevent the mid pivot
bolt from rotating in the spring beam. The correct orientation of the mid pivot bolt is necessary to reduce the
fatigue on the cross-drilled lubrication channel. If the incorrect access door is installed, the lubrication channel
will not be in the correct orientation. If the lubrication channel is not in the correct orientation, fatigue cracks
could develop in the mid pivot bolt assembly. The fatigue cracks may result in the fracture of the mid pivot bolt
assembly. Fracture of the mid pivot bolt assembly could result in the loss of the spring beam load path. Loss of
the spring beam load path could result in the separation of a strut and engine from the airplane during flight.
Inspection of the access door assembly part numbers on each side of struts no. 1 and 4 will determine if the
correct door is installed. Installation of markers on the doors will help prevent the inadvertent installation of the
doors on the wrong side of the strut. Inspection and replacement of the mid pivot bolt assemblies at the locations
where the incorrect access doors were installed will help prevent fatigue fracture of the mid pivot bolt assemblies
due to the incorrect orientation. Rotating the mid pivot bolt assembly to the correct orientation, and replacing
the access doors at the locations where the incorrect access doors were installed will ensure the mid pivot bolt
assemblies are properly oriented.
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### Page 6

Boeing Service Related Problem (SRP) 747-SRP-54-0121 is related to this service bulletin.
ACTION (PRR 85901-92S)
Part 1 - Access Door Inspection
Remove the spring beam mid pivot bolt assembly access door from each side of the no. 1 and 4 struts. Do an
inspection to determine the part number. Install the spring beam mid pivot bolt assembly access door on each
side of the no. 1 and 4 struts.
Part 2 - Marker Installation
Install markers on the inside surface of mid pivot bolt assembly access doors on each side of the no. 1 and 4
struts.
Part 3 - Mid Pivot Bolt Assembly Replacement
At locations where the incorrect access door was installed, remove and discard the spring beam mid pivot bolt
assembly. Install new spring beam mid pivot bolt assembly.
Part 4 - Access Door Replacement
At locations where the incorrect access door was installed, rotate the mid pivot bolt assembly to the correct
orientation, if required, and replace the access door with an access door with the correct part number
Part 5 - Mid Pivot Bolt Assembly Inspection
Remove the spring beam mid pivot bolt assembly access door from each side of the no. 1 and 4 struts, if required.
Do an Ultrasonic Inspection (UT) of the mid pivot bolt assembly for cracks. Install the spring beam mid pivot bolt
assembly access door on each side of the no. 1 and 4 struts.
EFFECTIVITY
747-200B, -300, -400, -400D, -400F airplanes powered by Pratt and Whitney 4000 series engines or General
Electric CF6-80C2 series engines. Refer to Paragraph 1.A., Effectivity
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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspections, ,and/or repair procedures
given in this service bulletin.
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MANPOWER
Elapsed
Hours
Total Task
Hours
Task
2.003.00Part 1 - Access Door Inspection
0.400.40Part 2 - Marker Installation
50.50362.00Part 3 - Mid Pivot Bolt Assembly Replacement
4.604.60Part 4 - Access Door Replacement
3.004.00Part 5 - Mid Pivot Bolt Assembly Inspection
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
ENGINE NO. 1
(LEFT SIDE)
PART 4:
AT LOCATION WHERE
INCORRECT ACCESS DOOR
WAS INSTALLED, REPLACE
THE ACCESS DOOR WITH AN
ACCESS DOOR WITH THE
CORRECT PART NUMBER
PART 2:
INSTALL MARKER
PART 1:  DO AN INSPECTION TO  DETERMINE IF THE  (LEFT SIDE SHOWN, STRUT NO. 1 RIGHT SIDE,  STRUT NO. 4 LEFT SIDE, AND STRUT NO. 4  RIGHT SIDE SIMILAR)  STRUT NO. 1
CORRECT ACCESS DOOR
IS INSTALLED  MID PIVOT
BOLT ASSEMBLY
PART 3:
AT LOCATION WHERE
INCORRECT ACCESS DOOR
WAS INSTALLED, REPLACE
MID PIVOT BOLT ASSEMBLY
PART 5:
ACCESS  DO AN ULTRASONIC INSPECTION  (UT) OF THE MID PIVOT BOLT
DOOR PANEL  ASSEMBLY FOR CRACKS
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-54A2232
Original Issue: April 15, 2010
ATA System: 5410 5451 5432 5462 1113
SUBJECT: NACELLES/PYLONS - Nacelle Strut Spring Beam - Spring Beam Mid Pivot Bolt
Assembly - Access Door Inspection and Replacement, Marker Installation, and Bolt
Assembly Inspection and 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 airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 85901-92S for data about this change.
Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
747-400, -400F airplanes powered by PW4000 series engines, line
numbers 696 through 1375.
-1
747-200B, -300 airplanes powered by GE CF6-80C2 series engines,
line numbers 679 through 719.
-2
747-400, -400D, -400F airplanes powered by GE CF6-80C2 series
engines, line numbers 700 through 1400.
-3
Airplane Models:
747-200B, 747-300, 747-400, 747-400D, 747-400F
GroupVariable Number
2RD166 - RD167
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GroupVariable Number
3RF001 - RF006
3RL401 - RL403
3RL411 - RL430
1RL431 - RL436
1RL451 - RL456
3RL461 - RL462
3RL471 - RL476
3RL481
1RL491 - RL492
1RL501 - RL502
3RL511 - RL516
3RL521 - RL522
3RL531 - RL534
3RL561 - RL563
3RL576 - RL577
3RL651 - RL655
3RL671 - RL675
3RL681 - RL684
1RL751 - RL752
3RM001 - RM007
3RM010
1RM011 - RM013
1RM021 - RM024
3RM026 - RM030
1RM036 - RM045
3RM051 - RM053
3RM071
3RM081 - RM084
1RM091
3RM116 - RM117
3RM126 - RM132
3RM156 - RM158
1RM166 - RM177
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GroupVariable Number
3RM191 - RM192
3RM231 - RM233
1RM241 - RM246
3RM316 - RM318
1RM341
3RM351 - RM355
1RM366 - RM367
3RM401 - RM403
3RM426
3RM431
3RM441 - RM443
3RM445
3RM801 - RM803
1RM811 - RM813
1RM851 - RM855
3RM861 - RM863
1RM871 - RM880
3RM891 - RM899
3RM901 - RM906
3RM911
3RR701
3RR721 - RR724
3RR746 - RR748
1RR851 - RR856
1RR861 - RR862
2RS331 - RS333
2RS341 - RS342
2RS781 - RS782
3RT001 - RT014
3RT021 - RT022
1RT031 - RT035
3RT041 - RT047
1RT061
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GroupVariable Number
3RT071 - RT075
1RT101 - RT103
3RT121
3RT131 - RT137
3RT151 - RT152
3RT161 - RT168
1RT401 - RT412
3RT431 - RT447
1RT501 - RT530
3RT531 - RT535
1RT571 - RT590
3RT591
1RT601 - RT640
3RT641 - RT657
3RT681 - RT682
3RT691 - RT699
3RT701 - RT704
3RT711 - RT717
3RT741 - RT742
1RT743 - RT750
3RT751 - RT757
3RT776 - RT777
3RT801 - RT803
1RT811 - RT814
1RT831 - RT837
3RT861 - RT864
1RT876 - RT880
3RT931 - RT932
3RT945 - RT949
3RT951 - RT955
3RT966 - RT967
1RU001 - RU006
1RU016 - RU017
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GroupVariable Number
3RU031 - RU032
3RU051 - RU052
3RU059 - RU062
1RU081 - RU083
3RU101 - RU102
3RU801 - RU809
3RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will make sure both spring beam mid pivot bolt assemblies on
the outboard struts are correctly installed. If the mid pivot bolt assembly is not correctly installed the
internal lubrication channel of the bolt assembly will not be in the correct orientation. When the lubrication
channel is not in the correct orientation, the mid pivot bolt assembly could fatigue and eventually crack
or fracture. A cracked or fractured mid pivot bolt assembly could result in the loss of the spring beam
load path. Loss of the spring beam load path could result in the separation of a strut and engine from
the airplane during flight.
An operator reported that the left and right spring beam mid pivot bolt assembly access doors for the
no. 1 strut were inadvertently installed in the incorrect position. It is believed that the doors were installed
on the wrong side of the strut during strut modification. The design of the access doors can allow the
doors to be installed on either side of the strut. The mid pivot access door has machined tabs that fit
the slots in the head of the mid pivot bolt assembly. The machined tabs correctly orient the mid pivot
bolt assembly and prevent the mid pivot bolt from rotating in the spring beam. The correct orientation
of the mid pivot bolt is necessary to reduce the fatigue on the cross-drilled lubrication channel. If the
incorrect access door is installed, the lubrication channel will not be in the correct orientation. If the
lubrication channel is not in the correct orientation, fatigue cracks could develop in the mid pivot bolt
assembly. The fatigue cracks may result in the fracture of the mid pivot bolt assembly. Fracture of the
mid pivot bolt assembly could result in the loss of the spring beam load path. Loss of the spring beam
load path could result in the separation of a strut and engine from the airplane during flight.
Inspection of the access door assembly part numbers on each side of struts no. 1 and 4 will determine
if the correct door is installed. Installation of markers on the doors will help prevent the inadvertent
installation of the doors on the wrong side of the strut. Inspection and replacement of the mid pivot bolt
assemblies at the locations where the incorrect access doors were installed will help prevent fatigue
fracture of the mid pivot bolt assemblies due to the incorrect orientation. Rotating the mid pivot bolt
assembly to the correct orientation, and replacing the access doors at the locations where the incorrect
access doors were installed will ensure the mid pivot bolt assemblies are properly oriented.
BOEING PROPRIETARY -
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### Page 14

Boeing Service Related Problem (SRP) 747-SRP-54-0121 is related to this service bulletin.
D. Description
Part 1 - Access Door Inspection
Remove the spring beam mid pivot bolt assembly access door from each side of the no. 1 and 4 struts.
Do an inspection to determine the part number. Install the spring beam mid pivot bolt assembly access
door on each side of the no. 1 and 4 struts.
Part 2 - Marker Installation
Install markers on the inside surface of mid pivot bolt assembly access doors on each side of the no.
1 and 4 struts.
Part 3 - Mid Pivot Bolt Assembly Replacement
At locations where the incorrect access door was installed, remove and discard the spring beam mid
pivot bolt assembly. Install new spring beam mid pivot bolt assembly.
Part 4 - Access Door Replacement
At locations where the incorrect access door was installed, rotate the mid pivot bolt assembly to the
correct orientation, if required, and replace the access door with an access door with the correct part
number.
Part 5 - Mid Pivot Bolt Assembly Inspection
Remove the spring beam mid pivot bolt assembly access door from each side of the no. 1 and 4 struts,
if required. Do an Ultrasonic Inspection (UT) of the mid pivot bolt assembly for cracks. Install the spring
beam mid pivot bolt assembly access door on each side of the no. 1 and 4 struts.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
452, 482747-400, 747-400F
Group 2:
Affected Maintenance Zones
ZoneModel
452, 482747-200B, 747-300
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### Page 15

Group 3:
Affected Maintenance Zones
ZoneModel
452, 482747-400, 747-400D, 747-400F
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.
Accomplish Part 1 through Part 5, as required in Table 1 below in accordance with Paragraph 3.,
Accomplishment Instructions.
Table 1: Mid Pivot Bolt and Access Door Inspection, Change and Replacement
Repeat
Inter-
val
(Not to
Ex-
ceed)
Compliance
Time
Action (a)Condition
-Within 24
Months after
the original
issue date of
this service
bulletin.
Do an inspection to determine if the correct mid pivot access door is
installed in accordance with Part 1 - Access Door Inspection.
All Airplanes
-Before fur-
ther flight.
Install marker on mid pivot access door in accordance with Part 2 -
Marker Installation (Terminating Action).
Condition 1 -
Correct ac-
cess door is
installed.
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### Page 16

Table 1: Mid Pivot Bolt and Access Door Inspection, Change and Replacement
Repeat
Inter-
val
(Not to
Ex-
ceed)
Compliance
Time
Action (a)Condition
Do 1), 2), and 3) below:Condition 2 -
Correct ac-
cess door is
not installed.
-Before fur-
ther flight.
Rotate mid pivot bolt assembly to correct orientation and replace
the mid pivot access door in accordance with Part 4 - Access Door
Replacement.
1)
AND
-Before fur-
ther flight.
Install marker on mid pivot access door in accordance with Part 2
- Marker Installation
2)
AND
Do Option 1) or Option 2):3)
-Before fur-
ther flight.
Do an Ultrasonic Inspection (UT) of the mid pivot bolt
assembly for cracks in accordance with Part 5 - Mid Pivot
Bolt Assembly Inspection.
Option 1)
24
Months
-Repeat Ultrasonic Inspection (UT)
of the mid pivot bolt assembly for
cracks in accordance with Part 5 -
Mid Pivot Bolt Assembly Inspection.
Condition 2A -
No Crack found
AND
-Within 60
Months after
after the
original is-
sue date of
this service
bulletin.
Replace the mid pivot bolt assem-
bly in accordance with Part 3 - Mid
Pivot Bolt Assembly Replacement
(Terminating Action).
-Before fur-
ther flight.
Replace the mid pivot bolt assem-
bly in accordance with Part 3 - Mid
Pivot Bolt Assembly Replacement
(Terminating Action).
Condition 2B -
Cracked mid
pivot bolt assem-
bly found
OR
-Before fur-
ther flight.
Replace the mid pivot bolt assembly in accordance with
Part 3 - Mid Pivot Bolt Assembly Replacement (Terminat-
ing Action).
Option 2)
(a) Action applies separately to each access door and bolt assembly location (4 locations per airplane).
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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 inspection and change for
each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate
with operator task hour data if necessary. The estimate does not include lost time. These are some
examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Part 1 - Access Door Inspection
Elapsed
Hours
Task HoursNumber of
Persons
Task
0.0501.002Open Access
Inspect
0.250.251... Strut No. 1 Outboard - FIGURE 1
0.250.251... Strut No. 1 Inboard - FIGURE 2
0.250.251... Strut No. 4 Inboard - FIGURE 3
0.250.251... Strut No. 4 Outboard - FIGURE 4
0.501.002Close Access
2.003.00TOTAL FOR EACH AIRPLANE
Group 1:
Part 2 - Marker Installation
Elapsed
Hours
Task HoursNumber of
Persons
Task
Install Marker
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Group 1:
Part 2 - Marker Installation
Elapsed
Hours
Task HoursNumber of
Persons
Task
0.100.101... Strut No. 1 Outboard - FIGURE 5
0.100.101... Strut No. 1 Inboard - FIGURE 6
0.100.101... Strut No. 4 Inboard - FIGURE 7
0.100.101... Strut No. 4 Outboard - FIGURE 8
0.400.40TOTAL FOR EACH AIRPLANE
Group 2:
Part 2 - Marker Installation
Elapsed
Hours
Task HoursNumber of
Persons
Task
Install Marker
0.100.101... Strut No. 1 Outboard - FIGURE 9
0.100.101... Strut No. 1 Inboard - FIGURE 10
0.100.101... Strut No. 4 Inboard - FIGURE 11
0.100.101... Strut No. 4 Outboard - FIGURE 12
0.400.40TOTAL FOR EACH AIRPLANE
Group 3:
Part 2 - Marker Installation
Elapsed
Hours
Task HoursNumber of
Persons
Task
Install Marker
0.100.101... Strut No. 1 Outboard - FIGURE 13
0.100.101... Strut No. 1 Inboard - FIGURE 14
0.100.101... Strut No. 4 Inboard - FIGURE 15
0.100.101... Strut No. 4 Outboard - FIGURE 16
0.400.40TOTAL FOR EACH AIRPLANE
Part 3 - Mid Pivot Bolt Assembly Replacement
Elapsed
Hours
Task HoursNumber of
Persons
Task
21.00168.008Open Access
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Part 3 - Mid Pivot Bolt Assembly Replacement
Elapsed
Hours
Task HoursNumber of
Persons
Task
Replace Mid Pivot Bolt Assembly
1.501.501... Strut No. 1 Outboard - FIGURE 17
1.501.501... Strut No. 1 Inboard - FIGURE 18
1.501.501... Strut No. 4 Inboard - FIGURE 19
1.501.501... Strut No. 4 Outboard - FIGURE 20
23.50188.00Close Access
50.50362.00TOTAL FOR EACH AIRPLANE
Part 4 - Access Door Replacement
Elapsed
Hours
Task HoursNumber of
Persons
Task
Replace Access Door
1.151.151... Strut No. 1 Outboard - FIGURE 21
1.151.151... Strut No. 1 Inboard - FIGURE 22
1.151.151... Strut No. 4 Inboard - FIGURE 23
1.151.151... Strut No. 4 Outboard - FIGURE 24
4.604.60TOTAL FOR EACH AIRPLANE
Part 5 - Mid Pivot Bolt Assembly Inspection
Elapsed
Hours
Task HoursNumber of
Persons
Task
0.501.002Open Access
Inspect
0.500.501... Strut No. 1 Outboard - FIGURE 25
0.500.501... Strut No. 1 Inboard - FIGURE 26
0.500.501... Strut No. 4 Inboard - FIGURE 27
0.500.501... Strut No. 4 Outboard - FIGURE 28
0.501.002Close Access
3.004.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR 85901-92S
b. Boeing Service Related Problem (SRP) 747-SRP-54-0121
c. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-50-05, 20-50-10
d. 747 Non-Destructive Testing (NDT) Manual Part 1, 51-01-00, Part 1, 51-04-00
e. 747-100/200/300 Aircraft Maintenance Manual (AMM) 12-09-09, 54-10-04
f. 747-400 Aircraft Maintenance Manual (AMM) 06-09-09, 54-51-03
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Door Instl - Pin Access Outboard Strut CF6-80C2321U2163
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified change, and are not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
54-10, 54-51747 Maintenance Manual
54-10, 54-51747 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
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L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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### Page 23

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown
below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru
Sep 30/10
ROLT (Weeks)NameKit Number
$ 168.0012Top Kit - Strut No. 1 and 4 (PW) - Mid-pivot
Access Door - Modification
015U1847-1
Unit Price thru
Sep 30/10
ROLT (Weeks)NameKit Number
$ 168.0012Top Kit - Strut No. 1 and 4 (GE) - Mid-pivot
Access Door - modification
015U1847-3
Unit Price thru
Sep 30/10
ROLT (Weeks)NameKit Number
$ 168.0012Top Kit - Strut No. 1 and 4 (GE) - Mid-pivot
Access Door - Modification
015U1847-2
ALL AIRPLANES:
Unit Price thru Sep 30/10NamePart Number
$ 3,021.00Bolt Assembly - Mid Pivot (a)321U2149-5
$ 1,245.00Access Door - Left Side - Strut No.
1 or 4 (b)
321U2164Y3
$ 1,937.00Access Door - Right Side - Strut No.
1 or 4 (b)
321U2164Y8
(a) Required only for locations where incorrect access door was installed.
(b) Required only if correct part number door is not available
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair
procedures given in 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.
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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
Figure Kit
1098765Top Kit
--1111015U1847-1
------015U1847-2
11----015U1847-3
Figure Kit
161514131211Top Kit
------015U1847-1
1111--015U1847-2
----11015U1847-3
Group 1:
KIT 015U1847-1
NOTES
Existing Part
NumberName
Figure
New Part Number
8765
QTY
AL MARKER,
452FR
1BAC27EPP664
AL MARKER,
482GL
1BAC27EPP665
AL MARKER,
482FR
1BAC27EPP666
AL MARKER,
452GL
1BAC27EPP667
Group 3:
KIT 015U1847-2
NOTES
Existing Part
NumberName
Figure
New Part Number
16151413
QTY
AL MARKER,
482TR
1BAC27EPP668
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Group 3:
KIT 015U1847-2
NOTES
Existing Part
NumberName
Figure
New Part Number
16151413
QTY
AL MARKER,
452TL
1BAC27EPP669
AL MARKER,
452TR
1BAC27EPP670
AL MARKER,
482TL
1BAC27EPP671
Group 2:
KIT 015U1847-3
NOTES
Existing Part
NumberName
Figure
New Part Number
1211109
QTY
AL MARKER,
482HRX
1BAC27EPP681
AL MARKER,
452FL
1BAC27EPP682
AL MARKER,
452HRX
1BAC27EPP683
AL MARKER,
482FL
1BAC27EPP684
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number/ Specification
(b)Bolt Assembly - Mid Pivot4321U2149-5
(c)Access Door - Left Side - Strut
No. 1 or 4
2321U2164Y3
(d)Access Door - Right Side - Strut
No. 1 or 4
2321U2164Y8
(a)Primer1 OzBMS 10-11, TYPE I
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
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NotesNameQTYPart Number/ Specification
(b) Total quantity required per airplane if the incorrect door is installed at all locations. Bolt
assembly is only required at access door location where the incorrect door was installed
or cracked bolt assembly was found.
(c) Total quantity of left hand doors required per airplane if the incorrect access door was
installed. If the incorrect door is installed, the correct door may be installed on the other
side of the strut. The airplane may have the total required number of left side doors and
right side doors installed, but in the incorrect locations.
(d) Total quantity of right hand doors required per airplane if the incorrect access door was
installed. If the incorrect door is installed, the correct door may be installed on the other
side of the strut. The airplane may have the total required number of left side doors and
right side doors installed, but in the incorrect locations.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. 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.
5. Action applies to each access door and bolt assembly location (4 locations per
airplane) separately
6. Refer to APPENDIX A for method to determine the access door part number if the
part number can not be read.
7. APPENDIX B is an Ultrasonic Inspection (UT) procedure used to find cracks in the
mid pivot bolt assembly.
8. Refer to APPENDIX C for Scope of Change.
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B. WORK INSTRUCTIONS
1. Do an inspection to determine if the correct mid pivot access door is installed in accordance with
Part 1 - Access Door Inspection.
a. Condition 1 - Correct access door is installed.
Install marker on mid pivot access door in accordance with Part 2 - Marker Installation at the
compliance time in Paragraph 1.E., Compliance as terminating action.
b. Condition 2 - Correct access door is not installed.
Do (1), (2), and (3) below:
(1) Rotate mid pivot bolt assembly to correct orientation and replace the mid pivot access
door in accordance with Part 4 - Access Door Replacement at the compliance time in
Paragraph 1.E., Compliance; and
(2) Install marker on mid pivot access door in accordance with Part 2 - Marker Installation at
the compliance time in Paragraph 1.E., Compliance; and
(3) Do Option 1) or Option 2):
(a) Option 1):
Do an Ultrasonic Inspection (UT) of the mid pivot bolt assembly for cracks in
accordance with Part 5 - Mid Pivot Bolt Assembly Inspection at the compliance time
in Paragraph 1.E., Compliance.
1) Condition 2A- No crack found.
a) Repeat Ultrasonic Inspection (UT) of the mid pivot bolt assembly for cracks
in accordance with Part 5 - Mid Pivot Bolt Assembly Inspection at the repeat
interval in Paragraph 1.E., Compliance; and
b) Replace the mid pivot bolt assembly in accordance with Part 3 - Mid Pivot
Bolt Assembly Replacement at the compliance time in Paragraph 1.E.,
Compliance as terminating action
2) Condition 2B - Cracked mid pivot bolt assembly found.
Replace the mid pivot bolt assembly in accordance with Part 3 - Mid Pivot Bolt
Assembly Replacement at the compliance time in Paragraph 1.E., Compliance
as terminating action.
(b) Option 2):
Replace the mid pivot bolt assembly in accordance with Part 3 - Mid Pivot Bolt
Assembly Replacement at the compliance time in Paragraph 1.E., Compliance as
terminating action.
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PART 1 - ACCESS DOOR INSPECTION
1. Remove the mid pivot access door shown below. Refer to 747-100/200/300 AMM 12-09-09 or
747-400 AMM 06-09-09 for location of these panels. It is recommended that operator's mark the
up direction, forward direction, and the location (Strut No. 1 Outboard, Strut No. 1 Inboard, Strut
No. 4 Inboard, or Strut No. 4 Outboard) on a piece of tape on the door before removing. This
information would be used to determine the door part number in Appendix A, if the door part number
can not be read.
Group 1:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482FR482GL452FR452GL
Group 2:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482HRX482FL452HRX452FL
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Group 3:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482TR482TL452TR452TL
2. Do an inspection of the mid pivot access doors to determine if the correct part number is installed
in accordance with the figure below:
NOTE: Refer to Appendix A for method to determine the access door part number if the part
number can not be read.
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 4FIGURE 3FIGURE 2FIGURE 1Figure
321U2164-8321U2164-1 or -3321U2164-8321U2164-1 or -3
Correct Mid Pivot
Access Door Part
Number
3. Install the mid pivot access door shown below. Refer to 747-100/200/300 AMM 12-09-09 or 747-400
AMM 06-09-09 for location of these panels.
Group 1:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482FR482GL452FR452GL
Group 2:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482HRX482FL452HRX452FL
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Group 3:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482TR482TL452TR452TL
4. Put the airplane back to a serviceable condition.
PART 2 - MARKER INSTALLATION
1. Install marker on mid pivot access door in accordance with the figure below:
Group 1:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 8FIGURE 7FIGURE 6FIGURE 5
Group 2:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 12FIGURE 11FIGURE 10FIGURE 9
Group 3:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 16FIGURE 15FIGURE 14FIGURE 13
PART 3 - MID PIVOT BOLT ASSEMBLY REPLACEMENT
1. Replace existing mid pivot bolt assembly in accordance with the figure shown below:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 20FIGURE 19FIGURE 18FIGURE 17
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PART 4 - ACCESS DOOR REPLACEMENT
1. Replace the mid pivot access door in accordance with the figure shown below:
NOTE: If the incorrect door is installed, the correct door may been installed on the other side of
the strut. The airplane may have the total required number of left side doors and right
side doors installed, but in the incorrect location.
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 24FIGURE 23FIGURE 22FIGURE 21
PART 5 - MID PIVOT BOLT ASSEMBLY INSPECTION
1. Remove the mid pivot access door shown below, if not already removed. Refer to 747-100/200/300
AMM 12-09-09 or 747-400 AMM 06-09-09 for location of these panels.
Group 1:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482FR482GL452FR452GL
Group 2:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482HRX482FL452HRX452FL
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Group 3:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482TR482TL452TR452TL
2. Do an Ultrasonic Inspection (UT) of the mid pivot bolt assembly for cracks in accordance with the
figure below:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
FIGURE 28FIGURE 27FIGURE 26FIGURE 25Figure
3. Install the mid pivot access door shown below. Refer to 747-100/200/300 AMM 12-09-09 or 747-400
AMM 06-09-09 for location of these panels.
Group 1:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482FR482GL452FR452GL
Group 2:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482HRX482FL452HRX452FL
Group 3:
Strut No.
41
Outboard SideInboard SideInboard SideOutboard Side
482TR482TL452TR452TL
4. Put the airplane back to a serviceable condition.
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(OUTBOARD SIDE)
1567201
FIGURE 1: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 1 OF 2)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to determine part number
321U2164-(). If part number
is not visible, see AP-
PENDIX A to determine the
part number.
1-Mid pivot access doorInspect1
FIGURE 1: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 2 OF 2)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
ENGINE NO. 1
TaND
ACCESS PANEL
STRUT NO. 1
(INBOARD SIDE)
1567311
FIGURE 2: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 1 OF 2)
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### Page 37

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to determine part number
321U2164-(). If part number
is not visible, see AP-
PENDIX A to determine the
part number.
1-Mid pivot access doorInspect1
FIGURE 2: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 2 OF 2)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
ENGINE NO. 4
ACCESS PANEL
STRUT NO. 4
(INBOARD SIDE)
1567351
FIGURE 3: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 1 OF 2)
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### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to determine part number
321U2164-(). If part number
is not visible, see AP-
PENDIX A to determine the
part number.
1-Mid pivot access doorInspect1
FIGURE 3: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
39 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
ENGINE NO. 4
TaND
ACCESS PANEL
STRUT NO. 4
(OUTBOARD SIDE)
1567357
FIGURE 4: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  40 of 99

### 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 each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to determine part number
321U2164-(). If part number
is not visible, see AP-
PENDIX A to determine the
part number.
1-Mid pivot access doorInspect1
FIGURE 4: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - INSPECTION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
41 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 1.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(OUTBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  1567765
FIGURE 5: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  42 of 99

### 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 each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP667AL MARKER, 452GLInstall (New)1
FIGURE 5: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
43 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 1.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(INBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  1567807
FIGURE 6: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  44 of 99

### 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 each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP664AL MARKER, 452FRInstall (New)1
FIGURE 6: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
45 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 1.
ENGINE NO. 4
ACCESS PANEL
STRUT NO. 4
(INBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  9182991
FIGURE 7: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  46 of 99

### 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 each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP665AL MARKER, 482GLInstall (New)1
FIGURE 7: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
47 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 48 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 1.
ENGINE NO. 4
ACCESS PANEL
STRUT NO. 4
(OUTBOARD SIDE)
THICK BUILD -UP
*ACCESS PANEL
THIN BUILD -UP
A-A  1567852
FIGURE 8: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  48 of 99

### 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 each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP666AL MARKER, 482FRInstall (New)1
FIGURE 8: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
49 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 2.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(OUTBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  1567864
FIGURE 9: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  50 of 99

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP682AL MARKER, 452FLInstall (New)1
FIGURE 9: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
51 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 2.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(INBOARD SIDE)
THICK BUILD -UP
*ACCESS PANEL
THIN BUILD -UP
A-A  1567863
FIGURE 10: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  52 of 99

### Page 53

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP683AL MARKER, 452HRXInstall (New)1
FIGURE 10: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
53 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 2.
ENGINE NO. 4
ACCESS PANEL
STRUT NO. 4
(INBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  2982991
FIGURE 11: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  54 of 99

### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP684AL MARKER, 482FLInstall (New)1
FIGURE 11: STRUT NO. 4 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
55 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 56 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 2.
ENGINE NO. 4
ACCESS PANEL
STRUT NO. 4
(OUTBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  1567861
FIGURE 12: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  56 of 99

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP681AL MARKER, 482HRXInstall (New)1
FIGURE 12: STRUT NO. 4 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
57 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 3.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(OUTBOARD SIDE)
THICK BUILD -UP
ACCESS PANEL
THIN BUILD -UP
A-A  1567874
FIGURE 13: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  58 of 99

### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each access door location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-50-05 as
an accepted procedure.
Align UP and FWD on
marker to align with up and
forward directions of the
door assembly.
1BAC27EPP669AL MARKER, 452TLInstall (New)1
FIGURE 13: STRUT NO. 1 - OUTBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: April 15, 2010
747-54A2232
59 of 99
BOEING SERVICE BULLETIN 747-54A2232
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 747-54A2232
ALERT  ALERT
This Figure applies only to: Group 3.
ENGINE NO. 1
ACCESS PANEL
STRUT NO. 1
(INBOARD SIDE)
THICK BUILD -UP
*ACCESS PANEL
THIN BUILD -UP
A-A  1567882
FIGURE 14: STRUT NO. 1 - INBOARD SIDE - MID PIVOT ACCESS DOOR - MARKER INSTALLATION
(SHEET 1 OF 2)
Original Issue: April 15, 2010
BOEING PROPRIETARY -  747-54A2232
Copyright © Unpublished Work - See page 1 for details.  60 of 99

The text continues at https://openairdocs.org/service-documents/boeing/747-54a2232/file/6155fb816a4d.md?from=61

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