# Boeing Alert Service Bulletin 747-57A2343: U.S. DOT/FAA - SB-747-57A2343-00

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0871; AD 2013-23-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-57A2343](https://openairdocs.org/service-documents/boeing/747-57a2343.md)
- Title as filed: U.S. DOT/FAA - SB-747-57A2343-00
- Pages: 54
- PDF: https://openairdocs.org/files/sha256/09/87/0987fa62c5fced81b45fce5f6695844ded35e7487c8856ea3dede47c4fd7bbe2
- Page: https://openairdocs.org/service-documents/boeing/747-57a2343/file/0987fa62c5fc

## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2343
Original Issue: September 12, 2013
ATA System: 5752 2751
SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals
No.s 2 and 7) - Inspection, Rework, and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2013 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Unpublished Work.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.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 8
C. Reason ................................................ 1 8
D. Description .............................................. 1 9
E. Compliance .............................................. 2 0
F. Approval ............................................... 2 2
G. Manpower .............................................. 2 2
H. Weight and Balance Changes .................................... 2 4
I. Electrical Load Data ......................................... 2 4
J. References .............................................. 2 4
1. Existing Data: ......................................... 2 4
2. Data Supplied with this Service Bulletin: ........................... 2 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 5
K. Publications Affected ........................................ 2 5
L. Interchangeability and Intermixability of Parts ........................... 2 5
M. Software Accomplishment Summary ................................ 2 6
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 7
C. Parts Necessary for Each Airplane ................................. 2 7
1. Kits/Parts ............................................ 2 7
2. Parts and Materials Supplied by the Operator ........................ 2 7
3. Parts Modified and Reidentified ................................ 2 8
4. Parts Removed and Not Replaced .............................. 2 8
D. Parts Necessary to Change Spares ................................. 2 8
E. Special Tooling - Price and Availability ............................... 2 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 3 1
FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . . 35
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION ......... 3 7
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS
INSPECTION .......................................... 4 0
FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . 44
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION ........ 4 6
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS
INSPECTION .......................................... 4 9
APPENDIX A: LOGIC DIAGRAM ....................................... 5 3
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-57A2343Original Issue: September 12, 2013
ATA System: 5752 2751
SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals
No.s 2 and 7) - Inspection, Rework, 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
The inspections and replacement in this service bulletin will help prevent fracture of the outboard flap, inboard
actuator support fitting assembly (no. 2 or no. 7 gimbal). A fractured inboard actuator fitting combined with the
loss of the outboard actuator load path could result in the uncontrolled retraction of the outboard flap and
subsequent damage to flight control systems at the rear spar. Uncontrolled retraction of the flap or damage to
flight control systems could lead to reduced controllability of the airplane.
One operator reported the fracture of a 65B08564-7 actuator attach fitting. The actuator attach fitting had
approximately 5,500 flight-cycles and 20,600 flight-hours. The actuator attach fitting was installed by service
bulletin 747-57A2316. The actuator attach fitting fractured in the internal conical machined area. Inspection of
the actuator attach fitting revealed that a portion of the interior surface was machined with a cylindrical profile
instead of a conical profile. This results in reduced wall thickness. The thickness of the fitting in the cylindrical
area was approximately half the design wall thickness. The operator inspected the remaining airplanes in their
fleet and found another actuator attach fitting with the cylindrical defect with a wall thickness below design
requirements. An inspection of spare 65B08564-7 actuator attach fittings at Boeing revealed some actuator
attach fittings with the cylindrical defect with reduced wall thicknesses. In addition, some actuator attach fittings
which did not have the cylindrical defect had wall thicknesses which were below design requirements. Reduced
wall thickness results in the inability of the actuator attach fitting to carry required loads.
This service bulletin provides instructions to inspect and replace 65B08564-7 no. 2 and no. 7 actuator attach
fittings which could have insufficient wall thickness.
Boeing Service Related Problem (SRP) 747-SRP-57-0264 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-13003 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedYesSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 85901-129RS)
Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the actuator
attach fitting. Do an inspection of the actuator attach fitting to determine if a 65B08564-7 Actuator Attach Fitting
is installed. Attach actuator ball screw to the actuator attach fitting. Activate and retract the trailing edge flaps.
Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the actuator
attach fitting. Do a Detailed (DET) inspection of the Actuator Attach Fitting to determine if it has the cylindrical
defect. Attach actuator ball screw to the actuator attach fitting. Activate and retract the trailing edge flaps.
Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Do an Ultrasonic
(UT) inspection or mechanically determine the thickness of the Actuator Attach Fitting. Install the Actuator Attach
Fitting. Activate and retract the trailing edge flaps.
Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement
Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Install actuator
attach fitting assemblies not affected by this service bulletin. Activate and retract the trailing edge flaps.
EFFECTIVITY
747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D, -400F,and 747SR Airplanes. Refer to
Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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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 available for airplanes in warranty as of June 5, 2013. Please refer to Paragraph
2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of
this service bulletin.
MANPOWER
Elapsed HoursTotal Task Hours
4.007.00Part 1: Outboard Flap, Inboard Actuator Attach Fitting -
Part Number Inspection
4.007.00Part 2: Outboard Flap, Inboard Actuator Attach Fitting -
DET Inspection
5.008.00Part 3: Outboard Flap, Inboard Actuator Attach Fitting -
Minimum Thickness Inspection
6.006.00Part 4: Outboard Flap, Inboard Actuator Attach Fitting -
Replacement
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 8 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
PART 1:
DO AN INSPECTION TO DETERMINE IF A
65B08564-7 IS INSTALLED
PART 2:
DO A DET TO DETERMINE IF ACTUATOR
ATTACH FITTING HAS THE CYLINDRICAL
DEFECT
PART 3:
RIGHT WING OPPOSITE  LEFT WING SHOWN,  DO A UT INSPECTION OR MECHANICALLY  DETERMINE THE MINIMUM WALL
THICKNESS OF THE ACTUATOR ATTACH
FITTING
PART 4:
REPLACE ACTUATOR ATTACH FITTING
WITH FITTING NOT AFFECTED BY THIS
SERVICE BULLETIN
ACTUATOR
• ATTACH FITTING
→ PART NUMBER
LOCATION
A-A  2267858
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### Page 9

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2343
Original Issue: September 12, 2013
ATA System: 5752 2751
SUBJECT: WINGS - Trailing Edge Flaps - Outboard Flap Inboard Actuator Attach Fittings (Gimbals
No.s 2 and 7) - Inspection, Rework, 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 airplane(s) shown below. Refer to PRR 85901-129RS 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
747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400, -400D,
-400F, 747SR Airplanes line numbers 1 through 1263. These
airplanes were not delivered with a 65B08564-7 Actuator Attach
Fitting, but could have had a 65B08564-7 Actuator Attach Fitting
installed by service bulletin 747-57A2316.
-1
747-400 and -400F Airplanes line numbers 1264 through 1419. These
airplanes were delivered with a 65B08564-7 Actuator Attach Fitting
and could have replaced the 65B08564-7 Actuator Attach Fitting by
service bulletin 747-57A2316 with an Actuator Attach Fitting not
affected by this service bulletin.
-2
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR
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GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
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GroupVariable Number
1RB101 - RB102
1RB411 - RB413
1RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
1RD311
1RD351 - RD358
1RD361 - RD366
1RD381 - RD383
1RD411 - RD414
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GroupVariable Number
1RD421 - RD426
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
2RF001 - RF006
1RJ131 - RJ133
1RJ151 - RJ152
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GroupVariable Number
1RJ301 - RJ303
1RJ321 - RJ322
1RJ331 - RJ333
1RL401
2RL402 - RL403
1RL411 - RL414
2RL415 - RL436
2RL451 - RL456
2RL461 - RL462
2RL471 - RL481
2RL491 - RL492
2RL501 - RL502
2RL511 - RL516
2RL521 - RL522
2RL531 - RL534
2RL551
2RL561 - RL568
2RL571 - RL572
2RL576 - RL577
2RL579
2RL581 - RL586
1RL651 - RL653
2RL654 - RL655
2RL671 - RL675
2RL681 - RL684
2RL751 - RL752
1RM001 - RM004
2RM005 - RM007
2RM010
1RM011 - RM012
2RM013
1RM021 - RM024
1RM026 - RM027
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GroupVariable Number
2RM028 - RM030
1RM036 - RM039
2RM040
1RM041
2RM042 - RM045
1RM051
2RM052 - RM053
1RM071
1RM081 - RM084
1RM091
1RM096 - RM097
1RM116 - RM117
1RM126 - RM131
2RM132
1RM136 - RM147
1RM156 - RM157
2RM158
1RM166 - RM177
1RM191 - RM192
1RM231 - RM233
1RM241 - RM244
2RM245 - RM246
1RM261 - RM264
1RM316 - RM318
1RM331 - RM333
1RM341
2RM351 - RM355
2RM366 - RM367
2RM401 - RM403
2RM426
2RM431
2RM441 - RM443
2RM445
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GroupVariable Number
1RM801 - RM802
2RM803
1RM811 - RM813
1RM851 - RM853
2RM854 - RM855
1RM856
2RM857 - RM859
1RM861
2RM862 - RM863
1RM871 - RM873
2RM874 - RM880
1RM881 - RM885
2RM886 - RM890
1RM891 - RM899
1RM901 - RM903
2RM904 - RM906
1RM911
1RR001 - RR005
1RR021 - RR025
1RR031
1RR201 - RR206
1RR221 - RR226
1RR261 - RR267
1RR301 - RR310
1RR331 - RR332
1RR336
1RR341 - RR345
1RR361 - RR362
1RR421 - RR422
1RR431 - RR432
1RR441 - RR442
1RR451
1RR501 - RR504
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GroupVariable Number
1RR521 - RR522
1RR526
1RR531
1RR551 - RR556
1RR561
1RR566
1RR701
1RR721 - RR724
1RR746 - RR748
1RR851 - RR856
1RR861 - RR862
1RR951 - RR952
1RS001 - RS002
1RS201
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
1RS721 - RS722
1RS731 - RS732
1RS741 - RS743
1RS751 - RS752
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GroupVariable Number
1RS761 - RS762
1RS771
1RS781 - RS782
1RS786
1RT001 - RT014
1RT021 - RT022
1RT031 - RT035
1RT041 - RT047
1RT061
1RT071 - RT075
1RT101 - RT103
1RT121
1RT131 - RT137
1RT151 - RT152
1RT161 - RT168
1RT401 - RT412
1RT431 - RT447
1RT451 - RT469
1RT471 - RT499
1RT501 - RT535
1RT551 - RT568
1RT571 - RT591
1RT601 - RT657
1RT671 - RT673
1RT681 - RT682
1RT691 - RT699
1RT701 - RT704
1RT711 - RT717
1RT741 - RT757
1RT776 - RT777
1RT781 - RT784
1RT801 - RT803
1RT811 - RT814
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GroupVariable Number
1RT831 - RT837
1RT861 - RT864
1RT876 - RT880
1RT931 - RT932
1RT945 - RT949
1RT951 - RT955
1RT966 - RT967
1RU001 - RU006
1RU016 - RU017
1RU031 - RU032
1RU051 - RU052
1RU059 - RU062
1RU081 - RU083
1RU101 - RU102
1RU121 - RU132
1RU801 - RU809
1RU831 - RU841
2. Spares Affected
Examine your spares supply for the parts or components identified below. If any parts or components
are found, refer to Paragraph 3.B., Work Instructions for the recommended action.
Part Number
65B08564-7
B. Concurrent Requirements
None.
C. Reason
The inspections and replacement in this service bulletin will help prevent fracture of the outboard flap,
inboard actuator support fitting assembly (no. 2 or no. 7 gimbal). A fractured inboard actuator fitting
combined with the loss of the outboard actuator load path could result in the uncontrolled retraction of
the outboard flap and subsequent damage to flight control systems at the rear spar. Uncontrolled
retraction of the flap or damage to flight control systems could lead to reduced controllability of the
airplane.
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### Page 19

One operator reported the fracture of a 65B08564-7 actuator attach fitting. The actuator attach fitting
had approximately 5,500 flight-cycles and 20,600 flight-hours. The actuator attach fitting was installed
by service bulletin 747-57A2316. The actuator attach fitting fractured in the internal conical machined
area. Inspection of the actuator attach fitting revealed that a portion of the interior surface was machined
with a cylindrical profile instead of a conical profile. This results in reduced wall thickness. The thickness
of the fitting in the cylindrical area was approximately half the design wall thickness. The operator
inspected the remaining airplanes in their fleet and found another actuator attach fitting with the cylindrical
defect with a wall thickness below design requirements. An inspection of spare 65B08564-7 actuator
attach fittings at Boeing revealed some actuator attach fittings with the cylindrical defect with reduced
wall thicknesses. In addition, some actuator attach fittings which did not have the cylindrical defect had
wall thicknesses which were below design requirements. Reduced wall thickness results in the inability
of the actuator attach fitting to carry required loads.
This service bulletin provides instructions to inspect and replace 65B08564-7 no. 2 and no. 7 actuator
attach fittings which could have insufficient wall thickness.
Boeing Service Related Problem (SRP) 747-SRP-57-0264 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-13003 is related to this service bulletin.
D. Description
Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the
actuator attach fitting. Do an inspection of the Actuator Attach Fitting to determine if a 65B08564-7
actuator attach fitting is installed. Attach actuator ball screw to the actuator attach fitting. Activate and
retract the trailing edge flaps.
Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Disconnect actuator ball screw nut from the
actuator attach fitting. Do a Detailed (DET) inspection of the Actuator Attach Fitting to determine if it
has the cylindrical defect. Attach actuator ball screw to the actuator attach fitting. Activate and retract
the trailing edge flaps.
Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection
Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Do an
Ultrasonic (UT) inspection or mechanically determine the minimum wall thickness of the Actuator Attach
Fitting. Install the Actuator Attach Fitting. Activate and retract the trailing edge flaps.
Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement
Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Install
actuator attach fitting assemblies not affected by this service bulletin. Activate and retract the trailing
edge flaps.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
587, 687747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C,
747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
587, 687747-400, 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.
A logic diagram showing compliance tasks and compliance times is included as an aid in Appendix A.
The Conditions, Actions and Compliance times shown apply to each Actuator Attach Fitting
independently.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7)
– PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION
Repeat In-
terval (Not
to Exceed)
Compliance TimeActionCondition
-Within 90 days after the
original issue date of
this service bulletin
Do PART 1: OUTBOARD FLAP, IN-
BOARD ACTUATOR ATTACH FIT-
TING - PART NUMBER INSPECTION
to determine if a 65B08564-7 actuator
attach fitting is installed
All Airplanes
--No additional work required (Terminat-
ing Action) (a)
CONDITION 1:
65B08564-7 ACTUATOR AT-
TACH FITTING IS NOT IN-
STALLED
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Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7)
– PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION
Repeat In-
terval (Not
to Exceed)
Compliance TimeActionCondition
-Before further flightOPTION 1: Do PART 2: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - DET INSPECTION
for cylindrical defect
CONDITION 2:
65B08564-7 ACTUATOR AT-
TACH FITTING IS INSTALLED
OPTION 2: Do PART 4: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - REPLACEMENT
(Terminating Action) (a)
-Within 24 months after
the original issue date
of this service bulletin
OPTION 3: Do PART 3: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - MINIMUM THICK-
NESS INSPECTION to determine
minimum wall thickness of the Actuator
Fitting Assembly
CONDITION 3:
NO CYLINDRICAL DEFECT
FOUND
OPTION 4: Do PART 4: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - REPLACEMENT
(Terminating Action) (a)
-Before further flightOPTION 5: Do PART 3: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - MINIMUM THICK-
NESS INSPECTION to determine
minimum wall thickness of the Actuator
Fitting Assembly
CONDITION 4:
CYLINDRICAL DEFECT
FOUND
OPTION 6: Do PART 4: OUTBOARD
FLAP, INBOARD ACTUATOR AT-
TACH FITTING - REPLACEMENT
(Terminating Action) (a)
--No additional work required (Terminat-
ing Action) (a)
CONDITION 5:
MINIMUM THICKNESS OF
WALL IS 0.140 INCH OR
GREATER
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Table 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING (GIMBAL FITTING NO.S 2 AND 7)
– PART NUMBER INSPECTION, MINIMUM THICKNESS INSPECTION, AND DET INSPECTION
Repeat In-
terval (Not
to Exceed)
Compliance TimeActionCondition
-The later of 1) or 2):Do PART 4: OUTBOARD FLAP, IN-
BOARD ACTUATOR ATTACH FIT-
TING - REPLACEMENT (Terminating
Action) (a)
CONDITION 6:
MINIMUM THICKNESS OF
WALL IS 0.130 INCH OR
GREATER AND LESS THAN
0.140 INCH
1) Before 96 total
months or 6,000 total
flight-cycles, whichever
occurs first, on an actu-
ator attach fitting; (a)
or
2) Within 48 months or
3,000 flight-cycles after
the original issue date
of this service bulletin,
whichever occurs first.
(a)
-Before further flightDo PART 4: OUTBOARD FLAP, IN-
BOARD ACTUATOR ATTACH FIT-
TING - REPLACEMENT (Terminating
Action) (a)
CONDITION 7:
MINIMUM THICKNESS OF
WALL IS LESS THAN 0.130
INCH
(a) Repeat overhauls of the actuator attach fittings are still required in accordance with service bulletin 747-
57A2316.
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 overhaul for
each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate
with operator task hour data if necessary. The estimate does not include lost time. These are some
examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
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 Time to make the parts
 Time to find the tools.
Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002Open Access
1.002.002Disconnect Actuator
Ball Screw Nut
Inspect
0.500.501...Left Wing - FIG-
URE 1
0.500.501...Right Wing - FIG-
URE 4
1.002.002Connect Actuator
Ball Screw Nut
0.501.002Close Access
2.003.50TOTAL FOR EACH WING
4.007.00TOTAL FOR EACH AIRPLANE
Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002Open Access
1.002.002Disconnect Actuator
Ball Screw Nut
Inspect
0.500.501...Left Wing - FIG-
URE 2
0.500.501...Right Wing - FIG-
URE 5
1.002.002Connect Actuator
Ball Screw Nut
0.501.002Close Access
2.003.50TOTAL FOR EACH WING
4.007.00TOTAL FOR EACH AIRPLANE
Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002Open Access
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Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Remove the Actuator
Attach Fitting
Inspect
1.001.001...Left Wing - FIG-
URE 3
1.001.001...Right Wing - FIG-
URE 6
1.002.002Install the Actuator
Attach Fitting
0.501.002Close Access
2.504.00TOTAL FOR EACH WING
5.008.00TOTAL FOR EACH AIRPLANE
Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002Open Access
1.002.002Remove the Actuator
Attach Fitting
1.002.002Install the Actuator
Attach Fitting
0.501.002Close Access
1.503.00TOTAL FOR EACH WING
3.006.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR 85901-129RS
b. Boeing Service Bulletin 747-57A2316
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c. Boeing Service Related Problem (SRP) 747-SRP-57-0264
d. Component Maintenance Manual (CMM) 57-52-55
e. Service Bulletin Index D6-30300
f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-42-10, 20-50-01
g. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
h. 747 Fleet Team Digest (FTD) 57-13003
i. 747 Non-Destructive Testing (NDT) Manual Part 4, 51-00-00
j. 747-100/200/300 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-41, 27-51-46
k. 747-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-41, 27-51-46
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Inbd. Transmission Instl Outbd. T.E. Flap Drive No. 2 And 765B81115
The table above lists the applicable drawing used to prepare this service bulletin. This drawing is
not necessary to make the specified changes, and is not supplied with this service bulletin. The
drawing may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
57-52Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane . As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are available for 747 airplanes in warranty as of June 5, 2013. For inspection
labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Warranty & Product Assurance Contracts. If the condition described in this service bulletin is found
during the inspection for airplanes in warranty as of that date and additional task hours and kits, parts,
and/or special tools are required, send a warranty claim to Boeing Warranty & Product Assurance
Contracts. Please refer to this service bulletin number and reference the airplane variable numbers in
your purchase order. The warranty remedies will expire eight years from the original issue date of this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
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)FITTING ASSY265B08564-9  (65B08564-1 or 65B08564-5 or
65B08564-7 WHICH MEET CONDITION 5 IN
THIS SERVICE BULLETIN optional)
(b)Primer1 PtBMS 10-11, TYPE I
(b)Enamel1 PtBMS 10-60, TYPE I
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NotesNameQTYPart Number / Specification
(a) A new Actuator Attach Fittings is only required if the installed 65B08564-7 Assemblies
do not meet Condition 5 in this service bulletin.
65B08564-7 Actuator Attach Fittings sold by Boeing Spares after 17 June 2013 have blue
enamel applied to the feet of the Actuator Attach Fittings and have a minimum wall
thickness of 0.130 inch or greater. These actuators attach fittings are affected by this
service bulletin.
65B08564-1, 65B08564-5, or 65B08564-9 Actuator Attach Fittings are not affected by
this service bulletin.
The 65B08564-9 is a new Actuator Attach Fitting which is not affected by this service
bulletin and will be available at a later date.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Airplane Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 747
Airplane Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
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7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
8. A Detailed Inspection (DET) is defined as: An intensive examination of a specific
item, installation, or assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good lighting at an intensity
deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may
be necessary. Surface cleaning and elaborate procedures may be required.
9. 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.
10. Refer to Appendix A for logic diagram. Logic diagrams are provided as an aid only.
Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
11. 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.
12. 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.
13. 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.
14. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each actuator attach
fitting independently.
17. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
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B. WORK INSTRUCTIONS
1. Do PART 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER
INSPECTION to determine if a 65B08564-7 actuator attach fitting is installed
CONDITION 1: 65B08564-7 ACTUATOR ATTACH FITTING IS NOT INSTALLED
a. No additional work required (Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
CONDITION 2: 65B08564-7 ACTUATOR ATTACH FITTING IS INSTALLED
a. OPTION 1: Do PART 2: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - DET
INSPECTION for cylindrical defect.
b. OPTION 2: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -
REPLACEMENT (Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
CONDITION 3: NO CYLINDRICAL DEFECT FOUND
a. OPTION 3: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -
MINIMUM THICKNESS INSPECTION to determine minimum wall thickness of the Actuator
Fitting Assembly
b. OPTION 4: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -
REPLACEMENT (Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
CONDITION 4: CYLINDRICAL DEFECT FOUND
a. OPTION 5: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -
MINIMUM THICKNESS INSPECTION to determine minimum wall thickness of the Actuator
Fitting Assembly
b. OPTION 6: Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -
REPLACEMENT (Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
CONDITION 5: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER
a. No additional work required (Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
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CONDITION 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS
THAN 0.140 INCH
a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT
(Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
CONDITION 7: MINIMUM THICKNESS OF WALL IS LESS THAN 0.130 INCH
a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT
(Terminating Action).
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
PART 1: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER
INSPECTION
1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00
or 747-400 AMM 27-51-00 as accepted procedures.
2. Optional. Disconnect actuator ball screw nut from the actuator attach fitting. Refer to
747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures. May be
required if rubber stamped part number is not visible.
3. RC - Do an inspection of the Actuator Attach Fitting to determine if part number 65B08564-7 is
installed in accordance with the figure below. As an alternative, a review of the maintenance or
delivery records can be used if the part number of the installed Actuator Attach Fitting can be
positively determined.
Right Wing
(No. 7 Actuator Attach Fitting)
Left Wing
(No. 2 Actuator Attach Fitting)
FIGURE 4FIGURE 1
4. Attach actuator ball screw to the actuator attach fitting, if disconnected. Refer to 747-100/200/300
AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures.
5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400
AMM 27-51-00 as accepted procedures.
6. Put the airplane back to a serviceable condition.
PART 2: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - DET INSPECTION
1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00
or 747-400 AMM 27-51-00 as accepted procedures.
2. Optional. Disconnect actuator ball screw nut from the actuator attach fitting. Refer to
747-100/200/300 AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures.
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3. RC - Do a DET inspection of the Actuator Attach Fitting to determine if it has the cylindrical defect
in accordance with the figure below.
Right Wing
(No. 7 Actuator Attach Fitting)
Left Wing
(No. 2 Actuator Attach Fitting)
FIGURE 5FIGURE 2
4. Attach actuator ball screw to the actuator attach fitting, if disconnected. Refer to 747-100/200/300
AMM 27-51-41 or 747-400 AMM 27-51-41 as accepted procedures.
5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400
AMM 27-51-00 as accepted procedures.
6. Put the airplane back to a serviceable condition.
PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS
INSPECTION
1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00
or 747-400 AMM 27-51-00 as accepted procedures.
2. Remove the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM
27-51-46 as accepted procedures.
3. RC - Do an Ultrasonic (UT) inspection or mechanically determine the minimum thickness of the
Actuator Attach Fitting in accordance with the figure below.
Right Wing
(No. 7 Actuator Attach Fitting)
Left Wing
(No. 2 Actuator Attach Fitting)
FIGURE 6FIGURE 3
4. Install the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM
27-51-46 as accepted procedures.
5. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400
AMM 27-51-00 as accepted procedures.
6. Put the airplane back to a serviceable condition.
PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT
1. Extend the trailing edge flaps to detent 30 and deactivate. Refer to 747-100/200/300 AMM 27-51-00
or 747-400 AMM 27-51-00 as accepted procedures.
2. Remove the Actuator Attach Fitting. Refer to 747-100/200/300 AMM 27-51-46 or 747-400 AMM
27-51-46 as accepted procedures.
3. RC - Install 1) Actuator Attach Fitting 65B08564-1, 65B08564-5, or 65B08564-9: or 2) Actuator
Attach Fitting 65B08564-7 Assembly which meets Condition 5 in this service bulletin. Refer to
747-100/200/300 AMM 27-51-46 or 747-400 AMM 27-51-46 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: September 12, 2013
747-57A2343
33 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 34

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.
NOTE: A new Actuator Attach Fitting is being designed, which will meet the terminating action
requirements in this service bulletin. These new Actuator Attach Fitting will require repeat
inspections and overhaul in accordance with service bulletin 747-57A2316.
4. Activate and retract the trailing edge flaps. Refer to 747-100/200/300 AMM 27-51-00 or 747-400
AMM 27-51-00 as accepted procedures.
5. Put the airplane back to a serviceable condition.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
34 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 35 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
B ATTACH FITTING
A-A  2268231
FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION
(SHEET 1 OF 2)
Original Issue: September 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  Work - See page 1 for details.  747-57A2343  35 of 54

### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
to determine if a 65B08564-7 is installed.
The part number is rubber stamped between
the feet on either the inboard or outboard
side of the fitting.
1-Actuator Attach Fit-
ting
Inspect1
If the part number is not visible,it can be de-
termined if a 65B08564-7 is installed by
measuring the internal diameter at the loca-
tion shown. It may be necessary to discon-
nect the actuator ball screw nut to gain ac-
cess. Refer to 747-100/200/300 AMM 27-51-
41 or 747-400 AMM 27-51-41 as accepted
procedures.
1-Actuator Attach Fit-
ting
Measure2
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataFlag Note
The diameter of the feature is:1
1. 2.5 +/- 0.05 inches for the 65B08564-7
2. 2.85 +/- 0.05 inches for the 65B08564-1 or -5.
FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
36 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
B ATTACH FITTING
A-A  2268657
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 1 OF 3)
Original Issue: September 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-57A2343
Work - See page 1 for details.  37 of 54

### Page 38 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
MINIMUM
THICKNESS •
CONICAL
PROFILE
CYLINDRICAL (
DEFECT
CIRCULAR  D
RIDGE
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 2 OF 3)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-57A2343
Work - See page 1 for details.  38 of 54

### 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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do a DET to determine if the cylindrical de-
fect is present. The Actuator Attach Fitting
should only have a conical profile. On some
fittings the upper portion of the bore was
made with a cylindrical defect perpendicular
to the base. A borescope can be used to do
this inspection.
1-Actuator Attach Fit-
ting
Inspect1
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataFlag Note
The cylindrical defect results in a circular ridge where the ID transitions
from a conical section to a hemispherical section. When looking into the
fitting with a bright light, the circular ridge is seen as change in the color,
due to the change in angle of the machining. The cylindrical defect, if
present, will be seen as a straight wall perpendicular to the base until it
transitions into the hemispherical region.
1
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
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39 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
B ATTACH FITTING
A-A
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 1 OF 4)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  40 of 54

### Page 41 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
UPPER
JOURNAL
2.0
MINIMUM
LOWER
JOURNAL
2268691
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 2 OF 4)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  ELS LAL
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  41 of 54

### Page 42 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
UPPER
JOURNAL
UPPER
JOURNAL
MINIMUM
THICKNESS
CONICAL
PROFILE
0.5
MINIMUM
THICKNESS
0.5
WITHOUT CYLINDRICAL DEFECT
CONICAL
PROFILE
WITH CYLINDRICAL DEFECT
2268817
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 3 OF 4)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  747-57A2343
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  42 of 54

### 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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do an Ultrasonic inspection to determine the
minimum thickness of the actuator attach
fitting wall in the indicated area in accor-
dance with 747 NDT Manual Part 4, 51-00-
00, Procedure 2 or Procedure 3. It is recom-
mend the measurements be recorded for
future reference. Remove finish if required;
refer to SOPM 20-30-03 as an accepted
procedure. As an option, mechanically
measure the Actuator Attach Fitting to deter-
mine the minimum thickness of the Actuator
Attach Fitting in the indicated area. Scan the
vertical surface every 45 + or - 10 degrees.
Mark the minimum thickness location, then
scan the entire circumference a minimum of
0.5 inch above and below location of the
minimum thickness.
1-Actuator Attach Fit-
ting
Inspect1
Touch-up bare surfaces. Refer to SOPM 20-
42-10 as an accepted procedure. (a)
--Low Hydrogen Em-
brittlement Cadmi-
um Plating
Apply2
Touch-up bare surfaces. 2 coats. (a)-BMS 10-11,
TYPE I
PrimerApply
(a) Required only if the actuator attach fitting is not being replaced and the existing finish was removed to
accomplish the inspection.
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
43 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
ATTACH FITTING  B
A-A  2268860
FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION
(SHEET 1 OF 2)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-57A2343
Work - See page 1 for details.  44 of 54

### 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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
to determine if a 65B08564-7 is installed.
The part number is rubber stamped between
the feet on either the inboard or outboard
side of the fitting.
1-Actuator Attach Fit-
ting
Inspect1
If the part number is not visible,it can be de-
termined if a 65B08564-7 is installed by
measuring the internal diameter at the loca-
tion shown. It may be necessary to discon-
nect the actuator ball screw nut to gain ac-
cess. Refer to 747-100/200/300 AMM 27-51-
41 or 747-400 AMM 27-51-41 as accepted
procedures.
1-Actuator Attach Fit-
ting
Measure2
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataFlag Note
The diameter of the feature is approximately as follows:1
1. 2.5 +/- 0.05 inches for the 65B08564-7
2. 2.85 +/- 0.05 inches for the 65B08564-1 or -5.
FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
45 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
ATTACH FITTING
A-A  2268871
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 1 OF 3)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  747-57A2343
Work - See page 1 for details.  46 of 54

### Page 47 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
MINIMUM
THICKNESS
CONICAL
PROFILE
CYLINDRICAL (1)
DEFECT
RIDGE  CIRCULAR  D  2268908
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 2 OF 3)
Original Issue: September 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-57A2343
Work - See page 1 for details.  47 of 54

### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do a DET to determine if the cylindrical de-
fect is present. The Actuator Attach Fitting
should only have a conical profile. On some
fittings the upper portion of the bore was
made with a cylindrical defect perpendicular
to the base.
1-Actuator Attach Fit-
ting
Inspect1
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
More DataFlag Note
The cylindrical defect results in a circular ridge where the ID transitions
from a conical section to a hemispherical section. When looking into the
fitting with a bright light, the circular ridge is seen as change in the color,
due to the change in angle of the machining, with a cylindrical profile
perpendicular to the base until it transitions into the hemispherical region.
1
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
48 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
ATTACH FITTING
A-A  2268907
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 1 OF 4)
Original Issue: September 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  747-57A2343
Work - See page 1 for details.  49 of 54

### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
UPPER
JOURNAL.
2.0
MINIMUM
LOWER
JOURNAL
2268916
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 2 OF 4)
Original Issue: September 12, 2013
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Work - See page 1 for details.  50 of 54

### Page 51 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
UPPER
JOURNAL
0.5
UPPER
JOURNAL
MINIMUM
THICKNESS
0.5
MINIMUM
THICKNESS
WITHOUT CYLINDRICAL DEFECT  0.5
CONICAL
E  PROFILE
WITH CYLINDRICAL DEFECT
2268917
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 3 OF 4)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  747-57A2343
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  51 of 54

### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do an Ultrasonic inspection to determine the
minimum thickness of the actuator attach
fitting wall in the indicated area in accor-
dance with 747 NDT Manual Part 4, 51-00-
00, Procedure 2 or Procedure 3. It is recom-
mend the measurements be recorded for
future reference. Remove finish if required;
refer to SOPM 20-30-03 as an accepted
procedure. As an option, mechanically
measure the Actuator Attach Fitting to deter-
mine the minimum thickness of the Actuator
Attach Fitting in the indicated area. Scan the
vertical surface every 45 + or - 10 degrees.
Mark the minimum thickness location, then
scan the entire circumference a minimum of
0.5 inch above and below location of the
minimum thickness.
1-Actuator Attach Fit-
ting
Inspect1
Touch-up bare surfaces. Refer to SOPM 20-
42-10 as an accepted procedure. (a)
--Low Hydrogen Em-
brittlement Cadmi-
um Plating
Apply2
Touch-up bare surfaces. 2 coats. (a)-BMS 10-11,
TYPE I
PrimerApply
(a) Required only if the actuator attach fitting is not being replaced and the existing finish was removed to
accomplish the inspection.
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: September 12, 2013
747-57A2343
52 of 54
BOEING SERVICE BULLETIN 747-57A2343
ALERTALERT

### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
WITHIN 90 DAYS AFTER ORIGINAL ISSUE DATE OF THIS SERVICE BULLETIN, DO PART 1
OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION TO
DETERMINE IF A 65B08564-7 ACTUATOR FITTING ASSEMBLY IS INSTALLED
CONDITION 1:  CONDITION 2:
65B08564-7 ACTUATOR ATTACH  65B08564-7 ACTUATOR ATTACH
FITTING IS NOT INSTALLED  FITTING IS INSTALLED
NO ADDITIONAL WORK REQUIRED  (TERMINATING ACTION) E  BEFORE FURTHER FLIGHT
OPTION 1:  OPTION 2:
DO PART 2: OUTBOARD FLAP  DO PART 4: OUTBOARD FLAP,
INBOARD ACTUATOR ATTACH  INBOARD ACTUATOR ATTACH
FITTING - DET INSPECTION FOR  FITTING - REPLACEMENT
CYLINDRICAL DEFECT  (TERMINATING ACTION) 1
CONDITION 3:  CONDITION 4:
NO CYLINDRICAL DEFECT FOUND  CYLINDRICAL DEFECT FOUND
WITHIN 24 MONTHS AFTER ORIGINAL  BEFORE FURTHER FLIGHT
ISSUE DATE OF THIS SERVICE BULLETIN
OPTION 3:  OPTION 4:  OPTION 5:  OPTION 6:
MINIMUM THICKNESS  ATTACH FITTING -  - LAP. INBOARL  INSPECTION  OUTBOARD  DO PART 3:  ACTUATOF  ATTACH FITTING -  FLAP, INBOARD  REPLACEMENT  (TERMINATING  OUTBOARD  ACTUATOR  DO PART 4:  ACTION) T  MINIMUM THICKNESS  ATTACH FITTING -  FLAP, INBOARD  INSPECTION  OUTBOARD  ACTUATOR  DO PART 3:  ATTACH FITTING -  REPLACEMENT  (TERMINATING  -LAP, INBOARL  OUTBOARD  DO PART 4:  ACTUATOF  ACTION) F
CONDITION 5:  CONDITION 6:  CONDITION 7:
MINIMUM THICKNESS OF  MINIMUM THICKNESS OF WALL IS  MINIMUM THICKNESS
WALL IS 0.140 INCH OR  0.130 INCH OR GREATER AND  OF WALL IS LESS
GREATER  LESS THAN 0.140 INCH  THAN 0.130 INCH
IC
APPENDIX A: LOGIC DIAGRAM
(SHEET 1 OF 2)
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### Page 54 (OCR)

BOEING SERVICE BULLETIN 747-57A2343
ALERT  ALERT
CONDITION 5:  CONDITION 6:  CONDITION 7:
MINIMUM THICKNESS OF  MINIMUM THICKNESS OF WALL IS  MINIMUM THICKNESS
WALL IS 0.140 INCH OR  0.130 INCH OR GREATER AND  OF WALL IS LESS
GREATER  LESS THAN 0.140 INCH  THAN 0.130 INCH
NO ADDITIONAL WORK
REQUIRED (TERMINATING  BEFORE FURTHER FLIGHT
ACTION) F
THE LATER OF 1) OR 2):
1) BEFORE 96 TOTAL MONTHS OR 6,000
ATTACH FITING: OR ACTUATOKE
2) WITHIN 48 MONTHS OR 3,000
FLIGHT-CYCLES AFTER THE ORIGINAL
BULLETIN, WHICHEVER OCCURS FIRST  ISSUE DATE OF THIS SERVICE
DO PART 4: OUTBOARD FLAP, INBOARD
ACTUATOR ATTACH FITTING -
REPLACEMENT (TERMINATING ACTION)
2269137
Flag Note  More Data
1  Repeat overhauls of the actuator attach fittings are still required in accor-
dance with service bulletin 747-57A2316.
APPENDIX A: LOGIC DIAGRAM
(SHEET 2 OF 2)
Original Issue: September 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  747-57A2343  54 of 54

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