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.

ECCN: 9E991

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Unpublished Work.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

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ALERT ALERT

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 25

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 27

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . . 35

FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION . . . . . . . . . 37

FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . 44

FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION . . . . . . . . 46

FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

APPENDIX A: LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary 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.

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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Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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

Total Task Hours Elapsed Hours

Part 1: Outboard Flap, Inboard Actuator Attach Fitting - 7.00 4.00

Part Number Inspection

Part 2: Outboard Flap, Inboard Actuator Attach Fitting - 7.00 4.00

DET Inspection

Part 3: Outboard Flap, Inboard Actuator Attach Fitting - 8.00 5.00

Minimum Thickness Inspection

Part 4: Outboard Flap, Inboard Actuator Attach Fitting - 6.00 6.00

Replacement

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Paragraph 2.A., Material - Price and Availability.

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ALERT ALERT
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.

GROUP CONFIGURATION DESCRIPTION

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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Variable Number Group

RA001 - RA034 1

RA101 - RA115 1

RA161 - RA164 1

RA201 - RA203 1

RA216 - RA217 1

RA245 - RA246 1

RA251 - RA266 1

RA301 - RA318 1

RA351 - RA360 1

RA369 - RA373 1

RA401 - RA418 1

RA501 - RA502 1

RA521 - RA528 1

RA532 - RA548 1

RA551 - RA552 1

RA559 - RA561 1

RA581 - RA582 1

RA585 1

RA601 - RA602 1

RA631 - RA635 1

RA651 - RA652 1

RA671 - RA677 1

RA701 - RA702 1

RA721 - RA731 1

RA741 - RA745 1

RA749 - RA750 1

RA761 - RA762 1

RA781 - RA784 1

RA901 - RA916 1

RB001 - RB016 1

RB041 - RB044 1

RB071 - RB075 1

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Variable Number Group

RB101 - RB102 1

RB411 - RB413 1

RB421 1

RB601 - RB607 1

RB681 - RB697 1

RB711 1

RB721 - RB723 1

RB741 - RB748 1

RD001 - RD004 1

RD021 - RD022 1

RD041 - RD059 1

RD071 - RD072 1

RD081 - RD083 1

RD091 - RD092 1

RD101 - RD104 1

RD121 - RD127 1

RD131 - RD144 1

RD166 - RD167 1

RD171 - RD172 1

RD181 - RD183 1

RD201 - RD204 1

RD221 - RD227 1

RD231 - RD235 1

RD241 - RD243 1

RD251 - RD262 1

RD271 - RD272 1

RD291 - RD292 1

RD301 - RD302 1

RD311 1

RD351 - RD358 1

RD361 - RD366 1

RD381 - RD383 1

RD411 - RD414 1

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Variable Number Group

RD421 - RD426 1

RD431 - RD435 1

RD441 - RD442 1

RD451 - RD456 1

RD461 1

RD471 - RD475 1

RD513 - RD519 1

RD531 - RD533 1

RD551 1

RD561 1

RD571 1

RD581 - RD583 1

RD591 - RD593 1

RD601 - RD607 1

RD621 - RD623 1

RD641 - RD649 1

RD651 - RD659 1

RD661 1

RD671 1

RD681 - RD682 1

RD691 - RD692 1

RD701 - RD702 1

RD721 - RD722 1

RD741 - RD742 1

RD751 - RD755 1

RD761 1

RD771 - RD775 1

RD781 - RD783 1

RD791 - RD792 1

RE001 1

RF001 - RF006 2

RJ131 - RJ133 1

RJ151 - RJ152 1

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Variable Number Group

RJ301 - RJ303 1

RJ321 - RJ322 1

RJ331 - RJ333 1

RL401 1

RL402 - RL403 2

RL411 - RL414 1

RL415 - RL436 2

RL451 - RL456 2

RL461 - RL462 2

RL471 - RL481 2

RL491 - RL492 2

RL501 - RL502 2

RL511 - RL516 2

RL521 - RL522 2

RL531 - RL534 2

RL551 2

RL561 - RL568 2

RL571 - RL572 2

RL576 - RL577 2

RL579 2

RL581 - RL586 2

RL651 - RL653 1

RL654 - RL655 2

RL671 - RL675 2

RL681 - RL684 2

RL751 - RL752 2

RM001 - RM004 1

RM005 - RM007 2

RM010 2

RM011 - RM012 1

RM013 2

RM021 - RM024 1

RM026 - RM027 1

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ALERT ALERT
Variable Number Group

RM028 - RM030 2

RM036 - RM039 1

RM040 2

RM041 1

RM042 - RM045 2

RM051 1

RM052 - RM053 2

RM071 1

RM081 - RM084 1

RM091 1

RM096 - RM097 1

RM116 - RM117 1

RM126 - RM131 1

RM132 2

RM136 - RM147 1

RM156 - RM157 1

RM158 2

RM166 - RM177 1

RM191 - RM192 1

RM231 - RM233 1

RM241 - RM244 1

RM245 - RM246 2

RM261 - RM264 1

RM316 - RM318 1

RM331 - RM333 1

RM341 1

RM351 - RM355 2

RM366 - RM367 2

RM401 - RM403 2

RM426 2

RM431 2

RM441 - RM443 2

RM445 2

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ALERT ALERT
Variable Number Group

RM801 - RM802 1

RM803 2

RM811 - RM813 1

RM851 - RM853 1

RM854 - RM855 2

RM856 1

RM857 - RM859 2

RM861 1

RM862 - RM863 2

RM871 - RM873 1

RM874 - RM880 2

RM881 - RM885 1

RM886 - RM890 2

RM891 - RM899 1

RM901 - RM903 1

RM904 - RM906 2

RM911 1

RR001 - RR005 1

RR021 - RR025 1

RR031 1

RR201 - RR206 1

RR221 - RR226 1

RR261 - RR267 1

RR301 - RR310 1

RR331 - RR332 1

RR336 1

RR341 - RR345 1

RR361 - RR362 1

RR421 - RR422 1

RR431 - RR432 1

RR441 - RR442 1

RR451 1

RR501 - RR504 1

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Variable Number Group

RR521 - RR522 1

RR526 1

RR531 1

RR551 - RR556 1

RR561 1

RR566 1

RR701 1

RR721 - RR724 1

RR746 - RR748 1

RR851 - RR856 1

RR861 - RR862 1

RR951 - RR952 1

RS001 - RS002 1

RS201 1

RS211 - RS212 1

RS221 - RS222 1

RS231 - RS241 1

RS251 - RS259 1

RS263 1

RS265 - RS268 1

RS271 - RS276 1

RS291 - RS292 1

RS301 - RS306 1

RS311 - RS320 1

RS331 - RS333 1

RS341 - RS342 1

RS699 1

RS701 - RS703 1

RS711 - RS713 1

RS721 - RS722 1

RS731 - RS732 1

RS741 - RS743 1

RS751 - RS752 1

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ALERT ALERT
Variable Number Group

RS761 - RS762 1

RS771 1

RS781 - RS782 1

RS786 1

RT001 - RT014 1

RT021 - RT022 1

RT031 - RT035 1

RT041 - RT047 1

RT061 1

RT071 - RT075 1

RT101 - RT103 1

RT121 1

RT131 - RT137 1

RT151 - RT152 1

RT161 - RT168 1

RT401 - RT412 1

RT431 - RT447 1

RT451 - RT469 1

RT471 - RT499 1

RT501 - RT535 1

RT551 - RT568 1

RT571 - RT591 1

RT601 - RT657 1

RT671 - RT673 1

RT681 - RT682 1

RT691 - RT699 1

RT701 - RT704 1

RT711 - RT717 1

RT741 - RT757 1

RT776 - RT777 1

RT781 - RT784 1

RT801 - RT803 1

RT811 - RT814 1

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Variable Number Group

RT831 - RT837 1

RT861 - RT864 1

RT876 - RT880 1

RT931 - RT932 1

RT945 - RT949 1

RT951 - RT955 1

RT966 - RT967 1

RU001 - RU006 1

RU016 - RU017 1

RU031 - RU032 1

RU051 - RU052 1

RU059 - RU062 1

RU081 - RU083 1

RU101 - RU102 1

RU121 - RU132 1

RU801 - RU809 1

RU831 - RU841 1

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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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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ALERT ALERT
Group 1:

Affected Maintenance Zones

Model Zone

747-100, 747-100B, 747-100B 587, 687

SUD, 747-200B, 747-200C,

747-200F, 747-300, 747-400,

747-400D, 747-400F, 747SR

Group 2:

Affected Maintenance Zones

Model Zone

747-400, 747-400F 587, 687

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 Interval (Not

to Exceed)

Condition Action Compliance Time

Within 90 days after the -

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

attach fitting is installed

All Airplanes

No additional work required (Terminat- - -

ing Action) (a)

CONDITION 1:

65B08564-7 ACTUATOR ATTACH FITTING IS NOT INSTALLED

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ALERT ALERT
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 Interval (Not

to Exceed)

Condition Action Compliance Time

OPTION 1: Do PART 2: OUTBOARD Before further flight -

FLAP, INBOARD ACTUATOR ATTACH FITTING - DET INSPECTION

for cylindrical defect

CONDITION 2:

65B08564-7 ACTUATOR ATTACH FITTING IS INSTALLED

OPTION 2: Do PART 4: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH 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 ATTACH FITTING - MINIMUM THICKNESS 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 ATTACH FITTING - REPLACEMENT

(Terminating Action) (a)

OPTION 5: Do PART 3: OUTBOARD Before further flight -

FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS 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 ATTACH 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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ALERT ALERT
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 Interval (Not

to Exceed)

Condition Action Compliance Time

Do PART 4: OUTBOARD FLAP, IN- The later of 1) or 2): -

BOARD ACTUATOR ATTACH FITTING - 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 actuator 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)

Do PART 4: OUTBOARD FLAP, IN- Before further flight -

BOARD ACTUATOR ATTACH FITTING - 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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
• Time to make the parts

• Time to find the tools.

Part 1: Outboard Flap, Inboard Actuator Attach Fitting - Part Number Inspection

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

Disconnect Actuator 2 2.00 1.00

Ball Screw Nut

Inspect

...Left Wing - FIG- 1 0.50 0.50

URE 1

...Right Wing - FIG- 1 0.50 0.50

URE 4

Connect Actuator 2 2.00 1.00

Ball Screw Nut

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.50 2.00

TOTAL FOR EACH AIRPLANE 7.00 4.00

Part 2: Outboard Flap, Inboard Actuator Attach Fitting - DET Inspection

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

Disconnect Actuator 2 2.00 1.00

Ball Screw Nut

Inspect

...Left Wing - FIG- 1 0.50 0.50

URE 2

...Right Wing - FIG- 1 0.50 0.50

URE 5

Connect Actuator 2 2.00 1.00

Ball Screw Nut

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.50 2.00

TOTAL FOR EACH AIRPLANE 7.00 4.00

Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

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ALERT ALERT
Part 3: Outboard Flap, Inboard Actuator Attach Fitting - Minimum Thickness Inspection

Task Number of Persons Task Hours Elapsed Hours

Remove the Actuator 2 2.00 1.00

Attach Fitting

Inspect

...Left Wing - FIG- 1 1.00 1.00

URE 3

...Right Wing - FIG- 1 1.00 1.00

URE 6

Install the Actuator 2 2.00 1.00

Attach Fitting

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 4.00 2.50

TOTAL FOR EACH AIRPLANE 8.00 5.00

Part 4: Outboard Flap, Inboard Actuator Attach Fitting - Replacement

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

Remove the Actuator 2 2.00 1.00

Attach Fitting

Install the Actuator 2 2.00 1.00

Attach Fitting

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.00 1.50

TOTAL FOR EACH AIRPLANE 6.00 3.00

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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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:

Drawing Number Title

65B81115 Inbd. Transmission Instl Outbd. T.E. Flap Drive No. 2 And 7

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:

Publication Chapter-Section

Component Maintenance Manual 57-52

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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ALERT ALERT
M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Part Number / Specification QTY Name Notes

65B08564-9 (65B08564-1 or 65B08564-5 or 2 FITTING ASSY (a)

65B08564-7 WHICH MEET CONDITION 5 IN

THIS SERVICE BULLETIN optional)

BMS 10-11, TYPE I 1 Pt Primer (b)

BMS 10-60, TYPE I 1 Pt Enamel (b)

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ALERT ALERT
Part Number / Specification QTY Name Notes

(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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ALERT ALERT
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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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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ALERT ALERT
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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ALERT ALERT
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 1 FIGURE 4

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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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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 2 FIGURE 5

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 3 FIGURE 6

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.

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

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.

Actuator Attach Fit- - 1

ting

1 Inspect

If the part number is not visible,it can be determined if a 65B08564-7 is installed by

measuring the internal diameter at the location shown. It may be necessary to disconnect the actuator ball screw nut to gain access. Refer to 747-100/200/300 AMM 27-51-

41 or 747-400 AMM 27-51-41 as accepted

procedures.

Actuator Attach Fit- - 1

ting

2 Measure

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

Flag Note More Data

1 The diameter of the feature is:

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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do a DET to determine if the cylindrical defect 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.

Actuator Attach Fit- - 1

ting

1 Inspect

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

Flag Note More Data

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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 3: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do an Ultrasonic inspection to determine the

minimum thickness of the actuator attach

fitting wall in the indicated area in accordance with 747 NDT Manual Part 4, 51-00-

00, Procedure 2 or Procedure 3. It is recommend 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 determine 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.

Actuator Attach Fit- - 1

ting

1 Inspect

Touch-up bare surfaces. Refer to SOPM 20-

42-10 as an accepted procedure. (a)

Low Hydrogen Em- - -

brittlement Cadmium Plating

2 Apply

BMS 10-11, - Touch-up bare surfaces. 2 coats. (a)

TYPE I

Apply Primer

(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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION

(SHEET 1 OF 2)

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747-57A2343

44 of 54

BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

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.

Actuator Attach Fit- - 1

ting

1 Inspect

If the part number is not visible,it can be determined if a 65B08564-7 is installed by

measuring the internal diameter at the location shown. It may be necessary to disconnect the actuator ball screw nut to gain access. Refer to 747-100/200/300 AMM 27-51-

41 or 747-400 AMM 27-51-41 as accepted

procedures.

Actuator Attach Fit- - 1

ting

2 Measure

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

Flag Note More Data

1 The diameter of the feature is approximately as follows:

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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION

(SHEET 2 OF 3)

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47 of 54

BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do a DET to determine if the cylindrical defect 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.

Actuator Attach Fit- - 1

ting

1 Inspect

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

Flag Note More Data

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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
FIGURE 6: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - MINIMUM WALL THICKNESS INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do an Ultrasonic inspection to determine the

minimum thickness of the actuator attach

fitting wall in the indicated area in accordance with 747 NDT Manual Part 4, 51-00-

00, Procedure 2 or Procedure 3. It is recommend 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 determine 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.

Actuator Attach Fit- - 1

ting

1 Inspect

Touch-up bare surfaces. Refer to SOPM 20-

42-10 as an accepted procedure. (a)

Low Hydrogen Em- - -

brittlement Cadmium Plating

2 Apply

BMS 10-11, - Touch-up bare surfaces. 2 coats. (a)

TYPE I

Apply Primer

(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)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
APPENDIX A: LOGIC DIAGRAM

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Flag Note More Data

Repeat overhauls of the actuator attach fittings are still required in accordance with service bulletin 747-57A2316.1

APPENDIX A: LOGIC DIAGRAM

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT