Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-57A2343

Original Issue: September 12, 2013

Revision 1: June 23, 2014

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Unpublished Work.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.

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5.0
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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 9

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 30

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 34

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

FIGURE 1: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . . 45

FIGURE 2: LEFT WING - NO. 2 ACTUATOR ATTACH FITTING - DET INSPECTION . . . . . . . . . 47

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

MACHINING DEFECT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 4: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - PART NUMBER INSPECTION . 55

FIGURE 5: RIGHT WING - NO. 7 ACTUATOR ATTACH FITTING - DET INSPECTION . . . . . . . . 57

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

MACHINING DEFECT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

APPENDIX A: LOGIC DIAGRAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65

APPENDIX B: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 747-57A2343

Original Issue: September 12, 2013

Revision 1: June 23, 2014

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 revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service bulletin.

More work is required on airplanes with an actuator attach fitting 65B08564-7 installed which accomplished

PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS INSPECTION

in accordance with the Original Issue of this service bulletin. These airplanes should do PART 3: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM THICKNESS AND MACHINING DEFECT

INSPECTION to determine if the machining defect is present and accomplish any required follow-on actions

within the compliance time in Paragraph 1.E., Compliance.

The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to

Revision 1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and times given

in Revision 1 of this service bulletin mandatory.

REASON FOR REVISION

This revision is sent to:

1. Add an inspection for a machining defect that can reduce the durability of the fitting. During inspection

of the actuator fittings, many actuator attach fittings 65B08564-7 were found to have a machining defect,

visible under the protective finishes, in the area where the tapered machining transitioned to the

hemispherical machining at the top of the inner surface.

2. Limit the compliance time that fitting assemblies with a wall thickness 0.130 inch or greater and less

than 0.140 inch and do not have a machining defect can remain in-service, to 48 months or 3,000

flight-cycles after the Original Issue date of this service bulletin, whichever occurs first.

These sections were changed:

1. Summary

a. Background - Add machining defect.

b. Action

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(1) Add inspection for machining defect to Part 3.

(2) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140

inch to allow removal of the machining defect.

c. Compliance - Add Reference to AD 2013-23-03. Show that it is expected that additional rule-making

is expected against Revision 1 of this service bulletin.

d. Manpower

(1) Revise title for Part 3 to account for inspection for the machining defect.

(2) Add new Part 5 - Overhaul.

e. Illustration

(1) Revise title for Part 3 to account for inspection for the machining defect.

(2) Add new Part 5 - Overhaul.

f. Material Information - Reference new Spares Input Survey in APPENDIX B.

2. Planning Information

a. Paragraph 1.C., Reason

(1) Add machining defect.

(2) Add Reason for revision

b. Paragraph 1.D., Description

(1) Add inspection for machining defect to Part 3.

(2) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140

inch to allow removal of the machining defect.

(3) Add compliance information related to the revision.

c. Paragraph 1.E., Compliance

(1) Add Reference to AD 2013-23-03. Show that it is expected that additional rule-making is

expected against Revision 1 of this service bulletin.

(2) Add new row for airplanes which accomplished Part 3 - Inspection in accordance with the

Original Issue.

(3) Add inspection for machining defect to Part 3.

(4) Include no machining defect in existing Conditions 5 and 6. Add new Conditions 8 and 9 which

are the same as Conditions 5 and 6 with the machining defect. Show that for Condition 7 it

does not matter if the machining defect is or is not present.

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
(5) Add Part 5 - Overhaul for fittings with minimum wall thickness greater than 0.140 inch to allow

removal of the machining defect.

(6) Revise the compliance time for Condition 6 due to durability concerns.

d. Paragraph 1.F., Approval - Add AMOC paragraph for AD 2013-23-03.

e. Paragraph 1.G., Manpower

(1) Revise title for Part 3.

(2) Add new table for Part 5 - Overhaul.

f. Paragraph 1.J., References - Add reference to AD 2013-23-03 and to SOPM for storage of fitting

assemblies after overhaul or new.

3. Material Information

a. Paragraph 2.A., Material - Price and Availability - Add price and availability information for new

65B08564-9 Fitting Assembly and reference new Spares Input Survey in APPENDIX B.

b. Paragraph 2.C.2., Parts and Materials Supplied by the Operator

(1) Clarify the condition of the spare actuator assemblies sold by Boeing.

(2) Clarify what parts are not affected by this service bulletin.

c. Paragraph 2.B., Industry Support Information - Correct model number.

4. Accomplishment Instructions

a. Paragraph 3.B., Work Instructions

(1) General work Flow

(a) Add inspection for airplanes which accomplished Part 3 - Inspection in accordance with

the Original Issue.

(b) Add inspection for machining defect to Part 3.

(c) Add Part 5 - Overhaul for fittings with minimum wall thickness greater than 0.140 inch to

allow removal of the machining defect.

(2) Part 3 - DET Insection - Add inspection for machining defect.

(3) Part 4 Overhaul - Add additional Actuator attach fitting options.

(4) Part 5 - Overhaul - Add new part for fittings with minimum wall thickness greater than 0.140

inch to allow removal of the machining defect.

(5) FIGURE 2

(a) Revise illustration to help clarify cylindrical defect.

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ALERT ALERT
(b) Revise Flag Note 1 text to help clarify cylindrical defect.

(6) FIGURE 3

(a) General - Revise title to add inspection for machining defect.

(b) Illustration - Add new illustration showing a typical machining defect.

(c) Step 3 - Add new step to inspect for the machining defect. Note that finish restoration is

not required if fitting is being overhauled.

(7) FIGURE 5

(a) Revise illustration to help clarify cylindrical defect.

(b) Revise Flag Note 1 text to help clarify cylindrical defect.

(8) FIGURE 6

(a) General - Revise title to add inspection for machining defect.

(b) Illustration - Add new illustration showing a typical machining defect.

(c) Step 3 - Add new step to inspect for the machining defect. Note that finish restoration is

not required if fitting is being overhauled.

(9) APPENDIX A - Revise logic diagram to add inspection for machining defect. This adds new

initial compliance time box for airplanes that accomplished Part 3 in accordance with the

original issue of this service bulletin. Revise title of Part 3 to add inspection for the machining

defect. Add Condition 8 and 9 which are the same as Condition 5 and 6 except with the

machining defect. Revise compliance time for fitting replacement for Condition 6 (wall thickness

0.130 or greater and less than 0.140 inch and machining defect is not present).

(10) APPENDIX B - Add new appendix with Spares survey.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

Original Issue: September 12, 2013

Revision 1: June 23, 2014

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-57A2343

Original Issue: September 12, 2013

Revision 1: June 23, 2014

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. Some of the actuator

assemblies inspected at Boeing also were found to have a machining defect at the point where the tapered

machining transitioned to the hemispherical machining at the top of the inner surface. This defect was visible

under the finishes. This defect could eventually lead to fatigue cracks and subsequent fracture.

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 or the machining defect.

Boeing Service Related Problem (SRP) 747-SRP-57-0264 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING

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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.

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 and Machining Defect 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. Do a DET

to determine if the machining defect is present on the inner wall. 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.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul

Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Overhaul the

Actuator attach fitting and remove the machining defect. Install the Actuator Attach Fitting. 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.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service bulletin.

The effective date of AD 2013-23-03 is November 29, 2013.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Revision

1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in Revision

1 of 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 and Machining Defect Inspection

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

Replacement

Part 5: Outboard Flap, Inboard Actuator Attach Fitting - 6.00 3.00

Overhaul

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Operators are encouraged to complete the survey provided in the Appendix of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-57A2343

Original Issue: September 12, 2013

Revision 1: June 23, 2014

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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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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ALERT ALERT
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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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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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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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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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. Some of the actuator assemblies inspected at

Boeing also were found to have a machining defect at the point where the tapered machining transitioned

to the hemispherical machining at the top of the inner surface. This defect was visible under the finishes.

This defect could eventually lead to fatigue cracks and subsequent fracture.

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 or the machining defect.

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.

Revision 1 is sent to:

1. Add an inspection for a machining defect that can reduce the durability of the fitting. During

inspection of the actuator fittings, many actuators were found to have a machining defect, visible

under the protective finishes, in the area where the tapered machining transitioned to the

hemispherical machining at the top of the inner surface.

2. Limit the compliance time that fitting assemblies with a wall thickness 0.130 inch or greater and

less than 0.140 inch and do not have a machining defect can remain in-service, to 48 months or

3,000 flight-cycles after the original issue date of this service bulletin, whichever occurs first.

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 and Machining Defect

Inspection

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ALERT ALERT
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. Do a DET to determine if the machining defect is present on the inner wall. 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.

Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul

Extend the trailing edge flaps to detent 30 and deactivate. Remove the Actuator Attach Fitting. Overhaul

the Actuator attach fitting and remove the machining defect. Install the Actuator Attach Fitting. Activate

and retract the trailing edge flaps.

Revision 1 - More work is required on airplanes with an actuator attach fitting 65B08564-7 installed

which accomplished PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM

THICKNESS INSPECTION in accordance with the Original Issue of this service bulletin. These airplanes

should do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM

THICKNESS AND MACHINING DEFECT INSPECTION to determine if the machining defect is present

and accomplish any required follow-on actions within the compliance time in Paragraph 1.E., Compliance.

The work in this service bulletin is done in the maintenance zone(s) given below.

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

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-23-03 is related to this service

bulletin. The effective date of AD 2013-23-03 is November 29, 2013.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

Revision 1 of this service bulletin. The Airworthiness Directive will make the compliance tasks and

times given in Revision 1 of this service bulletin mandatory.

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ALERT ALERT
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 effective date of

AD 2013-23-03

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

Within 24 months -

after the Revision 1

date of this service

bulletin

OPTION 9: Do PART 3: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH

FITTING - MINIMUM THICKNESS AND

MACHINING DEFECT INSPECTION, except only determine if the machining defect

is present

Airplanes with an Actuator Attach Fitting 65B08564-7 installed which accomplished

PART 3: OUTBOARD FLAP,

INBOARD ACTUATOR ATTACH FITTING - MINIMUM

THICKNESS INSPECTION in

accordance with the Original Issue of this service bulletin (c)

Within 24 months -

after the Revision 1

date of this service

bulletin

OPTION 10: Do PART 4: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH

FITTING - REPLACEMENT (Terminating

Action) (a)

No additional work required (Terminating - -

Action) (a)

CONDITION 1:

65B08564-7 ACTUATOR ATTACH FITTING IS NOT INSTALLED

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)

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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

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 AND

MACHINING DEFECT INSPECTION to

determine minimum wall thickness of the

Actuator Fitting Assembly and if the machining defect is present

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 AND

MACHINING DEFECT INSPECTION to

determine minimum wall thickness of the

Actuator Fitting Assembly and if the machining defect is present

CONDITION 4:

CYLINDRICAL DEFECT

FOUND

OPTION 6: Do PART 4: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH

FITTING - REPLACEMENT (Terminating

Action) (a)

No additional work required (Terminating - -

Action) (a)

CONDITION 5:

MINIMUM THICKNESS OF

WALL IS 0.140 INCH OR

GREATER AND MACHINING

DEFECT IS NOT PRESENT

OPTION 7: Do PART 5: OUTBOARD Before further flight

FLAP, INBOARD ACTUATOR ATTACH

FITTING - OVERHAUL (Terminating Action) (a)

CONDITION 8:

MINIMUM THICKNESS OF

WALL IS 0.140 INCH OR

GREATER AND MACHINING

DEFECT IS PRESENT OPTION 8: Do PART 4: OUTBOARD

FLAP, INBOARD ACTUATOR ATTACH

FITTING - REPLACEMENT (Terminating

Action) (a)

Within 48 months or -

3,000 flight-cycles

after the Original Issue date of this service bulletin,

whichever occurs

first. (a) (b)

Do PART 4: OUTBOARD FLAP, INBOARD

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 AND MACHINING

DEFECT IS NOT PRESENT

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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, INBOARD Before further flight

ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

CONDITION 9:

MINIMUM THICKNESS OF

WALL IS 0.130 INCH OR

GREATER AND LESS THAN

0.140 INCH AND MACHINING

DEFECT IS PRESENT

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

ACTUATOR ATTACH FITTING - REPLACEMENT (Terminating Action) (a)

CONDITION 7:

MINIMUM THICKNESS OF

WALL IS LESS THAN 0.130

INCH AND MACHINING DEFECT IS OR IS NOT PRESENT

(a) Repeat overhauls of the actuator attach fittings are still required in accordance with service bulletin 747-

57A2316.

(b) Compliance time for the attach fitting is the in-service time, and does not include storage time if an attach

fitting was new, used or was overhauled and subsequently stored. Refer to SOPM 20-44-02 and SOPM

20-70-01 as accepted procedures to prepare attach fittings for storage.

(c) This includes Actuator Attach Fittings that were installed that met the requirements of CONDITION 5 or

CONDITION 6 in the Original Issue of this service bulletin.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the inspection,

rework and replacement defined in this service bulletin, as an alternative method of compliance to the

inspection, rework and replacement requirements of paragraphs (g) and (h) of AD 2013-23-03. All

provisions of AD 2013-23-03 that are not specifically referenced in the above statement remain fully

applicable and must be complied with accordingly

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ALERT ALERT
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

• 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 Ball Screw Nut 2 2.00 1.00

Inspect

...Left Wing - FIGURE 1 1 0.50 0.50

...Right Wing - FIGURE 4 1 0.50 0.50

Connect Actuator Ball Screw Nut 2 2.00 1.00

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 Ball Screw Nut 2 2.00 1.00

Inspect

...Left Wing - FIGURE 2 1 0.50 0.50

...Right Wing - FIGURE 5 1 0.50 0.50

Connect Actuator Ball Screw Nut 2 2.00 1.00

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.50 2.00

TOTAL FOR EACH AIRPLANE 7.00 4.00

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

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

Remove the Actuator Attach Fitting 2 2.00 1.00

Inspect

...Left Wing - FIGURE 3 1 1.00 1.00

...Right Wing - FIGURE 6 1 1.00 1.00

Install the Actuator Attach Fitting 2 2.00 1.00

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 Attach Fitting 2 2.00 1.00

Install the Actuator Attach Fitting 2 2.00 1.00

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.00 1.50

TOTAL FOR EACH AIRPLANE 6.00 3.00

Part 5: Outboard Flap, Inboard Actuator Attach Fitting - Overhaul

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 1.00 0.50

Remove the Actuator Attach Fitting 2 2.00 1.00

Overhaul the Actuator (a) (a)

Install the Actuator Attach Fitting 2 2.00 1.00

Close Access 2 1.00 0.50

TOTAL FOR EACH WING 3.00 1.50

TOTAL FOR EACH AIRPLANE 6.00 3.00

(a) Time to overhaul actuator dependent upon condition found during inspection.

H. Weight and Balance Changes

None.

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ALERT ALERT
I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85901-129RS

b. Boeing Service Bulletin 747-57A2316

c. Boeing Service Related Problem (SRP) 747-SRP-57-0264

d. Component Maintenance Manual (CMM) 57-52-55

e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-23-03

f. Service Bulletin Index D6-30300

g. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-42-10, 20-44-02 , 20-50-01,

20-70-01

h. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

i. 747 Fleet Team Digest (FTD) 57-13003

j. 747 Non-Destructive Testing (NDT) Manual Part 4, 51-00-00

k. 747-100/200/300 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-41, 27-51-46

l. 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:

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ALERT ALERT
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.

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The parts are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Revision 1

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 1 date of

this Service Bulletin (Calendar

Days)

Part Number Name Date QTY

65B08564-9 FITTING ASSY Mar 03/14 25 169 $ 13,720.00

Mar 31/14 25

Apr 28/14 25

May 27/14 25

Jun23/14 20

Operators are encouraged to complete the survey provided in the Appendix of this service bulletin to

help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

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

Fleet Support Contracts - Warranty. 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 Fleet Support Contracts - Warranty. 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.

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ALERT ALERT
C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Part Number / Specification QTY Name Notes

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

65B08564-7 WHICH MEET CONDITION 5 OR

CONDITION 8 (AFTER OVERHAUL) IN THIS

SERVICE BULLETIN optional)

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

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

(a) A new Actuator Attach Fittings is only required if the installed 65B08564-7 Assemblies

do not meet Condition 5 or Condition 8 (after Overhaul) in this service bulletin.

(b) 65B08564-7 Actuator Attach Fittings sold by Boeing Spares after 17 June 2013 meet

Condition 3 requirements. These parts will need to accomplish Part 3: Outboard Flap,

Inboard Actuator Attach Fitting - Minimum Thickness and Machining Defect Inspection

and any required follow-on actions within the compliance time in Paragraph 1.E., Compliance, if installed. These actuators attach fittings are affected by this service bulletin if installed.

(c) 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.

(d) 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.

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ALERT ALERT
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

BLANK PAGE
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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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. Additional work required for airplanes with an actuator attach fitting 65B08564-7 installed which

accomplished PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - MINIMUM

THICKNESS INSPECTION in accordance with the Original Issue of this service bulletin. This

includes actuator fittings that were installed that met the requirements of CONDITION 5 or

CONDITION 6 in the Original Issue of this service bulletin.

a. OPTION 9: Do PART 3: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -

MINIMUM THICKNESS AND MACHINING DEFECT INSPECTION, except only determine if

the machining defect is present.

CONDITION 5: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND

MACHINING DEFECT IS NOT PRESENT

(1) No additional work required (Terminating Action).

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

CONDITION 8: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND

MACHINING DEFECT IS PRESENT

(1) OPTION 7: Do PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING

- OVERHAUL (Terminating Action).

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

(2) OPTION 8: 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 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS

THAN 0.140 INCH AND MACHINING DEFECT IS NOT PRESENT

(1) Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -

REPLACEMENT (Terminating Action).

NOTE: 1. Repeat overhaul is still required in accordance with service bulletin

747-57A2316.

2. Compliance time for the attach fitting is the in-service time, and does

not include storage time if an attach fitting was new, used or was

overhauled and subsequently stored. Refer to SOPM 20-44-02 and

SOPM 20-70-01 as accepted procedures to prepare attach fittings for

storage.

CONDITION 9: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS

THAN 0.140 INCH AND MACHINING DEFECT IS PRESENT

(1) Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -

REPLACEMENT (Terminating Action).

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ALERT ALERT
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

b. OPTION 10: 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.

2. 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 AND MACHINING DEFECT INSPECTION to determine minimum

wall thickness of the Actuator Fitting Assembly and if the machining defect is present

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 AND MACHINING DEFECT INSPECTION to determine minimum

wall thickness of the Actuator Fitting Assembly and if the machining defect is present

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 AND MACHINING

DEFECT IS NOT PRESENT

a. No additional work required (Terminating Action).

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ALERT ALERT
NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

CONDITION 8: MINIMUM THICKNESS OF WALL IS 0.140 INCH OR GREATER AND MACHINING

DEFECT IS PRESENT

a. OPTION 7: Do PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING -

OVERHAUL (Terminating Action).

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

b. OPTION 8: 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 6: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS

THAN 0.140 INCH AND MACHINING DEFECT IS NOT PRESENT

a. Do PART 4: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - REPLACEMENT

(Terminating Action).

NOTE: 1. Repeat overhaul is still required in accordance with service bulletin

747-57A2316.

2. Compliance time for the attach fitting is the in-service time, and does not

include storage time if an attach fitting was new, used or was overhauled

and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01

as accepted procedures to prepare attach fittings for storage.

CONDITION 9: MINIMUM THICKNESS OF WALL IS 0.130 INCH OR GREATER AND LESS

THAN 0.140 INCH AND MACHINING DEFECT IS PRESENT

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 AND MACHINING

DEFECT IS OR IS NOT PRESENT

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.

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ALERT ALERT
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.

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

AND MACHINING DEFECT 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.

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ALERT ALERT
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 and a DET of the inner conical section to determine if the machining defect

is present 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 a replacement Actuator Attach Fitting listed below. Refer to 747-100/200/300 AMM

27-51-46 or 747-400 AMM 27-51-46 as an accepted procedure.

a. Actuator Attach Fitting 65B08564-1, 65B08564-5, or 65B08564-9 (Terminating Action)

b. Actuator Attach Fitting 65B08564-7 Assembly which meets Condition 5 in Revision 1 of this

service bulletin (Terminating Action)

c. Actuator Attach Fitting 65B08564-7 Assembly which meets Condition 8 in which PART 5:

OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL has been

accomplished (Terminating Action)

d. Actuator attach fittings that meet the requirements of CONDITION 5 or CONDITION 6 in the

Original Issue of this service bulletin. These actuator attach fittings will require additional work.

These parts will need to accomplish Part 3: Outboard Flap, Inboard Actuator Attach Fitting -

Minimum Thickness and Machining Defect Inspection and any required actions within the

compliance times in Paragraph 1.E., Compliance.

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

A new Actuator Attach Fitting is being designed, 65B08564-9, 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.

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ALERT ALERT
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.

PART 5: OUTBOARD FLAP, INBOARD ACTUATOR ATTACH FITTING - OVERHAUL

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- Overhaul the Actuator attach fitting and remove the machining defect. Refer to the most recent

revision of CMM 57-52-55 as an accepted procedure.

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.

NOTE: Repeat overhaul is still required in accordance with service bulletin 747-57A2316.

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.

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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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45 of 68

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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48 of 68

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 constant diameter feature 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 AND

MACHINING DEFECT INSPECTION

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 747-57A2343

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

MACHINING DEFECT INSPECTION

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 747-57A2343

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

MACHINING DEFECT INSPECTION

(SHEET 3 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: September 12, 2013

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52 of 68

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

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

MACHINING DEFECT INSPECTION

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Step Task Name Identification Qty More Data

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

Do a DET of the inner surface of the fitting

assembly to determine if a machining defect

is present. There should be a smooth transition between the conical section and the

hemispherical section. A machining defect

is present when there is an obvious step,

mismatch, gouge, or irregularity that is

clearly visible under the protective finish in

this area. Finish removal is not required to

identify if any of these defects are present.

Actuator Attach Fit- - 1

ting

3 Inspect

(a) Required only if the actuator attach fitting is not being replaced or overhauled and the existing finish was

removed to accomplish the inspection.

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

MACHINING DEFECT INSPECTION

(SHEET 5 OF 5)

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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)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: September 12, 2013

Revision 1 June 23, 2014 747-57A2343

55 of 68

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)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

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57 of 68

BOEING SERVICE BULLETIN 747-57A2343

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

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: September 12, 2013

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58 of 68

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. The cylindrical defect, if

present, will be seen as a constant diameter feature 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 AND

MACHINING DEFECT INSPECTION

(SHEET 1 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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60 of 68

BOEING SERVICE BULLETIN 747-57A2343

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

MACHINING DEFECT INSPECTION

(SHEET 2 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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61 of 68

BOEING SERVICE BULLETIN 747-57A2343

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

MACHINING DEFECT INSPECTION

(SHEET 3 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: September 12, 2013

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62 of 68

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

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

MACHINING DEFECT INSPECTION

(SHEET 4 OF 5)

Export Controlled ECCN: 9E991 - BOEING

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63 of 68

BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
Step Task Name Identification Qty More Data

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

Do a DET of the inner surface of the fitting

assembly to determine if a machining defect

is present. There should be a smooth transition between the conical section and the

hemispherical section. A machining defect

is present when there is an obvious step,

mismatch, gouge, or irregularity that is

clearly visible under the protective finish in

this area. Finish removal is not required to

identify if any of these defects are present.

Actuator Attach Fit- - 1

ting

3 Inspect

(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 AND

MACHINING DEFECT INSPECTION

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
APPENDIX A: LOGIC DIAGRAM

(SHEET 1 OF 3)

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ALERT ALERT
APPENDIX A: LOGIC DIAGRAM

(SHEET 2 OF 3)

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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

Compliance time for the attach fitting is the in-service time, and does not

include storage time if an attach fitting was new, used or was overhauled

and subsequently stored. Refer to SOPM 20-44-02 and SOPM 20-70-01

as accepted procedures to prepare attach fittings for storage.

2

This includes actuator fittings that were installed that met the requirements

of CONDITION 5 or CONDITION 6 in the Original Issue of this service

bulletin.

3

APPENDIX A: LOGIC DIAGRAM

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT
APPENDIX B: INPUT SURVEY

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 747-57A2343

ALERT ALERT