Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Number: 747-57-2338

Original Issue: January 14, 2014

ATA System: 5740 2781

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Variable Camber

Flaps - Lightning Strike Applique Damage Inspection and Repair

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 © 2014 Boeing.

Unpublished Work. All Rights Reserved.

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BOEING SERVICE BULLETIN 747-57-2338

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 14

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

FIGURE 1: LEFT WING - VCK FLAP NUMBER 6 THROUGH 9 - INSPECTION . . . . . . . . . . . . 24

FIGURE 2: RIGHT WING - VCK FLAP NUMBER 18 THROUGH 21 - INSPECTION . . . . . . . . . . 26

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BOEING SERVICE BULLETIN 747-57-2338

BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Summary Number: 747-57-2338

Original Issue: January 14, 2014

ATA System: 5740 2781

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Variable Camber

Flaps - Lightning Strike Applique Damage Inspection and Repair

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of this service bulletin will ensure Leading Edge (LE) Variable Camber Krueger (VCK) flaps at

position 6 through 9 (Left Wing) and 18 through 21 (Right Wing) do not contain Lightning Strike Applique (LSA)

delamination damage. Excessive delamination damage can reduce the lightning strike protection capability on

VCK flaps. Loss of lightning strike protection could expose the Leading Edge Failure Indication (LEFI) system

electrical traces on the back side of the VCK flaps to direct lightning strike. Direct lightning strike to VCK flaps

with LSA damage could result in direct lightning attachment to the High Lift Flap Control Units (FCUs) and

potentially resulting in an uncommanded motion of the trailing edge flap system.

LSA is new on 747-8 airplanes and has been found to be prone to damage in-service. Six operators and Boeing

Manufacturing have reported damage to the LSA on the VCK flaps during ground inspections. The damage

included delamination of topcoat and metal foil layers from the underlying dielectric layer of the LSA. In some

cases the LSA damage was incorrectly identified as missing or peeling paint.

This service bulletin provides instructions to do a General Visual Inspection (GVI) of the VCK flaps at position

6 through 9 and 18 through 21 for delamination damage to LSA. If delamination damage is found, the service

bulletin provides repair and replacement options. No delamination damage will ensure the VCK flaps continue

to provide required protection from direct lightning strike.

This service bulletin is related to the LSA GVI task in Maintenance Review Board Report (MRB) 747-8 MRB

Item 20-503-01.

Boeing Fleet Team Digest (FTD) 747 FTD 27-11004 and 747 FTD 27-12005 are related to this service bulletin.

Boeing Service Related Problem (SRP) 747-SRP-27-0220 is related to this service bulletin.

Multi-Operator Message MOM-MOM-12-0530-01B for 747-8 LEFI VCK Exchange Program 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 No 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 86657-R)

PART 1: VCK FLAPS GENERAL VISUAL INSPECTION (GVI)

1. Do a GVI of VCK flaps for delamination damage of LSA.

PART 2: VCK FLAP REPAIR

1. Repair LSA delamination damage in accordance with 747-8F/-8P Structural Repair Manual.

PART 3: VCK FLAP REPLACEMENT

1. Replace VCK flap.

EFFECTIVITY

All 747-8 and 747-8F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

Refer to Paragraph 1.A.2., Spares Affected for the list of affected components.

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.

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BOEING SERVICE BULLETIN 747-57-2338
INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of August 22, 2012. Please refer to Paragraph

2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of

this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

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

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BOEING SERVICE BULLETIN 747-57-2338
Commercial 

Airplanes 747

Service Bulletin

SPECIAL ATTENTION

Number: 747-57-2338

Original Issue: January 14, 2014

ATA System: 5740 2781

SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge Variable Camber

Flaps - Lightning Strike Applique Damage Inspection and Repair

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below. Refer to PRR 86657-R for data about this

change.

Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

This service bulletin is for the airplane(s) shown below.

NOTE: This service bulletin is for the airplanes identified in the Group Configuration table. The

effectivity list shown below includes airplanes up to line number 1482. Some airplanes

before line number 1482 may be affected by this service bulletin but not included in the

effectivity list because they are being delivered out of sequence. At least one airplane,

either before or after line number 1482 or both, is affected by this service bulletin and

these airplanes are in Group(s) 1. These airplanes will be added to the service bulletin's

MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet

Profile Page.

GROUP CONFIGURATION DESCRIPTION

1 - All 747-8 and 747-8F airplanes line number 1420 and on.

Airplane Models:

747-8, 747-8F

Variable Number Group

RC001 - RC008 1

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Variable Number Group

RC021 - RC030 1

RC501 - RC509 1

RC521 - RC525 1

RC541 1

RC546 - RC547 1

RC551 - RC560 1

RC571 - RC572 1

RC574 - RC582 1

RC601 - RC605 1

2. Spares Affected

Examine your spares supply for the parts or components identified in the table below. If any parts

or components are found, refer to Paragraph 3.B., Work Instructions for the recommended action.

Part Number

114U4003-( )

114U4016-( )

654U6625-( )

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will ensure Leading Edge (LE) Variable Camber Krueger (VCK)

flaps at position 6 through 9 (Left Wing) and 18 through 21 (Right Wing) do not contain Lightning Strike

Applique (LSA) delamination damage. Excessive delamination damage can reduce the lightning strike

protection capability on VCK flaps. Loss of lightning strike protection could expose the Leading Edge

Failure Indication (LEFI) system electrical traces on the back side of the VCK flaps to direct lightning

strike. Direct lightning strike to VCK flaps with LSA damage could result in direct lightning attachment

to the High Lift Flap Control Units (FCUs) and potentially resulting in an uncommanded motion of the

trailing edge flap system.

LSA is new on 747-8 airplanes and has been found to be prone to damage in-service. Six operators

and Boeing Manufacturing have reported damage to the LSA on the VCK flaps during ground inspections.

The damage included delamination of topcoat and metal foil layers from the underlying dielectric layer

of the LSA. In some cases the LSA damage was incorrectly identified as missing or peeling paint.

This service bulletin provides instructions to do a General Visual Inspection (GVI) of the VCK flaps at

position 6 through 9 and 18 through 21 for delamination damage to LSA. If delamination damage is

found, the service bulletin provides repair and replacement options. No delamination damage will

ensure the VCK flaps continue to provide required protection from direct lightning strike.

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BOEING SERVICE BULLETIN 747-57-2338
This service bulletin is related to the LSA GVI task in Maintenance Review Board Report (MRB) 747-8

MRB Item 20-503-01.

Boeing Fleet Team Digest (FTD) 747 FTD 27-11004 and 747 FTD 27-12005 are related to this service

bulletin.

Boeing Service Related Problem (SRP) 747-SRP-27-0220 is related to this service bulletin.

Multi-Operator Message MOM-MOM-12-0530-01B for 747-8 LEFI VCK Exchange Program is related

to this service bulletin.

D. Description

PART 1: VCK FLAPS GENERAL VISUAL INSPECTION (GVI)

1. Do a GVI of VCK flaps for delamination damage of LSA.

PART 2: VCK FLAP REPAIR

1. Repair LSA delamination damage in accordance with 747-8F/-8P Structural Repair Manual.

PART 3: VCK FLAP REPLACEMENT

1. Replace VCK flap.

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

Affected Maintenance Zones

Model Zone

747-8, 747-8F 523, 524, 525, 526, 623, 624, 625, 626

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.

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.

The Conditions, Actions, and Compliance Times shown apply to each Variable Camber Krueger (VCK)

Flap independently.

Do the actions in accordance with Paragraph 3. Accomplishment Instructions.

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BOEING SERVICE BULLETIN 747-57-2338
Table 1: Inspection and Repair of VCK Flap Assembly for Lightning Strike Applique Damage

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

Original Issue

date of this service bulletin.

Before 6000 total airplane flight

hours.

Do PART 1: VCK FLAPS

GENERAL VISUAL INSPECTION (GVI) for delamination damage of

LSA.

All Airplanes

Repeat PART 1: VCK - - 6000 flight hours

FLAPS GENERAL VISUAL INSPECTION (GVI)

for delamination damage

of LSA.

CONDITION 1: NO LSA

DELAMINATION DAMAGE

IS FOUND.

Before further - -

flight.

OPTION 1 (ACTION 1):

Do PART 2: VCK FLAP

REPAIR.

CONDITION 2: ANY LSA

DELAMINATION DAMAGE

IS FOUND.

OPTION 1 (ACTION 2): - - 6000 flight hours

Repeat PART 1: VCK

FLAPS GENERAL VISUAL INSPECTION (GVI)

for delamination damage

of LSA.

Before further - -

flight.

OPTION 2 (ACTION 1):

Do PART 3: VCK FLAP

REPLACEMENT.

OPTION 2 (ACTION 2): - - 6000 flight hours

Repeat PART 1: VCK

FLAPS GENERAL VISUAL INSPECTION (GVI)

for delamination damage

of LSA.

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.

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BOEING SERVICE BULLETIN 747-57-2338
G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection and repair 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: VCK FLAPS GENERAL VISUAL INSPECTION (GVI)

Task Number of Persons Task Hours Elapsed Hours

Inspect

...FIGURE 1: Left 2 3.60 1.80

Wing - Flap 6, 7,

8,and 9

...FIGURE 2: Right 2 3.60 1.80

Wing - Flap 18,

19,20, and 21

TOTAL FOR EACH AIRPLANE 7.20 3.60

PART 2: VCK FLAP REPAIR

Task Number of Persons Task Hours Elapsed Hours

Repair - (a) (a)

TOTAL FOR EACH AIRPLANE

(a) Total time dependent upon the total amount of delamination damage found.

PART 3: VCK FLAP REPLACEMENT

Task Number of Persons Task Hours Elapsed Hours

Replace - (a) (a)

TOTAL FOR EACH AIRPLANE

(a) Total time dependent upon total VCK flap assemblies that are replaced.

H. Weight and Balance Changes

None.

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BOEING SERVICE BULLETIN 747-57-2338
I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 86657-R

b. Boeing Service Related Problem (SRP) 747-SRP-27-0220

c. Service Bulletin Index D6-30300

d. Multi-Operator Message (MOM) Message Number MOM-MOM-12-0530-01B

e. 747 Fleet Team Digest (FTD) 27-11004, 27-12005

f. 747-8 Aircraft Maintenance Manual (AMM) 05-55-21, 27-81-02

g. 747-8 Maintenance Review Board Report (MRB)

h. 747-8F Structural Repair Manual (SRM) 57-43-02

i. 747-8P Structural Repair Manual (SRM) 57-43-02

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

114U4010 Variable Camber Flap Installation - Midspan, Wing Leading Edge

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

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BOEING SERVICE BULLETIN 747-57-2338
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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BOEING SERVICE BULLETIN 747-57-2338

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, and Paragraph

2.D., Parts Necessary to Change Spares. 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 original issue date of this

Service Bulletin

(US Dollars)

ROLT as of the

original issue

date of this Service Bulletin

(Calendar Days)

Part Number Name Date QTY

April 2, 10 98 12.00

2013

LSA - VCK, REPAIR

PATCH

478R1BT11S1HTHG7084

(a)

LSA - VCK, REPAIR 10

PATCH

478R2BT11S1HTHG7084

(a)

LSA - VCK, REPAIR 33

PATCH

478R3BT11S1HTHG7084

(a)

LSA - VCK, REPAIR 10 9.00

PATCH

478R4BT11S1HTHG7084

(a)

LSA - VCK FLAP DI- 10

ELECTRIC LAYER 1

478V5BRT14S1P (a)

LSA - VCK FLAP DI- 10

ELECTRIC LAYER 2

478V6BRT14S1P (a)

LSA - VCK FLAP DI- 20

ELECTRIC LAYER 3

478V7BRT14S1P (a)

LSA - VCK FLAP DI- 20

ELECTRIC LAYER 4

478V8BRT14S1P (a)

(a) Parts only required when accomplishing LSA Permanent Repair procedure in accordance with 747-8F

SRM 57-43-02 or 747-8P SRM 57-43-02.

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BOEING SERVICE BULLETIN 747-57-2338
B. Industry Support Information

Boeing warranty remedies are available for 747 airplanes in warranty as of August 22, 2012. For task

hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Warranty

& Product Assurance Contracts. The parts for airplanes in warranty as of that date will be supplied at

no charge. Send a purchase order for the parts to Boeing Material Management. 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

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.

QTY Name Notes

(a)

Part Number / Specification

478R1BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH

478R2BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH

478R3BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH

478R4BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH

LSA - VCK FLAP DIELECTRIC

LAYER 1

478V5BRT14S1P 1

LSA - VCK FLAP DIELECTRIC

LAYER 2

478V6BRT14S1P 1

LSA - VCK FLAP DIELECTRIC

LAYER 3

478V7BRT14S1P 1

LSA - VCK FLAP DIELECTRIC

LAYER 4

478V8BRT14S1P 1

(a) Quantity is an estimate for LSA Permanent Repair. More or less required parts will be dependent on the results of the inspection in Paragraph 3.B., Work Instructions and the repair

type described in 747-8F SRM 57-43-02 or 747-8P SRM 57-43-02.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

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D. Parts Necessary to Change Spares

To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

QTY

(a)

Part Number Name

478R1BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1

478R2BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1

478R3BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1

478R4BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1

LSA - VCK FLAP DIELECTRIC 1

LAYER 1

478V5BRT14S1P

LSA - VCK FLAP DIELECTRIC 1

LAYER 2

478V6BRT14S1P

LSA - VCK FLAP DIELECTRIC 1

LAYER 3

478V7BRT14S1P

LSA - VCK FLAP DIELECTRIC 1

LAYER 4

478V8BRT14S1P

(a) Quantity is an estimate for LSA Permanent Repair. More or less required parts will be dependent on the results of the inspection in

Paragraph 3.B., Work Instructions and the repair type described in

747-8F SRM 57-43-02 or 747-8P SRM 57-43-02.

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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BOEING SERVICE BULLETIN 747-57-2338

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 747-8F/-8P Structural Repair

Manual, Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 747-8

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 747-8

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

4. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

5. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

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BOEING SERVICE BULLETIN 747-57-2338
6. 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.

7. 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.

8. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

9. 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.

10. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

11. The CONDITIONS, ACTIONS and OPTIONS shown apply to each Variable Camber

Krueger (VCK) Flap independently.

B. WORK INSTRUCTIONS

1. Do PART 1: VCK FLAPS GENERAL VISUAL INSPECTION (GVI) for delamination damage of

LSA.

CONDITION 1: NO LSA DELAMINATION DAMAGE IS FOUND.

a. Repeat PART 1: VCK FLAPS GENERAL VISUAL INSPECTION (GVI) for delamination damage

of LSA.

CONDITION 2: ANY LSA DELAMINATION DAMAGE IS FOUND.

a. OPTION 1:

(1) OPTION 1 (ACTION 1): Do PART 2: VCK FLAP REPAIR.

(2) OPTION 1 (ACTION 2): Repeat PART 1: VCK FLAPS GENERAL VISUAL INSPECTION

(GVI) for delamination damage of LSA.

b. OPTION 2:

(1) OPTION 2 (ACTION 1): Do PART 3: VCK FLAP REPLACEMENT.

(2) OPTION 2 (ACTION 2): Repeat PART 1: VCK FLAPS GENERAL VISUAL INSPECTION

(GVI) for delamination damage of LSA.

2. Put the airplane back to a serviceable condition.

PART 1: VCK FLAPS GENERAL VISUAL INSPECTION (GVI)

1. Do a GVI of the VCK flaps for LSA delamination damage in accordance with the figures below:

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BOEING SERVICE BULLETIN 747-57-2338
Left Wing Right Wing

Flap No. 6, 7, 8, and 9 Flap No. 18, 19, 20, and 21

FIGURE 1 FIGURE 2

PART 2: VCK FLAP REPAIR

1. Evaluate any LSA delamination damage found in accordance with 747-8F SRM 57-43-02 or 747-8P

SRM 57-43-02.

2. Do the required actions, based on the LSA delamination damage found, in accordance with 747-8F

SRM 57-43-02 or 747-8P SRM 57-43-02.

PART 3: VCK FLAP REPLACEMENT

1. Replace VCK flap assembly. Refer to 747-8 AMM 27-81-02 as an accepted procedure.

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FIGURE 1: LEFT WING - VCK FLAP NUMBER 6 THROUGH 9 - INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2338
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 the left wing.

Step Task Name Identification Qty More Data

Do a general visual

inspection for delamination damage of

the LSA. Refer to

747-8 AMM 05-55-

21 as an accepted

procedure.

1 Inspect VCK FLAP ASSEMBLY - 4

FIGURE 1: LEFT WING - VCK FLAP NUMBER 6 THROUGH 9 - INSPECTION

(SHEET 2 OF 2)

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FIGURE 2: RIGHT WING - VCK FLAP NUMBER 18 THROUGH 21 - INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 747-57-2338
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 the right wing.

Step Task Name Identification Qty More Data

Do a general visual

inspection for delamination damage of

the LSA. Refer to

747-8 AMM 05-55-

21 as an accepted

procedure.

1 Inspect VCK FLAP ASSEMBLY - 4

FIGURE 2: RIGHT WING - VCK FLAP NUMBER 18 THROUGH 21 - INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 747-57-2338