### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: January 14, 2014 747-57-2338 1 of 27 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 2 of 27 **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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 3 of 27 **BOEING SERVICE BULLETIN 747-57-2338**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 4 of 27 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 5 of 27**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected Yes Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts No Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required

**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 6 of 27 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 7 of 27 **BOEING SERVICE BULLETIN 747-57-2338**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 8 of 27 **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.
**DESCRIPTION CONFIGURATION**  **GROUP** All 747-8 and 747-8F airplanes line number 1420 and on.

- 1

Airplane Models: 747-8, 747-8F **Group Variable Number**  1 RC001 - RC008

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 9 of 27**Group Variable Number**  1 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 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 10 of 27 **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 Zone**  **Model** 523, 524, 525, 526, 623, 624, 625, 626 747-8, 747-8F **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 11 of 27 **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)**  **Action Condition** 

- Within 12 months after the Original Issuedate of this service bulletin.Before 6000 total airplane flight hours. Do PART 1: VCK FLAPSGENERAL VISUAL INSPECTION (GVI) for delamination damage of LSA. All Airplanes

6000 flight hours

- - Repeat PART 1: VCKFLAPS 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. 6000 flight hours

- - OPTION 1 (ACTION 2): Repeat PART 1: VCKFLAPS GENERAL VISUAL INSPECTION (GVI) for delamination damage of LSA.

- - Before further flight. OPTION 2 (ACTION 1): Do PART 3: VCK FLAP REPLACEMENT. 6000 flight hours

- - OPTION 2 (ACTION 2): Repeat PART 1: VCKFLAPS 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 12 of 27 **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) Elapsed Hours**  **Task Hours Number of Persons**  **Task** Inspect 1.80 3.60 2 ...FIGURE 1: Left Wing - Flap 6, 7, 8,and 9 1.80 3.60 2 ...FIGURE 2: Right Wing - Flap 18, 19,20, and 21 3.60 7.20 TOTAL FOR EACH AIRPLANE
**PART 2: VCK FLAP REPAIR Elapsed Hours**  **Task Hours Number of Persons**  **Task** (a) (a)

- Repair TOTAL FOR EACH AIRPLANE (a) Total time dependent upon the total amount of delamination damage found.
**PART 3: VCK FLAP REPLACEMENT Elapsed Hours**  **Task Hours Number of Persons**  **Task** (a) (a)

- Replace TOTAL FOR EACH AIRPLANE (a) Total time dependent upon total VCK flap assemblies that are replaced. **H. Weight and Balance Changes** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 13 of 27 **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:
**Title Drawing Number**  Variable Camber Flap Installation - Midspan, Wing Leading Edge 114U4010 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 14 of 27 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 15 of 27 **BOEING SERVICE BULLETIN 747-57-2338**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 16 of 27 **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 is**  **sue date of this Service Bulletin** 

**(US Dollars) ROLT as of the**  **original issue date of this Ser** 

**vice Bulletin (Calendar Days)**  **QTY Date**  **Name Part Number** 

12.00 98 10 April 2, 2013 LSA - VCK, REPAIR PATCH 478R1BT11S1HTHG7084 (a) 10 LSA - VCK, REPAIR PATCH 478R2BT11S1HTHG7084 (a) 33 LSA - VCK, REPAIR PATCH 478R3BT11S1HTHG7084 (a) 9.00 10 LSA - VCK, REPAIR PATCH 478R4BT11S1HTHG7084 (a) 10 LSA - VCK FLAP DI- ELECTRIC LAYER 1 478V5BRT14S1P (a)

10 LSA - VCK FLAP DI- ELECTRIC LAYER 2 478V6BRT14S1P (a)

20 LSA - VCK FLAP DI- ELECTRIC LAYER 3 478V7BRT14S1P (a)

20 LSA - VCK FLAP DI- 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 17 of 27 **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.
**Notes Name**  **QTY**

**(a) Part Number / Specifica**  **tion** LSA - VCK, REPAIR PATCH 1 478R1BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1 478R2BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1 478R3BT11S1HTHG7084 LSA - VCK, REPAIR PATCH 1 478R4BT11S1HTHG7084 LSA - VCK FLAP DIELECTRIC LAYER 1 1 478V5BRT14S1P
LSA - VCK FLAP DIELECTRIC LAYER 2 1 478V6BRT14S1P
LSA - VCK FLAP DIELECTRIC LAYER 3 1 478V7BRT14S1P
LSA - VCK FLAP DIELECTRIC LAYER 4 1 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.
3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 18 of 27 **BOEING SERVICE BULLETIN 747-57-2338 D. Parts Necessary to Change Spares**  To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
**QTY (a)**  **Name Part Number** 

1 LSA - VCK, REPAIR PATCH 478R1BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH 478R2BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH 478R3BT11S1HTHG7084 1 LSA - VCK, REPAIR PATCH 478R4BT11S1HTHG7084 1 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(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 19 of 27 **BOEING SERVICE BULLETIN 747-57-2338**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 20 of 27 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 21 of 27 **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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 22 of 27 **BOEING SERVICE BULLETIN 747-57-2338 Right Wing**  **Left Wing Flap No. 18, 19, 20, and 21**  **Flap No. 6, 7, 8, and 9** FIGURE 2 FIGURE 1
**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 23 of 27 **BOEING SERVICE BULLETIN 747-57-2338 FIGURE 1: LEFT WING - VCK FLAP NUMBER 6 THROUGH 9 - INSPECTION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 24 of 27 **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.
**More Data Qty**  **Identification Name**  **Task Step**  Do a general visualinspection for delamination damage of the LSA. Refer to 747-8 AMM 05-55- 21 as an accepted procedure. 4

- VCK FLAP ASSEMBLY Inspect 1

**FIGURE 1: LEFT WING - VCK FLAP NUMBER 6 THROUGH 9 - INSPECTION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 25 of 27 **BOEING SERVICE BULLETIN 747-57-2338 FIGURE 2: RIGHT WING - VCK FLAP NUMBER 18 THROUGH 21 - INSPECTION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 26 of 27 **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.
**More Data Qty**  **Identification Name**  **Task Step**  Do a general visualinspection for delamination damage of the LSA. Refer to 747-8 AMM 05-55- 21 as an accepted procedure. 4

- VCK FLAP ASSEMBLY Inspect 1

**FIGURE 2: RIGHT WING - VCK FLAP NUMBER 18 THROUGH 21 - INSPECTION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: January 14, 2014 747-57-2338 27 of 27 **BOEING SERVICE BULLETIN 747-57-2338**