# Airbus Mandatory Service Bulletin A340-55-4035 Copy: No revision named ("A340-55-4035 R01"), 80 pages: PDF https://openairdocs.org/files/sha256/66/df/66df9d79288d583032cd84dbbee38a6c480ff214ca10a62aa069fabc44584e1e; text https://openairdocs.org/service-documents/airbus/a340-55-4035/file/66df9d79288d.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0712, the docket of AD 2020-04-10. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md) - Type: Service bulletin (Mandatory Service Bulletin) - Number: A340-55-4035 - Page: https://openairdocs.org/service-documents/airbus/a340-55-4035 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2011-03-10](https://openairdocs.org/ad/2011-03-10.md), effective Mar 14, 2011: No revision named Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a340-55-4035/proposed.md). ## Text (80 pages) Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0712, the docket of AD 2020-04-10. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 TITLE: STABILIZERS - ELEVATORS - INSPECTION OF ELEVATOR UPPER AND LOWER SKIN PANELS FOR LIQUID INGRESS MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A340-55-4035 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 01 issued to add aircraft for operators ABB and GJL, new configuration due to MOD No. 56519C10665 and clarifications in the Accomplishment Instructions. CHANGES The main changes of this revision are: - Addition of new aircraft in EFFECTIVITY paragraph - Updation of EFFECTIVITY - Creation of Config. 003 due to technical definition change - Updation of references in ACCOMP LISHMENT INSTRUCTIONS paragraph - Creation of new Fig. A-SFAAA and Fig. A-SFAAB. NOTE : Revised text and layout changes of this revision are not identified with revision bars. FRONT MATTER STABILIZERS - ELEVATORS - INSPECTION OF ELEVATOR UPPER AND LOWER SKIN PANELS FOR LIQUID INGRESS CONFIGURATION UPDATED R DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 1 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 2 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET SUMMARY GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE ADDED N EFFECTIVITY OPERATOR LIST UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R MANPOWER MANPOWER ADDED N PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONFIGURATION LIST UPDATED R CONF 001 CONFIGURATION DEFINITION UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED R CONF 003 CONFIGURATION ADDED N DESCRIPTION DESCRIPTION UPDATED R COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE ADDED N MANPOWER MANPOWER ADDED N REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION ADDED N PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R MATERIAL INFORMATION TOOLING Tools Standard tool TOOLC01 TOOL MATERIAL SET UPDATED QUANTITY UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 554035- 832-942-001-Inspection TASK SOLUTION UPDATED R Task associated data - 003 TASK ASSOCIATED DATA ADDED N Subtask 554035-910-601-001 SUBTASK SOLUTION UPDATED R Subtask 554035-839-601-001 SUBTASK SOLUTION UPDATED R Subtask 554035-910-601-001 SUBTASK SOLUTION UPDATED R Subtask 554035-839-601-001 SUBTASK SOLUTION UPDATED R Subtask 554035-910-601-002 SUBTASK SOLUTION ADDED N Subtask 554035-839-601-001 SUBTASK SOLUTION ADDED N Subtask 554035-941-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 2 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 3 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 554035-941-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 554035-941-601-002 SUBTASK SOLUTION ADDED N Subtask 554035-832-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED REFERENCES UPDATED R Subtask 554035-832-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED REFERENCES UPDATED R Subtask 554035-832-601-002 SUBTASK SOLUTION ADDED N TASK 554035- 833-942-001-Repair TASK SOLUTION UPDATED R Task associated data - 003 TASK ASSOCIATED DATA ADDED N Subtask 554035-910-602-001 SUBTASK SOLUTION UPDATED R Subtask 554035-839-602-001 SUBTASK SOLUTION UPDATED R Subtask 554035-910-602-001 SUBTASK SOLUTION UPDATED R Subtask 554035-839-602-001 SUBTASK SOLUTION UPDATED R Subtask 554035-910-602-002 SUBTASK SOLUTION ADDED N Subtask 554035-839-602-001 SUBTASK SOLUTION ADDED N Subtask 554035-941-602-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 554035-941-602-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 554035-941-602-002 SUBTASK SOLUTION ADDED N Subtask 554035-833-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED CAUTION UPDATED REFERENCES UPDATED FIGURE REFERENCE UPDATED R Subtask 554035-833-601-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED NOTE UPDATED CAUTION UPDATED REFERENCES UPDATED FIGURE REFERENCE UPDATED R Subtask 554035-833-601-002 SUBTASK SOLUTION ADDED N Subtask 554035-700-603-002 SUBTASK SOLUTION ADDED N DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 3 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 4 @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Subtask 554035-942-602-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 554035-942-602-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R Subtask 554035-942-602-002 SUBTASK SOLUTION ADDED N Fig. A-SBA FIGURE DELETED FOR APPLICABLE MSN D Fig. A-SBDAA FIGURE SOLUTION UPDATED CONFIGURATION UPDATED R Fig. A-SBDAA Sheet 01 SHEET UPDATED R Fig. A-SBDAB FIGURE SOLUTION ADDED N Fig. A-SBDAB Sheet 01 SHEET ADDED N Fig. A-SFAAA FIGURE SOLUTION ADDED N Fig. A-SFAAA Sheet 01 SHEET ADDED N Fig. A-SFAAB FIGURE SOLUTION ADDED N Fig. A-SFAAB Sheet 01 SHEET ADDED N APPENDIX 1 - INSPECTION REPORT Fig. A-SAAAA Fig. A-SAAAA Sheet 01 SHEET UPDATED R FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Aug 07/09 REVISION No. : 01 - Feb 15/19 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 4 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 5 @A340 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 This summary is for information only and is not approved for modification of the aircraft. MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 TITLE: STABILIZERS - ELEVATORS - INSPECTION OF ELEVATOR UPPER AND LOWER SKIN PANELS FOR LIQUID INGRESS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES End 2003 Service Bulletin A340-55-4029 was launched for one time inspection of the elevator skin panels installed on A340 MSNs up to 0091, to detect potential liquid ingress and repair as necessary. This Service Bulletin was mandated by the Airworthiness Directive (AD) F-2004-118 R1 Further in-service experience has shown that in order to ensure the structural integrity of the aircraft elevator skin panels with sandwich construction, it is necessary to perform a repetitive thermographic inspection. Liquid ingress could cause de-bonding in the adhesive joint between the honeycomb core and CFRP laminates. If not detected, damage on the elevator could require extensive and complex repairs. Therefore, in case of liquid indications, it will be necessary to perform a tap test inspection on and around that point to detect debonded areas. Furthermore, any panel honeycomb core area in which liquid ingress has been detected must be considered as damaged. Damage and repair evaluation are to be performed in accordance with the SRM guidelines. Any damage found beyond the allowable damage limits will have to be reported to Airbus for analysis and further repair instructions, which must be accomplished before next elevator flight. In Addition, it is mandatory to perform a reprotection as described in this Service Bulletin to prevent liquid accumulation. Accomplishment of this Service Bulletin will address possible damage caused by liquid inside the elevator and will minimize the risk of further damage from occurring in the future. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 1 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 6 @A340 SERVICE BULLETIN SUMMARY GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO LROPS AFFECTED NO STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO NOTE (1) : Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLC01 1 See SB Pin, tap test tool **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLC01 1 See SB Pin, tap test tool **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Standard tool TOOLC01 1 See SB Pin, tap test tool EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) : 01V 14S 15R 17M 26L 31V 36L 39N 41N 65W 68M 74W 78U 83V 98W ABB ABD AFR AIB ALD ARG AXY BEL BOE CAL D2F DGA DLH EDW F2I GAF HFM HFY IRC IRM KAC KMF M3R MAU MDG MRJ PAL PUE QQE ROI S3R SAA SAS SFB SLM SWR SYR TAP THT THY U6A VCV CONCURRENT REQUIREMENTS None DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 2 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 7 @A340 SERVICE BULLETIN SUMMARY REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None ISI None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER OIT 999.0013/09 NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 554035-832-942-001: Inspection TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 Task 554035-833-942-001: Repair TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF 002 Task 554035-832-942-001: Inspection TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 Task 554035-833-942-001: Repair TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF 003 Task 554035-832-942-001 : Inspection TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 Task 554035-833-942-001 : Repair TOTAL MANHOURS 24.00 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 3 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 8 @A340 SERVICE BULLETIN SUMMARY Task 554035-833-942-001 : Repair ELAPSED TIME (HOURS) 12.00 APPENDICES **CONF ALL APPENDIX 1 - INSPECTION REPORT DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 4 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 9 @A340 SERVICE BULLETIN SUMMARY **CONF ALL AREA TO BE INSPECTED UPPER AND LOWER AREA STATIC DISCHARGER DRAINAGE HOLES (LOWER SKIN) LH SHOWN RH SYMMETRICALINSPECTION AREA Z335 Z345 FRONT SPAR HOLE COVERS INSTALLATION F_SB_554035_0_SAAA_01_00 AA A Figure A-SSAAA - Sheet 01 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 5 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 10 @A340 SERVICE BULLETIN SUMMARY This Page Intentionally Left Blank DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 6 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 11 @A340 SERVICE BULLETIN AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE T e l:( 3 3 )56 19 33 33 3 Telex : AIRBU 530526F F a x:( 3 3 )56 19 34 25 1 MANDATORY MANDATORY MANDATORY ATA SYSTEM: 55 TITLE: STABILIZERS - ELEVATORS - INSPECTION OF ELEVATOR UPPER AND LOWER SKIN PANELS FOR LIQUID INGRESS MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY (1) Models 340-211 340-212 340-213 340-311 340-312 340-313 (2) Effectivity by MSN 0002 0004 0009 0014 0020 0022 0026 0029 0031 0038 0041 0043-0044 0046-0047 0051 0056 0058 0061 0063 0074-0076 0078-0081 0084 0089-0091 0093-0094 0101 0104 0115 0117 0123 0125-0126 0128 0134-0135 0145-0146 0151-0152 0156 0158-0159 0163-0164 0166-0168 0170 0174-0175 0178-0180 0185-0186 0190 0192-0194 0197 0199 0201-0202 0204 0207-0208 0210 0212-0213 0215 0217 0221 0233 0236-0237 0242-0243 0245-0246 0252 0257 0260 0264 0268 0270 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0367 0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415 0424 0430 0433-0435 0438 0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546 0554 0556 0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 0835 0844 0921 0938 0955 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 1 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 12 @A340 SERVICE BULLETIN (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN 01V 0146 14S 0058 0152 15R 0151 17M 0955 26L 0125 0134 0145 0217 0221 0329 31V 0093 36L 0406 39N 0168 0174 41N 0009 65W 0029 0208 68M 0078 74W 0047 0051 78U 0175 0179 83V 0280 98W 0014 0022 ABB 0835 0844 0921 0938 ABD 0210 AFR 0186 0207 0245 0246 0260 0377 AIB 0192 0243 0264 ALD 0156 0159 0178 ARG 0063 0074 0080 0123 0126 0170 0193 AXY 0374 BEL 0335 0354 BOE 0554 CAL 0402 0411 0415 0433 0541 D2F 0128 DGA 0075 0081 DLH 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0347 0352 0379 0390 0434 0447 EDW 0556 0559 0561 0562 F2I 0038 0043 0084 0094 0117 0237 0307 0310 GAF 0274 0355 HFM 0163 0166 0185 0236 0367 0483 HFY 0190 0202 IRC 0002 IRM 0020 0056 0164 0282 0292 KAC 0089 0090 0101 0104 KMF 0278 0318 0387 M3R 0061 MAU 0076 0194 0268 0793 0800 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 2 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 13 @A340 SERVICE BULLETIN OPERATOR MSN MDG 0319 MRJ 0257 PAL 0302 0332 0474 PUE 0212 0215 0399 0459 QQE 0026 0528 ROI 0199 0201 S3R 0004 0204 SAA 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0167 0413 0424 0430 0435 0450 0467 0470 SFB 0046 SLM 0242 SWR 0538 0545 0546 0585 0598 SYR 0381 TAP 0041 0044 0079 0091 THT 0385 0395 0438 0446 0668 THY 0115 0180 0270 0331 U6A 0373 VCV 0031 (4) Configuration by MSN MSN CONFIGURATION 0002 0004 0009 0014 0020 0022 0026 0029 0031 0038 0041 0043 0044 0046 0047 0051 0056 0058 0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0089 0090 0091 001 0093 0094 0101 0104 0115 0117 0123 0125 0126 0128 0134 0135 0145 0146 0151 0152 0156 0158 0159 0163 0164 0166 0167 0168 0170 0174 0175 0178 0179 0180 0185 0186 0190 0192 0193 0194 0197 0199 0201 0202 0204 0207 0208 0210 0212 0213 0215 0217 0221 0233 0236 0237 0242 0243 0245 0246 0252 0257 0260 0264 0268 0270 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335 0347 0352 0354 0355 0367 0373 0374 0377 0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0415 0424 0430 0433 0434 0435 0438 0446 0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544 0545 0546 0554 0556 0559 0561 0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800 0835 0844 002 0921 0938 0955 003 (5) Configuration definition **CONF 001 Config. 001 is applicable to all the aircraft which have accomplished the Service Bulletin A340-55-4029 and have the Elevator S/N in the list that follows: - LH Elevator S/N: CG1002-CG1091 CG1093 CG1094 CG2001 - RH Elevator S/N: CG1002-CG1094 CG2001 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 3 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 14 @A340 SERVICE BULLETIN **CONF 002 Config. 002 is applicable to all the aircraft which have not accomplished the Service Bulletin A340-55-4029 and do not have the Elevator S/N in the list that follows: - LH Elevator S/N: CG1002-CG1091 CG1093 CG1094 CG2001 - RH Elevator S/N: CG1002-CG1094 CG2001 **CONF 003 Config. 003 is valid for all aircraft on which MOD No. 56519C10665 is embodied, the Service Bulletin A340-55-4029 is not accomplished and do not have the Elevator S/N in the list that follows: - LH Elevator S/N: CG1002-CG1091 CG1093 CG1094 CG2001 - RH Elevator S/N: CG1002-CG1094 CG2001 NOTE : This Service Bulletin is applicable to all aircraft serial numbers (MSNs) fitted with all serial numbers of elevators P /Ns, which first twelve digits are the following: - LH Elevator: F55280000000 or F55280000002 or F55280000004 or F55280000006 or F55280000008 or F55280000012 or F55280002000 or F55280005000 or F55280005002 or F55280005004. - RH Elevator: F55280000001 or F55280000003 or F55280000005 or F55280000007 or F55280000009 or F55280000013 or F55280002001 or F55280005001 or F55280005003 or F55280005005. NOTE : In the case of an elevator originally fitted on one aircraft (refer to AIR delivery document) that has been removed and installed on another aircraft, it is the responsibility of the operator to apply the required instructions contained in this SB to the new aircraft. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLC01 As required Standard tool TOOLC01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History End 2003 Service Bulletin A340-55-4029 was launched for one time inspection of the elevator skin panels installed on A340 MSNs up to 0091, to detect potential liquid ingress and repair as necessary. This Service Bulletin was mandated by the Airworthiness Directive (AD) F-2004-118 R1 Further in-service experience has shown that in order to ensure the structural integrity of the aircraft elevator skin panels with sandwich construction, it is necessary to perform a repetitive thermographic inspection. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 4 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 15 @A340 SERVICE BULLETIN (2) Objective/Action Liquid ingress could cause de-bonding in the adhesive joint between the honeycomb core and CFRP laminates. If not detected, damage on the elevator could require extensive and complex repairs. Therefore, in case of liquid indications, it will be necessary to perform a tap test inspection on and around that point to detect debonded areas. Furthermore, any panel honeycomb core area in which liquid ingress has been detected must be considered as damaged. Damage and repair evaluation are to be performed in accordance with the SRM guidelines. Any damage found beyond the allowable damage limits will have to be reported to Airbus for analysis and further repair instructions, which must be accomplished before next elevator flight. In Addition, it is mandatory to perform a reprotection as described in this Service Bulletin to prevent liquid accumulation. (3) Advantages Accomplishment of this Service Bulletin will address possible damage caused by liquid inside the elevator and will minimize the risk of further damage from occurring in the future. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 554035-832-942-001: Inspection (1) Inspection Task 554035-833-942-001: Repair (1) Repair **CONF 002 Task 554035-832-942-001: Inspection (1) Inspection Task 554035-833-942-001: Repair (1) Repair DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 5 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 16 @A340 SERVICE BULLETIN **CONF 003 Task 554035-832-942-001 : Inspection (1) Inspection Task 554035-833-942-001 : Repair (1) Repair **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. Elevators inspected in accordance with SB A340-55-4029 - Threshold: Either within 6 years (72 months) since the date of the elevator first flight after embodiment of the SB A340-55-4029 or within 24 months after the original issue dated Aug 07/09 of the SB A340-55-4035, whichever occurs later. - Interval: 6 years since the date of the elevator first flight after last embodiment of SB A340-55-4035 **CONF 002 Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. Elevators not inspected in accordance with SB A340-55-4029 - Threshold: Either within 12 years (144 months) since the date of elevator first flight or within 24 months after the original issue dated Aug 07/09 of the SB A340-55-4035, whichever occurs later. - Interval: 6 years since the date of the elevator first flight after last embodiment of SB A340-55-4035 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 6 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 17 @A340 SERVICE BULLETIN **CONF 003 Accomplishment of this Service Bulletin has been rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandatory accomplishment timescale. Elevators not inspected in accordance with SB A340-55-4029 - Threshold: Either within 12 years (144 months) since the date of elevator first flight or within 24 months after the original issue dated Aug 07/09 of the SB A340-55-4035, whichever occurs later. - Interval: 6 years since the date of the elevator first flight after last embodiment of SB A340-55-4035 **CONF ALL F. APPROVAL Approved under EASA Design Organisation Approval No. EASA 21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. NOTE : The required time for repair in case of findings in the inspection, is not described as it can be different depending on the quantity and type of repairs to be done **CONF 001 Task 554035-832-942-001: Inspection Get Access 2.00 On Aircraft Inspection 12.00 TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 NOTE : The man-hours given above are for the inspection method heating the elevator with blankets DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 7 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 18 @A340 SERVICE BULLETIN If a different method of inspection is selected, the man-hours will be increased to add the time required for removal of the elevators from the aircraft. Task 554035-833-942-001: Repair Get Access 6.00 On Aircraft Repair 10.00 Close-Up 8.00 TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 NOTE : The man-hours given above are for the inspection method heating the elevator with blankets If a different method of inspection is selected, the man-hours will be increased to add the time to install the elevators on the aircraft. **CONF 002 Task 554035-832-942-001: Inspection Get Access 2.00 On Aircraft Inspection 12.00 TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 NOTE : The man-hours given above are for the inspection method heating the elevator with blankets If a different method of inspection is selected, the man-hours will be increased to add the time required for removal of the elevators from the aircraft. Task 554035-833-942-001: Repair Get Access 6.00 On Aircraft Repair 10.00 Close-Up 8.00 TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 NOTE : The man-hours given above are for the inspection method heating the elevator with blankets If a different method of inspection is selected, the man-hours will be increased to add the time to install the elevators on the aircraft. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 8 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 19 @A340 SERVICE BULLETIN **CONF 003 Task 554035-832-942-001 : Inspection Get Access 2.00 On Aircraft Inspection 12.00 TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 NOTE : The minimum man-hours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional man- hours can apply. Task 554035-833-942-001 : Repair Get Access 6.00 On Aircraft Repair 10.00 Close-Up 8.00 TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF ALL H. WEIGHT AND BALANCE None I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 12-34-24 27-34-00 27-34-41 55-13-11 55-13-13 55-22-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-03 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-24-00 51-44-21 51-75-00 51-75-11 51-77-00 51-77-12 55-21-11 Tool Equipment Manual (TEM) 27-92-41 **CONF 002 Aircraft Maintenance Manual (AMM) 12-34-24 27-34-00 27-34-41 55-13-11 55-13-13 55-22-11 Consumable Material List (CML) DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 9 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 20 @A340 SERVICE BULLETIN Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-03 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-24-00 51-44-21 51-75-00 51-75-11 51-77-00 51-77-12 55-21-11 Tool Equipment Manual (TEM) 27-92-41 **CONF 003 Aircraft Maintenance Manual (AMM) 12-34-24 27-34-00 27-34-41 55-13-11 55-13-13 55-21-11 55-22-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-03 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-24-00 51-44-21 51-75-00 51-75-11 51-77-00 51-77-12 55-21-11 Tool Equipment Manual (TEM) 27-92-41 **CONF ALL K. PUBLICATION AFFECTED Maintenance Planning Document (MPD) 55-20-07 55-20-08 Non Destructive Test Manual (NTM) 55-20-07 55-20-08 Structural Repair Manual (SRM) 55-21-11 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES Before installation on an aircraft, it is the responsibility of the operator to apply the required instructions contained in this Service Bulletin A340-55-4035 on all serial number of elevators held as spare with any P/Ns, which first twelve digits are the following: - LH Elevator: F55280000000 or F55280000002 or F55280000004 or F55280000006 or F55280000008 or F55280000012 or F 55280002000 or F55280005000 or F55280005002 or F55280005004. - RH Elevator: F55280000001 or F55280000003 or F55280000005 or F55280000007 or F55280000009 or F55280000013 or F 55280002001 or F55280005001 or F55280005003 or F55280005005. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 10 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 21 @A340 SERVICE BULLETIN 2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY None B. INDUSTRY SUPPORT INFORMATION This Service Bulletin will be subject to specific support provided by AIRBUS, details of which can be referred to in OIT 999.0013/09. For details regarding the applicable commercial policy, ref 97B.0115/09, please contact your Customer Support Director. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLC01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant 09-001B As required Sealant 09-001D As required Sealant 09-002B As required Sealant 09-002D As required Cleaning agent 11-010 As required Protective varnish 16-021 As required Tedlar 19-015 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 11 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 22 @A340 SERVICE BULLETIN F. TOOLING (1) Tooling - Price and Availability None (2) Tools Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 98D27903500000 PIN-SIDE STICK LOCKING 99A55209001000 TEST TOOL 2 (3) Special Tools Refer to NTM 55-20-07 for blankets kit P/N if the Inspection method with Heating Blankets is selected. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 12 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 23 @A340 SERVICE BULLETIN 3. ACCOMPLISHMENT INSTRUCTIONS Task 554035-832-942-001 - Inspection WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. WARNING : MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION (REFER TO ESPM 20-55-00) Task Associated Data **CONF 001 Zone 334 344 Access Panel 334CB 334CT 344CB 344CT Manpower TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 **CONF 002 Zone 334 344 Access Panel 334CB 334CT 344CB 344CT DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 13 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 24 @A340 SERVICE BULLETIN Manpower TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 **CONF 003 Zone 334 344 Access Panel 334CB 334CT 344CB 344CT Manpower TOTAL MANHOURS 14.00 ELAPSED TIME (HOURS) 7.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 554035-910-601-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 334 344 Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML) (b) For information on composite structures. (Refer to SRM 51-77-00) (c) For information on sealing. (Refer to SRM 51-24-00) (2) Subtask 554035-839-601-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 14 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 25 @A340 SERVICE BULLETIN **CONF 002 (1) Subtask 554035-910-601-001 - Standard Practices Work Zones and Access Panels Zone Access/Work location 334 344 Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML) (b) For information on composite structures. (Refer to SRM 51-77-00) (c) For information on sealing. (Refer to SRM 51-24-00) (2) Subtask 554035-839-601-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 554035-910-601-002 - Standard Practices Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML) (b) For information on composite structures, refer to SRM 51-77-00. (c) Apply sealant in accordance with SRM 51-24-00. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 15 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 26 @A340 SERVICE BULLETIN (2) Subtask 554035-839-601-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 554035-941-601-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334CB, Panel 334CT 344 Access Panel 344CB, Panel 344CT Manpower Resources Skills AIRFRAME Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 98D27903500000 PIN-SIDE STICK LOCKING References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 27-34-41-000-801 Task 55-13-11-000-801 Task 55-13-13-000-801 Non Destructive Test Manual (NTM) 55-20-07 Tool Equipment Manual (TEM) 27-92-41 (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Make sure that the aircraft is in a maintenance status (c) Make sure that the pitch control wheels are in a neutral position (d) Display the warning notices in the flight compartment to prevent operation of the flight controls. (e) Put the access platforms in position at zone 334 for the LH Elevator and at zone 344 for the RH Elevator DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 16 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 27 @A340 SERVICE BULLETIN (f) Install the PIN-SIDE STICK LOCKING on the CAP and F/O side sticks. (Refer to TEM 27-92-41) 98D27903500000 PIN-SIDE STICK LOCKING 1 (g) Select one of the follow inspection methods. (Refer to NTM 55-20-07): NOTE : The preferred inspection method is heating the elevator with blankets. 1 Heating the elevator inside an oven. Do step (h). 2 Cooling the elevator inside a refrigerator. Do step (h). 3 Heating the elevator with blankets. Do step (i). (h) Remove the elevators from the aircraft, refer to AMM Task 27-34-41-000-801 and put them on an applicable support. (i) Open the Trailing Edge Access Panels 334CB and 344CB, 334CT and 344CT, refer to AMM Task 55-13-11-000-801 and AMM Task 55-13-13-000-801. **CONF 002 (1) Subtask 554035-941-601-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334CB, Panel 334CT 344 Access Panel 344CB, Panel 344CT Manpower Resources Skills AIRFRAME Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 98D27903500000 PIN-SIDE STICK LOCKING References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 27-34-41-000-801 Task 55-13-11-000-801 Task 55-13-13-000-801 Non Destructive Test Manual (NTM) 55-20-07 Tool Equipment Manual (TEM) 27-92-41 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 17 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 28 @A340 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Make sure that the aircraft is in a maintenance status (c) Make sure that the pitch control wheels are in a neutral position (d) Display the warning notices in the flight compartment to prevent operation of the flight controls. (e) Put the access platforms in position at zone 334 for the LH Elevator and at zone 344 for the RH Elevator (f) Install the PIN-SIDE STICK LOCKING on the CAP and F/O side sticks. (Refer to TEM 27-92-41) 98D27903500000 PIN-SIDE STICK LOCKING 1 (g) Select one of the follow inspection methods. (Refer to NTM 55-20-07): NOTE : The preferred inspection method is heating the elevator with blankets. 1 Heating the elevator inside an oven. Do step (h). 2 Cooling the elevator inside a refrigerator. Do step (h). 3 Heating the elevator with blankets. Do step (i). (h) Remove the elevators from the aircraft, refer to AMM Task 27-34-41-000-801 and put them on an applicable support. (i) Open the Trailing Edge Access Panels 334CB and 344CB, 334CT and 344CT, refer to AMM Task 55-13-11-000-801 and AMM Task 55-13-13-000-801. **CONF 003 (1) Subtask 554035-941-601-002 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334CB , Panel 334CT 344 Access Panel 344CB , Panel 344CT Manpower Resources Skills AIRFRAME DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 18 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 29 @A340 SERVICE BULLETIN Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 98D27903500000 PIN-SIDE STICK LOCKING References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 27-34-41-000-801 Task 55-13-11-000-801 Task 55-13-13-000-801 Non Destructive Test Manual (NTM) 55-20-07 Tool Equipment Manual (TEM) 27-92-41 NOTE : For the basic Aircraft configuration, refer to AMM Chapter "Introduction - Aircraft status for maintenance" in Manual Front Matter section. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Put the access platforms in position at zone 334 for the LH Elevator and at zone 344 for the RH Elevator. (c) Install the PIN-SIDE STICK LOCKING on the CAP and F/O side sticks, refer to TEM 27-92-41. 98D27903500000 PIN-SIDE STICK LOCKING 1 (d) Select one of the following inspection methods, refer to NTM 55-20-07: NOTE : The preferred inspection method is heating the elevator with blankets. 1 Heating the elevator inside an oven. Do step (h). 2 Cooling the elevator inside a refrigerator. Do step (h). 3 Heating the elevator with blankets. Do step (i). (e) Remove the elevators from the aircraft, refer to AMM Task 27-34-41-000-801 and put them on an applicable support. (f) Open the Trailing Edge Access Panels 334CB and 344CB, 334CT and 344CT, refer to AMM Task 55-13-11-000-801 and AMM Task 55-13-13-000-801. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 19 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 30 @A340 SERVICE BULLETIN **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 554035-832-601-001 - Inspection Work Zones and Access Panels Zone Access/Work location 334 344 Manpower Resources Manhours 12.00 Minimum number of person 2 Subtask elapsed time 6.00 Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 99A55209001000 TEST TOOL 1 References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-44-21 51-75-00 51-75-11 -911-003 55-21-11 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 Fig. A-SBDAA Repair of holes Sheet 01 Fig. A-SFAAA Flowchart Sheet 01 (a) Do a special detailed inspection: Refer to Fig. A-SFAAA . 1 Remove the access hole cover of the front spar between ER4 and ER5. Refer to Fig. A-SBBAA Sheet 02 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 20 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 31 @A340 SERVICE BULLETIN 2 Inspect using a flexible endoscope, the inner skin of each, upper and lower elevator panels in the sandwich area between ER4 and ER5 and 440 mm long from the front spar looking for any damage in the tedlar film such as scratch, debonding or tears. (Refer to NTM 55-20-08). A rigid endoscope with a rear oblique or right angle direction of view can be used in cases where the elevator is removed. (Refer to NTM 51-90-00) 3 Do an inspection by tap test in the inner side of each, upper and lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar. (Refer to NTM 55-20-08). Use the test tool, refer to NTM Task 51-10-03-280-801. 99A55209001000 TEST TOOL 1 4 If there is any damage of the tedlar, before next elevator flight contact AIRBUS for instructions and accomplish them. 5 If any debonding indication is found in the inner side of any, upper and/or lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. 6 Do the thermographic inspection of each, upper and lower elevator skin panels out of the area between ER4 and ER5 and 440 mm long backwards from the front spar. (Refer to NTM 55-20-07) Refer to Fig. A-SBBAA Sheet 01 Detail A NOTE : Before doing the thermographic inspection, check that the access holes from the elevator front spar are covered. 7 In case thermographic indications of trapped water partially hidden by lightning strips, do one of the following procedures: CAUTION : REMOVAL OF THE LIGHTNING STRIP CAN CAUSE DAMAGE TO THE CARBON FIBER OF THE SKIN PANEL a Remove the lightning strip, refer to SRM 55-21-11 and repeat the thermographic inspection to fully determine damage size. (Refer to NTM 55-20-07) b Do an X-Ray inspection procedure. (Refer to NTM 55-20-07) 8 Do an inspection by tap test on and around the liquid indications, refer to NTM Task 51-10-03-280-801. 9 In case of doubtful thermographic indications, do the following procedure: Refer to Fig. A-SBDAA Sheet 01 NOTE : Definition of a doubtful indication: No possibility to confirm that it is a liquid ingress damage (segregation between liquid spot and resin indication). DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 21 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 32 @A340 SERVICE BULLETIN Definition of a regular indication: Square or circular shape. NOTE : This procedure is only applicable to the sandwich structure of elevator skin panels where thermographic inspection according to NTM 55-20-07 is performed. a After thermographic inspection, make marks on all the doubtful indications in the elevator panel surface and classify the indications as regular and irregular. CAUTION : MAKE SURE THAT THE TAP-TEST INSPECTION ACCORDING TO NTM 51-10-03 HAS BEEN DONE ON AND AROUND EACH INDICATION. b Do a visual inspection of the panel surface, look for not homogeneous areas that show signs of existing repairs. CAUTION : DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE MADE OF CARBON FIBER REINFORCED PLASTIC. In case of doubt, remove locally the external surface protection looking for repair plies using the abrading procedure described in SRM 51-75-11-911-003. NOTE : Sometimes, an aerodynamic smoother is applied to the repaired area. If this occurs, remove the aerodynamic smoother by same method as external surface protection. c Do the analysis of the results from the two steps before. <1> Case 1: - The indication is regular in each, geometrical shape and grey color. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as an existing repair without liquid ingress damage. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <2> Case 2: - The indication is regular in each, geometrical shape and grey color. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 22 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 33 @A340 SERVICE BULLETIN - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - No tap test difference is noticed from the affected area. The indication is evaluated as an existing repair without liquid ingress damage. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <3> Case 3: - The indication is regular only in geometrical shape (but not in grey color). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - Tap-test results are not significant for indication evaluation. The indication could be evaluated as an existing repair with liquid ingress damage or non-homogeneous repair. ACTION: Contact AIRBUS for instructions and accomplish them before next elevator flight (the image of thermographic indication must be reported to AIRBUS for analysis). <4> Case 4: - The indication is irregular (in geometrical shape, in grey color or in each). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as a potted area of the panel. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <5> Case 5: - The indication is irregular. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - No tap test difference is noticed from the affected area. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 23 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 34 @A340 SERVICE BULLETIN The indication could be evaluated as liquid ingress or resin accumulation. ACTION: In case of doubt to confirm liquid ingress in the thermographic indications, do the procedure that follows: NOTE : The procedure to check for liquid ingress is categorized as destructive method. It must only be applied when necessary. Drill a hole of 2 mm diameter in accordance with general requirements of SRM 51-44-21 and the guidelines that follow: CAUTION : ONLY OUTER SANDWICH SKIN MUST BE DRILLED. SPECIAL CARE MUST BE TAKEN AT SANDWICH CHAMFER AREAS. - Refer to SRM 51-44-21 - No more than three holes must be drilled for the same thermographic indication. - Use a stop to limit the depth of the drill to 2 mm. Refer to Fig. A-SBDAA Sheet 01 - The holes must be drilled centered in the darker area of the thermographic indication. - If more than one hole is drilled: . The holes must be a minimum distance of 4 to 6 diameters (8 to 12 mm) between centers. . Total damaged area caused by hole drilling in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665 interaction criteria, must not be more than 1000 mm2. Refer to Fig. A-SBDAA Sheet 01 When the skin has been drilled, blown air with a dry syringe to detect liquid existence. Repair the holes refer to the instructions given in TASK 554035-833-942 001 Repair before next elevator flight. (b) If there are no liquid indications, before next elevator flight do the reprotection actions. Follow the instruction given in TASK 554035-833-942 001 Repair (c) Return the Ins pection Report Sheet to AIRBUS (SEES2). (d) If there are liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 24 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 35 @A340 SERVICE BULLETIN (e) If there are no liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight: 1 Do a damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665 and SRM 55-21-11 - C1 - Repairs - B56519C10665. **CONF 002 (1) Subtask 554035-832-601-001 - Inspection Work Zones and Access Panels Zone Access/Work location 334 344 Manpower Resources Manhours 12.00 Minimum number of person 2 Subtask elapsed time 6.00 Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 99A55209001000 TEST TOOL 1 References Non Destructive Test Manual (NTM) Task 51-10-03-280-801 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-44-21 51-75-00 51-75-11 -911-003 55-21-11 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 Fig. A-SBDAA Repair of holes Sheet 01 Fig. A-SFAAA Flowchart Sheet 01 (a) Do a special detailed inspection: Refer to Fig. A-SFAAA . 1 Remove the access hole cover of the front spar between ER4 and ER5. Refer to Fig. A-SBBAA Sheet 02 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 25 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 36 @A340 SERVICE BULLETIN 2 Inspect using a flexible endoscope, the inner skin of each, upper and lower elevator panels in the sandwich area between ER4 and ER5 and 440 mm long from the front spar looking for any damage in the tedlar film such as scratch, debonding or tears. (Refer to NTM 55-20-08). A rigid endoscope with a rear oblique or right angle direction of view can be used in cases where the elevator is removed. (Refer to NTM 51-90-00) 3 Do an inspection by tap test in the inner side of each, upper and lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar. (Refer to NTM 55-20-08). Use the test tool, refer to NTM Task 51-10-03-280-801. 99A55209001000 TEST TOOL 1 4 If there is any damage of the tedlar, before next elevator flight contact AIRBUS for instructions and accomplish them. 5 If any debonding indication is found in the inner side of any, upper and/or lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. 6 Do the thermographic inspection of each, upper and lower elevator skin panels out of the area between ER4 and ER5 and 440 mm long backwards from the front spar. (Refer to NTM 55-20-07) Refer to Fig. A-SBBAA Sheet 01 Detail A NOTE : Before doing the thermographic inspection, check that the access holes from the elevator front spar are covered. 7 In case thermographic indications of trapped water partially hidden by lightning strips, do one of the following procedures: CAUTION : REMOVAL OF THE LIGHTNING STRIP CAN CAUSE DAMAGE TO THE CARBON FIBER OF THE SKIN PANEL a Remove the lightning strip, refer to SRM 55-21-11 and repeat the thermographic inspection to fully determine damage size. (Refer to NTM 55-20-07) b Do an X-Ray inspection procedure. (Refer to NTM 55-20-07) 8 Do an inspection by tap test on and around the liquid indications, refer to NTM Task 51-10-03-280-801. 9 In case of doubtful thermographic indications, do the following procedure: Refer to Fig. A-SBDAA Sheet 01 NOTE : Definition of a doubtful indication: No possibility to confirm that it is a liquid ingress damage (segregation between liquid spot and resin indication). DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 26 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 37 @A340 SERVICE BULLETIN Definition of a regular indication: Square or circular shape. NOTE : This procedure is only applicable to the sandwich structure of elevator skin panels where thermographic inspection according to NTM 55-20-07 is performed. a After thermographic inspection, make marks on all the doubtful indications in the elevator panel surface and classify the indications as regular and irregular. CAUTION : MAKE SURE THAT THE TAP-TEST INSPECTION ACCORDING TO NTM 51-10-03 HAS BEEN DONE ON AND AROUND EACH INDICATION. b Do a visual inspection of the panel surface, look for not homogeneous areas that show signs of existing repairs. CAUTION : DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE MADE OF CARBON FIBER REINFORCED PLASTIC. In case of doubt, remove locally the external surface protection looking for repair plies using the abrading procedure described in SRM 51-75-11-911-003. NOTE : Sometimes, an aerodynamic smoother is applied to the repaired area. If this occurs, remove the aerodynamic smoother by same method as external surface protection. c Do the analysis of the results from the two steps before. <1> Case 1: - The indication is regular in each, geometrical shape and grey color. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as an existing repair without liquid ingress damage. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <2> Case 2: - The indication is regular in each, geometrical shape and grey color. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 27 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 38 @A340 SERVICE BULLETIN - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - No tap test difference is noticed from the affected area. The indication is evaluated as an existing repair without liquid ingress damage. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <3> Case 3: - The indication is regular only in geometrical shape (but not in grey color). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - Tap-test results are not significant for indication evaluation. The indication could be evaluated as an existing repair with liquid ingress damage or non-homogeneous repair. ACTION: Contact AIRBUS for instructions and accomplish them before next elevator flight (the image of thermographic indication must be reported to AIRBUS for analysis). <4> Case 4: - The indication is irregular (in geometrical shape, in grey color or in each). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as a potted area of the panel. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <5> Case 5: - The indication is irregular. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - No tap test difference is noticed from the affected area. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 28 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 39 @A340 SERVICE BULLETIN The indication could be evaluated as liquid ingress or resin accumulation. ACTION: In case of doubt to confirm liquid ingress in the thermographic indications, do the procedure that follows: NOTE : The procedure to check for liquid ingress is categorized as destructive method. It must only be applied when necessary. Drill a hole of 2 mm diameter in accordance with general requirements of SRM 51-44-21 and the guidelines that follow: CAUTION : ONLY OUTER SANDWICH SKIN MUST BE DRILLED. SPECIAL CARE MUST BE TAKEN AT SANDWICH CHAMFER AREAS. - Refer to SRM 51-44-21 - No more than three holes must be drilled for the same thermographic indication. - Use a stop to limit the depth of the drill to 2 mm. Refer to Fig. A-SBDAA Sheet 01 - The holes must be drilled centered in the darker area of the thermographic indication. - If more than one hole is drilled: . The holes must be a minimum distance of 4 to 6 diameters (8 to 12 mm) between centers. . Total damaged area caused by hole drilling in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665 interaction criteria, must not be more than 1000 mm2. Refer to Fig. A-SBDAA Sheet 01 When the skin has been drilled, blown air with a dry syringe to detect liquid existence. Repair the holes refer to the instructions given in TASK 554035-833-942 001 Repair before next elevator flight. (b) If there are no liquid indications, before next elevator flight do the reprotection actions. Follow the instruction given in TASK 554035-833-942 001 Repair (c) Return the Ins pection Report Sheet to AIRBUS (SEES2). (d) If there are liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 29 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 40 @A340 SERVICE BULLETIN (e) If there are no liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight: 1 Do a damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665 and SRM 55-21-11 - C1 - Repairs - B56519C10665. **CONF 003 (1) Subtask 554035-832-601-002 - Inspection Work Zones and Access Panels Zone Access/Work location 334 344 Manpower Resources Manhours 12.00 Minimum number of person 2 Subtask elapsed time 6.00 Skills NON SPECIFIC Material necessary to do the job Standard tool TOOLC01 ITEM TOOL N˚ TOOL NAME QTY SEE NOTES 99A55209001000 TEST TOOL 1 References Non Destructive Test Manual (NTM) Task 51-10-03-280-001 51-90-00 55-20-07 55-20-08 Structural Repair Manual (SRM) 51-44-21 51-75-00 51-75-11 -911-003 55-21-11 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 Fig. A-SBDAB Repair of holes Sheet 01 Fig. A-SFAAB Flowchart Sheet 01 (a) Do a special detailed inspection: Refer to Fig. A-SFAAB . 1 Remove the access hole cover of the front spar between ER4 and ER5, refer to Fig. A-SBBAA Sheet 02 . DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 30 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 41 @A340 SERVICE BULLETIN 2 Inspect using a flexible endoscope, the inner skin of each, upper and lower elevator panels in the sandwich area between ER4 and ER5 and 440 mm long from the front spar looking for any damage in the tedlar film such as scratch, debonding or tears, refer to NTM 55-20-08. A rigid endoscope with a rear oblique or right angle direction of view can be used in cases where the elevator is removed, refer to NTM 51-90-00. 3 Do an inspection by tap test in the inner side of each, upper and lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar, refer to NTM 55-20-08. Use the test tool, refer to NTM Task 51-10-03-280-001. 99A55209001000 TEST TOOL 1 4 If there is any damage of the tedlar, before next elevator flight contact AIRBUS for instructions and accomplish them. 5 If any debonding indication is found in the inner side of any, upper and/or lower, elevator panels in the sandwich area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. 6 Do the thermographic inspection of each, upper and lower elevator skin panels out of the area between ER4 and ER5 and 440 mm long backwards from the front spar, refer to NTM 55-20-07. Refer to Fig. A-SBBAA Sheet 01 ,v i e wA NOTE : Before doing the thermographic inspection, check that the access holes from the elevator front spar are covered. 7 Do an inspection by tap test on and around the liquid indications, refer to NTM Task 51-10-03-280-001. 8 In case of doubtful thermographic indications, do the following procedure: Refer to Fig. A-SBDAB Sheet 01 . NOTE : Definition of a doubtful indication: No possibility to confirm that it is a liquid ingress damage (segregation between liquid spot and resin indication). Definition of a regular indication: Square or circular shape. NOTE : This procedure is only applicable to the sandwich structure of elevator skin panels where thermographic inspection according to NTM 55-20-07 is performed. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 31 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 42 @A340 SERVICE BULLETIN a After thermographic inspection, make marks on all the doubtful indications in the elevator panel surface and classify the indications as regular and irregular. CAUTION : MAKE SURE THAT THE TAP-TEST INSPECTION ACCORDING TO NTM 51-10-03 HAS BEEN DONE ON AND AROUND EACH INDICATION. b Do a visual inspection of the panel surface, look for not homogeneous areas that show signs of existing repairs. CAUTION : DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE MADE OF CARBON FIBER REINFORCED PLASTIC. In case of doubt, remove locally the external surface protection looking for repair plies using the abrading procedure described in SRM 51-75-11-911-003. NOTE : Sometimes, an aerodynamic smoother is applied to the repaired area. If this occurs, remove the aerodynamic smoother by same method as external surface protection. c Do the analysis of the results from the two steps before. <1> Case 1: - The indication is regular in each, geometrical shape and grey color. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as an existing repair without liquid ingress damage. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <2> Case 2: - The indication is regular in each, geometrical shape and grey color. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - No tap test difference is noticed from the affected area. The indication is evaluated as an existing repair without liquid ingress damage. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 32 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 43 @A340 SERVICE BULLETIN ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <3> Case 3: - The indication is regular only in geometrical shape (but not in grey color). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) shows an existing repair. - Tap-test results are not significant for indication evaluation. The indication could be evaluated as an existing repair with liquid ingress damage or non-homogeneous repair. ACTION: Contact AIRBUS for instructions and accomplish them before next elevator flight (the image of thermographic indication must be reported to AIRBUS for analysis). <4> Case 4: - The indication is irregular (in geometrical shape, in grey color or in each). - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - The tap-test gives a ringing sound (not dull, not dumped) (filler/resin confirmed at affected area). The indication is evaluated as a potted area of the panel. ACTION: Re-protection of the affected surface before next elevator flight, refer to SRM 51-75-00. <5> Case 5: - The indication is irregular. - Visual inspection of the panel surface plus removal of a local external surface (if necessary) does not show an existing repair. - No tap test difference is noticed from the affected area. The indication could be evaluated as liquid ingress or resin accumulation. ACTION: In case of doubt to confirm liquid ingress in the thermographic indications, do the procedure that follows: NOTE : The procedure to check for liquid ingress is categorized as destructive method. It must only be applied when necessary. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 33 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 44 @A340 SERVICE BULLETIN Drill a hole of 2 mm diameter in accordance with general requirements of SRM 51-44-21 and the guidelines that follow: CAUTION : ONLY OUTER SANDWICH SKIN MUST BE DRILLED. SPECIAL CARE MUST BE TAKEN AT SANDWICH CHAMFER AREAS. - Refer to SRM 51-44-21. - No more than three holes must be drilled for the same thermographic indication. - Use a stop to limit the depth of the drill to 2 mm. Refer to Fig. A-SBDAB Sheet 01 . - The holes must be drilled centered in the darker area of the thermographic indication. - If more than one hole is drilled: . The holes must be a minimum distance of 4 to 6 diameters (8 to 12 mm) between centers. . Total damaged area caused by hole drilling in accordance with SRM 55-21-11 - C2 - Allowable Damage - A56519C10665 interaction criteria, must not be more than 1000 mm 2. Refer to Fig. A-SBDAB Sheet 01 . When the skin has been drilled, blown air with a dry syringe to detect liquid existence. Repair the holes refer to the instructions given in TASK 554035-833-942 001 Repair before next elevator flight. (b) If there are no liquid indications, before next elevator flight do the reprotection actions. Follow the instruction given in TASK 554035-833-942 001 Repair . (c) Return the Ins pection Report Sheet to AIRBUS (SEES2). (d) If there are liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight contact AIRBUS for instructions and accomplish them. (e) If there are no liquid indications adjacent to the panel area between ER4 and ER5 and 440 mm long backwards from the front spar, before next elevator flight: 1 Do a damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11 - C2 - Allowable Damage - A56519C10665 and SRM 55-21-11 - C2 - Repairs - A56519C10665. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 34 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 45 @A340 SERVICE BULLETIN **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF 003 None **CONF ALL E. CLOSE-UP **CONF 001 None **CONF 002 None **CONF 003 None DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 35 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 46 @A340 SERVICE BULLETIN This Page Intentionally Left Blank DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 36 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 47 @A340 SERVICE BULLETIN Task 554035-833-942-001 - Repair **CONF ALL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE. WARNING : MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IN CASE OF CONTAMINATION (REFER TO ESPM 20-55-00) Task Associated Data **CONF 001 Zone 334 335 344 345 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 37 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 48 @A340 SERVICE BULLETIN Access Panel 334AB 334BB 334CB 334CT 334DB 334EB 334FB 334GB 344AB 344BB 344CB 344CT 344DB 344EB 344FB 344GB Other access 335AB 335BB 335CB 335DB 335EB 335FB 345AB 345BB 345CB 345DB 345EB 345FB Manpower TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF 002 Zone 334 335 344 345 Access Panel 334AB 334BB 334CB 334CT 334DB 334EB 334FB 334GB 344AB 344BB 344CB 344CT 344DB 344EB 344FB 344GB Other access 335AB 335BB 335CB 335DB 335EB 335FB 345AB 345BB 345CB 345DB 345EB 345FB Manpower TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF 003 Zone 334 335 344 345 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 38 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 49 @A340 SERVICE BULLETIN Access Panel 334AB 334BB 334CB 334CT 334DB 334EB 334FB 334GB 344AB 344BB 344CB 344CT 344DB 344EB 344FB 344GB Other access 335AB 335BB 335CB 335DB 335EB 335FB 345AB 345BB 345CB 345DB 345EB 345FB Manpower TOTAL MANHOURS 24.00 ELAPSED TIME (HOURS) 12.00 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 554035-910-602-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML) (b) For information on composite structures. (Refer to SRM 51-77-00) (c) For information on sealing. (Refer to SRM 51-24-00) (2) Subtask 554035-839-602-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 39 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 50 @A340 SERVICE BULLETIN **CONF 002 (1) Subtask 554035-910-602-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of materials (Mat. No.) that you must use in this Service Bulletin refer to Consumable Materials List (CML) (b) For information on composite structures. (Refer to SRM 51-77-00) (c) For information on sealing. (Refer to SRM 51-24-00) (2) Subtask 554035-839-602-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 003 (1) Subtask 554035-910-602-002 - Standard Practices Manpower Resources Skills NON SPECIFIC References Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-77-00 (a) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML) (b) For information on composite structures, refer to SRM 51-77-00. (c) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 554035-839-602-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 40 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 51 @A340 SERVICE BULLETIN **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 554035-941-602-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334AB, Panel 334BB, Panel 334DB, Panel 334EB, Panel 334FB, Panel 334GB 344 Access Panel 344AB, Panel 344BB, Panel 344DB, Panel 344EB, Panel 344FB, Panel 344GB 335 Access Other access 335AB, Other access 335BB, Other access 335CB, Other access 335DB, Other access 335EB, Other access 335FB 345 Access Other access 345AB, Other access 345BB, Other access 345CB, Other access 345DB, Other access 345EB, Other access 345FB Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 55-13-11-000-801 Task 55-22-11-000-801 (a) Open the Trailing Edge Access Panels 334AB and 344AB, 334BB and 344BB,334DB and 344DB, 334EB and 344EB, 334FB and 344FB, 334GB and 344GB, refer to AMM Task 55-13-11-000-801. (b) Remove the Elevator Leading Edge 335AB and 345AB, 335BB and 345BB, 335CB and 345CB, 335DB and 345DB, 335EB and 345EB, 335FB and 345FB, refer to AMM Task 55-22-11-000-801. **CONF 002 (1) Subtask 554035-941-602-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334AB, Panel 334BB, Panel 334DB, Panel 334EB, Panel 334FB, Panel 334GB 344 Access Panel 344AB, Panel 344BB, Panel 344DB, Panel 344EB, Panel 344FB, Panel 344GB 335 Access Other access 335AB, Other access 335BB, Other access 335CB, Other access 335DB, Other access 335EB, Other access 335FB DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 41 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 52 @A340 SERVICE BULLETIN 345 Access Other access 345AB, Other access 345BB, Other access 345CB, Other access 345DB, Other access 345EB, Other access 345FB Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 55-13-11-000-801 Task 55-22-11-000-801 (a) Open the Trailing Edge Access Panels 334AB and 344AB, 334BB and 344BB,334DB and 344DB, 334EB and 344EB, 334FB and 344FB, 334GB and 344GB, refer to AMM Task 55-13-11-000-801. (b) Remove the Elevator Leading Edge 335AB and 345AB, 335BB and 345BB, 335CB and 345CB, 335DB and 345DB, 335EB and 345EB, 335FB and 345FB, refer to AMM Task 55-22-11-000-801. **CONF 003 (1) Subtask 554035-941-602-002 - Job Set-up Work Zones and Access Panels Zone Access/Work location 334 Access Panel 334AB , Panel 334BB , Panel 334DB , Panel 334EB , Panel 334FB , Panel 334GB 344 Access Panel 344AB , Panel 344BB , Panel 344DB , Panel 344EB , Panel 344FB , Panel 344GB 335 Access Other access 335AB , Other access 335BB , Other access 335CB , Other access 335DB , Other access 335EB , Other access 335FB 345 Access Other access 345AB , Other access 345BB , Other access 345CB , Other access 345DB , Other access 345EB , Other access 345FB Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 55-13-11-000-801 Task 55-22-11-000-801 (a) Open the Trailing Edge Access Panels 334AB and 344AB, 334BB and 344BB,334DB and 344DB, 334EB and 344EB, 334FB and 344FB, 334GB and 344GB, refer to AMM Task 55-13-11-000-801. (b) Remove the Elevator Leading Edge 335AB and 345AB, 335BB and 345BB, 335CB and 345CB, 335DB and 345DB, 335EB and 345EB, 335FB and 345FB, refer to AMM Task 55-22-11-000-801. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 42 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 53 @A340 SERVICE BULLETIN **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 554035-833-601-001 - Repair Work Zones and Access Panels Zone Access/Work location 335 345 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Consumable CMLC01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant 09-001B As required Sealant 09-001D As required Sealant 09-002B As required Sealant 09-002D As required Cleaning agent 11-010 As required Protective varnish 16-021 As required Tedlar 19-015 As required References Structural Repair Manual (SRM) 51-77-12 -911-001 55-21-11 55-21-11 -283-006 55-21-11 -283-002 55-21-11 -300-015 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 Fig. A-SBCAA Installation of the hole covers and sealing of static dischargers contour. Sheet 01 (a) Before next elevator flight: Do damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11 . DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 43 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 54 @A340 SERVICE BULLETIN NOTE : In case lightning strips have been removed in Task Inspection, install the lightning strips in accordance with SRM 55-21-11 - C1 - Repairs - B56519C10665. (b) Instructions for holes repair before next elevator flight. Holes done in Case 5 for evaluation of the thermographic indication. 1 Holes to be repaired located in an area that has liquid ingress a Do a damage evaluation in accordance with SRM 55-21-11-283-006. Holes must be included to obtain total damaged area. b Repair in accordance with SRM 55-21-11 - C1 - Repairs - B56519C10665. c If the procedure to drill holes for evaluation of thermographic indication mentioned in the Case 5, has been applied to an elevator in which the allowable damage limit (ADL) of the liquid ingress, included in SRM 55-21-11-283-006 is going to be applied, repair the holes using one of the methods that follows: CAUTION : THE REPAIRS DONE ACCORDING TO BOTH METHODS ARE TEMPORARY ACCEPTABLE FOR 2400 FH OR 1200 FC OR 200 DAYS SINCE NEXT ELEVATOR FLIGHT (WHICHEVER OCCURS FIRST) WHICH CORRESPONDS TO THE VALIDITY OF TEMPORARY LIQUID INGRESS ADL. <1> Method 1: Do a damage evaluation in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665. The total area affected by holes must not be more than 1000 mm2 (liquid ingress area must not be included for evaluation of damaged area). Repair in accordance with SRM 51-77-12-911-001. NOTE : The integrity of applied high speed tape have to be ensured during liquid ingress ADL validity <2> Method 2: Do a damage evaluation in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665. The total area affected by holes must not be more than 1000 mm2 (liquid ingress area must not be included for evaluation of damaged area). Repair in accordance with SRM 55-21-11-300-015. NOTE : To remove the core between holes is not necessary. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 44 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 55 @A340 SERVICE BULLETIN The repair plies must overlap the damage area. 2 Holes to be repaired not located in an area that has liquid ingress a Do a damage evaluation in accordance with SRM 55-21-11-283-002. The total area affected by holes must not be more than 1000 mm2 b Repair in accordance with SRM 55-21-11-300-015. NOTE : To remove the core between holes is not necessary. The repair plies must overlap the damage area. (c) Further to damage repair, before next elevator flight, re-protect the elevator as follow: 1 Do a visual inspection of the drainage holes to make sure the holes are clean. Refer to Fig. A-SBBAA Sheet 01 a If drainage holes are clean, no further action is necessary. b If the drainage holes are not clean or any obstruction is found, clean the holes 2 Seal of the static discharges contour. Refer to Fig. A-SBCAA Sheet 01 a Do a check the existing bead of sealant of the static discharges contour. b If the sealant is covering all the contour and remains in good condition, no action is required. c If the sealant is not covering all the contour or it is damaged: <1> Remove all the existing bead of sealant, using a nylon spatula. <2> Clean the area with: Cleaning agent 11-010 As required <3> Apply to the contour of the static discharger base a bead of sealant: Sealant 09-002B As required or Sealant 09-002D As required <4> Protect the sealant bead with: Protective varnish 16-021 As required DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 45 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 56 @A340 SERVICE BULLETIN 3 Installation of the front spar access hole covers. Refer to Fig. A-SBCAA Sheet 01 a Remove all the existing hole covers. b Cut a piece of tedlar with 20 mm (0.787 in) larger than the hole dimension. Tedlar 19-015 As required c Abrade the paint of the front spar with scotch brite type A on the area where the tedlar will be bonded. d Clean the area with: Cleaning agent 11-010 As required e Bond the tedlar with sealant: Sealant 09-001B As required or Sealant 09-001D As required **CONF 002 (1) Subtask 554035-833-601-001 - Repair Work Zones and Access Panels Zone Access/Work location 335 345 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Consumable CMLC01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant 09-001B As required Sealant 09-001D As required Sealant 09-002B As required Sealant 09-002D As required Cleaning agent 11-010 As required DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 46 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 57 @A340 SERVICE BULLETIN ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Protective varnish 16-021 As required Tedlar 19-015 As required References Structural Repair Manual (SRM) 51-77-12 -911-001 55-21-11 55-21-11 -283-006 55-21-11 -283-002 55-21-11 -300-015 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 Fig. A-SBCAA Installation of the hole covers and sealing of static dischargers contour. Sheet 01 (a) Before next elevator flight: Do damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11 . NOTE : In case lightning strips have been removed in Task Inspection, install the lightning strips in accordance with SRM 55-21-11 - C1 - Repairs - B56519C10665. (b) Instructions for holes repair before next elevator flight. Holes done in Case 5 for evaluation of the thermographic indication. 1 Holes to be repaired located in an area that has liquid ingress a Do a damage evaluation in accordance with SRM 55-21-11-283-006. Holes must be included to obtain total damaged area. b Repair in accordance with SRM 55-21-11 - C1 - Repairs - B56519C10665. c If the procedure to drill holes for evaluation of thermographic indication mentioned in the Case 5, has been applied to an elevator in which the allowable damage limit (ADL) of the liquid ingress, included in SRM 55-21-11-283-006 is going to be applied, repair the holes using one of the methods that follows: CAUTION : THE REPAIRS DONE ACCORDING TO BOTH METHODS ARE TEMPORARY ACCEPTABLE FOR 2400 FH OR 1200 FC OR 200 DAYS SINCE NEXT ELEVATOR FLIGHT (WHICHEVER OCCURS FIRST) WHICH CORRESPONDS TO THE VALIDITY OF TEMPORARY LIQUID INGRESS ADL. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 47 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 58 @A340 SERVICE BULLETIN <1> Method 1: Do a damage evaluation in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665. The total area affected by holes must not be more than 1000 mm2 (liquid ingress area must not be included for evaluation of damaged area). Repair in accordance with SRM 51-77-12-911-001. NOTE : The integrity of applied high speed tape have to be ensured during liquid ingress ADL validity <2> Method 2: Do a damage evaluation in accordance with SRM 55-21-11 - C1 - Allowable Damage - B56519C10665. The total area affected by holes must not be more than 1000 mm2 (liquid ingress area must not be included for evaluation of damaged area). Repair in accordance with SRM 55-21-11-300-015. NOTE : To remove the core between holes is not necessary. The repair plies must overlap the damage area. 2 Holes to be repaired not located in an area that has liquid ingress a Do a damage evaluation in accordance with SRM 55-21-11-283-002. The total area affected by holes must not be more than 1000 mm2 b Repair in accordance with SRM 55-21-11-300-015. NOTE : To remove the core between holes is not necessary. The repair plies must overlap the damage area. (c) Further to damage repair, before next elevator flight, re-protect the elevator as follow: 1 Do a visual inspection of the drainage holes to make sure the holes are clean. Refer to Fig. A-SBBAA Sheet 01 a If drainage holes are clean, no further action is necessary. b If the drainage holes are not clean or any obstruction is found, clean the holes 2 Seal of the static discharges contour. Refer to Fig. A-SBCAA Sheet 01 DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 48 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 59 @A340 SERVICE BULLETIN a Do a check the existing bead of sealant of the static discharges contour. b If the sealant is covering all the contour and remains in good condition, no action is required. c If the sealant is not covering all the contour or it is damaged: <1> Remove all the existing bead of sealant, using a nylon spatula. <2> Clean the area with: Cleaning agent 11-010 As required <3> Apply to the contour of the static discharger base a bead of sealant: Sealant 09-002B As required or Sealant 09-002D As required <4> Protect the sealant bead with: Protective varnish 16-021 As required 3 Installation of the front spar access hole covers. Refer to Fig. A-SBCAA Sheet 01 a Remove all the existing hole covers. b Cut a piece of tedlar with 20 mm (0.787 in) larger than the hole dimension. Tedlar 19-015 As required c Abrade the paint of the front spar with scotch brite type A on the area where the tedlar will be bonded. d Clean the area with: Cleaning agent 11-010 As required e Bond the tedlar with sealant: Sealant 09-001B As required or Sealant 09-001D As required DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 49 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. ### Page 60 @A340 SERVICE BULLETIN **CONF 003 (1) Subtask 554035-833-601-002 - Repair Work Zones and Access Panels Zone Access/Work location 335 345 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Consumable CMLC01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant 09-001B As required Sealant 09-001D As required Sealant 09-002B As required Sealant 09-002D As required Cleaning agent 11-010 As required Protective varnish 16-021 As required Tedlar 19-015 As required References Structural Repair Manual (SRM) 51-77-12 -911-001 55-21-11 -283-009 55-21-11 -300-022 55-21-11 55-21-11 -283-034 Fig. A-SBCAA Installation of the hole covers and sealing of static dischargers contour. Sheet 01 Fig. A-SBBAA Inspection. General location Sheet 01 Sheet 02 (a) Before next elevator flight: Do damage evaluation and apply allowable damage criteria or repair in accordance with SRM 55-21-11. DATE: Aug 07/09 SERVICE BULLETIN No.: A340-55-4035 REVISION No.: 01 - Feb 15/19 Page: 50 0 Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved. 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