# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS MODIFICATION No.: None This page transmits Revision No.03 of Service Bulletin No.A340-53-4208 ADDITIONAL WORK **CONF ALL Additional work is required by this revision for aircraft modified by any previous issue. The additional work involves a repetitive inspection for strut-end diameter less than 43mm (1.69in). REASON Revision No. 03 issued to update the effectivity, the compliance time, the inspection procedure and the flow chart. CHANGES SUMMARY EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER UPDATED R PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R PUBLICATIONS AFFECTED ADDED N MATERIAL INFORMATION LIST OF MATERIALS - OPERATOR SUPPLIED DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Consumable Materials Consumable CMLD01 CONSUMABLE MATERIAL SET UPDATED CONSUMABLE UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 534208- 832-848-001-Inspection of the THS support struts TASK SOLUTION UPDATED NOTE UPDATED R Task associated data - 001 ELAPSED TIME UPDATED R Subtask 534208-832-201-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 534208-280-201-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED R
Subtask 534208-280-202-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED R
Subtask 534208-020-201-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED MATERIAL LIST UPDATED R
Subtask 534208-420-201-001 SUBTASK SOLUTION UPDATED CONSUMABLE UPDATED NOTE UPDATED MATERIAL LIST UPDATED R
TASK 534208- 832-850-001-Inspection - ADDITIONAL WORK TASK SOLUTION ADDED N Task associated data - 001 TASK ASSOCIATED DATA ADDED N Subtask 534208-910-202-001 SUBTASK SOLUTION ADDED N Subtask 534208-839-202-001 SUBTASK SOLUTION ADDED N Subtask 534208-941-202-001 SUBTASK SOLUTION ADDED N Subtask 534208-280-203-001 SUBTASK SOLUTION ADDED N Subtask 534208-942-202-001 SUBTASK SOLUTION ADDED N Fig. A-GFAAA Fig. A-GFAAA Sheet 01 SHEET UPDATED R Fig. A-GFAAA Sheet 02 SHEET UPDATED R Fig. A-GFAAA Sheet 03 SHEET UPDATED R Fig. A-GBAAA Fig. A-GBAAA Sheet 01 SHEET UPDATED R FILLING 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 Revision No. 01 issued to amend the compliance sentence due to the issue of the AD, add a check of the strut-end diameter and to amend the procedure accordingly.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 2 6

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Revision No. 02 issued to update the effectivity and Fig. A-GBAAA and reduce the gap from 2.50mm (0.098in) to 1.00mm (0.039in). REVISION SEQUENCE ORIGINAL: Feb 07/13 REVISION No. : 01 - Jun 10/13 REVISION No. : 02 - Aug 08/13 REVISION No. : 03 - Feb 28/14

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 3 6

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# @A340 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

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# @A340 SERVICE BULLETIN SUMMARY AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft. 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91. Any lateral movement is prevented by 4 diagonal support struts. During routine maintenance done on several aircraft in this area, support struts have been found cracked. The affected area is the strut end and typical cracks are longitudinal. On some aircraft several cracks per support strut have been found. The Airbus Technical Disposition, LR5350D12005293, has been released to do a sampling inspection on selected aircraft to confirm the issue. Further investigation has shown that there are two different suppliers of the struts which makes it possible to have a mixture of both struts installed on the aircraft. It is therefore necessary to do a check of the strut-end diameter to determine the correct inspection procedure. To prevent a support strut rupture, Airbus has decided to do a dedicated repeat inspection of the affected area on all A330 and A340 aircraft. After the inspection, depending on the supplier and result, it is necessary to install a clamping device to the strut end through the accomplishment of the modification Service Bulletin, A330-53-4199. The installation of the clamping device is temporary pending a permanent solution which will be introduced through a modification Service Bulletin at a later date. Airbus has issued an SBIT, Ref 13-0015 dated Apr 29/13 and an AMOC, Ref 10044559R01 dated Apr 23/13 to inform operators. The accomplishment of this Service Bulletin will detect potential damage at the support strut end and limit the risk of THS lateral movement.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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# @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 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPD01 See SB Component COMPD02 See SB EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

06Y 15R 15T 36V 38W 58X 83V 98X ABD AFR AIB ALK ARG CAL CCA CPA DGA DLH FIN GAF GFA HFY I2L IBE IRC IRM KAC LAN M3R MAU MDG MSR NMB OAL PAL QAF RJA S3R SAA SAS SFB SLM SVW SWR TAP THT THY UAE VCV VIR XAX CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 53.53.04.001 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 2 6

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# @A340 SERVICE BULLETIN SUMMARY MANPOWER Task 534208-832-848-001: Inspection of the THS support struts TOTAL MANHOURS 6.50 ELAPSED TIME (HOURS) 6.50 Task 534208-832-850-001: Inspection - ADDITIONAL WORK TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00 APPENDICES Appendix 01 - Inspection Report

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 3 6

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# @A340 SERVICE BULLETIN SUMMARY

**CONF ALL



### B FR91

Z310 

### A

TYPICAL 

## A **B**

**B**

**B**



## B AREA TO BE INSPECTED AREA TO BE INSPECTED

F_SB_534208_6_SAAA_01_00 Figure A-GSAAA - Sheet 01

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 4 6

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# @A340 SERVICE BULLETIN
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS 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 0006 0009 0014 0020 0022-0026 0029 0031-0035 0038 0041 0043-0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081 0084-0085 0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128 0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164 0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199 0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233 0236-0237 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329 0331-0332 0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413-0415 0424 0429-0430 0433-0435 0438 0442 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: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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# @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 06Y 0139 0149 15R 0151 15T 0009 36V 0024 38W 0282 58X 0004 83V 0133 98X 0429 ABD 0210 AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377 0399 AIB 0131 0141 0161 0182 ALK 0032 0033 0034 0367 0374 0381 ARG 0063 0074 0080 0085 0093 0094 0123 0126 0128 0170 0193 0373 CAL 0402 0406 0411 0415 0433 0541 CCA 0192 0199 0201 0242 0243 0264 CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228 DGA 0075 0081 DLH 0035 0052 0053 0135 0158 0213 0233 0252 0297 0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447 FIN 0058 0168 0174 0835 0844 0921 0938 GAF 0274 0355 GFA 0212 0215 0554 HFY 0117 0190 0202 I2L 0048 0216 0257 IBE 0088 0125 0134 0145 0146 0217 0221 0329 0414 0459 0474 0483 IRC 0002 IRM 0020 0056 KAC 0089 0090 0101 0104 LAN 0359 0363 0442 M3R 0061 MAU 0076 0152 0194 0268 0793 0800 MDG 0319 MSR 0156 0159 0178 NMB 0047 0051 OAL 0280 0292 PAL 0173 0176 0187 0196 0302 0318 0332 0387 QAF 0026 0528 RJA 0014 0022 0038 0043 S3R 0204 DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 2 6

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# @A340 SERVICE BULLETIN

OPERATOR MSN SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651 SAS 0167 0413 0424 0430 0435 0450 0467 0470 SFB 0046 SLM 0049 SVW 0955 SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561 0562 0585 0598 TAP 0041 0044 0079 0091 THT 0385 0395 0438 0446 0668 THY 0023 0025 0057 0115 0180 0270 0331 UAE 0163 0166 0185 0236 VCV 0031 VIR 0114 0164 0214 0225 XAX 0273 0278 (4) Configuration by MSN MSN CONFIGURATION 0002 0004 0006 0009 0014 0020 0022 0023 0024 0025 0026 0029 0031 0032 0033 0034 0035 0038 0041 0043 0044 0046 0047 0048 0049 0051 0052 0053 0056 0057 0058 0061 0063 0074 0075 0076 0078 0079 0080 0081 0084 0085 0088 0089 0090 0091 0093 0094 0101 0104 0114 0115 0117 0123 0125 0126 0128 0131 0133 0134 0135 0136 0137 0139 0141 0142 0145 0146 0147 0149 0150 0151 0152 0154 0156 0157 0158 0159 0160 0161 0163 0164 0166 0167 0168 0169 0170 0173 0174 0175 0176 0178 0179 0180 0182 0185 0186 0187 0190 0192 0193 0194 0196 0197 0199 0201 0202 0204 0207 0208 0210 0212 0213 0214 0215 0216 0217 0218 0220 0221 0225 0227 0228 0233 0236 0237 0242 0243 0245 0246 0252 0257 0260 0263 0264 0268 0270 0273 0274 0278 0280 0282 0292 0297 0302 0304 0307 0310 0318 0319 0321 0325 0327 0329 0331 0332 0335 0347 0352 0354 0355 0359 0363 0367 0373 0374 0377 0378 0379 0381 0385 0387 0390 0395 0399 0402 0406 0411 0413 0414 0415 0424 0429 0430 0433 0434 0435 0438 0442 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 0921 0938 0955 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Component COMPD01 As required DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 3 6

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# @A340 SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES Component COMPD02 As required Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91. Any lateral movement is prevented by 4 diagonal support struts. During routine maintenance done on several aircraft in this area, support struts have been found cracked. The affected area is the strut end and typical cracks are longitudinal. On some aircraft several cracks per support strut have been found. The Airbus Technical Disposition, LR5350D12005293, has been released to do a sampling inspection on selected aircraft to confirm the issue. Further investigation has shown that there are two different suppliers of the struts which makes it possible to have a mixture of both struts installed on the aircraft. It is therefore necessary to do a check of the strut-end diameter to determine the correct inspection procedure. (2) Objective/Action To prevent a support strut rupture, Airbus has decided to do a dedicated repeat inspection of the affected area on all A330 and A340 aircraft. After the inspection, depending on the supplier and result, it is necessary to install a clamping device to the strut end through the accomplishment of the modification Service Bulletin, A330-53-4199. The installation of the clamping device is temporary pending a permanent solution which will be introduced through a modification Service Bulletin at a later date. Airbus has issued an SBIT, Ref 13-0015 dated Apr 29/13 and an AMOC, Ref 10044559R01 dated Apr 23/13 to inform operators. (3) Advantages The accomplishment of this Service Bulletin will detect potential damage at the support strut end and limit the risk of THS lateral movement. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 4 6

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# @A340 SERVICE BULLETIN Task 534208-832-848-001: Inspection of the THS support struts (1) Do a check of the Strut-End Diameter (2) Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm (3) Do a High Frequency Eddy Current Inspection of the support struts with an end dia of less than 43mm (4) Remove the clamps from the THS support struts (5) Install the clamps on the THS support struts Task 534208-832-850-001: Inspection - ADDITIONAL WORK (1) Specific/Special Inspection/Check E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale For the first batch of aircraft (MSN 0002 up to MSN 0210): - This Service Bulletin must be accomplished within 6 months from Service Bulletin original issue date. - Repetitive inspections are to be accomplished at intervals of 42 months or 20000 FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal or more than 43mm (1.69in). For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to be accomplished at intervals of 12 months from the last inspection date or within 3 months after ISB revision 03 issue date, whatever occurs later and thereafter at intervals not to exceed 12 months since the last inspection, inspect in accordance with SB A330-53-4208. For the second batch of aircraft (MSN 0212 up to MSN 0447): - This Service Bulletin must be accomplished within 24 months from Service Bulletin original issue date. - Repetitive inspections are to be accomplished at intervals of 42 months or 20000 FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal or more than 43mm (1.69in). For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to be accomplished at intervals of 12 months from the last inspection date or within 3 months after ISB revision 03 issue date, whatever occurs later and thereafter at intervals not to exceed 12 months since the last inspection, inspect in accordance with SB A330-53-4208.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 5 6

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# @A340 SERVICE BULLETIN For the third batch of aircraft (MSN 0450 up to MSN 0955): - This Service Bulletin must be accomplished within 36 months from Service Bulletin original issue date. - Repetitive inspections are to be accomplished at intervals of 42 months or 20000 FH whichever occurs first, from the last inspection date for TAC strut-end dia. equal or more than 43mm (1.69in). For SARMA strut-end dia. less than 43mm (1.69in.) the repetitive inspections are to be accomplished at intervals of 12 months from the last inspection date or within 3 months after ISB revision 03 issue date, whatever occurs later and thereafter at intervals not to exceed 12 months since the last inspection, inspect in accordance with SB A330-53-4208. NOTE: Aircraft previously inspected by AIRBUS Technical Disposition, LR5350D12005293 have to be considered as part of the third batch of aircraft. This Service Bulletin has been classified 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 mandated accomplishment timescale. F. APPROVAL The technical content of this document is approved under the authority of 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 elapsed time is calculated for only one of the possible HFEC inspections of all four struts taking into account the possible removal/installation of clamps. If clamps are not installed then the elapsed time is reduced accordingly. Task 534208-832-848-001: Inspection of the THS support struts Get Access 0.50 On Aircraft Do a check of the Strut-End Diameter 0.50 Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm 2.00

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 6 6

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# @A340 SERVICE BULLETIN
Task 534208-832-848-001: Inspection of the THS support struts Do a High Frequency Eddy Current Inspection of the support struts with an end dia of less than 43mm 2.00 Remove the clamps from the THS support struts 0.50 Install the clamps on the THS support struts 0.50 Close-Up 0.50 TOTAL MANHOURS 6.50 ELAPSED TIME (HOURS) 6.50 Task 534208-832-850-001: Inspection - ADDITIONAL WORK Get Access 0.50 On Aircraft Specific/Special Inspection/Check 2.00 Close-Up 0.50 TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 24-42-00 53-53-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 53-56-10 Service Bulletin (SB) A340-53-4199 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-42-00 K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 535127-01-1 535127-01-2 535127-01-3 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 7 6

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# @A340 SERVICE BULLETIN

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# @A340 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign. Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Component COMPD01 AIRBUS Material, Logistics and Suppliers IFD - In Flight Desk Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 4012 For ordering by E-mail: ifd.spares@airbus.com AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive multiple suppliers ensure access to minimum prices. AIRBUS recommends Customers with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to B/E Aerospace. The address is: Component COMPD02 B/E AEROSPACE INC. CONSUMABLES MANAGEMENT 10000 NW 15th Terrace Miami FL 33172 USA Tel EMEA: +49 (0) 40 822 285 31500 Tel US: +1 305 925 2600 Tel ASIA: +1 310 900 1300 Fax EMEA: +49 (0) 40 822 285 31010 Fax US: +1 305 507 7191 Fax ASIA: +1 310 819 1200 SITA: MIAMMCR E-Mail: AOGdesk_CMG@beaerospace.com internet: http://www.beconsumables.com or, alternatively any other source on the open market. (2) Price and Availability No AIRBUS kit will be provided. Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be purchased by a spares purchase order.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 9 6

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# @A340 SERVICE BULLETIN Operator supplied standard hardware parts required to accomplish this Service Bulletin are to be supplied from the Operator’s stock. B. INDUSTRY SUPPORT INFORMATION As a special policy applied to this Service Bulletin, and in case of findings only, AIRBUS will provide the material at no charge for orders placed before Dec 31/15. For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit management department. AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX France E-mail : monitored.retrofit@airbus.com Tel : (33) 5 67 19 06 22 Fax : (33) 5 61 93 27 45 C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials NOTE: To accomplish this Service Bulletin, and in case of strut replacement, it is necessary to use the expendable parts listed in AMM 53-53-11, Page Block 401. Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Varnish-- Electrical Bonding Structure 04TMB2 As required Polysulfide Sealant-Low Adhesion Fillet Structure 06AEB2 As required Non Hardening Jointing Putty-High Temp. Area - St 06LDG2 As required Non Aqueous Cleaner-General - - 08BAA9 As requiredCorrosion Preventive CompoundWater Displacing & 12ADB1 As required Textile-Lint Free Cotton - 14SBA1 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 10 6

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# @A340 SERVICE BULLETIN (2) Components Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES F5357414000000 STRUT NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE: The components listed above are only required if the replacement of a support strut is necessary. The quantity of these items are to be ordered as required. Component COMPD02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES MS24665-153 PIN MS24665-157 PIN NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. NOTE: The components listed above are only required if the replacement of a support strut is necessary. The quantity of these items are to be ordered as required. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools If it is required to replace a support strut to accomplish this Service Bulletin it is necessary to use the tools listed in AMM 53-53-11, Page Block 401.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 11 6

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# @A340 SERVICE BULLETIN (3) Special Tools None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 12 6

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# @A340 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 534208-832-848-001 - Inspection of the THS support struts WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 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. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS 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 AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 13 6

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# @A340 SERVICE BULLETIN
Task Associated Data Zone 310 Access Door 312AR 313AL Manpower TOTAL MANHOURS 6.50 ELAPSED TIME (HOURS) 6.50 A. GENERAL (1) Subtask 534208-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-00 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 534208-839-201-001 - 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: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 14 6

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# @A340 SERVICE BULLETIN
B. PREPARATION (1) Subtask 534208-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 312AR, Door 313AL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 24-42-00-861-801 (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Energize the ground service network, refer to AMM Task 24-42-00-861-801. (c) Put an access platform in position below the access door 312AR. (d) Open the access doors 312AR and 313AL. (e) Set the light switch 4LJ to ON. C. PROCEDURE (1) Subtask 534208-832-201-001 - Do a check of the Strut-End Diameter Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 Fig. A-GDAAA Check of Strut-end Diameter Sheet 01
Refer to Fig. A-GFAAA Sheet 01 and Fig. A-GDAAA (a) Inspect the strut ends for the installation of clamps. 1 If clamps are installed: - Remove them in accordance with SUBTASK 534208-020-201 001 Remove the clamps from the THS support struts .

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 15 6

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# @A340 SERVICE BULLETIN - Continue with the inspection detailed in SUBTASK 534208-280-201 001 Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm . NOTE : If clamps are installed then the diameter of the strut end is equal to or more than 43mm (1.69in.). 2 If clamps are not installed:
a Do a check of the strut end diameter "D", refer to Fig. A-GDAAA Sheet 01

. <1> If the diameter "D" is equal to or more than 43mm (1.69in.), continue with the inspection detailed in SUBTASK 534208-280-201 001 Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm . <2> If the diameter "D" is less than 43mm (1.69in.), continue with the inspection detailed in SUBTASK 534208-280-202 001 Do a High Frequency Eddy Current Inspection of the support struts with an end dia of less than 43mm . (2) Subtask 534208-280-201-001 - Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm Work Zones and Access Panels Zone Access/Work location 310 Access Door 312AR Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401 Non Destructive Test Manual (NTM) 53-56-10 Service Bulletin (SB) A340-53-4199

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 16 6

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# @A340 SERVICE BULLETIN

References Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 Fig. A-GCAAA Inspection Area - Strut-end dia. equal to or more than 43mm Sheet 01 Sheet 02
Refer to Fig. A-GFAAA Sheet 02, Fig. A-GCAAA and Appendix 01 - Inspection Report (a) If necessary, clean the support struts with: Non Aqueous Cleaner-General - - 08BAA9 As required
Textile-Lint Free Cotton - 14SBA1 As required (b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks in accordance with NTM 53-56-10. 1 No cracks found: - If previously installed, reinstall the clamps before next flight, in accordance with SUBTASK 534208-420-201 001 Install the clamps on the THS support struts .
or - If no clamps where previously installed, accomplish Service Bulletin A340-53-4199 before next flight, to install them. 2 Individual crack with a max length less than 15 mm (0.59 in.) or no more than 4 cracks less than or equal to 15 mm (0.59 in.) found on at least one strut end: - If previously installed, reinstall the clamps before next flight, in accordance with SUBTASK 534208-420-201 001 Install the clamps on the THS support struts .
or - If no clamps where previously installed, accomplish Service Bulletin A340-53-4199 before next flight, to install them. 3 Individual crack with a max length equal to or more than 15 mm (0.59 in.) or more than 4 cracks less than or equal to 15 mm (0.59 in.) found on at least one strut end: - Replace the affected strut with a new strut, which has an end diameter equal to or more than 43mm (1.69in.), before next flight, refer to AMM 53-53-11, Page Block 401 and use the parts listed in Component COMPD01 and Component COMPD02.
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 17 6

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# @A340 SERVICE BULLETIN - If previously installed, reinstall the clamps before next flight, in accordance with SUBTASK 534208-420-201 001 Install the clamps on the THS support struts .
or - Replace the affected strut with a new strut, which has an end diameter equal to or more than 43mm (1.69in.), before next flight, refer to AMM 53-53-11, Page Block 401 and use the parts listed in Component COMPD01 and Component COMPD02. - If no clamps where previously installed, accomplish Service Bulletin A340-53-4199 before next flight, to install them. (c) Report the results of this inspection to AIRBUS within 10 days, refer to Appendix 01 - Inspection Report . (d) Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service Bulletin. (3) Subtask 534208-280-202-001 - Do a High Frequency Eddy Current Inspection of the support struts with an end dia of less than 43mm Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401 Non Destructive Test Manual (NTM) 53-56-10 Service Bulletin (SB) A340-53-4199 Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 Fig. A-GEAAA Inspection Area - Strut-end dia. less than 43mm Sheet 01

Refer to Fig. A-GFAAA Sheet 03, Fig. A-GEAAA and Appendix 01 - Inspection Report
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 18 6

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# @A340 SERVICE BULLETIN (a) If necessary, clean the support struts with: Non Aqueous Cleaner-General - - 08BAA9 As required
Textile-Lint Free Cotton - 14SBA1 As required (b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks in accordance with NTM 53-56-10. 1 No cracks found: - Report the results of this inspection to AIRBUS within one month, refer to Appendix 01 - Inspection Report . - Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service Bulletin. 2 Cracks found on at least one strut end: - Replace the affected strut with a new strut, which has an end diameter equal to or more than 43mm (1.69in.), before next flight, refer to AMM 53-53-11, Page Block 401 and use the parts listed in Component COMPD01 and Component COMPD02. - Accomplish Service Bulletin A340-53-4199 before next flight. - Report the results of this inspection to AIRBUS within 10 days, refer to Appendix 01 - Inspection Report . - Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service Bulletin. (4) Subtask 534208-020-201-001 - Remove the clamps from the THS support struts Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 19 6

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# @A340 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Fig. A-GBAAA Removal/Installation of the clamps Sheet 01
Refer to Fig. A-GBAAA Sheet 01 (a) From each support strut, remove: 2 Nut NAS1726-5E Item (4) Retain 2 Washer NAS1149D0563K Item (3) Retain 2 Bolt NSA5031-5-42 Item (2) Retain 2 Clamp F5357685020000 Item (1) Retain (b) Remove the remaining sealant from the support struts and clean them with: Non Aqueous Cleaner-General - - 08BAA9 As required
Textile-Lint Free Cotton - 14SBA1 As required (5) Subtask 534208-420-201-001 - Install the clamps on the THS support struts Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 20 6

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# @A340 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Varnish-- Electrical Bonding Structure 04TMB2 As required Polysulfide Sealant-Low Adhesion Fillet Structure 06AEB2 As required Non Hardening Jointing Putty-High Temp. Area - St 06LDG2 As required Corrosion Preventive Compound-Water Displacing & 12ADB1 As required

NOTE: Slightly rotate the clamp to maintain a sufficient gap between the clamp and the rudder servo-command hydraulic tube to prevent interference. (a) To the interface surfaces of the clamps, Item (1), apply:Polysulfide SealantLow Adhesion Fillet Structure 06AEB2 As required

NOTE: Application of the sealant is required at the interfaces between the two clamp halves and at the interfaces between the clamps and the support struts. (b) To the bolts, item (2), apply: Non Hardening Jointing Putty-High Temp. Area - St 06LDG2 As required
(c) On each support strut, install: 2 Nut NAS1726-5E Item (4) Retained at removal 2 Washer NAS1149D0563K Item (3) Retained at removal 2 Bolt NSA5031-5-42 Item (2) Retained at removal 2 Clamp F5357685020000 Item (1) Retained at removal (d) Protect the visible edges of the sealant, 09-019, with: Varnish-- Electrical Bonding Structure 04TMB2 As required

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 21 6

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# @A340 SERVICE BULLETIN (e) On the clamps and fasteners which you have installed, apply: Corrosion Preventive Compound-Water Displacing & 12ADB1 As required

D. TEST None E. CLOSE-UP (1) Subtask 534208-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-42-00-862-801 (a) Make sure that the work area is clean and clear of tools and other items of equipment. (b) Set the light switch 4LJ to OFF. (c) Close the access doors 312AR and 313AL. (d) Remove the access platform. (e) De-energize the ground service network, refer to AMM Task 24-42-00-862-801.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 22 6

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# @A340 SERVICE BULLETIN Task 534208-832-850-001 - Inspection - ADDITIONAL WORK WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. 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. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS 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 AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 23 6

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# @A340 SERVICE BULLETIN
Task Associated Data Zone 310 Access Door 312AL 312AR Manpower TOTAL MANHOURS 3.00 ELAPSED TIME (HOURS) 3.00 A. GENERAL (1) Subtask 534208-910-202-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-801 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-42-00 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 534208-839-202-001 - 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: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 24 6

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# @A340 SERVICE BULLETIN
B. PREPARATION (1) Subtask 534208-941-202-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 312AR, Door 312AL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802 Task 24-42-00-861-801 (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802. (b) Energize the ground service network, refer to AMM Task 24-42-00-861-801. (c) Put an access platform in position below the access door 312AR. (d) Open the access doors 312AR and 313AL. (e) Set the light switch 4LJ to ON. C. PROCEDURE (1) Subtask 534208-280-203-001 - Specific/Special Inspection/Check Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Aircraft Maintenance Manual (AMM) 53-53-11, Page Block 401 Non Destructive Test Manual (NTM) 53-56-10 Service Bulletin (SB) A340-53-4199

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 25 6

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# @A340 SERVICE BULLETIN

References Fig. A-GEAAA Inspection Area - Strut-end dia. less than 43mm Sheet 01 Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 Refer to Fig. A-GFAAA Sheet 03, Fig. A-GEAAA and Appendix 01 - Inspection Report (a) If necessary, clean the support struts with: Non Aqueous Cleaner-General - - 08BAA9 As required
Textile-Lint Free Cotton - 14SBA1 As required (b) Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks in accordance with NTM 53-56-10. 1 No cracks found: - Report the results of this inspection to AIRBUS within one month, refer to Appendix 01 - Inspection Report

. - Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service Bulletin. 2 Cracks found on at least one strut end: - Replace the affected strut with a new strut, which has an end diameter equal to or more than 43mm (1.69in.), before next flight, refer to AMM 53-53-11, Page Block 401 and use the parts listed in Component COMPD01 and Component COMPD02. - Accomplish Service Bulletin A340-53-4199 before next flight. - Report the results of this inspection to AIRBUS within 10 days, refer to Appendix 01 - Inspection Report

. - Repeat the inspection at the intervals given in Paragraph 1.E.(2) of this Service Bulletin. D. TEST None

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 26 6

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# @A340 SERVICE BULLETIN
E. CLOSE-UP (1) Subtask 534208-942-202-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 24-42-00-862-801 (a) Make sure that the work area is clean and clear of tools and other items of equipment. (b) Set the light switch 4LJ to OFF. (c) Close the access doors 312AR and 313AL. (d) Remove the access platform. (e) De-energize the ground service network, refer to AMM Task 24-42-00-862-801.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 27 6

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# @A340 SERVICE BULLETIN

**CONF ALL

Z310 

### A



## A FR91 

### B

**B B** 

**B B** 



## B

**NOTE:** CHECK DIAMETER D 01 D 01

F_SB_534208_6_DAAA_01_00 Figure A-GDAAA - Sheet 01 Check of Strut-end Diameter
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 28 6

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# @A340 SERVICE BULLETIN

**CONF ALL

CHECK THE STRUT ENDS FOR THE INSTALLATION OF CLAMPS

NO YES INSTALLED

CLAMPS

CHECK THE DIAMETER OF THE STRUT END

YES NO THAN 43.0mm (1.69in.) DIA. LESS

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN. REMOVE CLAMPS

CONTINUE ON

SHEET 02

CONTINUE ON

SHEET 03

**NOTE:** IT IS POSSIBLE THAT A MIXTURE OF 01 BOTH STRUTS MAY BE INSTALLED ON THE AIRCRAFT 01

F_SB_534208_6_FAAA_01_04 Figure A-GFAAA - Sheet 01 Inspection Flow Chart
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 29 6

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# @A340 SERVICE BULLETIN

**CONF ALL

HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE STRUT ENDS FOR CRACKS DO A

NO ON AT LEAST ONE STRUT END CRACKS FOUND

YES REPLACE THE AFFECTED SUPPORT STRUT

INSTALL THE REMOVED CLAMPS ACCOMPLISH A340−53−4199 SERVICE BULLETIN

PARA. 1.E.(2) OF THIS SERVICE BULLETIN REPEAT THE INSPECTION AT THE INTERVALS GIVEN IN RESULTS TO AIRBUS REPORT THE INSPECTION CONTINUED FROM SHEET 01

YES

WITHIN THE GIVEN LIMITS

CRACKS NO

INSTALLED ON

THE STRUT WERE CLAMPS
ENDS YES NO

**NOTE:** NEW STRUT DIAMETER 43.0mm (1.69in.) TAC 02 02

F_SB_534208_6_FAAA_02_03 Figure A-GFAAA - Sheet 02 Inspection Flow Chart
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 30 6

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# @A340 SERVICE BULLETIN

**CONF ALL

HIGH FREQUENCY EDDY CURRENT INSPECTION OF THE STRUT ENDS FOR CRACKS DO A

NO ON AT LEAST ONE STRUT END CRACKS FOUND

YES

REPLACE THE AFFECTED SUPPORT STRUT

ACCOMPLISH A340−53−4199 SERVICE BULLETIN

PARA. 1.E.(2) OF THIS SERVICE BULLETIN REPEAT THE INSPECTION AT THE INTERVALS GIVEN IN RESULTS TO AIRBUS REPORT THE INSPECTION WITHIN 10 DAYS RESULTS TO AIRBUS REPORT THE INSPECTION WITHIN ONE MONTH

EVERY 12 MONTHS REPEAT INSPECTION CONTINUED FROM SHEET 01

**NOTE:** NEW STRUT DIAMETER 43.0mm (1.69in.) TAC 02 02

F_SB_534208_6_FAAA_03_02 Figure A-GFAAA - Sheet 03 Inspection Flow Chart
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 31 6

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# @A340 SERVICE BULLETIN

**CONF ALL



### C **C B**  FR91

Z310 

### A

TYPICAL (1)

(2) (3) (4)



## C

**D B**  **A B** 

**B**

**B**

(2) (3) (4)

(1) 

### D

**D**

**NOTE:** 02

ENSURE THAT THERE IS NO CONTACT 02 BETWEEN THE CLAMPS, ITEM (1) AND THE NUT CYLINDRICAL AREA 01

ENSURE THAT THERE IS NO CONTACT 01 BETWEEN THE CLAMPS, ITEM (1) AND THE CONICAL AREA

F_SB_534208_6_BAAA_01_04 Figure A-GBAAA - Sheet 01 Removal/Installation of the clamps
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 32 6

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# @A340 SERVICE BULLETIN

**CONF ALL

Z310 

### A



## A **B**

**C** FR91

F_SB_534208_6_CAAA_01_01 Figure A-GCAAA - Sheet 01 Inspection Area - Strut-end dia. equal to or more than 43mm
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 33 6

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# @A340 SERVICE BULLETIN

**CONF ALL

POSSIBLE CRACK

POSSIBLE CRACKS 

## B

**C** F_SB_534208_6_CAAA_02_01 Figure A-GCAAA - Sheet 02 Inspection Area - Strut-end dia. equal to or more than 43mm
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 34 6

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# @A340 SERVICE BULLETIN

**CONF ALL FR91

Z310 

### A



## A

**B B**  **B**

**B B** 

F_SB_534208_6_EAAA_01_00 Figure A-GEAAA - Sheet 01 Inspection Area - Strut-end dia. less than 43mm
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 35 6

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# @A340 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 36 6

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# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL 

## INSPECTION REPORT

SERVICE BULLETIN NO:

DATE OF INSPECTION: AIRCRAFT MSN: FLIGHT CYCLES: FLIGHT HOURS: PLEASE SEND REPORTING SHEET TO: AIRBUS CUSTOMER SERVICES ENGINEERING 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−MAIL: structure.sbinspectionresult@airbus.com A340−53−4208
SEES1

YES NO FINDINGS: INSPECTION METHOD: SPECIAL DETAILED INSPECTION FAX: +33(0)561 93 36 14

TYPICAL AREA TO BE INSPECTED

AREA TO BE INSPECTED Z310 

### A



## B FR91

A

B

B A A B B A



## A **B**

**B**

**B B**  4 3
1 2

F_SB_534208_6_AAAA_01_02 Figure A-GAAAA - Sheet 01 Inspection Report
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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# @A340 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALLINSPECTION REPORTSTRUTNUMBER1234DIAMETERENDPOS.CRACKQUANTITYLENGTHCRACK 1LENGTHCRACK 2LENGTHCRACK 3LENGTHCRACK 4LENGTHCRACK 5ABABABAB

F_SB_534208_6_AAAA_02_01 Figure A-GAAAA - Sheet 02 Inspection Report
DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 2 6

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# @A340 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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# @A340 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - Is this SB easy to understand ? Y/N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials Operator Supplied X Mod/Inspection X Manpower X Industry support X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations Comments:

Operator: Date: Name/Title: Please return this form to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: Feb 07/13 SERVICE BULLETIN No.: A340-53-4208 REVISION No.: 03 - Feb 28/14 Page: 1 6

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