# @A310 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 four 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 and support strut end have been found. This Service Bulletin gives the instruction to do a repetitive inspection of the affected area on all A310 aircraft, to prevent a support strut rupture. After the inspection (depending on aircraft records and general visual inspection results), it is necessary to install a clamping device which will ensure the rod body end insert is kept in place. This installation is temporary pending the definition of a new strut which will be introduced through another Mandatory Modification Service Bulletin. The accomplishment of this Service Bulletin will detect potential damage at the support strut end and limit the risk of THS lateral movement. 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 DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 SERVICE BULLETIN SUMMARY EVALUATION TABLE COST SAVING NO ETOPS 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 Component COMPD01 1 See SB Strut Component COMPD02 1 See SB Cotter-pin **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Component COMPD01 1 See SB Strut Component COMPD02 1 See SB Cotter-pin EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

18T 19U 40T 52X 58X 82Z 85Z 98W 99Y AFG AIC BAF BBC C9L CFC DGA FDX GAF HFY IRA IRM IYE JAV K1P KAC KZU MGL PCA PIA QAF R1T RJA ROT RZO SBI SGX SUD THY TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU 53.19.89.001 OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 2 6

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# @A310 SERVICE BULLETIN SUMMARY NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 532137-832-848-001: Inspection TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 5.00 **CONF 002 Task 532137-832-848-001: Inspection TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 4.50 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumptions

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 3 6

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL FR91

Z310



## A **B**

**B**

**B B**  **A**

TYPICAL 

## B AREA TO BE INSPECTED AREA TO BE INSPECTED

B_SB_532137_6_SAAA_01_01 Figure A-GSAAA - Sheet 01

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 4 6

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# @A310 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 310-203 310-221 310-222 310-304 310-308 310-322 310-324 310-325 (2) Effectivity by MSN 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356-0357 0362 0364 0367 0369 0372 0378 0394 0399 0407 0410 0413 0418-0419 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452 0454 0456-0458 0467 0472-0473 0478 0480-0484 0488-0492 0494-0500 0502-0503 0519-0520 0522-0524 0526-0527 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651-0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 (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. DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 SERVICE BULLETIN
OPERATOR MSN 18T 0473 19U 0399 40T 0413 52X 0410 58X 0431 82Z 0550 0551 85Z 0527 98W 0495 99Y 0489 AFG 0496 0497 AIC 0407 BAF 0367 0372 BBC 0594 0700 C9L 0652 CFC 0425 0441 0444 0446 0482 DGA 0418 0421 0422 FDX 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356 0362 0364 0369 0378 0394 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500 0539 0549 0552 0593 GAF 0434 0484 0498 0503 0522 0523 HFY 0565 IRA 0436 0671 IRM 0488 0499 0524 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 JAV 0357 0481 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526 PCA 0419 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0445 0490 0491 ROT 0636 0644 RZO 0571 0624 0651 0661 SBI 0520 SGX 0519 0562 SUD 0437 THY 0478 0480 0502 TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494

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# @A310 SERVICE BULLETIN (4) Configuration by MSN MSN CONFIGURATION 0162 0230 0237 0245 0248 0267 0278 0281 0283 0316 0331 0356 0357 0362 0364 0367 0369 0372 0378 0394 0399 0407 0410 0413 0418 0419 0421 0422 0425 0431 0434 0436 0437 0439 0441 0444 0445 0446 0447 0449 0452 0454 0456 0457 0458 0467 0472 0473 0478 0480 0481 0482 0483 0484 0488 0489 0490 0491 0492 0494 0495 0496 0497 0498 001

0499 0500 0502 0503 0519 0520 0522 0523 0524 0526 0527 0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647 0648 0649 0651 0652 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 002

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft on which Mod.No.06101D5165 is not embodied. **CONF 002 Config. 002 is valid for all the aircraft on which Mod.No.06101D5165 is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 Component COMPD01 1 Component COMPD02 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 Component COMPD01 1 Component COMPD02 1 **CONF ALL B. CONCURRENT REQUIREMENTS None

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# @A310 SERVICE BULLETIN
C. REASON (1) History The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame (FR)91. Any lateral movement is prevented by four 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 and support strut end have been found. (2) Objective/Action This Service Bulletin gives the instruction to do a repetitive inspection of the affected area on all A310 aircraft, to prevent a support strut rupture. After the inspection (depending on aircraft records and general visual inspection results), it is necessary to install a clamping device which will ensure the rod body end insert is kept in place. This installation is temporary pending the definition of a new strut which will be introduced through another Mandatory Modification Service Bulletin. (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 : **CONF 001 Task 532137-832-848-001: Inspection (1) Identify the support struts installed (2) Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends (3) Do a HFEC inspection of the strut ends after removal of the clamps (4) Remove the clamps from the THS support struts (5) Install the clamps on the THS support struts (6) Replace the THS support struts
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# @A310 SERVICE BULLETIN
**CONF 002 Task 532137-832-848-001: Inspection (1) Do a HFEC inspection of the Trimmable Horizontal Stabilizer (THS) support strut ends (2) Do a HFEC inspection of the strut ends after removal of the clamps (3) Remove the clamps from the THS support struts (4) Install the clamps on the THS support struts (5) Replace the THS support struts **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 Table 1,Config. 001 - High Frequency Eddy Current (HFEC) inspection of the THS support strut ends Condition Action Compliance time Repetitive interval All aircraft pre-mod 06101 High Frequency Eddy Current (HFEC) inspection of the THS support strut ends 24 months from SB issuance date NOTE : Do the GVI of the struts within 12 months from SB issuance date 24 months

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds and intervals given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

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# @A310 SERVICE BULLETIN
**CONF 002 Table 1, Config. 002 - High Frequency Eddy Current (HFEC) inspection of the THS support strut ends Condition Action Compliance time Repetitive interval From MSN 0499 to MSN 0706 High Frequency Eddy Current (HFEC) inspection of the THS support strut ends 12 months from SB issuance date 24 months

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the thresholds and intervals given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. **CONF ALL 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. For an explanation of the manhours and elapsed time, refer to the Gantt Chart given in Appendix 01 - Elapsed Time Assumptions . NOTE : The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. **CONF 001 Task 532137-832-848-001: Inspection Get Access 0.50 On Aircraft Identify the support struts installed 0.50 Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends 2.00

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# @A310 SERVICE BULLETIN
Task 532137-832-848-001: Inspection Do a HFEC inspection of the strut ends after removal of the clamps 2.00 Remove the clamps from the THS support struts 0.50 Install the clamps on the THS support struts 0.50 Replace the THS support struts 1.00 Close-Up 0.50 TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 5.00 **CONF 002 Task 532137-832-848-001: Inspection Get Access 0.50 On Aircraft Do a HFEC inspection of the Trimmable Horizontal Stabilizer (THS) support strut ends 2.00 Do a HFEC inspection of the strut ends after removal of the clamps 2.00 Remove the clamps from the THS support struts 0.50 Install the clamps on the THS support struts 0.50 Replace the THS support struts 1.00 Close-Up 0.50 TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 4.50 **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-00 06-41-00 20-21-12 24-00-00 53-10-47 55-10-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Illustrated Parts Catalog (IPC) 53-19-89 Non Destructive Test Manual (NTM) 53-19-47 Service Bulletin (SB) A310-53-2136 DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 7 6

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# @A310 SERVICE BULLETIN Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-20 **CONF 002 Aircraft Maintenance Manual (AMM) 06-21-00 06-31-00 06-41-00 20-21-12 24-00-00 53-10-47 55-10-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Illustrated Parts Catalog (IPC) 53-19-89 Non Destructive Test Manual (NTM) 53-19-47 Service Bulletin (SB) A310-53-2136 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-20 **CONF ALL K. PUBLICATION AFFECTED Impact on scheduled maintenance: Refer to MPD L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A310 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.

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# @A310 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 AIRBUS will not provide industry support for accomplishment of this Service Bulletin. 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 53-10-47, Page Block 401. Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Coating - Flexible Structure 04QAB2 As required Polysulfide Sealant-Low Adhesion Fillet Structure 06AEB2 As required Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required Non Aqueous Cleaner-General 08BAA9 As requiredCorrosion Preventive CompoundWater Displacing 12ADB1 As required Textile-Lint Free Cotton 14SBA1 As required (2) Components Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES R21449H 1 ROD

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# @A310 SERVICE BULLETIN
NOTE : Alternatively, it is possible to install PN R21449, PN R21449D, PN R21449G or PN R21449H, refer to IPC 53-19-89. 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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPD02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES MS24665-374 2 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 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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. (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 53-10-47, Page Block 401. (3) Special Tools None

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 532137-832-848-001 - Inspection 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. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. 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: 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 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.

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# @A310 SERVICE BULLETIN
Task Associated Data **CONF 001 Zone 310 Access Door 313AL Manpower TOTAL MANHOURS 7.50 ELAPSED TIME (HOURS) 5.00 **CONF 002 Zone 310 Access Door 313AL Manpower TOTAL MANHOURS 7.00 ELAPSED TIME (HOURS) 4.50 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 532137-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-00, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-20 (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 06-31-00, Page Block 001. (c) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
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# @A310 SERVICE BULLETIN (e) Torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (f) Remove and install the fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 532137-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 532137-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-00, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-20 (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 06-31-00, Page Block 001. (c) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (e) Torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (f) Remove and install the fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (2) Subtask 532137-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC

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# @A310 SERVICE BULLETIN 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 532137-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (c) Put the access platform(s) in position below the access door 313AL. (d) Open the access door 313AL.

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# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 532137-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (c) Put the access platform(s) in position below the access door 313AL. (d) Open the access door 313AL.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 17 6

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# @A310 SERVICE BULLETIN
**CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 532137-832-201-001 - Identify the support struts installed 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 References Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) Check the records of the THS support struts located at FR91 in tail cone, if struts replacement is recorded since aircraft Entry Into Service (EIS), within 12 months from Service Bulletin issuance date. Refer to Fig. A-GFAAA Sheet 01

. 1 If the complete records are not available since aircraft EIS:
a Do a General Visual Inspection (GVI) of the struts on aircraft within 12 months from Service Bulletin issuance date. <1> If the installed struts are not in accordance with the one given in Fig. A-GBAAA Sheet 01 , View B. <a> Report the inspection results to Airbus within 1 month. <b> No further action. <2> If the installed struts are in accordance with the one given in Fig. AGBAAA Sheet 01 , View B. <a> If clamps are installed, continue with SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut ends after removal of the clamps

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 18 6

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# @A310 SERVICE BULLETIN <b> If clamps are not installed, continue with SUBTASK 532137-280-201 001 Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends 2 If the complete records are available since aircraft EIS:
a If the struts were replaced since aircraft EIS. <1> Do a GVI of the struts on aircraft within 12 months from Service Bulletin issuance date. <a> If the installed struts are not in accordance with the one given in Fig. A-GBAAA Sheet 01 , View B. [1] Report the inspection results to Airbus within 1 month. [2] No further action. <b> If the installed struts are in accordance with the one given in Fig. A-GBAAA Sheet 01 , View B. [1] If clamps are installed, continue with SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut ends after removal of the clamps . [2] If clamps are not installed, continue with SUBTASK 532137-280-201 001 Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends . b If the struts were not replaced since aircraft EIS. <a> Report the inspection results to Airbus within 1 month. <b> No further action. (2) Subtask 532137-280-201-001 - Do a High Frequency Eddy Current (HFEC) inspection of the THS support strut ends Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 19 6

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# @A310 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 Non Destructive Test Manual (NTM) 53-19-47 -Part 6 Service Bulletin (SB) A310-53-2136 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) Clean the THS support struts with: Non Aqueous Cleaner-General 08BAA9 As required

and Textile-Lint Free Cotton 14SBA1 As required (b) Do an HFEC inspection of each strut end located at FR91 in tail cone as given in NTM 53-19-47 -Part 6 at Threshold given in para 1.E.(2), refer to Fig. A-GBAAA Sheet 01 , View B. Refer to Fig. A-GFAAA Sheet 02

. 1 If there is/are no crack(s) found on strut end, refer to Fig. A-GBAAA Sheet 01 , View C.
a Accomplish Service Bulletin No. A310-53-2136 before next flight. b Report the inspection results to Airbus within 1 month.
c Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 20 6

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# @A310 SERVICE BULLETIN
2 If there is/are crack(s) found on at least one strut end, refer to Fig. A-GBAAA Sheet 01 , View C.
a If the individual maximum crack length is more than 15.0 mm (0.591 in), or more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Replace the damaged strut by a new one before next flight, refer to SUBTASK 532137-831-201 001 Replace the THS support struts . <2> Accomplish Service Bulletin No. A310-53-2136 before next flight. <3> Report the inspection results to Airbus within 10 days. <4> Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months. b If the individual maximum crack length is equal or less than 15.0 mm (0.591 in), or not more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Accomplish Service Bulletin No. A310-53-2136 before next flight. <2> Report the inspection results to Airbus within 10 days. <3> Do SUBTASK 532137-280-202 001 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months. (3) Subtask 532137-280-202-001 - Do a HFEC inspection of the strut ends after removal of the clamps Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 53-19-47 , Part 6 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAA Inspection Flow Chart Sheet 01 Sheet 02 Sheet 03 (a) Remove clamp from each support strut end at interval given in para 1.E.(2) and refer to SUBTASK 532137-020-201 001 Remove the clamps from the THS support struts . DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 21 6

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# @A310 SERVICE BULLETIN (b) Do an HFEC inspection of each strut end where clamps were installed before next flight as per NTM 53-19-47 , Part 6, refer to Fig. A-GBAAA Sheet 01 , View B and Fig. A-GFAAA Sheet 03

. 1 If no crack(s) found on strut ends, refer to Fig. A-GBAAA Sheet 01 , View C.
a Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . b Report the inspection results to Airbus within 1 month.
c Do the work steps C.(3)(a) to C.(3)(b) again every 24 months. 2 If crack(s) found on at least one strut end, refer to Fig. A-GBAAA Sheet 01 , View C.
a If the individual maximum crack length is more than 15.0 mm (0.591 in), or more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Replace the damaged strut by a new one before next flight, refer to SUBTASK 532137-831-201 001 Replace the THS support struts . <2> Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . <3> Report the inspection results to Airbus within 10 days. <4> Do the work steps C.(3)(a) to C.(3)(b) again every 24 months. b If the individual maximum crack length is equal or less than 15.0 mm (0.591 in), or not more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . <2> Report the inspection results to Airbus within 10 days. <3> Do the work steps C.(3)(a) to C.(3)(b) again every 24 months. (4) Subtask 532137-020-201-001 - 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 NON SPECIFIC
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 22 6

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# @A310 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-GBBAA Removal/Installation of the Clamps Sheet 01 (a) From each support strut, remove: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. 2 Nut NAS1726-5E Item (4) Retain 2 Washer NAS1149D0563K Item (3) Retain 2 Bolt NSA5031-5-38 Item (2) Retain 2 Clamp A5347310320000 Item (1) Retain (b) Remove the remaining sealant from the support struts and clean them with: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. Non Aqueous Cleaner-General 08BAA9 As required
Textile-Lint Free Cotton 14SBA1 As required (5) Subtask 532137-420-201-001 - 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 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 23 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Coating - Flexible Structure 04QAB2 Polysulfide Sealant-Low Adhesion Fillet Structure 06AEB2 As required Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required Corrosion Preventive Compound-Water Displacing 12ADB1 As required

References Fig. A-GBBAA Removal/Installation of the Clamps Sheet 01 (a) To the interface surfaces of the clamps, Item (1), apply: Refer to Fig. A-GBBAA Sheet 01 , Views A to D.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: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required
(c) On each support strut, install: Refer to Fig. A-GBBAA Sheet 01 , Views B to D. NOTE : Consider that the clamps must be installed within the cylindrical area only. NOTE: Make sure that the dimension of the gap is between 3.0 mm and 3.5 mm (0.118 in and 0.138 in). NOTE: Before installation of the clamp, mark the correct position with a pen.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 24 6

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# @A310 SERVICE BULLETIN 2 Nut NAS1726-5E Item (4) Retained at removal 2 Washer NAS1149D0563K Item (3) Retained at removal 2 Bolt NSA5031-5-38 Item (2) Retained at removal 2 Clamp A5347310320000 Item (1) Retained at removal (d) Protect the visible edges of the sealant with: Refer to Fig. A-GBBAA Sheet 01 , Views C and D. Coating - Flexible Structure 04QAB2 As required (e) On the clamps and fasteners which you have installed, apply: Refer to Fig. A-GBBAA Sheet 01 , Views C and D. Corrosion Preventive Compound-Water Displacing 12ADB1 As required

(6) Subtask 532137-831-201-001 - Replace the THS support struts Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES R21449H 1 ROD NOTE : Alternatively, it is possible to install PN R21449, PN R21449D, PN R21449G or PN R21449H, refer to IPC 53-19-89.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 25 6

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# @A310 SERVICE BULLETIN
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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPD02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES MS24665-374 2 PIN 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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. References Aircraft Maintenance Manual (AMM) 53-10-47, Page Block 401 55-10-11, Page Block 401 Illustrated Parts Catalog (IPC) 53-19-89 (a) Remove the affected THS support strut CAUTION : ONLY ONE SUPPORT STRUT MAY BE REMOVED AT ONE TIME. CAUTION : IF ALL SUPPORT STRUTS ARE TO BE REMOVED, TWO STRUTS P/N 98A27407568000 MUST BE INSTALLED, REFER TO AMM 53-10-47, Page Block 401. NOTE: If necessary, you can lift the THS by using slings to ease the strut removal, refer to AMM 55-10-11, Page Block 401. (b) Remove the affected THS support strut, refer to AMM 53-10-47, Page Block 401. (c) Install the affected THS support strut, refer to AMM 53-10-47, Page Block 401 and use these parts: 1 Rod Assy R21449H NOTE: Alternatively, it is possible to install PN R21449, PN R21449D, PN R21449G or PN R21449H, refer to IPC 53-19-89. and 2 Pin-Cotter MS24665-374

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 26 6

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# @A310 SERVICE BULLETIN
**CONF 002 (1) Subtask 532137-280-201-002 - Do a HFEC inspection of the Trimmable Horizontal Stabilizer (THS) support strut ends Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC 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 Non Destructive Test Manual (NTM) 53-19-47 -Part 6 Service Bulletin (SB) A310-53-2136 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAB Inspection Flow Chart Sheet 01 Sheet 02 (a) Clean the THS support struts with: Non Aqueous Cleaner-General 08BAA9 As required

and Textile-Lint Free Cotton 14SBA1 As required (b) Do a Special Detailed Inspection of the Trimmable Horizontal Stabilizer (THS) support struts located at FR91 in tail cone at Threshold given in para 1.E.(2), refer to Fig. A-GBAAA Sheet 01 , View B. Refer to Fig. A-GFAAB Sheet 01

. (c) If clamps are installed, continue with SUBTASK 532137-280-202 002 Do a HFEC inspection of the strut ends after removal of the clamps
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 27 6

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# @A310 SERVICE BULLETIN (d) If clamps are not installed: 1 Do an HFEC inspection of all 8 strut ends as per NTM 53-19-47 -Part 6, before next flight, refer to Fig. A-GBAAA Sheet 01 , View B.
a If there is/are crack(s) found on at least one strut end, refer to Fig. AGBAAA Sheet 01 , View C. <1> If the individual maximum crack length is more than 15.0 mm (0.591 in), or more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <a> Replace the damaged strut by a new one before next flight, refer to SUBTASK 532137-831-201 001 Replace the THS support struts . <b> Accomplish Service Bulletin No. A310-53-2136 before next flight. <c> Report the inspection results to Airbus within 10 days. <d> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months. <2> If the individual maximum crack length is equal or less than 15.0 mm (0.591 in), or not more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <a> Accomplish Service Bulletin No. A310-53-2136 before next flight. <b> Report the inspection results to Airbus within 10 days. <c> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months. b If there is/are no crack(s) found on strut ends, refer to Fig. A-GBAAA Sheet 01 , View C. <1> Accomplish Service Bulletin No. A310-53-2136 before next flight. <2> Report the inspection results to Airbus within 1 month. <3> Do SUBTASK 532137-280-202 002 Do a HFEC inspection of the strut ends after removal of the clamps every 24 months. (2) Subtask 532137-280-202-002 - Do a HFEC inspection of the strut ends after removal of the clamps Work Zones and Access Panels Zone Access/Work location 310

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 28 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills NON SPECIFIC References Non Destructive Test Manual (NTM) 53-19-47 , Part 6 Fig. A-GBAAA Inspection Area Sheet 01 Fig. A-GFAAB Inspection Flow Chart Sheet 01 Sheet 02 (a) Remove clamp from each support strut end, refer to SUBTASK 532137-020-201 001 Remove the clamps from the THS support struts . (b) Do a HFEC inspection of each strut end where clamps were installed as per NTM 53-19-47 , Part 6 before next flight, refer to Fig. A-GBAAA Sheet 01 , View B and Fig. A-GFAAB Sheet 02

. 1 If no cracks found on strut ends, refer to Fig. A-GBAAA Sheet 01 , View C.
a Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . b Report the inspection results to Airbus within 1 month.
c Do the work steps C.(2)(a) to C.(2)(b) again every 24 months. 2 If crack(s) found on at least one strut end, refer to Fig. A-GBAAA Sheet 01 , View C.
a If the individual maximum crack length is more than 15.0 mm (0.591 in), or more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Replace the damaged strut by a new one before next flight, refer to SUBTASK 532137-831-201 001 Replace the THS support struts . <2> Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . <3> Report the inspection results to Airbus within 10 days. <4> Do the work steps C.(2)(a) to C.(2)(b) again every 24 months. b If the individual maximum crack length is equal or less than 15.0 mm (0.591 in), or not more than 4 cracks per strut end are equal or less than 15.0 mm (0.591 in). <1> Install clamp on each strut end before next flight, refer to SUBTASK 532137-420-201 001 Install the clamps on the THS support struts . DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 29 6

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# @A310 SERVICE BULLETIN <2> Report the inspection results to Airbus within 10 days. <3> Do the work steps C.(2)(a) to C.(2)(b) again every 24 months. (3) Subtask 532137-020-201-001 - 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 NON SPECIFIC 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-GBBAA Removal/Installation of the Clamps Sheet 01 (a) From each support strut, remove: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. 2 Nut NAS1726-5E Item (4) Retain 2 Washer NAS1149D0563K Item (3) Retain 2 Bolt NSA5031-5-38 Item (2) Retain 2 Clamp A5347310320000 Item (1) Retain (b) Remove the remaining sealant from the support struts and clean them with: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. Non Aqueous Cleaner-General 08BAA9 As required
Textile-Lint Free Cotton 14SBA1 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 30 6

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# @A310 SERVICE BULLETIN (4) Subtask 532137-420-201-001 - 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 Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Coating - Flexible Structure 04QAB2 Polysulfide Sealant-Low Adhesion Fillet Structure 06AEB2 As required Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required Corrosion Preventive Compound-Water Displacing 12ADB1 As required

References Fig. A-GBBAA Removal/Installation of the Clamps Sheet 01 (a) To the interface surfaces of the clamps, Item (1), apply: Refer to Fig. A-GBBAA Sheet 01 , Views A to D.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: Refer to Fig. A-GBBAA Sheet 01 , Views A to D. Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 31 6

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# @A310 SERVICE BULLETIN (c) On each support strut, install: Refer to Fig. A-GBBAA Sheet 01 , Views B to D. NOTE : Consider that the clamps must be installed within the cylindrical area only. NOTE: Make sure that the dimension of the gap is between 3.0 mm and 3.5 mm (0.118 in and 0.138 in). NOTE: Before installation of the clamp, mark the correct position with a pen. 2 Nut NAS1726-5E Item (4) Retained at removal 2 Washer NAS1149D0563K Item (3) Retained at removal 2 Bolt NSA5031-5-38 Item (2) Retained at removal 2 Clamp A5347310320000 Item (1) Retained at removal (d) Protect the visible edges of the sealant with: Refer to Fig. A-GBBAA Sheet 01 , Views C and D. Coating - Flexible Structure 04QAB2 As required (e) On the clamps and fasteners which you have installed, apply: Refer to Fig. A-GBBAA Sheet 01 , Views C and D. Corrosion Preventive Compound-Water Displacing 12ADB1 As required

(5) Subtask 532137-831-201-001 - Replace the THS support struts Work Zones and Access Panels Zone Access/Work location 310 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 32 6

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# @A310 SERVICE BULLETIN
Material necessary to do the job Component COMPD01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES R21449H 1 ROD NOTE : Alternatively, it is possible to install PN R21449, PN R21449D, PN R21449G or PN R21449H, refer to IPC 53-19-89. 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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. Component COMPD02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES MS24665-374 2 PIN 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. NOTE: The above list of components is not an AIRBUS Kit, the required parts shall be ordered as necessary through the given channel. References Aircraft Maintenance Manual (AMM) 53-10-47, Page Block 401 55-10-11, Page Block 401 Illustrated Parts Catalog (IPC) 53-19-89 (a) Remove the affected THS support strut CAUTION : ONLY ONE SUPPORT STRUT MAY BE REMOVED AT ONE TIME. CAUTION : IF ALL SUPPORT STRUTS ARE TO BE REMOVED, TWO STRUTS P/N 98A27407568000 MUST BE INSTALLED, REFER TO AMM 53-10-47, Page Block 401. NOTE: If necessary, you can lift the THS by using slings to ease the strut removal, refer to AMM 55-10-11, Page Block 401. (b) Remove the affected THS support strut, refer to AMM 53-10-47, Page Block 401. (c) Install the affected THS support strut, refer to AMM 53-10-47, Page Block 401 and use these parts: 1 Rod Assy R21449H DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 33 6

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# @A310 SERVICE BULLETIN
NOTE : Alternatively, it is possible to install PN R21449, PN R21449D, PN R21449G or PN R21449H, refer to IPC 53-19-89. and 2 Pin-Cotter MS24665-374 **CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 532137-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Manpower Resources Skills NON SPECIFIC (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 313AL. (c) Remove the access platform(s). **CONF 002 (1) Subtask 532137-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Manpower Resources Skills NON SPECIFIC

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 34 6

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# @A310 SERVICE BULLETIN (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Close the access door 313AL. (c) Remove the access platform(s).

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 35 6

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# @A310 SERVICE BULLETIN

**CONF 001

COMPLETE RECORDS AVAILABLE SINCE

AIRCRAFT EIS

DO A GENERAL VISUAL INSPECTION OF STRUTS ON AIRCRAFT STRUT(S) REPLACED SINCE AIRCRAFT

REPORT THE INSPECTION RESULTS TO AIRBUS

WITHIN 1 MONTH

NO FURTHER ACTION

CLAMPS INSTALLED

CONTINUE ON

SHEET 02 CONTINUE ON SHEET 03 NO YES

YES NO

NO YES

REPORT THE INSPECTION RESULTS TO AIRBUS

WITHIN 1 MONTH

NO FURTHER ACTION NO YES EIS

STRUT(S) AFFECTED INSTALLED

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 **NOTE:** CHECK, IF STRUTS REPLACEMENT IS RECORDED SINCE AIRCRAFT ENTRY INTO SERVICE (EIS)

B_SB_532137_6_FAAA_01_02 Figure A-GFAAA - Sheet 01 Inspection Flow Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 36 6

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# @A310 SERVICE BULLETIN

**CONF 001
CONTINUED FROM SHEET 01

CRACK(S) FOUND ON AT LEAST ONE STRUT END NO YES

ACCOMPLISH SERVICE BULLETIN NO. A310−53−2136 YES

NO

REPLACE THE DAMAGED

STRUT BY A NEW ONE CRACKS WITHIN THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS: −WITHIN 10 DAYS WHEN FINDING −WITHIN 1 MONTH WHEN NIL FINDING DO A HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF EACH STRUT END

AT THRESHOLD GIVEN IN PARA 1.E.(2) OF THIS SERVICE BULLETIN

REPEAT THE INSPECTION AT INTERVALS GIVEN IN PARA 1.E.(2) BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

B_SB_532137_6_FAAA_02_03 Figure A-GFAAA - Sheet 02 Inspection Flow Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 37 6

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# @A310 SERVICE BULLETIN

**CONF 001

CONTINUED FROM SHEET 01

REMOVE CLAMP FROM EACH SUPPORT

STRUT END AT INTERVAL GIVEN IN PARA 1.E.(2) OF THIS SERVICE BULLETIN

DO A HFEC INSPECTION OF EACH STRUT END WHERE CLAMPS WERE INSTALLED

CRACK(S) FOUND ON AT LEAST ONE STRUT END NO YES

NO

REPLACE THE DAMAGED

STRUT BY A NEW ONE RE−INSTALL CLAMP ON EACH STRUT END YES CRACKS WITHIN THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS: −WITHIN 10 DAYS WHEN FINDING −WITHIN 1 MONTH WHEN NIL FINDING

REPEAT THE INSPECTION AT INTERVALS GIVEN IN PARA 1.E.(2) BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

BEFORE NEXT FLIGHT

B_SB_532137_6_FAAA_03_02 Figure A-GFAAA - Sheet 03 Inspection Flow Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 38 6

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# @A310 SERVICE BULLETIN

**CONF 002

CLAMPS INSTALLED CONTINUE ON SHEET 02 NO YES DO A SPECIAL DETAILED INSPECTION OF THE TRIMMABLE HORIZONTAL STABILIZER (THS) SUPPORT STRUTS LOCATED AT FR91 IN TAIL CONE AT THRESHOLD GIVEN IN PARA 1.E.(2) OF THIS SERVICE BULLETIN

CRACK(S) FOUND ON AT LEAST ONE STRUT NO YES END

NO YES

REPLACE THE DAMAGED STRUT BY A NEW ONE ACCOMPLISH SERVICE BULLETIN NO. A310−53−2136

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 **NOTE:** CRACKS WITHIN THE GIVEN LIMITS

REPORT THE INSPECTION

RESULTS TO AIRBUS: −WITHIN 10 DAYS WHEN FINDING −WITHIN 1 MONTH WHEN NIL FINDING REPEAT THE INSPECTION AT INTERVALS GIVEN IN PARA 1.E.(2) BEFORE NEXT FLIGHT DO A HFEC INSPECTION OF ALL 8 STRUT ENDS

B_SB_532137_6_FAAB_01_04 Figure A-GFAAB - Sheet 01 Inspection Flow Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 39 6

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# @A310 SERVICE BULLETIN

**CONF 002

CONTINUED FROM SHEET 01 REMOVE CLAMP FROM EACH SUPPORT STRUT END

DO A HFEC INSPECTION OF ALL 8 STRUT ENDS

CRACK(S) FOUND ON AT LEAST ONE STRUT YES NO END

YES NO

RE−INSTALL CLAMP AT EACH SUPPORT STRUT END REPLACE THE DAMAGED STRUT CRACKS WITHIN THE GIVEN LIMITS

REPORT THE INSPECTION RESULTS TO AIRBUS: −WITHIN 10 DAYS WHEN FINDING −WITHIN 1 MONTH WHEN NIL FINDING

REPEAT THE INSPECTION AT INTERVALS GIVEN IN PARA 1.E.(2) BEFORE NEXT FLIGHT

B_SB_532137_6_FAAB_02_03 Figure A-GFAAB - Sheet 02 Inspection Flow Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 40 6

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# @A310 SERVICE BULLETIN

**CONF ALL

FR91 

### B

**B**

**B**

AREA TO BE INSPECTED 

### C **C**



## B TYPICAL STRUT TO BE INSPECTED PN R21449 PN R21449D PN R21449G OR PN R21449H



## C TYPICAL TYPICAL CRACKS 

### B

Z310 

### A



## A

B_SB_532137_6_BAAA_01_01 Figure A-GBAAA - Sheet 01 Inspection Area
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 41 6

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# @A310 SERVICE BULLETIN

**CONF ALL



### C **C** FR91

TYPICAL 

### D

(1) (2) (3)

(4) 

## C

**D B**  **A**

**D**

(2) (3)

(4) (1) 

### B

**B B**  **B** Z310 

### A

PROTECT WITH COMPOUND (MAT. NO. 12ADB1) 01 02 **NOTE:** 01 02 3.0 mm TO 3.5 mm (0.118 in TO 0.138 in)

CONSIDER THAT THE CLAMPS MUST BE INSTALLED WITHIN THE CYLINDRICAL AREA ONLY B_SB_532137_6_BBAA_01_02 Figure A-GBBAA - Sheet 01 Removal/Installation of the Clamps
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 42 6

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# @A310 SERVICE BULLETIN

**CONF 001

FR91

Z310



## A **A** 

## 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 A310−53−2137
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 A

B

B A A B B A 

### B

**B**

**B B** 



## B 43 1 2

B_SB_532137_6_AAAA_01_01 Figure A-GAAAA - Sheet 01 Inspection Report
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 43 6

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# @A310 SERVICE BULLETIN

**CONF 001 

## INSPECTION REPORT STRUT NUMBER RECORDS COMPLETE SINCE AIRCRAFT EIS STRUT REPLACED SINCE AIRCRAFT EIS STRUT AFFECTED CLAMPS INSTALLED

YES NO YES NO YES NO YES NO 1

YES NO YES NO YES NO YES NO 2

YES NO YES NO YES NO YES NO 3

YES NO YES NO YES NO YES NO 4

STRUT NUMBER

1

2

3

4 CRACK QUANTITY LENGTH CRACK 1 LENGTH CRACK 2 LENGTH CRACK 3 LENGTH CRACK 4 STRUT REPLACED INSTALLED PARTNUMBER YES NO YES NO YES NO YES NO A B END POS

A B A B A B LENGTH CRACK 5

B_SB_532137_6_AAAA_02_02 Figure A-GAAAA - Sheet 02 Inspection Report
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 44 6

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# @A310 SERVICE BULLETIN

**CONF 002

FR91

Z310



## A **A** 

## 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 A310−53−2137
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 A

B

B A A B B A 

### B

**B**

**B B** 



## B 43 1 2

B_SB_532137_6_AAAB_01_01 Figure A-GAAAB - Sheet 01 Inspection Report
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 45 6

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# @A310 SERVICE BULLETIN

**CONF 002INSPECTION REPORTCRACKQUANTITYLENGTHCRACK 1LENGTHCRACK 2LENGTHCRACK 3LENGTHCRACK 4STRUTREPLACEDINSTALLEDPARTNUMBERYESNOYESNOYESNOYESNOABENDPOSABABABCLAMPSINSTALLEDYESNOYESNOYESNOYESNOSTRUTNUMBER1234LENGTHCRACK 5

B_SB_532137_6_AAAB_02_01 Figure A-GAAAB - Sheet 02 Inspection Report
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 46 6

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# @A310 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumptions

**CONF 001 **ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−53−2137**

GET ACCESS MH ET/S

TOTAL MANHOURS SB ELAPSED TIME STEPS

0.50 0.50

5 0 0.50 0.50

2.00 2.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. ARE NOT REFLECTED IN THIS GANTT CHART. 01
02 **NOTES:** PER

1

1

1

: : SB ELAPSED TIME (HOURS) 123 4 6

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS IDENTIFY THE SUPPORT STRUTS INSTALLED

7 8 2.00 2.00 1 DO A HFEC INSPECTION OF THE STRUT ENDS AFTER REMOVAL OF THE CLAMPS 1 REMOVE THE CLAMPS FROM THE THS SUPPORT STRUTS
0.50 0.50 1 INSTALL THE CLAMPS ON THE THS SUPPORT STRUTS
1.00 1.00 1 REPLACE THE THS SUPPORT STRUTS
0.50 0.50 1 CLOSE−UP

7.50 5.00 DO A HFEC INSPECTION OF ENDS

0.50 0.50 THE THS SUPPORT STRUT

B_SB_532137_6_ABAA_01_01 Figure A-GABAA - Sheet 01 Gantt Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumptions

**CONF 002 **ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−53−2137**

GET ACCESS MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 7.00 4.50 STEPS

0.50 0.50

5 0 2.00 2.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. ARE NOT REFLECTED IN THIS GANTT CHART. 01
02 **NOTES:** PER

1

1

: : SB ELAPSED TIME (HOURS) 123 4 6

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS 7 8 2.00 2.00 1 DO A HFEC INSPECTION OF THE STRUT ENDS AFTER REMOVAL OF THE CLAMPS 0.50 0.50 1 REMOVE THE CLAMPS FROM THE THS SUPPORT STRUTS
0.50 0.50 1 INSTALL THE CLAMPS ON THE THS SUPPORT STRUTS
1.00 1.00 1 REPLACE THE THS SUPPORT STRUTS
0.50 0.50 1 CLOSE−UP DO A HFEC INSPECTION OF THE THS SUPPORT STRUT ENDS

B_SB_532137_6_ABAB_01_02 Figure A-GABAB - Sheet 01 Gantt Chart
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 2 6

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# @A310 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 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 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 14/14 SERVICE BULLETIN No.: A310-53-2137 REVISION No.: 00 - Feb 14/14 Page: 1 6

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