# @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 - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103 - REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR 13682D23322 MINOR None NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame 91. Any lateral movement is prevented by four diagonal support struts. During maintenance, support struts have been found cracked on some aircraft. The affected area is the strut end and typical cracks are longitudinal. On some aircraft, several cracks per support strut have been found. Inspection Service Bulletin A310-53-2137 inspects the struts for cracks. This Service Bulletin installs reinforcing clamps on the strut ends as a temporary solution. A permanent solution is expected to be introduced by Service Bulletin at a later date. By installing the clamp, the circumferential stresses in the rod-ends are reduced and the circular shape of the rod end is supported. As a result, the tendency to stress corrosion of the rod ends is stopped (or partially reduced) due to the lower circumferential stresses. Furthermore, the steel insert in the rod ends is properly kept in place due to maintaining the circular shape of the rod ends even in case of existing cracks.
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 SERVICE BULLETIN SUMMARY Depending on the result of the check (aircraft record or physical check) required in inspection Service Bulletin A310-53-2137, it is possible that clamps installation is not required on one or some struts (mixture of clamp installation is possible). 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 ETOPS 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 Kit 532136D01R00 1 2,100.00 Clamps EFFECTIVITY 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 Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) as per effectivity specified in this (these) Service Bulletin(s): Service Bulletin No. A310-53-2137 NOTE: A310-53-2137 FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS 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.: A310-53-2136 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 Task 532136-831-848-001: Modification TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 2.00 APPENDICES None

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 3 6

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL FR91



## A **B**

**B**

**B B**  Z310 

### A

TYPICAL CLAMP TO BE ADDED CLAMP TO BE ADDED



## B

B_SB_532136_6_SAAA_01_01 Figure A-GSAAA - Sheet 01

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 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 - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103 - REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS MODIFICATION No.: 13682D23322 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 Kit 532136D01R00 is only applicable on aircraft on which specific struts with PN R21449, PN R21449D, PN R21449G or PN R21449H are installed. This modification is applicable by Service Bulletin only. (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

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 1 6

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# @A310 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 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 DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 2 6

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# @A310 SERVICE BULLETIN

OPERATOR MSN TSC 0447 0472 0483 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494 (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 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 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 Kit 532136D01R00 1 Consumable CMLD01 As required B. CONCURRENT REQUIREMENTS Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the following Service Bulletin(s) as per effectivity specified in this (these) Service Bulletin(s): Service Bulletin No. A310-53-2137 NOTE: A310-53-2137 FUSELAGE - TAIL CONE - THS SUPPORT STRUTS AT FR91 - INSPECTION FOR CRACKS C. REASON (1) History The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame 91. Any lateral movement is prevented by four diagonal support struts.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 3 6

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# @A310 SERVICE BULLETIN During maintenance, support struts have been found cracked on some aircraft. The affected area is the strut end and typical cracks are longitudinal. On some aircraft, several cracks per support strut have been found. Inspection Service Bulletin A310-53-2137 inspects the struts for cracks. (2) Objective/Action This Service Bulletin installs reinforcing clamps on the strut ends as a temporary solution. A permanent solution is expected to be introduced by Service Bulletin at a later date. (3) Advantages By installing the clamp, the circumferential stresses in the rod-ends are reduced and the circular shape of the rod end is supported. As a result, the tendency to stress corrosion of the rod ends is stopped (or partially reduced) due to the lower circumferential stresses. Furthermore, the steel insert in the rod ends is properly kept in place due to maintaining the circular shape of the rod ends even in case of existing cracks. (4) Operational/Maintenance Consequences Depending on the result of the check (aircraft record or physical check) required in inspection Service Bulletin A310-53-2137, it is possible that clamps installation is not required on one or some struts (mixture of clamp installation is possible). D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 532136-831-848-001: Modification (1) Install the clamps at the THS support struts E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin must be accomplished, when applicable, immediately after the first inspection in accordance with the Inspection Service Bulletin A310-53-2137 requirement. 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.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 4 6

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# @A310 SERVICE BULLETIN
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. Task 532136-831-848-001: Modification Get Access 0.50 On Aircraft Install the clamps at the THS support struts 1.00 Close-Up 0.50 TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 2.00 H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator items. For the definition of MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +2.198 KG (+4.8457 LB) Effect on Balance +105.641 KGM (+764.101 LB.FT ) I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-00 06-41-00 20-21-12 24-00-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Service Bulletin (SB) A310-53-2137 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-20 51-40-30 Weight and Balance Manual (WBM) Chapter 1-00-07

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 5 6

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# @A310 SERVICE BULLETIN
K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 53-10-47 53-10-88 53-19-21 Illustrated Parts Catalog (IPC) 53-19-89 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 6 6

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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: NOTE: Kit 532136D01R00 is only applicable on aircraft on which specific struts with PN R21449, PN R21449D, PN R21449G or PN R21449H are installed. Kit 532136D01R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 2590 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 532136D01R00 Cost 2,100.00 USD Availability 120 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION As a special policy applied to this Service Bulletin, AIRBUS will provide a 10% reduction to the applicable kits sales prices given in the paragraph Price and Availability for orders placed before Dec 31/19. 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 DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 7 6

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# @A310 SERVICE BULLETIN
E-mail : monitored.retrofit@airbus.com Tel : (33) 5 67 19 06 22 Fax : (33) 5 61 93 27 45 C. LIST OF COMPONENTS Kit 532136D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 A5347310320000 16 CLAMP 2 NSA5031-5-38 16 BOLT 3 NAS1149D0563K 16 WASHER 4 NAS1726-5E 16 NUT 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: Kit 532136D01R00 is only applicable on aircraft on which specific struts with PN R21449, PN R21449D, PN R21449G or PN R21449H are installed. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials 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 requiredCorrosion Preventive CompoundWater Displacing 12ADB1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 8 6

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# @A310 SERVICE BULLETIN
F. TOOLING None

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 9 6

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# @A310 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 10 6

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 532136-831-848-001 - Modification 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. Task Associated Data Zone 310

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 11 6

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# @A310 SERVICE BULLETIN

Access Door 313AL Manpower TOTAL MANHOURS 2.00 ELAPSED TIME (HOURS) 2.00 A. GENERAL (1) Subtask 532136-910-201-001 - 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 51-40-30 (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 fasteners in accordance with SRM 51-40-20. (g) Apply sealant in accordance with SRM 51-24-00. (h) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30. (i) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’ column. (j) If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 12 6

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# @A310 SERVICE BULLETIN (2) Subtask 532136-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 532136-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Work location Frame 91 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 access door 313AL.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 13 6

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# @A310 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 532136-420-201-001 - Install the clamps at the THS support struts Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 91 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 532136D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 A5347310320000 16 CLAMP 2 NSA5031-5-38 16 BOLT 3 NAS1149D0563K 16 WASHER 4 NAS1726-5E 16 NUT NOTE: Kit 532136D01R00 is only applicable on aircraft on which specific struts with PN R21449, PN R21449D, PN R21449G or PN R21449H are installed. 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 Corrosion Preventive Compound-Water Displacing 12ADB1 As required

References Fig. A-GBAAA Installation of the Clamps at the THS Support Struts Sheet 01
(a) Apply: Refer to Fig. A-GBAAA Sheet 01 , View C.

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 14 6

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# @A310 SERVICE BULLETIN
Polysulfide SealantLow Adhesion Fillet Structure 06AEB2 As required
to the interface surfaces of the clamps, Item 1. 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) Apply to the bolts, Item 2: Refer to Fig. A-GBAAA Sheet 01 , View C. Non Hardening Jointing Putty-High Temp. Area Str 06LDG2 As required

and install: 16 Clamp A5347310320000 Item 1 with: Refer to Fig. A-GBAAA Sheet 01 , Views A 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. 16 Bolt NSA5031-5-38 Item 2 16 Washer NAS1149D0563K Item 3 16 Nut NAS1726-5E Item 4 (c) Protect the visible edges of the sealant, 06AEB2, with: Coating-- Flexible Structure 04QAB2 As required (d) On the clamps and fasteners which you have installed, apply: Corrosion Preventive Compound-Water Displacing 12ADB1 As required

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 15 6

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# @A310 SERVICE BULLETIN
D. TEST None E. CLOSE-UP (1) Subtask 532136-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Access Door 313AL Work location Frame 91 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).

DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 16 6

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# @A310 SERVICE BULLETIN

**CONF ALL



### C **C** FR91

TYPICAL 

### D

1 2

3

4 

## C **B A** 

**D B** 

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

### A



## D 2 3

4 1
PROTECT WITH COMPOUND (MAT. NO. 12ADB1) 01 02 **NOTE:** 01 02

CONSIDER THAT THE CLAMPS MUST BE INSTALLED WITHIN THE CYLINDRICAL AREA ONLY 3.0 mm TO 3.5 mm (0.118 in TO 0.138 in)

B_SB_532136_6_BAAA_01_03 Figure A-GBAAA - Sheet 01 Installation of the Clamps at the THS Support Struts
DATE: Feb 14/14 SERVICE BULLETIN No.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 17 6

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# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - FUSELAGE TAIL SECTION AND TAIL CONE FR80-FR103 - REINFORCE THS SUPPORT STRUTS AT FR91 BY CLAMPS MODIFICATION No.: 13682D23322 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.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 1 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

# @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.: A310-53-2136 REVISION No.: 00 - Feb 14/14 Page: 1 6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.