EASA AD No.: 20 1 5 - 0 0 08

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No . : 20 1 5 - 0 0 08

Date: 1 5 J anuary 2015 Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation

. This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordan ce with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

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### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330 and A340 aeroplanes TCDS Number s : EASA.A.004, EASA.A.015 F oreign AD: Not applicable Supersedure: None



### ATA 29 Hydraulic Power – Ram Air Turbine Actuator – Identification / Modification Manufacturer(s): Airbus (formerly Airbus I ndustrie) Applicability: Airbus A330 - 201, A330 - 202, A330 - 203, A330 - 223, A330 - 243, A330 - 223F, A330 - 243F, A330 - 301, A330 - 302, A330 - 303, A330 - 321, A330 - 322, A330 - 323, A330 - 341, A330 - 342 and A330 - 343 aeroplanes, all manufacturer serial numbers (MSN), except those on which Airbus modif ication 204067 has been embodied in production. Airbus A340 - 211, A340 - 212, A340 - 213, A340 - 311, A340 - 312, A340 - 313, A340 - 541, A340 - 542, A340 - 642 a nd A340 - 643 aeroplanes, all MSN

. Reason: During a scheduled Ram Air Turbine (RAT) operational test on an A330 aeroplane, the RAT did not deploy in automatic mode. The subsequent investigation conducted by the RAT manufacturer Hamilton Sundstrand (HS) and Arkwin Industries, revealed that th is failure to deploy was due to an inadequate stroke margin in the manu facturing shimming procedure of the actuator deployment solenoid s . This condition, if not corrected , could possibly result in reduced control of the aeroplane , particularly if occurring following a total engine flame out, or during a total loss of normal electrical power generation. Prompted by this unsafe condition, Airbus issued Service Bulletin ( SB ) A330 - 29 - 3126, SB A340 - 29 - 4097 and SB A340 - 29 - 5025 , providing instructions to identify the manufacturer , part number (P/N) and serial number (s/n) of the RAT actuator , and to modify the shimming procedure for the affected RAT actuator . For the reasons described above, this AD requires identification of the affectedEASA AD No.: 20 1 5 - 0 0 08

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. RAT actuator s and , depending on its configuration (modified or not), the accomplishment of applicable corrective actions. Effective Date: 2 9 January 2015 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 30 months after the effective date of this AD, in accordance with the instructions of Airbus SB A330 - 29 - 3126 or SB A340 - 29 - 4097 or SB A340 - 29 - 5025, as applicable to aeroplane model, accomplish the actions as required by paragraph ( 2 ) or ( 3 ) of this AD, as applicable to aeroplane type. (2) For A330 and A340 - 200/300 aeroplanes , i f the manufacturer of the actuator of the RAT is Arkwin Industries, i dentify the P/N and s/n of the installed RAT actuator , and : ( 2

. 1 ) I f the identified actuator P/N and s/n are listed in HS SB No. ERPS06M - 29 - 21 as already modified , but not yet re - identified, re identify the actuator and th e RAT. ( 2 .2 ) I f the identified actuator P/N and s/n are listed in HS SB No. ERPS06M - 29 - 21 as not modified , modify the RAT ac tuator and re i dentify the RAT. ( 2

. 3 ) I f the actuator identification plate is missing , or the P/N and s/n are not listed in HS SB No. ERPS06M - 29 - 21, modify the RAT actuator and re - identify the RAT. (3) For A340 - 500/600 aeroplanes , i dentify the P/N and s/n of the installed RAT actuator , and: ( 3

. 1 ) If the identified actuator P/N and s/n are listed in HS SB No. ERPS33T - 29 - 7 as already modified , but not yet re - identified, re identify the actuator and the RAT. ( 3

. 2 ) If the identified actuator P/N and s/n are listed i n HS SB No. ERPS33T - 29 - 7 as not modified , modify the RAT actuator and re identify the RAT. ( 3

. 3 ) If the actuator identification plate is missing or the P/N and s/n are not listed in HS SB No. ERPS33T - 29 - 7, modify the RAT actuator and re - identify the RAT. ( 4 ) From the effective date of this AD, installation on an aeroplane of any RAT actuator or RAT as listed by P/N in Table 1 of this AD is allowed , under the conditions as specified in paragraph (4.1) or (4.2) of this AD, as applicable to aeroplane type

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Tab le 1

– Affected RAT and Actuators A ffected A eroplanes RAT P/N RAT Actuator P/N

A330 - 200, A330 - 200F, A330 - 300 , A340 - 200 and A340 - 300 1702934C

1702934D 766351A 768084A 770379A 770952C 770952D 770952E 5912958

5915768

A340 - 500 and - 600 772722H 772722J 772722L 5912536

5915769EASA AD No.: 20 1 5 - 0 0 08

TE. CAP.0011 0 - 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA - Internet/Intranet. ( 4 .1) For A330 and A340 - 200/300 aeroplanes, a RAT actuator , or a RAT , having a s/n listed as affected and modified in HS SB No. ERPS06M - 29 - 21, and the RAT has been re - identified in accordance with the instructions of Airbus SB A330 - 29 - 3126 or SB A340 - 29 - 4097, as applicable to aeroplane model. ( 4 .2) For A340 - 500/600 aeroplanes, a RAT actuator , or a RAT , having a s/n listed as affected and modified in HS SB No. ERPS33T - 29 - 7, and the RAT has been re - identified in accordance with the instructions of Airbus SB A340 - 29 - 5025. ( 5 ) For A330 and A340 - 200/300 aeroplanes, modification of an aeroplane as required by this AD also constitutes compliance with the requirements of EASA AD 2011 - 0197, EASA AD 2011 - 0204R1 and EASA AD 2013 - 0274 for that aeroplane. ( 6 ) For A340 - 500/600 aeroplanes, modification of an aeroplane as required by this AD also constitutes compliance with the requirements of EASA AD 2011 - 0204R1 and EASA AD 2013 - 0274 for that aeroplane. Ref. Public ations: Airbus SB A330 - 29 - 31 26 original issue dated 12 June 201 4

. Airbus SB A340 - 29 - 409 7 original issue dated 12 June 2014. Airbus SB A340 - 29 - 50 25 original issue dated 1 6 June 2014. The use of later approved revisions of the above documents is acceptable for compliance with the requirements of this AD. Hamilton Sundstrand SB No. ERPS06M - 29 - 21 original issue dated 27 May 2014

. Hamilton Sundstrand SB No. ERPS33T - 29 - 7 original issue dated 06 June 2014

. Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD

. 2. This AD was posted on 10 November 2014 as PAD 14 - 16 5 for consultation until 0 8 December 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Safety Informatio n Section, Certification Directorate, EASA. E - mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in this AD, please contact: AIRBUS

– Airworthiness Office

– EAL. E - mail: airworthiness.A330 - A340@airbus.com

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