EASA AD No.: 2015-0008

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0008

Date: 15 January 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 accordance 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 operate 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A330 and A340 aeroplanes

TCDS Numbers: EASA.A.004, EASA.A.015

Foreign AD: Not applicable

Supersedure: None

ATA 29 Hydraulic Power – Ram Air Turbine Actuator – Identification / 

Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

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 modification 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 and 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 this failure to deploy was due to an 

inadequate stroke margin in the manufacturing shimming procedure of the 

actuator deployment solenoids.

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 affected 
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RAT actuators and, depending on its configuration (modified or not), the 

accomplishment of applicable corrective actions.

Effective Date: 29 January 2015

Required Action(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, if the manufacturer of the 

actuator of the RAT is Arkwin Industries, identify the P/N and s/n of the 

installed RAT actuator, and:

(2.1) If 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, reidentify the actuator and the RAT.

(2.2) If the identified actuator P/N and s/n are listed in HS SB No. 

ERPS06M-29-21 as not modified, modify the RAT actuator and reidentify the RAT.

(2.3) If 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, identify 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, reidentify the actuator and the RAT. 

(3.2) If the identified actuator P/N and s/n are listed in HS SB No. 

ERPS33T-29-7 as not modified, modify the RAT actuator and reidentify 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.

Table 1 – Affected RAT and Actuators

Affected Aeroplanes 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

5915769
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(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. Publications: Airbus SB A330-29-3126 original issue dated 12 June 2014.

Airbus SB A340-29-4097 original issue dated 12 June 2014.

Airbus SB A340-29-5025 original issue dated 16 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 14-165 for consultation 

until 08 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 Information 

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.