EASA AD No.: 2013-0251

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0251

[Correction: 16 October 2013]

Date: 15 October 2013

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 EC 2042/2003 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 

[EC 2042/2003 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 Number: EASA.A.004 and EASA.A.015

Foreign AD: Not applicable

Supersedure: None

ATA 27 Flight Controls – Spoiler Servo Control / Hydraulic Locking 

Function – Operational Test

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, 

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).

Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313,

A340-541, A340-542, A340-643 and A340-642 aeroplanes, all MSN.

Reason: During post-flight maintenance checks accomplished on an A330 and on an 

A340 aeroplane, it was identified that seven spoiler servo-controls MZ series 

had lost their hydraulic locking function. The results of the subsequent technical 

investigation accomplished in-shop by the part supplier confirmed the system 

failure was due to a sheared seal on the blocking valve, ensuring the blocking 

function of the spoiler. It is suspected that the seal damage may have occurred 

during accomplishment of a modification to fit a new design of maintenance 

cover on wing, required by EASA AD 2008-0160.

This condition, if not detected and corrected, in combination with one engine 

inoperative at take-off, could result in reduced control of the aeroplane.

Prompted by these findings, Airbus issued All Operators Telex (AOT) A330-

27A3185 and AOT A340-27A4181 to request a one-time operational test of the 

Hydraulic Locking Function for aeroplanes on which MZ type Spoiler Servo 

Control (SSC) Part Number (P/N) MZ4339390-12 or P/N MZ4306000-12 are 

fitted, and EASA issued AD 2012-0009 to require accomplishment of this test.
EASA AD No.: 2013-0251

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Since that AD was issued, Airbus re-assessed the situation and determined 

that it is necessary to introduce repetitive inspections of the SSC, irrespective 

of SSC type. Airbus issued three SBs for those repetitive inspections on all 

A330, A340, and A340-500/600 aeroplanes.

For the reason describe above, this AD requires repetitive operational tests of

the hydraulic locking function of the SSC installed on the Blue and Yellow 

hydraulic circuits, irrespective of SSC type, and, depending on test results, 

replacement of the SSC.

This AD has been re-published to correct the date (month) of publication.

Effective Date: 29 October 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) Initially, within the compliance time defined in the Table 1 of this AD, and,

thereafter, at intervals not to exceed 48 months, accomplish an operational 

test of the hydraulic locking function on each SSC (any type), when fitted 

on Blue or Yellow hydraulic circuits, in accordance with the instructions of 

Airbus SB A330-27-3195, or SB A340-27-4188, or SB A340-27-5059, as 

applicable.

Table 1 Initial Operational Test Threshold

Compliance time, whichever occurs later, A or B

A

Within 48 months since aeroplane first flight, or since 

accomplishment of an operational test in accordance with the 

instructions of Airbus AOT A330-27A3185 or AOT A340-

27A4181, as applicable

B Within 24 months after the effective date of this AD

(2) If, during any operational test as required by paragraph (1) of this AD, the

hydraulic locking function of a SSC fails the test, before next flight, replace 

the affected SSC with a serviceable part, in accordance with the 

instructions of Airbus SB A330-27-3195, or SB A340-27-4188, or

SB A340-27-5059, as applicable.

(3) Replacement of a SSC does not constitute terminating action for the 

repetitive operational tests as required by paragraph (1) of this AD.

Ref. Publications: Airbus AOT A330-27A3185, dated 04 January 2012.

Airbus AOT A340-27A4181, dated 04 January 2012.

Airbus SB A330-27-3195, original issue dated 07 December 2012.

Airbus SB A340-27-4188, original issue dated 07 December 2012.

Airbus SB A340-27-5059, original issue dated 10 April 2013.

The use of later approved revisions of these documents is acceptable for 

compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 29 August 2013 as PAD 13-131 for consultation 

until 26 September 2013. 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, Executive 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 – EIAS;

Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com.