EASA AD No.: 2012-0009

EASA Form 110 Page 1/2

EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0009

Date: 13 January 2012

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 EC 1702/2003, Part 21A.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].

Type Approval Holder’s Name :

AIRBUS

Type/Model designation(s) :

A330 and A340-200/-300 aeroplanes

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

Foreign AD : Not applicable

Supersedure : None

ATA 27 Flight Controls – Spoiler Servo Controls (SSC) – Identification /

Operational Test

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus 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 and A340-313 

aeroplanes, all MSN.

Reason: Two operators have reported that several spoilers did not remain locked in 

the retracted position (lifted up without order) after manual depressurization 

of the corresponding hydraulic circuit during flight test.

Subsequent checks on ground confirmed that, for each affected spoiler 

surface, the spoiler was fitted with one MZ-type Spoiler Servo Control (SSC) 

(Part Number (P/N) MZ4339390-12 or P/N MZ4306000-12).

The results of the investigations on the affected SSCs, done by the supplier,

revealed that the loss of the hydraulic locking function – which is ensured by 

a blocking valve – was due to an internal leakage caused by a sheared seal. 

This seal is installed at the left end of the blocking valve. 

During the on-wing modification of the maintenance cover, blocking valve 

movement may have damaged the seal on the outer diameter of the blocking 

valve assembly, causing the loss of the hydraulic locking function.

This condition, if not detected and corrected, if occurring during take-off and 

go-around phases in combination with one engine inoperative, could

jeopardise the aeroplane safe flight.

For the reasons described above, this AD requires the identification of the 
EASA AD No.: 2012-0009

EASA Form 110 Page 2/2

installed SSCs, to perform an operational test of the hydraulic locking function 

of the affected SSCs and to accomplish the applicable corrective actions if 

any discrepancy is detected during the operational test. This AD also requires 

reporting operational test results to Airbus.

Effective Date: 27 January 2012

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) Within 90 days after the effective date of this AD, identify the P/N of all 

SSCs installed on aeroplane in accordance with the instructions of Airbus 

All Operators Telex (AOT) A330-27A3185 or AOT A340-27A4181, as 

applicable to aeroplane type.

A review of aeroplane maintenance records is acceptable to identify the 

P/N of the installed SSC, provided that the P/N of the installed SSC can 

be conclusively determined from that review.

(2) If one of the installed SSC has a P/N MZ4339390-12 or a P/N 

MZ4306000-12 (MZ-Type), within 90 days after the effective date of this 

AD, accomplish an operational test of the hydraulic locking function at 

each position fitted with a MZ-type SSC. If any discrepancy is detected 

during this operational test, within the compliance time defined in the 

Airbus AOT A330-27A3185 or AOT A340-27A4181, as applicable to 

aeroplane type, depending on the hydraulic circuit, accomplish the 

applicable corrective actions in accordance with the instructions of Airbus 

AOT A330-27A3185 or AOT A340-27A4181, as applicable to aeroplane 

type.

(3) Within 30 days after accomplishment of the operational test as required 

by paragraph (2) of this AD, report the results of the test, including no 

findings, to Airbus.

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

Airbus AOT A340-27A4181 dated 04 January 2012.

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. The required actions and the risk allowance have granted the issuance of 

a Final AD with Request for Comments, postponing the public 

consultation process after publication.

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 SAS –Airworthiness Office – EIAL, Email: airworthiness.A330-A340@airbus.com.