EASA AD No.: 2012-0210 

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 EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2012-0210 

Date: 11 October 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 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): 

A330-300 and A340-200/-300 aeroplanes 

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

Foreign AD: Not applicable 

Supersedure: None 

ATA 27 Flight Controls – Trimmable Horizontal Stabilizer Actuator (THSA) 

Ballscrew – Integrity Check 

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), if fitted with THSA having Part Number (P/N) 47147-500 or P/N 47147-

700. 

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

aeroplanes, all MSN, if fitted with THSA having P/N 47147-500 or P/N 47147-

700. 

Reason: Since the issuance of EASA AD 2012-0061 which addresses the corrosion 

identified in service on THSA P/N 47147-500 and P/N 47147-700 at the level of 

the ballscrew lower splines, further analyses have been conducted to 

determine the need for any additional action. 

The ballscrew lower splines are not loaded in normal operation, only in case of 

ballscrew rupture. Analysis results have shown that such rupture could happen 

during the current inspection interval imposed by the Maintenance Review 

Board Report (MRBR), task 274000-12. 

Corrosion on the lower splines, in case of ballscrew rupture, may lead to loss of 

transmission of THSA torque loads from the ballscrew to the tie-bar and 

consequent THSA blowback, which could result in loss of control of the 

aeroplane. 

For the reasons described above, this AD requires reduction of the check 

interval of MRBR task 274000-12.
EASA AD No.: 2012-0210 

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 2/2 

Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

Effective Date: 25 October 2012 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously: 

(1) Within the compliance time indicated in Table 1 of this AD, as applicable, 

and thereafter, at intervals not to exceed 12 000 FH or 4 400 FC, 

whichever occurs first, accomplish a THSA ballscrew shaft integrity check 

in accordance with the instructions of Airbus Service Bulletin (SB) A330-

27-3191 or SB A340-27-4186, as applicable to aeroplane type. 

Table 1 – THSA ballscrew shaft initial check

Compliance time (whichever occurs later, A or B) 

A 

Within 12 000 FH since the aeroplane first flight or since the 

last THSA ball screw shaft integrity check accomplished in 

accordance with the MRBR task 274000-12 or in accordance 

with SB A330-27-3179 or SB A340-27-4175 (check required in 

case of type II or type III findings), as applicable. 

B 

Within 1 000 FH after the effective date of this AD but without 

exceeding 16 000 FH since the aeroplane first flight or since 

the last THSA ball screw shaft integrity check accomplished in 

accordance with the MRBR task 274000-12 or in accordance 

with SB A330-27-3179 or SB A340-27-4175 (check required in 

case of type II or type III findings), as applicable. 

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

ballscrew shaft integrity is not affirmed, before next flight, replace the 

THSA with a serviceable THSA in accordance with the instructions of SB 

A330-27-3191 or SB A340-27-4186, as applicable to aeroplane type. 

(3) Replacement of a THSA, as required by paragraph (2) of this AD, with a 

THSA having P/N 47147-500 or P/N 47147-700 does not constitute 

terminating action for the repetitive checks as required by paragraph (1) of 

this AD. 

Ref. Publications: Airbus SB A330-27-3191 at Original issue dated 07 June 2012. 

Airbus SB A340-27-4186 at Original issue dated 07 June 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. Based on the required actions and the compliance time, EASA have 

decided to issue of a Final AD with Request for Comments, postponing the 

public consultation process until 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 – Airworthiness Office – EIAL; 

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