EASA AD No.: 2012-0210

TE.CAP.00110-003 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0210

Date: 11 October 2012

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the Europe an 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, P art 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 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 A ctuator (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 manufact urer 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 whi ch 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 norma l operation, only in case of ballscrew rupture. Analysis results have shown that such rupture could happen during the current inspection interval imposed by t he Maintenance Review Board Report (MRBR), task 274000-12.
Corrosion on the lower splines, in case of ballscre w rupture, may lead to loss of transmission of THSA torque loads from the ballscre w to the tie-bar and consequent THSA blowback, which could result in los s of control of the aeroplane.
For the reasons described above, this AD requires r eduction 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. Co nfirm revision status through the EASA-Internet/Int ranet. Effective Date: 25 October 2012

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly:
(1) Within the compliance time indicated in Table 1 of this AD, as applicable, and thereafter, at intervals not to exceed 12 000 F H or 4 400 FC, whichever occurs first, accomplish a THSA ballscrew shaft integrity check in accordance with the instructions of Airbus Servi ce Bulletin (SB) A330- 27-3191 or SB A340-27-4186, as applicable to aeropl ane 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 o r since the last THSA ball screw shaft integrity check accompli shed in accordance with the MRBR task 274000-12 or in accor dance with SB A330-27-3179 or SB A340-27-4175 (check requ ired in case of type II or type III findings), as applicabl e.

B Within 1 000 FH after the effective date of this AD but without exceeding 16 000 FH since the aeroplane first fligh t or since the last THSA ball screw shaft integrity check acco mplished in accordance with the MRBR task 274000-12 or in accor dance with SB A330-27-3179 or SB A340-27-4175 (check requ ired in case of type II or type III findings), as applicabl e.

(2) If, during any check as required by paragraph ( 1) of this AD, the THSA ballscrew shaft integrity is not affirmed, before n ext 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 a eroplane 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 req uired by paragraph (1) of this AD.

Ref. Publications: Airbus SB A330-27-3191 at Origin al issue dated 07 June 2012. Airbus SB A340-27-4186 at Original issue dated 07 J une 2012.
The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 Com ments, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.
4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS – Airworthiness Off ice – EIAL; E-mail: airworthiness.A330-A340@airbus.com

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