EASA AD No : 2009-0260

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2009-0260 [Correction: 14 December 2009]

Date: 10 December 2009

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 th e 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 opera te an aircraft to which an AD applies, except in accordance with t he requirements of that AD, unless otherwise specified by the Ag ency [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) exemptio n]. 

### Type Approval Holder’s Name :

AIRBUS Type/Model designation(s) :
A330 and A340 aeroplanes

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

Foreign AD : Not applicable

Supersedure : None



### ATA 29 Hydraulic Power – Ram Air Turbine (RAT) Balance Weight Screws – Inspection / Replacement

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-2 03, A330-223, A330-243, A330-301, A330-302, A330-303, A330-321, A330 -322, A330-323, A330-341, A330-342 and A330-343 aeroplanes, all manufacturer serial numbers if equipped with a Hamilton Sundstrand RAT turbine lower gear box assembly, as identified byPart Number (P/N) in Hamilton Sundstrand Service Bulletin (SB) ERPS06G29-6. Airbus A340-211, A340-212, A340- 213, A340-311, A340-312 and A340-313 aeroplanes, all manufacturer serial numbers if equipped with Hamilton Sundstrand RAT turbine lower gear box assembly, as identified by P/N in Hamilton Sundstrand SB ERPS06G-29-6. Airbus A340-541, A340-542, A340-642 and A340-643 aeroplanes, all manufacturer serial numbers if equipped with Hamilton Sundstrand RAT turbine lower gear box assembly, as identified by P/N in Hamilton Sundstrand SB ERPS33G-29-1.

Reason: Hamilton Sundstrand (HS), the manufacture r of the RAT, reported the failure of a balance weight fastening screw on the RAT cover during a wind tunnel test. After investigation, it has been di scovered that a batch of screws, which are used to attach the balance wash ers of the Hamilton Sundstrand RAT turbine lower gear box assembly, has not been subject to the correct heat treatment and the screws are conseq uently exposed to potential fracture. This condition, if not corrected, might lead to the ejection of screw heads and consequently to the detachment of t he associated balance washers. The lossEASA AD No : 2009-0260

EASA Form 110 Page 2/3 of balance washers could increase RAT vibrations, which might lead to a possible detachment of RAT parts, and thus to damage to the aeroplane and risk of injury to persons on the ground. For the reasons described above, this AD requires the identification of the affected RAT turbine lower gear box assemblies and replacement of all balance screws or, in case balance wa sher detachment is found, replacement of the RAT turbine lower gear box assembly. This AD has been republished to correct some editorial errors.

Effective Date: 24 December 2009

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Before the next RAT spin test, or within 3 000 flight hours (FH) or 8 months after the effective date of this AD, whichever occurs first:

- Identify the P/N and serial number (s /n) of the RAT turbine lower gear box assembly, and

- In case the P/N and s/n of the RAT turbine lower gear box assembly are listed in the applicable HS SB, or if the P/N or s/n cannot be identified, inspect the RAT turbine lower gear box assembly in accordance with the instructions of Airbus All Operator Telex (AOT) A330-29A3110 or Airbus AOT A340-29A4085 or Airbus AOT A340-500/600 29A5015, as applicable to aeroplane model: (1.1) If all balance screws are fitted on the turbine, within 3 000 FH or 8 months, whichever occurs first afte r the effective date of this AD, either: - replace the RAT turbine lower gear box assembly, or - replace all balance screws on the RAT turbine lower gear box assembly. (1.2) If one or more screws are fractured but the associated balance washers are still fitted on the RAT tu rbine lower gear box assembly, then before next flight, perform one of the actions as specified in paragraph (1.1) of this AD. (1.3) If one or more screws are fractured and any balance washer is missing, before next flight, replace the RAT turbine lower gear box assembly. (2) Within 10 days after accomplishment of the inspection required by paragraph (1) of this AD, report the results, including no findings, to Airbus. (3) After the effective date of this AD, do not install on an aeroplane a RAT turbine lower gear box assembly as identified by P/N in HS SB ERPS06G-29-6 or HS SB ERPS33G-29-1, as applicable to aeroplane model, unless it has been inspected and, if necessary, corrected in accordance with the requirements of this AD.

Ref. Publications: Airbus AOT A330-29A3110 at original issue. Airbus AOT A340-29A4085 at original issue. Airbus AOT A340-500/600-29A5015 at original issue. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.
Hamilton Sundstrand SB ERPS06G-29-6. Hamilton Sundstrand SB ERPS33G-29-1.

Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.EASA AD No : 2009-0260

EASA Form 110 Page 3/3 2. This AD was posted on 07 October 2009 as PAD 09-122 for consultation until 04 November. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail ADs@easa.europa.eu

. 4. For any questions concerning the tech nical content of the requirements in this AD, please contact: AIRBUS – Airworthiness Office – EAL; E-mail: A330-A340@airbus.com

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