EASA AD No.: 2009-0202-E

EASA Form 111 Page 1/2 

## EASA EMERGENCY AIRW ORTHINESS DIRECTIVE

AD No.: 2009-0202-E [Corrected: 22 September 2009]

Date: 21 September 2009

Note: This Emergency 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 partici pate 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 a ccomplishing any applicable ADs. Consequently, no person may opera te an aircraft to which an AD applies, except in accordance with th e 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 Numbers : EASA.A.004, EASA.A.015

Foreign AD : Not applicable

Supersedure : None



### ATA 34 Navigation – Pitot Probe Quick-Disconnect Union – Torque Check

Manufacturer(s): Airbus ( fo rmerly 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, AIRBUS A340-211, A340-212, A340-2 13, A340-311, A340-312, A340-313, A340-541, A340-542, A340-642 and A340-6 43 aeroplanes, all manufacturer serial numbers, if fitted with Goodrich Pitot Probes Part Number (P/N) 0851HL, having serial numbers (s/n) 267328 through 270714 inclusive.

Reason: Several reports have recently been received of loose pneumatic quickdisconnect unions on Goodrich pitot probes P/N 0851HL. These may be the result of mis-torque of the affected unions at equipment manufacturing level. Investigations are still on-going to determine the root cause(s). This condition, if not corrected, could le ad to an air leak, resulting in incorrect total pressure measurement and consequent erroneous Calibrated Airspeed (CAS)/MACH parameters delivered by the Air Data Computer (ADC). As a precautionary measure, this AD requires a torque check of the pneumatic quick-disconnect union on certain Goodrich P/N 0851HL pitot probes and corrective action, depending on findings. This AD has been republished to remove an erroneous reference to Appendix A from the Reason section. No Appendi x to this AD has been published.
Effective Date: 23 September 2009EASA AD No.: 2009-0202-E

EASA Form 111 Page 2/2 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) Within 5 days after the effective dat e of this AD, perform a torque check of the pneumatic quick-disconnect union of each Goodrich P/N 0851HL pitot probe, identified by s/n in the Applicability section of this AD, and depending on findings, before next fligh t, apply the associated corrective action in accordance with instructio ns defined in AIRBUS All Operators Telex (AOT) A330-34A3235 Revision 01 or AOT A340-34A4241 Revision 01 or AOT A340-34A5074 Revision 01, as applicable to aeroplane model. (2) Within 10 days after accomplishment of the torque check required by paragraph (1) of this AD, report the results, including no findings, to Airbus. (3) Torque check of the pneumatic quick-disconnect union accomplished before the effective date of this AD in accordance with the instructions of Airbus AOT A330-34A3235 at Origi nal issue or AOT A340-34A4241 at Original issue or AOT A340-34A5074 at Original issue, as applicable to aeroplane model, is considered acceptable for compliance with the requirements of paragraph (1) of this AD. (4) After the effective date of this AD, when a P/N 0851HL pitot probe identified by s/n in the Applicabilit y of this AD is installed on an aeroplane, before next flight after in stallation, perform the torque-check in accordance with the requirements of paragraph (1) of this AD.

Ref. Publications: Airbus AOT A330-34A3235 at original issue or Revision 01. Airbus AOT A340-34A4241 at original issue or Revision 01. Airbus AOT A340-34A5074 at original issue or Revision 01. 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 safety assessment has requested not to implement the full consultation process and an immedi ate publication and notification. 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 question concerning the tec hnical content of the requirements in this AD, please contact: AIRBUS SAS – Airworthiness Office - EAL Fax: +33 5 61 93 45 80. E-mail: airworthiness.A330-A340@airbus.com

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