EASA AD No.: 2011-0138

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0138

Date: 20 July 2011

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

Foreign AD : Not applicable

Supersedure : This AD supersedes EASA AD 2009-0202R 1 dated 15 April 2010.



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

Manufacturer(s): Airbus ( fo rmerly AIRBUS INDUSTRIE)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, - A330-243F, A330-301, A330-302, A330- 303, A330-321, A330-322, A330-323, A330-341, A330-342 and A330-343 aeropl anes, 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, EASA issued Emergency AD 2009-0202 to require a torque check of the pneumatic quick-disconnect union on certain Goodrich P/N 0851HL pitot probes and corrective action, depending on findings. EASA AD 2009-0202-E was subsequent ly republished to remove an erroneous reference to Appendix A from the Reason section, as no Appendix was attached to this AD. AD 2009-0202 was later revised to exclude pitotEASA AD No.: 2011-0138

EASA Form 110 Page 2/2 probes marked with a red torque che ck-mark from the torque-check required by paragraph (2.1) of this AD. This AD retains the requirement s of EASA AD 2009-0202R1, which is superseded, and expands the Applicabilit y to include the newly certified Model A330-223F and Model A330-243F aeroplanes.

Effective Date: 03 August 2011

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously: (1) For all aeroplanes identified in the Applicability section of this AD, except A330-223F and A330-243F aeroplanes, (1.1) Within 5 days after 23 Septem ber 2009 [the effective date of EASA AD 2009-0202 at original issue], perform a torque check of the pneumatic quick-disconnect union of each Goodrich P/N 0851HL pitot probe, identified by s/n in t he Applicability section of this AD, and depending on findings, before next flight, apply the associated corrective action in accordance with instructions 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. (1.2) Within 10 days after accomp lishment of the torque check as required by paragraph (1.1) of this AD, report the results, including no findings, to Airbus. (1.3) A torque check of the pneumatic quick-disconnect union, accomplished before 23 September 2009, in accordance with the instructions of Airbus AOT A330-34A3235 at Original 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 (1.1) of this AD. (2) For all aeroplanes identified in the Applicability section of this AD : (2.1) After 23 September 2009, each time when a P/N 0851HL pitot probe, identified by s/n in the App licability section of this AD, is installed on an aeroplane, before next flight after installation, perform the torque-check in accordance with the requirements of paragraph (1.1) of this AD. (2.2) Torque checks as specified in paragraph (2.1) of this AD are no longer required if an intact red torque check mark is visible across the interface of the pneumatic quick disconnect union and the union mount.

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 Safety Information Section, Executive 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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