EASA AD No

_ 200g...0202R1 

## EASA

Date: 15April 2010
Note: This Airworthiness Directive](AD) is issued by EASA, acting in accordance with Regulation (Ee) No 215/2008 on behalf of the European Community, lis Member Slales and of the European third countries thai participate in the activities of EASA under Article 56 of that Regulation 

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This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In ao:!ordance with EC 2042/2003 Anne~ I, Part M.A,301, the continuing airworthiness of an aircrall: shall be ensured by accomplishing a~y applicable ADs Consequently, no person may operate an aircraft 10which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency lEe 2042/2003 Annex I, Part MA303} or agreed with the Authority of the Stioteof Registry [EC 216/2008, Article 14(4) exemption]. 

### Type Approval Holder's Name: 

### AIRBUS , 

### 1ype/Modei designation(s) : 

### fj'.330andA340 aeroplanes reDS Numbers: Foreign AD: Revision:



### ATA 34
Manufacturer(s): Applicability:

Reason: EASAA004, EA$AA015
No! applicable This AD revises EASA AD 2009-0202-E dated 21 September 2009 (Corrected on 22 September 2009) 

### I I Navigation - Pitot Probe dUiCk-Disconnect Union - Torque Check I I I Airbus (formerly AIRBUS IND~STR!E) AIRBUS A330-201, A330-202, ~330-203, A33Q.-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 A34Q-211, A340-212, k340-213, A340-311, A340-312, A340-313, A340-541, A340-542, A340-642 and A340-643 aeroplanes, all manufacturer serial numbers, 

# I iffitted with Goodrich Pilot Probes Part Number (PIN) 0851 HL, having serial numbers (sIn) 267328 through F70714 inclusive. Several reports have recently bben received of loose pneumatic quickdisconnect unions on Goodrichlpitot probes 

### PIN0851 

### HLThese may be the result of mis-torque ofthe affected unions atequipment manufacturing level. Investigations are still on-goinglto determine the root cause(s)_ This condition, ifnot corrected, could lead toan air leak, resulting in incorrect total pressure measurement and consequent erroneous Calibrated Airspeed (CAS)/MACH parameters deliv~red bythe Air Data Computer (ADC). As aprecautionary measure, t~iSAD requires atorque check ofthe pneumatic quick-disconnect union on certain Goodrich PIN 0851 HL pitot probes and corrective action, dt:lpending on findings. 

### I This AD has been republished to remove an erroneous reference to Appendix Afrom the Reason section asJo Appendix was attached tothis AD. This AD is revised in order to ekclude from the torque-check required by paragraph (4) ofthis AD those pitot probes marked with a red torque checkmark. 

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# I 'EA;MSA"'~F:m=m:-;';1O;;------------------'--------------"p~,=g=,C'=1~2EASA AD No,: 2009-0202R1
Effective Date: Original issue: 23 September e009 Revision 1 : 29 April 2010 Required Action(s) Required as indicated: 

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. and Compliance (1) Unless accomplished previously, within 5days after the effectIve date of Time(s): this AD atoriginal issue, p~rform atorque check ofthe pneumatic quickdisconnect union ofeach Goodrich PIN 0851HL pilot probe, identified by sin inthe Applicability section ofthis AD, and depending on findings, before next flight, apply thd associated corrective action in accordance with instructions defined inlAirbus All Operators Telex (AOT) A330- 34A3235 Revision 01 orAOT A340-34A4241 Revision 01 orAOT A340- 34A5074 Revision 01, as ~pplicable toaeroplane model. 

### (2) Within 10days after acco~Plishment ofthe torque check required by paragraph (1) ofthis AD, r~port the results, including nofindings, to (3) Airbus. 

### I Torque check ofthe pneumatic quick-disconnect union accomplished before the effective date ofthis AD in accordance with the instructions of Airbus AOT A330-34A3235 atoriginal issue orAOT A340-34A4241 at original issue orAOT A340-34A5074 atoriginal issue, as applicable to aeroplane model, isconsidered acceptable forcompliance with the requirements of paragraphl (1) ofthis AD. (4) After the effective date ofthis AD atoriginal issue, when a PIN 0851 Hl pitot probe identified by

### s/~inthe Applicability ofthis AD is installed on an aeroplane, before nextflight after installation, perform the torquecheck inaccordance with tlherequirements of paragraph (1) ofthis AD. (5) Requirements of paragrapr (4) ofthis AD are no longer required ifan intact redtorque check mark isvisible across the interface ofthe pneumatic quick disconnett union and the union mount.
, Ref. Publications: Airbus AOT A330-34A3235 at6riglnal issue or Revision 01. Airbus AOT A340-34A4241 at briginal issue or Revision 01. Airbus AOT A340-34A5074 atoriginal issue or Revision 01. The use of later approved revisions ofthese documents isacceptable for compliance with the requiremepts ofthis AD. Remarks: I



# ,. Ifrequested and appropriately substantiated, EASA can approve Alternative Methods ofCor\,pliance forthis AD. 

# I 2. The safety assessment ha1 requested for the original issue ofthis AD not to implement the full consJltation process and an immediate publication and notification. 

### I 3. Enquiries regarding this AI] should be referred tothe Airworthiness Directives, Safety Manage~ent 

### & Research Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu. 4. For any question concemi1g the technical content ofthe requirements in this AD, please contact: AIRBUS SAS
- Airworthiness Office
- EAL Fax: +33 5

### 61 934580_ E-mail: airworthiness.A33d-A340@airbus.com.
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# I EASA Form 110 Page 212