EASA AD No.: 2009-0202-E 

EASA Form 111 Page 1/2

EASA EMERGENCY AIRWORTHINESS 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 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 operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise 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, Article 14(4) exemption]. 

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 ( formerly AIRBUS INDUSTRIE) 

Applicability: 

AIRBUS A330-201, A330-202, A330-203, 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, A340-213, A340-311, A340-312, A340-313, 

A340-541, A340-542, A340-642 and A340-643 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 lead 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 Appendix to this AD has been published. 

Effective Date: 23 September 2009 
EASA 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 date 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 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. 

(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 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) of this AD. 

(4) After the effective date of this AD, when a P/N 0851HL pitot probe 

identified by s/n in the Applicability 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) 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 immediate publication and notification. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail: ADs@easa.europa.eu. 

4. For any question concerning the technical 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.