EASA AD No _200g...0202R1

EASA

Date: 15 April 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 I

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 10 which 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 Stiote of Registry [EC 216/2008, Article 14(4) exemption].

Type Approval Holder's Name:

AIRBUS

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1ype/Modei designation(s) :

fj'.330 and A340 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

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Navigation - Pitot Probe dUiCk-Disconnect Union - Torque Check

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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

if fitted 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 PIN 0851 HL These may be the

result of mis-torque of the affected unions at equipment manufacturing level.

Investigations are still on-goinglto 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 deliv~red by the Air Data Computer (ADC).

As a precautionary measure, t~iS AD requires a torque check of the

pneumatic quick-disconnect union on certain Goodrich PIN 0851 HL pitot

probes and corrective action, dt:lpending on findings.

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This AD has been republished to remove an erroneous reference to Appendix

A from the Reason section as Jo Appendix was attached to this AD.

This AD is revised in order to ekclude from the torque-check required by

paragraph (4) of this AD those pitot probes marked with a red torque checkmark. I

I 'EA;MSA"'~F:m=m:-;';1O;;------------------'--------------"p~,=g=,C'=1~2
EASA AD No,: 2009-0202R1

Effective Date: Original issue: 23 September e009

Revision 1 : 29 April 2010

Required Action(s) Required as indicated: I .

and Compliance (1) Unless accomplished previously, within 5 days after the effectIve date of

Time(s): this AD at original issue, p~rform a torque check of the pneumatic quickdisconnect union of each Goodrich PIN 0851HL pilot probe, identified by

sin in the Applicability section of this 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 or AOT A340-34A4241 Revision 01 or AOT A340-

34A5074 Revision 01, as ~pplicable to aeroplane model.

(2) Within 10 days after acco~Plishment of the torque check required by

paragraph (1) of this AD, r~port the results, including no findings, to

(3)

Airbus. I

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 paragraphl(1) of this AD.

(4) After the effective date of this AD at original issue, when a PIN 0851 Hl

pitot probe identified by s/~ in the Applicability of this AD is installed on

an aeroplane, before next flight after installation, perform the torquecheck in accordance with tlhe requirements of paragraph (1) of this AD.

(5) Requirements of paragrapr (4) of this AD are no longer required if an

intact red torque check mark is visible across the interface of the

pneumatic quick disconnett union and the union mount.

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Ref. Publications: Airbus AOT A330-34A3235 at 6riglnal issue or Revision 01.

Airbus AOT A340-34A4241 at briginal 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 requiremepts of this AD.

Remarks:

I

,. If requested and appropriately substantiated, EASA can approve

Alternative Methods of Cor\,pliance for this AD.

I 2. The safety assessment ha1 requested for the original issue of this AD not

to implement the full consJltation process and an immediate publication

and notification. I

3. Enquiries regarding this AI] should be referred to the Airworthiness

Directives, Safety Manage~ent & Research Section, Certification

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

4. For any question concemi1g the technical content of the 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