EASA AD No.: 2015-0134

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0134

Date: 08 July 2015

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 EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 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

[EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A330 and A340 aeroplanes

TCDS Numbers: EASA.A.004 and EASA.A.015

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2015-0089 dated 22 May 2015.

ATA 34 Navigation – Angle of Attack Sensors – Replacement

Manufacturer(s): Airbus (formerly 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 aeroplanes, all manufacturer serial 

numbers (MSN), and

Airbus A340-211, A340-212, A340-213, A340-311, A340-312, A340-313,

A340-541, A340-542, A340-642 and A340-643 aeroplanes, all MSN.

Reason: An occurrence was reported where an Airbus A321 aeroplane encountered a 

blockage of two Angle of Attack (AOA) probes during climb, leading to 

activation of the Alpha Protection (Alpha Prot) while the Mach number 

increased. The flight crew managed to regain full control and the flight landed 

uneventfully. It was determined that the affected AOA probes are also fitted on 

A330 and A340 aeroplanes.

When Alpha Prot is activated due to blocked AOA probes, the flight control laws 

order a continuous nose down pitch rate that, in a worst case scenario, cannot 

be stopped with backward sidestick inputs, even in the full backward position. If 

the Mach number increases during a nose down order, the AOA value of the 

Alpha Prot will continue to decrease. As a result, the flight control laws will 

continue to order a nose down pitch rate, even if the speed is above minimum 

selectable speed, known as VLS. 

This condition, if not corrected, could result in loss of control of the aeroplane.
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Investigation results indicated that aeroplanes equipped with certain UTC 

Aerospace (UTAS, formerly known as Goodrich) AOA sensors, or equipped

with certain SEXTANT/THOMSON AOA sensors, appear to have a greater 

susceptibility to adverse environmental conditions than aeroplanes equipped 

with the latest Thales AOA sensor, Part Number (P/N) C16291AB, which was

designed to improve AOA indication behaviour in heavy rain conditions. 

Having determined that replacement of these AOA sensors is necessary to 

achieve and maintain the required safety level of the aeroplane, EASA issued 

AD 2015-0089, to require modification of the aeroplanes by replacement of the 

affected P/N sensors, and, after modification, prohibits (re-)installation of those 

P/N AOA sensors. That AD also required repetitive detailed visual inspections 

(DET) and functional heating tests of certain Thales AOA sensors and provided

an optional terminating action for those inspections.

Since EASA AD 2015-0089 was issued, based on further analysis results, 

Airbus issued Operators Information Transmission (OIT) Ref. 999.0017/15 

Revision 1, instructing operators to speed up the removal from service of UTAS 

P/N 0861ED2 AOA sensors.

For the reasons described above, this AD retains the requirements of EASA

AD 2015-0089, which is superseded, but reduces the compliance times for 

aeroplanes with UTAS P/N 0861ED2 AOA sensors installed.

Effective Date: 15 July 2015

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

(1) For aeroplanes on which UTAS P/N 0861ED or P/N 0861ED2 AOA 

sensors are installed, within the compliance time as specified in Table 1 of 

this AD, as applicable, replace the Captain and First Officer AOA sensors 

with Thales P/N C16291AB AOA sensors in accordance with the 

instructions of Airbus SB A330-34-3315, or SB A340-34-4294, or 

SB A340-34-5105, as applicable, depending on aeroplane type.

Table 1 – AOA Sensors Replacement

P/N AOA Sensor(s)

installed

Compliance Time

(after 01 June 2015, the effective 

date of EASA AD 2015-0089)

P/N 0861ED 22 months

P/N 0861ED2 7 months

(2) For aeroplanes on which SEXTANT/THOMSON P/N 45150320 AOA 

sensors are installed, within 22 months after 01 June 2015 [the effective 

date of EASA AD 2015-0089], replace each SEXTANT/THOMSON P/N 

45150320 AOA sensor with a Thales P/N C16291AB AOA sensor in 

accordance with the instructions of Airbus SB A330-34-3228, or SB 

A340-34-4234, as applicable, depending on aeroplane type.

(3) For an aeroplane on which one or more Thales P/N C16291AA AOA 

sensors are installed, before exceeding 17 000 flight hours (FH) 

accumulated by each Thales AOA sensor since its first installation on an

aeroplane, or within 6 months after 01 June 2015 [the effective date of 

EASA AD 2015-0089], whichever occurs later, and thereafter at intervals

not to exceed 3 800 FH, accomplish a DET and a functional heating test of 

each P/N C16291AA AOA sensor in accordance with the instructions of

Airbus SB A330-34-3215 Revision 02 (or later), or SB A340-34-4215 

Revision 02 (or later), or SB A340-34-5062 Revision 01 (or later), as 

applicable depending on aeroplane type.
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(4) If, during any DET or functional heating test as required by paragraph (3) 

of this AD, discrepancies are detected, before next flight, replace all

affected AOA sensors with Thales P/N C16291AA AOA sensors that have 

passed a DET and a functional heating test in accordance with the 

instructions of Airbus SB A330-34-3215 Revision 02 (or later), or 

SB A340-34-4215 Revision 02 (or later), or SB A340-34-5062 Revision 01 

(or later), as applicable, depending on aeroplane type, or with Thales P/N 

C16291AB AOA sensors, in accordance with the instructions of Airbus SB 

A330-34-3215 Revision 02 (or later), or SB A340-34-4215 Revision 02 (or 

later), or SB A340-34-5062 Revision 01 (or later), as applicable, depending 

on aeroplane type.

(5) An aeroplane with Airbus modification (mod) 58555 (installation of Thales 

P/N C16291AB AOA sensors) but without Airbus mod 46921 (installation of 

UTAS AOA sensors) embodied in production, is not affected by the 

requirements of paragraphs (1) through (4) of this AD, provided it is 

determined that no AOA sensor having a P/N as listed in Table 2 of this AD

has been installed on that aeroplane since its date of manufacture.

(6) Modification of an aeroplane by replacing each Thales P/N C16291AA 

AOA sensor with a Thales P/N C16291AB AOA sensor in accordance with 

the instructions of Airbus SB A330-34-3228, or SB A340-34-4234, or SB 

A340-34-5070, as applicable depending on aeroplane type, constitutes 

terminating action for the repetitive DET and functional heating tests as 

required by paragraph (3) of this AD for that aeroplane.

Conditions for installation of an AOA sensor on an aeroplane:

(7) For an aeroplane on which only Thales P/N C16291AB AOA sensors are 

installed, from 01 June 2015 [the effective date of EASA AD 2015-0089], or 

after modification of the aeroplane as specified in paragraph (6) of this AD, 

as applicable, do not install a Thales P/N C16291AA AOA sensor on that 

aeroplane.

(8) For an aeroplane on which Thales P/N C16291AA and/or Thales P/N 

C16291AB AOA sensors are installed, from 01 June 2015 [the effective 

date of EASA AD 2015-0089], or after modification of the aeroplane as 

required by paragraph (2) of this AD, as applicable, do not install any AOA

sensor with a P/N as listed in Table 2 of this AD on that aeroplane.

(9) After modification of an aeroplane as required by paragraph (1) of this AD, 

do not install any AOA sensor with a P/N as listed in Table 2 of this AD on 

that aeroplane, with the exception that it remains allowed to install a UTAS 

P/N 0861ED AOA sensor in the standby position of that aeroplane.

Table 2 – AOA Sensors

AOA Sensor Manufacturer P/N

SEXTANT/THOMSON P/N 45150320

UTAS (formerly Goodrich)

P/N 0861ED

P/N 0861ED2

(10) Installation of AOA sensors having a P/N approved after 01 June 2015 [the 

effective date of EASA AD 2015-0089] is equal to compliance with the 

requirements of paragraph (1) or (2) of this AD, as applicable, provided the 

conditions as specified in paragraphs (10.1) and (10.2) of this AD are met.

(10.1) The AOA sensor P/N must be approved by EASA, or approved 

under Airbus DOA; and

(10.2) The installation must be accomplished in accordance with 

aeroplane modification instructions approved by EASA, or 

approved under Airbus DOA.
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Ref. Publications: Airbus OIT 999.0017/15 Revision 01, dated 29 June 2015.

Airbus SB A330-34-3315 original issue dated 26 March 2015.

Airbus SB A330-34-3228 original issue dated 07 October 2009.

Airbus SB A330-34-3215 Revision 02 dated 29 March 2010.

Airbus SB A340-34-4294 original issue dated 26 March 2015.

Airbus SB A340-34-4234 original issue dated 07 October 2009.

Airbus SB A340-34-4215 Revision 02 dated 29 March 2010.

Airbus SB A340-34-5105 original issue dated 26 March 2015.

Airbus SB A340-34-5062 Revision 01 dated 29 March 2010.

Airbus SB A340-34-5070 original issue dated 09 October 2009.

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. Based on the required actions and the compliance time, EASA have 

decided to issue a Final AD with Request for Comments, postponing the 

public consultation process until after publication.

3. Enquiries regarding this AD should be referred to the Safety Information 

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 – Airworthiness Office – EIAL,

E-mail: airworthiness.A330-A340@airbus.com.