EASA AD No.: 2013-0022

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2013-0022

Date: 01 February 2013

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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A318, A319, A320, and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not Applicable

Supersedure: This AD supersedes EASA AD 2012-0264-E dated 17 December 2012.

ATA 34 Navigation – Angle of Attack Sensor Conic Plates – Replacement

Manufacturer(s): Airbus (Formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112,

A319-113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, 

A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-232, 

A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, 

A321-231 and A321-232 aeroplanes, all manufacturer serial numbers

Reason: Recently, an Airbus A330 aeroplane equipped with Angle of Attack (AoA) 

sensors with conic plates installed, experienced blockage of all sensors during 

climb, leading to autopilot disconnection and activation of the alpha protection 

(Alpha Prot) when Mach number was increased. 

Based on the results of the subsequent analysis, it is suspected that these 

conic plates may have contributed to the event. Investigations are on-going to 

determine what caused the blockage of these AoA sensors. 

Blockage of two or three AoA sensors at the same angle may cause the Alpha 

Prot of the normal law to activate. Under normal flight conditions (in normal 

law), if the Alpha Prot activates and Mach number increases, the flight control 

laws order a pitch down of the aeroplane that the flight crew may be unable to 

counteract with a side stick deflection, even in the full backward position. 

This condition, if not corrected, could result in reduced control of the aeroplane.

AoA conic plates of similar design are also installed on A320 family aeroplanes, 

and installation of these AoA sensor conic plates was required by EASA AD 

2012-0236, making reference to Airbus Service Bulletin (SB) A320-34-1521 for 

in-service modification.
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That requirement was deleted by EASA AD 2012-0236R1. 

To address this potential unsafe condition on A320 family aeroplanes, Airbus 

developed an “AOA Blocked” emergency procedure, published as a temporary 

revision (TR) of the Airplane Flight Manual (AFM), to ensure that flight crews, in 

case of AoA sensors blockage, apply the applicable emergency procedure. 

Consequently, EASA issued Emergency AD 2012-0264-E to require 

amendment of the AFM by incorporating the Airbus TR.

Since that AD was issued, Airbus published approved instructions to re-install 

AoA sensor flat plates on A320 family aeroplanes. 

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

2012-0264-E which is superseded, and requires installation of AoA sensor flat 

plates, after which the AFM operational procedure can be removed.

Effective Date: 15 February 2013

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Re-statement of EASA AD 2012-0264-E requirement:

For aeroplanes on which Airbus modification (mod.) 153213 or 153214 has 

been embodied in production, or Airbus SB A320-34-1521 has been embodied 

in service:

(1) Before next flight after 22 December 2012 [the effective date of EASA AD 

2012-0264-E], amend the applicable AFM to incorporate Airbus AFM A320 

TR286 “AOA Blocked”, issue 1.0, inform all flight crews and thereafter 

operate the aeroplane accordingly.

New requirements of this AD:

For all aeroplanes as identified in the Applicability section of this AD:

(2) Within 5 months after the effective date of this AD, remove all AoA sensor

conic plates having Part Number (P/N) F3411060200000 or P/N 

F3411060900000 and install AoA sensor flat plates:

(2.1) P/N D3411013520200 in accordance with the instructions of Airbus 

SB A320-34-1564, or

(2.2) P/N D3411007620000, or P/N D3411013520000 in accordance with 

approved instructions.

(3) An aeroplane on which Airbus mod. 154863 (installation of AOA sensor flat 

plate) and mod. 154864 (Coating protection) have been embodied in 

production is not affected by the requirements of paragraphs (1) and (2) of 

this AD, provided that, since first flight, no AoA sensor conic plate P/N 

F3411060200000 or P/N F3411060900000 has been installed on that 

aeroplane.

(4) After modification of an aeroplane as required by paragraph (2) of this AD,

the operational procedure introduced by paragraph (1) of this AD is no 

longer required and must be removed from the AFM of that aeroplane.

(5) Do not install on an aeroplane any AoA sensor conic plate P/N 

F3411060200000 or P/N F3411060900000, and do not use AoA protection 

cover P/N 98D34203003000 on an aeroplane, as follows:

(5.1) For aeroplanes that, on the effective date of this AD, have AoA

sensor flat plates installed: From effective date of this AD.

(5.2) For aeroplanes that, on the effective date of this AD, have AoA 

sensor conic plates installed: After modification of the aeroplane as 

required by paragraph (2) of this AD.
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Ref. Publications: Airbus SB A320-34-1564 Original Issue dated 25 January 2013.

Airbus AFM TR 286 Issue 1.0 dated 17 December 2012.

Note: A copy of the AFM TR is attached to the record of this AD in the EASA 

AD publishing tool.

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, Executive 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 – EIAS

E-mail: account.airworth-eas@airbus.com.