EASA AD No.: 2015-0205

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2015-0205

Date: 09 October 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):

A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0237R1 dated 05 December 2014.

ATA 34 Navigation – Airspeed Pitot Probes – 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, A320-211, 

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: Occurrences were reported on A320 family aeroplanes of airspeed indication 

discrepancies while flying at high altitudes in inclement weather conditions. 

Investigation results indicated that A320 aeroplanes equipped with Thales 

Avionics Part Number (P/N) 50620-10 or P/N C16195AA pitot probes appear to 

have a greater susceptibility to adverse environmental conditions than 

aeroplanes equipped with certain other pitot probes.

Prompted by earlier occurrences, DGAC France issued AD 2001-362 to require 

replacement of Thales (formerly known as Sextant) P/N 50620-10 pitot probes 

with Thales P/N C16195AA probes.

Since that AD was issued, Thales pitot probe P/N C16195BA was designed,

which improved airspeed indication behaviour in heavy rain conditions, but did 

not demonstrate the same level of robustness to withstand high-altitude ice 

crystals. Based on these findings, EASA decided to implement replacement of 

the affected Thales probes as a precautionary measure to improve the safety 

level of the affected aeroplanes.

Consequently, EASA issued AD 2014-0237 (later revised), retaining the 

requirements of DGAC France AD 2001-362, which was superseded, and 

cancelling two other ADs, to require replacement of Thales Avionics pitot 

probes P/N C16195AA and P/N C16195BA.
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Since EASA AD 2014-0237R1 was issued, results of further analyses have 

determined that the compliance time (48 months) of that AD has to be reduced 

in relation to the risk assessment.

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

2014-0237R1, which is superseded, but reduces the compliance time.

Effective Date: 23 October 2015

Required Action(s) 

and Compliance 

Time(s):

Required as indicated, unless accomplished previously:

(1) For A319, A320 and A321 aeroplanes, all certified models, all serial 

numbers, except aeroplanes having embodied Airbus modification 25998 

in production:

Within 24 months after 18 August 2001 [the effective date of DGAC France 

AD 2001-362], replace Thales (previously SEXTANT) pitot probes P/N 

50620-10 with Thales pitot probes P/N C16195AA in accordance with the 

instructions of Airbus Service Bulletin (SB) A320-34-1127.

(2) Within 24 months after 12 November 2014 [the effective date of EASA AD 

2014-0237 at original issue], replace each Thales pitot probe P/N 

C16195AA and P/N C16195BA in accordance with the instructions of 

Airbus SB A320-34-1170.

(3) Modification of an aeroplane by replacement of the probes in accordance 

with the instructions of Airbus SB A320-34-1456 (pitot probes on Captain 

and stand-by side) and SB A320-34-1463 (pitot probes at F/O side) is an 

acceptable alternative method to comply with the requirements of 

paragraph (2) of this AD for that aeroplane.

(4) An aeroplane on which Airbus mod 25578 was embodied in production 

(except as specified below) is compliant with the requirements of 

paragraphs (1) and (2) of this AD, provided it is determined that no Thales 

pitot probe P/N 50620-10, P/N C16195AA or P/N C16195BA has been 

installed on that aeroplane since Airbus date of manufacture.

Post-mod 25578 aeroplanes, when mod 155737 (installation of Thales 

probes) was also embodied in production, must comply with paragraph (2) 

of this AD.

(5) After the manufacturing date of the aeroplane, do not install a Thales pitot 

probe P/N 50620-10, P/N C16195AA or P/N C16195BA, as required by 

paragraph (5.1) or (5.2) of this AD, as applicable:

(5.1) For aeroplanes that have a Thales pitot probe P/N C16195AA or 

P/N C16195BA installed: after modification of the aeroplane as 

required by paragraph (2) of this AD.

(5.2) For aeroplanes that do not have a Thales pitot probe P/N C16195AA 

or P/N C16195BA installed: from 12 November 2014 [the effective 

date of EASA AD 2014-0237 at original issue].

(6) Installation of a pitot probe P/N approved after the effective date of this AD 

and compliant with the new EASA icing requirements is equal to 

compliance with the requirements of paragraphs (1) and (2) of this AD, 

provided the conditions as specified in paragraphs (6.1) and (6.2) of this 

AD are met.

(6.1) The pitot probe P/N must be approved by EASA, or approved under 

Airbus DOA; and

(6.2) 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 SB A320-34-1127 original issue dated 24 April 1997, or Revision

(Rev.) 01 dated 04 December 2001.

Airbus SB A320-34-1456 original issue dated 02 December 2009, or Rev. 01 

dated 15 May 2012.

Airbus SB A320-34-1463 original issue dated 09 March 2010, or Rev. 01 dated 

15 May 2012.

Airbus SB A320-34-1170 original issue dated 18 December 1998, or Rev. 01 

dated 14 May 1999, or Rev. 02 dated 07 December 1999, or Rev. 03 dated

17 February 2000, or Rev. 04 dated 24 May 2000, or Rev. 05 dated

11 September 2000, or Rev. 06 dated 18 October 2001, or Rev. 07 dated

04 December 2001, or Rev. 08 dated 15 January 2003, or Rev. 09 dated

17 February 2003, or Rev. 10 dated 21 November 2003, or Rev. 11 dated

18 August 2004, or Rev. 12 dated 02 December 2004, or Rev. 13 dated

18 January 2005, or Rev. 14 dated 21 April 2005, or Rev. 15 dated 19 July

2005, or Rev. 16 dated 23 November 2006, or Rev. 17 dated 14 February 

2007, or Rev. 18 dated 09 October 2009, or Rev. 19 dated 09 November 2009, 

or Rev. 20 dated 01 December 2010, or Rev. 21 dated 24 March 2011, or 

Rev. 22 dated 19 July 2011, or Rev. 23 dated 03 February 2012, or Rev. 24

dated 12 April 2012, or Rev. 25 dated 04 September 2012, or Rev. 26 dated

16 September 2013, or Rev. 27 dated 18 March 2014.

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. This AD was posted on 03 September 2015 as PAD 15-115 for 

consultation until 01 October 2015. The Comment Response Document 

can be found at http://ad.easa.europa.eu.

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 – EIAS;

Fax +33 5 61 93 44 51; E-mail: account.airworth-eas@airbus.com