EASA AD No.: 20 14

- 0237 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 14
- 0237 R1

Date: 05 Dec ember 2014

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 accordan ce 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 ope rate 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) exempt ion]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not a pplicable

Revision : This AD revises EASA AD 2014

- 0237 dated 29 October 2014 , which supersede d

DGAC F rance AD 91

- 227

- 021 (B) R1 dated 24 December 1991
, AD 2001

- 362 (B) dated 08 August 2001, and AD 2002

- 586 (B)R 1 dated 02 April 2003.



### 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 manufact urer serial numbers

. Reason: Occurrences have been reported on A3 20 family aeroplanes of airspeed indication discrepancies while flying at high altitudes in inclement weather conditions. Investigation results indicate d that A3 2 0 aeroplanes equipped with Thales Avionics Part Number (P/N) 50620

- 10 or P/N C16195AA p itot probes appear to have a greater susceptibility to adverse environmental conditions than aeroplanes equipped with certain other p itot probes. Prompted by earlier occurrences, DGAC France issued AD 2001

- 362 t o 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 p itot probe P/N C16195BA was designed
, which improve d 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 ha ve decided to implement replacement of the affected Thales probes as a precautionary measure to improve the safety level of the affected aeroplane s

. Consequently, EASA issued AD 2014

- 0237, retain ing the requirements of DGAC France AD 2001

- 362, which wa s superseded, to require replace ment of T hales Avionics p itot p robes P/N C16195A A and P/N C16195BA

.EASA AD No.: 20 14

- 0237 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. The following related DGAC France ADs we re also cancelled by EASA AD 2014

- 0237 , without retaining any of their requirements:

 AD 91

- 227

- 021R1 that required replacement of Titeflex hoses; and

 AD 2002

- 586R1 that required cleaning of Thales P/N C16195AA probes

. Since EASA issued AD 2014

- 0237, it was brought to the Agency’s attention that Ai rbus modification (mod) 155737 w as introduced to install Thales probes in production. This affects paragraph (4) of the AD.
For the reasons described above, this AD is revised to amend paragraph (4), making reference to aeroplanes which are post

- mod 25578, but also post

- mod 155737 , as a result of which they have Thales probes installed.

Effective Date: Revision 1: 12 Dec ember 2014 Original issue: 12 November 2014
Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: Retained requirements from DGAC France AD 2001

- 362 : ( 1 ) For A319, A320 and A321 aeroplanes, all certified models, all serial numbers
, except aeroplanes having embodied Airbus modification 25998 in production : W ithin 24 months after 18 August 2001 [ the effective date of DGAC France AD 2001

- 362], replace Thales (p reviously 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. New requirements of this AD : (2) Within 48 months after 12 November 2014 [ the effective date of the original issue of this AD ] , 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 w as embodied in production (except as specified below) is compliant with the requirements of paragraph s (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 ha s been installed on that aeroplane since Airbus date of manufacture

. P ost

- mod 25578 a eroplanes
, 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, d o 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 : A fter 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 : F rom the effective date of this AD. ( 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 paragraph s (1) and (2) of this AD,EASA AD No.: 20 14

- 0237 R1

TE. CAP.0011 0

- 00 4 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. provided the conditions as specified in paragraphs ( 6 .1) and ( 6 .2) of this AD are met. ( 6 .1) T he pitot probe P/N must be approved by EASA, or approved under Air bus DOA; and ( 6 .2) The installation must be accomplished in accordance with aeroplane modification instructions approved by EASA, or approved under Airbus DOA.

Ref. Public ations : 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 19 99 , or Rev. 03 dated 17 Feb ruary 20 00 , or Rev. 04 dated 24 May 2 0 00 , or Rev. 05 dated 11 Sep tember 20 00 , or Rev. 06 dated 18 Oct ober 20 01 , or Rev. 07 dated 04 Dec ember 20 01 , or Rev. 08 dated 15 Jan uary 20 03 , or Rev. 09 dated 17 Feb ruary 20 03 , or Rev. 10 dated 21 Nov ember 2 0 03 , or Rev. 11 dated 18 Aug ust 20 04 , or Rev. 12 dated 02 Dec ember 2 0 04 , or Rev. 13 dated 18 Jan uary 20 05 , or Rev. 14 dated 21 Apr il 2 0 05 , or Rev. 15 dated 19 Jul y 20 05 , or Rev. 16 dated 23 Nov ember 2 0 06 , or Rev. 17 dated 14 Feb ruary 20 07 , or Rev. 18 dated 09 Oct ober 2 009 , or Rev. 19 dated 09 Nov ember 2 009 , or Rev. 20 dated 01 Dec ember 2 010 , or Rev. 21 dated 24 Mar ch 2 0 11 , or Rev. 22 dated 19 Jul y 20 11 , or Rev. 23 dated 03 Feb ruary 20 12 , or Rev. 24 dated 12 Apr il 2 0 12 , or Rev. 25 dated 04 Sep tember 2 012 , or Rev. 26 dated 16 Sep tember 20 13 , or Rev. 27 dated 18 March 20 14

. The u se of later approved revisions of th e s e document s 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. Th e original issue of th is AD was posted on 09 September 2014 as PAD 14

- 13 9 for consultation until 07 October 2014 . 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

.