EASA AD No.: 20 15

- 02 05

TE. CAP.00110

- 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.: 2015 - 02 05

Date: 0 9 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 E U 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 ope rate 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

F oreign 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 A3 20 family aeroplanes of airspeed indication discrepancies while flyin g 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 find ings, EASA 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 (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.EASA AD No.: 20 15

- 02 05

TE. CAP.00110

- 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. Since EASA AD 2014

- 0237R1 was issued, results of further analyses have determined that the compliance tim e (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: 2 3 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 : 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. (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 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

. 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, 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 in stalled: f rom 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 paragraph s (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) T he 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.EASA AD No.: 20 15

- 02 05

TE. CAP.00110

- 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. 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 the 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. 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 co ntent 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