E ASA AD No.: 2014

- 0174

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

. : 2014
- 01 7 4

Date: 23 July 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 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 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 ) exemption]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319, A320 and A321aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not Applicable
Supersedure: None



### ATA 34 Navigation

– Terrain Awareness Warning System

– Power Cycle ( Reset )

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

- 2 13, A321

- 231 and A321

- 232 aeroplanes, all manufacturer serial numbers (MSN).

Reason: Following two cases of spurious Terrain Ahead Warning System (TAWS) alert during approach and take off in Geneva, the concerned Transponder, Terrain and Traffic Collision Avoidance System ( T3CAS ) was sen t to ACSS, the manufacturer of the affected equipment , for investigation. The results of a laboratory investigation indicated that an internal frozen position anomaly occurs when T3 CAS is constantly powere d for more than 149 hours. The origin for this defect was identified as a counter limitation , which is identified as a purely T3CAS software misbehavio u r and is not self

- detected. Only T3CAS units having P art N umber (P/N) 9005000

- 10000 ( software Standard 1.0), P/N 9005000

- 10101 (Standard 1.1), and P/N 900500 0

- 10202 (Standard 1.2) are affected by this software error

. This condition, if not corrected , could lead to spurious TAWS alert s which could in crease flight crew workload during critical landing or take off phases , possibly resulting in reduced control of the aeroplane

. Prompted by these reports, Airbus issued Alert Operators Transmission (AOT) A34N004

- 1 3 to provide instructions to reset the T3CAS. For the reason s describe d above, this AD requires repetitive on ground power cycles ( reset s ) of the T3CAS unit

.E ASA AD No.: 2014

- 0174

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. Effective Date: 06 August 2014
Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) For aeroplanes equipped with a T3CAS unit having a P/N listed in T able 1 of this AD, w ithin 3 0 days after the effective date of this AD, and , thereafter , at interval s not to exceed 120 hours of continuous power of the T3CAS
, accomplish an on ground power cycle on the T3CAS in accordance with the instructions of Airbus AOT A34N004

- 13.

Table 1

– Affected T3CAS Units
P/N Software Standard
900500 0

- 10000 1.0
900500 0

- 10101 1.1
900500 0

- 10202 1.2
( 2 ) Within 12 months after the effective date of this AD, revise the approved aircraft maintenance programme (AMP) and standard practices, on the basis of which the operator or the owner ensures the continuing airworthiness of each operated aeroplane, by incor porating the T3CAS on ground power cycle instructions, as specified in Airbus AOT A34N004

- 13

. ( 3 ) Revising the AMP, as required b y paragraph (2 ) of this AD , constitutes compliance with the requirements of paragraph (1) of this AD. After revisin g the AMP , as required by paragraph (2) of this AD, it is not necessary that accomplishment of each T3CAS on ground power cycle action is recorded for demonstration of AD compliance on a continued basis. Note: For affected aeroplanes registered in Europe, complying with the approved AMP as specified in paragraph (2 ) of this AD is required by Commission Regulation (EC) No 2042/2003 , Part M.A.301, paragraph 3. (4) A n a eroplane on which Airbus modification (mod) 39146 , or mod 152980 , or mod 154341 , has not been embodied in production , does not have to compl y with the requirements of paragraphs (1) and (2) of this AD
, provided it can be demonstrated that no T3CAS unit having a P/N listed in Table 1 of this AD is installed o n th at aeroplane

. ( 5 ) From the effective date of this AD, installation on an aeroplane of a T3CAS unit having a P/N and software standard as listed in Table 1 of this AD is acceptable, provided that, following installation, the T3CAS unit is power cycled on a recurrent basis , as required by this AD. ( 6 ) Installation on an aeroplane of a version (P/N) of T3CAS approved after the effective date of this AD constitutes terminating action for the recurrent on ground power cycle s as required by this AD for that aeroplane , provided the conditions as specified in paragraphs ( 6 .1) and ( 6 .2) of this AD are met

. ( 6 .1) The version (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

. Ref. Public ations: Airbus AOT A34N004

- 13 o riginal issue, dated 25 November 2013 , or Revision 01 dated 19 March 2014

. The use of later approved revisions of th is document is acceptable for compliance with the requirements of this AD.E ASA AD No.: 2014

- 0174

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. 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 A D 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; Fax +33 5 61 93 44 51; E

- mail: account.airworth

- eas@airbus.com

.