E ASA AD No.: 2014

- 0266

- E

TE. CAP.0011 1

- 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 EMERGENCY AIRWORTHINESS DIRECTIVE

AD No
. : 2014 - 0266 - E

Date: 09 December 2014

Note: This Emergency 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 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 w ith 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
F oreign AD: Not applicable Supersedure: None



### ATA Airplane Flight Manual
– Undue 

### A ctivation of A lpha P rotection

– Emergency Procedure
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: An occurrence was reported where an Airbus A32 1 aeroplane encountered a blockage of two Angle Of Attack (AOA) probes during climb , le a d ing to activation of the A lpha P rotection (Alpha Prot) while the Mach number increas ed

. The flight crew managed to regain full control and the flight landed uneventfully. When Alpha Prot is activat ed due to blocked AOA probes, the flight control law s order a continuous nose down pitch rate that , in a worst case scenario, c an not be stopped with backward sidestick inputs , even in the full backward position. If the Mach number increases during a nose down order, the AOA value of the Alpha Prot will continue to decrease. As a result, the flight control laws will continue to order a nose down pitch rate, even if the speed is above minimum s e l e ctable speed , known as VLS

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

. To address this unsafe condition, Airbus have developed a specific Aircraft Flight Manual (AFM) procedure, which has been published in AFM Temporary Revision (TR) N° 502

. For the reasons described above, this AD requires amendment of the applicable AFM

.E ASA AD No.: 2014

- 0266

- E

TE. CAP.0011 1

- 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. This is considered to be an interim action and f urther AD action may follow

. Effective Date: 11 December 2014 Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Before next flight after the effective date of this AD, amend the applicable AFM by inserting a copy of Airbus AFM A320 TR 502 “ Abnormal V alpha Prot ”, issue 1

. Alternatively , amending the applicable AFM can be accomplished by insertin g of a copy of Appendix 1 of this AD into the Section Emergency Procedures

. (2) Concurrent with the AFM amendment as required by paragraph (1) of th is AD, inform all flight crews and , thereafter , ope rate the aeroplane accordingly.
Ref. Public ations: Airbus AFM A320 TR 502 issue 1 , EASA approved 0 5 December 201 4

. The use of later approved revisions of th i s document 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. The results of the safety assessment ha ve indicated the need for immediate publication and notification , without the full public consultation process

. 3. Enquiries regarding this A D 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

.E ASA AD No.: 2014

- 0266

- E

TE. CAP.0011 1

- 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. 

### Appendix 1

– AFM Procedure