EASA AD No.: 2014-0281

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 1/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2014-0281

Date: 22 December 2014

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EU 748/2012, P art 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption]. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A330 aeroplanes

TCDS Number: EASA.A.004

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2014-0273 d ated 17 December 2014.



### ATA 24 Electrical Power – Alternating Current Emergency Ge neration – Operational Procedure

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330-201, A330-202, A330-203, A330-223, A330-223F, A330-243, A330-243F, A330-301, A330-302, A330-303, A330-321, A330-322, A330-323, A330-341, A330-342 and A330-343 aeroplanes, all man ufacturer serial numbers.
Reason: The Constant Speed Motor/Generator (CSM/G), as installed on Airbus A330 aeroplanes, is qualified for an overload condition of 9.5kVA for 30 minutes. This duration is sufficient to perform safe landing and a GO-AROUND. However, electrical load analysis revealed that the hydrauli c power might not be sufficient to supply the CSM/G during slat/flap extension, whe n only one engine is running. This condition, if not corrected, and in conjunctio n with the loss of main electrical system, could lead to the scenario, wher e the crew is not clearly warned that the electrical system has switched on t he battery and thus has a limited duration that would allow a safe landing. To address this potential unsafe condition, Airbus issued an Aircraft Flight Manual (AFM) Temporary Revision (TR) on A330 aeropl ane to update the electrical emergency configuration “ELEC EMER CONFI G” procedure to require the pilot to deploy the ram air turbine man ually before setting the Landing Recovery to ON position to provide sufficie nt hydraulic power and avoid CSM/G shedding under worst-case operational c onditions. Consequently, EASA issued AD 2014-0273 to require amendment of the AFMEASA AD No.: 2014-0281

TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. 2/2 Proprietary document. Copies are not controlled. Co nfirm revision status through the EASA-Internet/Int ranet. by incorporating the applicable Airbus TR. After that AD was issued, EASA became aware that th e reference to Airbus modification (mod) 47930 was insufficient to define which AFM TR is applicable to which aeroplane (configuration), as this mod can be embodied in service with Airbus Service Bulletin (SB) A330-28-3067. For the reason described above, this AD retains the requirements of EASA AD 2014-0273, which is superseded, and corrects the information included in Table 1.

Effective Date: 05 January 2015

Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previous ly: (1) Within 15 days after the effective date of this AD, amend the emergency procedures section of Airbus A330 AFM to incorporat e the updated “ELEC - EMER CONFIG” procedure by inserting the AFM TR as defined in Table 1 of this AD, depending on aeroplane configur ation.

Table 1

Aeroplane configuration AFM TR A330 Pre-mod 47930; A330 Pre-SB A330-28-3067. TR 427 issue 1

A330 Post-mod 47930; A330 Post-SB A330-28-3067. TR 428 issue 1

Amending the applicable AFM to incorporate a later revision which includes the AFM TR as required by this AD, is acce ptable to comply with the requirements of paragraph (1) of this AD.
(2) Concurrent with the AFM amendment as required b y paragraph (1) of this AD, inform all flight crews and, thereafter, operat e the aeroplane accordingly.

Ref. Publications: Airbus A330 AFM TR 427 Issue 1 E ASA approved on 14 October 2014, Airbus A330 AFM TR 428 Issue 1 EASA approved on 14 October 2014, Airbus A330 SB A330-28-3067 Original issue dated 23 March 2001, or Revision 1 dated 16 July 2001. The use of later approved revisions of these docume nts is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA 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 Commen ts, postponing the public consultation process until after publication

. 3. Enquiries regarding this AD should be referred t o the Safety Information Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS SAS – Airworthiness Office – EAL. E-mail: airworthiness.A330-A340@airbus.com

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