EASA AD No.: 2014-0281 

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EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2014-0281 

Date: 22 December 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 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 operate 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): 

A330 aeroplanes 

TCDS Number: EASA.A.004 

Foreign AD: Not applicable 

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

ATA 24 Electrical Power – Alternating Current Emergency Generation – 

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 manufacturer 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 hydraulic power might not be sufficient 

to supply the CSM/G during slat/flap extension, when only one engine is 

running. 

This condition, if not corrected, and in conjunction with the loss of main 

electrical system, could lead to the scenario, where the crew is not clearly 

warned that the electrical system has switched on the 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 aeroplane to update the 

electrical emergency configuration “ELEC EMER CONFIG” procedure to 

require the pilot to deploy the ram air turbine manually before setting the 

Landing Recovery to ON position to provide sufficient hydraulic power and 

avoid CSM/G shedding under worst-case operational conditions. 

Consequently, EASA issued AD 2014-0273 to require amendment of the AFM 
EASA AD No.: 2014-0281 

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by incorporating the applicable Airbus TR. 

After that AD was issued, EASA became aware that the 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 previously: 

(1) Within 15 days after the effective date of this AD, amend the emergency 

procedures section of Airbus A330 AFM to incorporate the updated 

“ELEC - EMER CONFIG” procedure by inserting the AFM TR as defined in 

Table 1 of this AD, depending on aeroplane configuration. 

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 acceptable to comply with 

the requirements of paragraph (1) of this AD. 

(2) Concurrent with the AFM amendment as required by paragraph (1) of this 

AD, inform all flight crews and, thereafter, operate the aeroplane 

accordingly. 

Ref. Publications: Airbus A330 AFM TR 427 Issue 1 EASA 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 documents 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. 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 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 SAS – Airworthiness Office – EAL. 

E-mail: airworthiness.A330-A340@airbus.com.