EASA AD No.: 2010-0109 

EASA Form 110 Page 1/4 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0109 

Date: 28 June 2010 

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 EC 1702/2003, Part 21A.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 operate 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]. 

Type Approval Holder’s Name : 

AIRBUS 

Type/Model designation(s) : 

A330 and A340 aeroplanes 

TCDS Number : EASA.A.004, EASA.A.015 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2008-0010R1 dated 07 October 2008 

ATA 27 Flight Controls – Flight Control Primary Computer (FCPC) – 

Dispatch restriction and Operational Test 

Manufacturer(s): Airbus (formerly Airbus Industrie) 

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -223F, -243, 

-243F, -301, -302, -303, -321, -322, -323, -341, -342 and -343, all serial 

numbers. 

Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, -541, 

-542, -642 and -643, all serial numbers. 

Reason: On A330/A340 aeroplanes, the Flight Control Primary Computer 2 

(FCPC2) and FCPC3 are supplied with power from the 2PP bus bar. 

Electrical transients on the 2PP bus bar occur, in particular during engine 

n.2 failure on A330 aeroplanes or engine n.3 failure on A340 aeroplanes. 

Such electrical transients lead to a FCPC2 reset. FCPC3 reset does not 

occur thanks to the introduction of second electrical power supply to 

FCPC3 from 1PP bus bar associated to the Electrical Contactor 

Management Unit (ECMU) standard 5. 

During the evaluation of specific engine failure cases at take-off on Airbus 

flight simulators, it has been evidenced that with FCPC1 inoperative, in the 

worst case, when FCPC2 and FCPC3 resets occur during rotation at take 

off, a transient loss of elevator control associated with a temporary 

incorrect flight control law reconfiguration could occur. This condition leads 

to a movement of the elevators to the zero position, which induces a pitch 

down movement instead of a pitch up movement needed to lift off. In 

addition, it leads to a limitation of the pilot control on pitch axis and limits 
EASA AD No.: 2010-0109 

EASA Form 110 Page 2/4 

the pilot capacity to counter the pitch down movement during this flight 

phase, which constitutes an unsafe condition. 

To prevent such condition, Emergency Airworthiness Directive (EAD) 

2008-0010-E was issued to prohibit aeroplanes dispatch with FCPC1 

inoperative (from GO to NO-GO) for certain aeroplane configurations. For 

other configurations, dispatch is allowed when the integrity of the FCPC3 

second electrical power supply is ensured. 

EASA AD 2008-0010R1 was issued to : 

- For A340-500/-600, alleviate the dispatch restriction on aeroplanes fitted 

with new FCPC Standard W11 (part number (P/N) LA2K2B100GA0000) 

and 

- For A330 and A340-200/-300, to take into account the possibility to 

embody in service a new FCPC3 second electrical power supply 

equivalent to the production one. 

This AD, which supersedes EASA AD 2008-0010R1 retaining its 

requirements, is issued to extend the applicability to the newly certified 

models A330-223F and A330-243F. 

Effective Date: 12 July 2010 

Required action(s) 

and Compliance 

Time(s): 

(1) The following operational limitation is required as indicated after 

16 January 2008 [effective date of AD 2008-0010R1]: 

(1.1) For aeroplanes identified in the Applicability section of this AD, 

except A330-223F and A330-243F aeroplanes and: 

- A330 and A340-200/-300 aeroplanes on which Airbus 

modification 44385 has been embodied either in production or in 

service by Airbus Service Bulletin (SB) A330-27-3159 or SB 

A340-27-4158 AND Airbus modification 44431 has been 

embodied either in production or in service by Airbus SB 

A330-24-3011 or SB A340-24-4019, and 

- A340-500/-600 aeroplanes on which Airbus modification 57698 

has been embodied either in production or in service by Airbus 

SB A340-27-5046, 

Dispatch restriction: 

Dispatch with the FCPC “PRIM 1” inoperative (item numbered 

27-93-01-A) in the associated MMEL) is prohibited. 

Note 1: This dispatch restriction applies notably to A330 and A340-200/ 

-300 aeroplanes which have embodied Airbus SB A330-27-3040 

or A340-27-4046 in service. 

(1.2) For A330 and A340-200/-300 aeroplanes, except A330-223F and 

 A330-243F aeroplanes, on which: 

- Airbus modification 44385 has been embodied either in 

production or in service by Airbus SB A330-27-3159 or SB 

A340-27-4158, AND 

- Airbus modification 44431 has been embodied either in 

production or in service by Airbus SB A330-24-3011 or SB 

A340-24-4019, 

a) Dispatch with the FCPC “PRIM 1” inoperative (item numbered 

27-93-01-A) in the associated MMEL) is allowed provided that the 

operational test of the FCPC3 second electrical power supply is 

successfully performed in accordance with the instructions of Airbus 

AOT A330-27A3158 or AOT A340-27A4157, as applicable, before 

the first flight of the MMEL interval. 
EASA AD No.: 2010-0109 

EASA Form 110 Page 3/4 

b) If the test is not successful, repair in accordance with instructions of 

Airbus AOT A330-27A3158 or AOT A340-27A4157, as applicable, 

before dispatch with FCPC “PRIM 1” inoperative (item numbered 

27-93-01-A) in the associated MMEL). 

(2) The following operational limitation is required as indicated after the 

effective date of this AD for A330-223F and A330-243F aeroplanes:

a) Dispatch with the FCPC “PRIM 1” inoperative (item numbered 

27-93-01-A) in the associated MMEL) is allowed provided that the 

operational test of the FCPC3 second electrical power supply is 

successfully performed in accordance with the instructions of Airbus 

AOT A330-27A3158, before the first flight of the MMEL interval. 

b) If the test is not successful, repair in accordance with the 

instructions of Airbus AOT A330-27A3158, before dispatch with 

FCPC “PRIM 1” inoperative (item numbered 27-93-01-A) in the 

associated MMEL). 

Note 2: These operational limitations are included in the following 

Temporary Revision (TR) of the Master Minimum Equipment List 

(MMEL): 

A330 TR 01-27/01Z Issue 01 for A330-200/-300 aeroplane pre-mod 

44385 or post-SB A330-27-3040 (NO-GO), 

A330 TR 01-27/02Z Issue 01 for A330-200/-300 aeroplane with 

mechanical rudder and post-mod 44385 (GO-IF), 

A330 TR 01-27/03Z Issue 01 for A330-200/-300 aeroplane with 

electrical rudder and post-mod 44385 (GO-IF), 

A340 TR 01-27/01Z Issue 01 for A340-500/-600 aeroplane (NO-GO), 

A340 TR 01-27/02Z Issue 01 for A340-200/-300 aeroplane pre-mod 

44385 or post-SB A340-27-4046 (NO-GO), 

A340 TR 01-27/03Z Issue 01 for A340-200/-300 aeroplane with 

mechanical rudder and post-mod 44385 (GO-IF), 

A340 TR 01-27/04Z Issue 01 for A340-300 aeroplane with electrical 

rudder and post-mod 44385 (GO-IF). 

(3) Incorporation of the appropriate MMEL TR or inserting the above 

dispatch restrictions or a copy of this AD into the Aircraft Operations 

Manual (AOM) and strict adherence to the above dispatch restrictions 

by the flight crew is acceptable to comply with the requirements of this 

AD. 

Ref. Publications: AIRBUS A330 MMEL TR 01-27/01Z Issue 01, 

AIRBUS A330 MMEL TR 01-27/02Z Issue 01, 

AIRBUS A330 MMEL TR 01-27/03Z Issue 01, 

AIRBUS A340 MMEL TR 01-27/01Z Issue 01, 

AIRBUS A340 MMEL TR 01-27/02Z Issue 01, 

AIRBUS A340 MMEL TR 01-27/03Z Issue 01, 

AIRBUS A340 MMEL TR 01-27/04Z Issue 01, 

or any later JAA accepted revision of this MMEL TRs or any general 

MMEL revision including this procedure. 

All Operators Telex (AOT) A330-27A3158 Original issue, 

All Operators Telex (AOT) A340-27A4157 Original issue, 

AIRBUS Service Bulletin A330-27-3159, 
EASA AD No.: 2010-0109 

EASA Form 110 Page 4/4 

AIRBUS Service Bulletin A340-27-4158, 

AIRBUS Service Bulletin A340-27-5046, 

AIRBUS Service Bulletin A330-24-3011, 

AIRBUS Service Bulletin A340-24-4019. 

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. The required actions and the risk allowance have granted the 

issuance of a Final AD with Request for Comments, postponing the 

public consultation process after publication. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research 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. Fax: +33 5 61 93 45 80; 

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