EASA AD No.: 2012-0244R1

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0244R1

Date: 25 January 2013

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 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].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A330 and A340-200/-300 aeroplanes

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

Foreign AD: Not applicable

Revision: This AD revises EASA AD 2012-0244 dated 15 November 2012, which 

superseded EASA AD 2012-0070 dated 25 April 2012, including the Correction 

dated 26 April 2012.

ATA 29 Hydraulic Power – High Pressure Manifold Check Valves –

Inspection

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 (MSN), and

Airbus A340-211, A340-212, A340-213, A340-311, A340-312 and A340-313 

aeroplanes, all MSN.

Reason: An A330 operator experienced a yellow hydraulic circuit low level due to a

loose check valve, Part Number (P/N) CAR401. During the inspection on the 

other two hydraulic systems, the other three check valves P/N CAR401 were 

also found to be loose with their lock wire broken in two instances. Airbus 

A340 aeroplanes are also equipped with P/N CAR401 high pressure 

manifold check valves.

Additional cases of P/N CAR401 check valve loosening have been reported 

on aeroplanes having accumulated more than 1 000 flight cycles (FC). The 

check valve fitted on the Yellow hydraulic system is more affected, due to 

additional system cycles induced by cargo door operation.

This condition, if not detected and corrected, could result in hydraulic leaks, 

possibly leading to the loss of all three hydraulic systems and consequent 

loss of control of the aeroplane.

To address this unsafe condition, EASA issued Emergency AD 2009-0223-E 

to require an inspection programme to detect any check valve loosening and 
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if necessary, to apply the applicable corrective actions.

EASA AD 2010-0145, which superseded EASA EAD 2009-0223-E retaining 

its requirements, was issued to expand the applicability to the newly certified 

models A330-223F and A330-243F.

Prompted by further reported in-service events of check valve P/N CAR401 

loosening before reaching the threshold of 700 FC, EASA AD 2011-0139, 

which superseded EASA AD 2010-0145, retaining its requirements, was 

issued to:

- extend the requirement to identify the P/N CAR401 check valves to all

aeroplanes, and to

- reduce the inspection threshold for aeroplanes fitted with check valve P/N 

CAR401, either installed in production through Airbus modification 54491, or 

installed in service through Airbus Service Bulletin (SB) A330-29-3101 or 

Airbus SB A340-29-4078.

EASA AD 2012-0070, which superseded EASA AD 2011-0139, retaining its 

requirements, was issued to require an increased torque value of the check 

valve tightening and High Pressure (HP) manifold re-identification.

Since EASA AD 2012-0070 was issued, additional in-service events have 

been reported on aeroplanes fitted with check valves on which the increased 

torque value had been applied. Based on those events, it has been 

concluded that the action to re-torque the check valves with an increased 

value is not a satisfactory terminating action for addressing the issue of 

those check valves.

For the reasons described above, this new AD partially retains the 

requirements of EASA AD 2012-0070, which is superseded. Additionally, for 

aeroplanes equipped with P/N CAR401 on which the increased torque value 

has been applied, this new AD requires repetitive inspections of the check 

valves and HP manifolds. Finally, this AD also requires application of a 

lower torque value when a check valve P/N CAR401 is installed on an 

aeroplane.

Note: the reporting and the torque value increase requirements for check 

valves P/N CAR401 of EASA AD 2012-0070 are no longer part of this AD.

This AD is revised to clarify which actions are required for P/N CAR401 

check valves, depending on applied (or not) torque value.

This AD is still considered to be an interim action and further AD action may 

follow.

Effective Date: Revision 1: 01 February 2013

Original issue: 29 November 2012

Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously:

Re-statement of the requirements of EASA AD 2012-0070:

(1) For aeroplanes equipped with P/N CAR400 check valves, or equipped 

with P/N CAR401 check valves on which the increased torque value of 

400 Nm has never been applied:

Within 900 Flight Hours (FH) after 08 August 2011 [the effective date of 

EASA AD 2011-0139], accomplish a visual inspection of the check 

valves on Blue, Green and Yellow hydraulic systems to identify their 

P/N in accordance with the instructions of Airbus SB A330-29-3111 

Revision 02, or Airbus SB A340-29-4086 Revision 02, as applicable to 

aeroplane type.

(2) If during the inspection as required by paragraph (1) of the AD, it is 

identified that check valves P/N CAR401 are installed on all three 

hydraulic systems, before next flight, inspect the yellow and blue
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system check valves and, depending on findings, apply the applicable

corrective actions, before next flight, in accordance with the instructions 

of Airbus SB A330-29-3111 Revision 02, or Airbus SB A340-29-4086 

Revision 02, as applicable to aeroplane type.

(3) Within 900 FH after accomplishment of the actions as required by 

paragraph (2) of this AD, and, thereafter, at intervals not to exceed 900 

FH, perform the inspection programme on green, yellow and blue 

system check valves and, depending on findings, apply the applicable 

corrective actions, before next flight, in accordance with the instructions 

of SB A330-29-3111 Revision 02, or SB A340-29-4086 Revision 02, as 

applicable to aeroplane type.

(4) If during the inspection as required by paragraph (1) of the AD, it is 

identified that check valves P/N CAR401 are not installed on all three 

hydraulic systems, no immediate further action is required, except if a

check valve P/N CAR400 is replaced with a check valve P/N CAR401;

before next flight after that replacement, the aeroplane configuration 

must be inspected to determine if all three hydraulic systems are 

equipped with check valves P/N CAR401, in which case the 

requirements of paragraphs (2) and (3) of this AD must be 

accomplished.

(5) Inspections and corrective actions accomplished before 08 August 

2011 [the effective date of EASA AD 2011-0139], in accordance with 

the instructions of Airbus All Operators Telex (AOT) A330-29A3111 at 

Original issue or Revision 01, or AOT A340-29A4086 at Original issue 

or Revision 01, as applicable to aeroplane type, are acceptable to 

comply with the initial inspection programme as required by paragraph 

(2) of this AD. After 08 August 2011 [the effective date of EASA AD

2011-0139], all inspections and corrective actions, as required by 

paragraph (3) of this AD, must be accomplished in accordance with the 

instructions of Airbus SB A330-29-3111 Revision 02, or Airbus SB 

A340-29-4086 Revision 02, as applicable to aeroplane type.

New requirements introduced by the original issue of this AD:

(6) For aeroplanes equipped with P/N CAR401 check valves on which the 

increased torque value of 400 Nm has been applied:

Note: This increased torque value was applied with Airbus modification 

201384 in production, or through Airbus SB A330-29-3119 or Airbus SB 

A340-29-4091, as applicable, in-service.

(6.1) Within 1 000 FH after 29 November 2012 [the effective date of 

this AD at original issue], and, thereafter, at intervals not to 

exceed 900 FH, visually inspect the green, blue and yellow high 

pressure manifolds and check valves P/N CAR401 in accordance 

with the instructions of Airbus AOT A29L001-12.

(6.2) If, during any inspection as required by paragraph (6.1) of this 

AD, a discrepancy is found, before next flight, accomplish the 

applicable corrective actions in accordance with the instructions 

of Airbus AOT A29L001-12.

(7) Accomplishment of corrective actions as required by this AD does not 

constitute terminating action for the repetitive inspections required by 

this AD.

(8) From 29 November 2012 [the effective date of this AD at original issue], 

at each replacement of a check valve with a check valve P/N CAR401, 

apply a torque of 141 to 143 Nm (103.98 to 105.45 lbf.ft) during 

installation on an aeroplane.

Ref. Publications: Airbus AOT A330-29A3111 original issue dated 02 September 2009, or

Revision 01 dated 08 October 2009.
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Airbus SB A330-29-3111 Revision 02 dated 23 June 2011.

Airbus SB A330-29-3119 original issue dated 19 April 2011, or Revision 01

dated 09 December 2011, or Revision 02 dated 09 March 2012.

Airbus AOT A340-29A4086 original issue dated 02 September 2009, or

Revision 01 dated 08 October 2009.

Airbus SB A340-29-4086 Revision 02 dated 23 June 2011.

Airbus SB A340-29-4091 original issue dated 19 April 2011, or Revision 01

dated 09 December 2011.

Airbus AOT A29L001-12 dated 11 October 2012.

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, 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 – EIAL;

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