EASA AD No.: 2012

- 0244R1

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 2012 - 0244 R1

Date: 2 5 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 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 with the requ irements 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) exempt ion]

. 

### Design Approval Holder’s Name : AIRBUS Type/Model designation(s) : A330 and A340

- 200/

- 300 aeroplanes

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

F oreign AD: Not applicable
Revision : This AD revises EASA AD 2012

- 0 244 dated 1 5 November 2012 , which

supersede d EASA AD 201 2

- 0 070 dated 25 April 201 2, including the Correction dated 26 April 201 2.



### 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 thei r 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 flig ht 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 andEASA AD No.: 2012

- 0244R1

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. if necessary, to apply t he 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 eve nts 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 supersede d 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 i ssued , additional in

- service events have been reported on a eroplanes 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 th ose check valves. For th e reason s described above , this new AD partially retains the requirements of EASA AD 2012

- 0070 , whic h 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 requirement s for check valves P/N CAR401 of EASA AD 2012

- 0070 are no longer part of this AD. This AD is revised to clarify whic h 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: 0 1 Febru ary 2013 Original issue: 29 November 2012 Required A ction(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 F light H ours (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 Rev ision 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 , b efore next flight, inspect the yellow and blueEASA AD No.: 2012

- 0244R1

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 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 0 2, 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 replace d with a chec k 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 valve s P/N CAR401, in which case the requirements of paragraph s ( 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 inspection s 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: Th is 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 g reen, b lue and y ellow h igh p ressure 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 do es 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 ] , a t each replacement of a check valve with a check valve P/N CAR401 , apply a torque of 141 to 143 N m (103.98 to 105.45 lbf.ft) during installation on an aeroplane.
Ref. Public ations: Airbus AOT A330

- 29A3111 original issue dated 02 September 2009, or Revision 01 dated 08 October 2009.EASA AD No.: 2012

- 0244R1

TE. CAP.00110

- 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 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 Revisio n 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 t he 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 A D 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

.