AD/A330/32 Amdt 4 Main Landing Gear Retraction Actuator Piston Rod (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A330/32 Amdt 3 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Airbus Industrie A330 Series Aeroplanes
| AD/A330/32 Amdt 4 | Main Landing Gear Retraction Actuator Piston Rod | 12/2009 |
Applicability: | Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342 and -343, all serial numbers, except those on which Airbus modification (mod.) 52980 has been embodied in production or Airbus Service Bulletin (SB) A330-32-3180 Revision 01 or Airbus SB A330-32-3174 Revision 02 has been embodied in-service. Note: Aeroplanes which have received application of Airbus Service Bulletin (SB) A330-32-3173 at original issue or at Revision 01 or at Revision 02 are still affected by this AD. |
Requirement: | Action in accordance with EASA AD 2006-0302R1 with a revised effective date of 23 November 2006. |
Compliance: | Remains unchanged as detailed in amendment 3 of this AD as: In accordance with EASA AD 2006-0302R1 with a revised effective date of 23 November 2006. Compliance with Paragraph 6 of EASA AD 2006-0302R1 has a revised date of |
| This Amendment becomes effective on 19 November 2009. | |
Background: | During an approach phase, the flight crew of an A330 aircraft had to perform a free-fall extension of the left hand main landing gear. Rupture of the piston rod of the left hand main landing gear retraction actuator was observed near to the rod attachment point. The inspection revealed the presence of corrosion and many cracks in the vicinity of the break. This rupture led to an un-damped extension of the landing gear, which resulted in very high forces throughout the whole gear at full extension. The structural integrity of the landing gear was compromised. This situation, if not corrected, could lead to a potentially hazardous event during extension and landing. Amendment 1 of this AD was in response to another incident occurring since the issue of the original issue of this Directive. This amendment required more frequent visual inspection of the gear retract actuator. |
| Amendment 2 of this AD required additional work to be carried out including draining of fluid from the internal volume of the retraction actuator piston rod. It has been determined that the presence of water in the internal volume can present a potential source of stress in the piston rod. Amendment 3 changed the interval for the fluid drain procedure which has been extended. Removed the need of a visual inspection provided that a fluid drain and a one-time ultrasonic inspection of the entire piston rod are carried out. Added a new one-time ultrasonic longitudinal and circumferential inspection of the full piston rod and mandated a new design piston rod as a terminating action. Amendment 4 extends the service usage for retraction actuator piston rod part number (P/N) 114256321 issue 06 which has been re-identified as P/N 114256326 issue 01 in accordance with the instructions defined in SB A330-32-3216. The original issue of this AD became effective on 15 April 2004. Amendment 1 of this AD became effective on 30 September 2004. Amendment 2 of this AD became effective on 1 September 2005. Amendment 3 of this AD became effective on 23 November 2006. |
David Villiers
Delegate of the Civil Aviation Safety Authority
28 September 2009
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