AD/A330/32 Amdt 2 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 1 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 2 | Main Landing Gear Retraction Actuator Piston Rod | 9/2005 |
Applicability: | AIRBUS A330 aircraft, models -201, -202, -203, -223, -243, -301, -302, -303, -321, |
Requirement: | 1. Visual Inspections. (a) Perform a visual inspection of the visible chromed surface of the piston rod in fully extended position to look for any crack in accordance with the instructions defined in AIRBUS Service Bulletin (SB) A330-32-3173R2. (b) If any crack is found during the inspection defined in Requirement 1(a) of this Directive, replace the affected retraction actuator in accordance with the instructions defined in AIRBUS SB A330-32-3173R2. 2. Drain the fluid from the piston rod and seal the vent hole. Carry out the procedure to drain fluid from the retraction actuator piston rod internal volume and seal the vent hole in accordance with instructions detailed in AIRBUS SB A330-32-3173R2. 3. Visual and Ultrasonic Inspections. (a) Perform a visual inspection of the visible chromed surface of the piston rod in fully extended position to look for any crack in accordance with the instructions defined in AIRBUS SB A330-32-3173R2. (b) If any crack is found during the inspection defined in Requirement 3(a) of this Directive, replace the affected retraction actuator in accordance with the instructions defined in AIRBUS SB A330-32-3173R2. (c) If no crack is found during the inspection defined in Requirement 3(a) of this Directive, perform a special detailed ultrasonic inspection of the retraction actuator piston rod eye end in accordance with the instructions defined in AIRBUS SB A330-32-3173R2. |
| (d) If the results of the inspection, as detailed in Requirement 3(c) of this Directive, give an indication above 90% Full Screen Height (FSH) and between 5 and 7 on the time base, replace the retraction actuator. (e) If the results of the inspection, as detailed in Requirement 3(c) of this Directive, give an indication between 75% and 90% FSH and between 5 and 7 on the time base, replace the retraction actuator. (f) If the results of the inspection, as detailed in Requirement 3(c) of this Directive, give an indication below 75% FSH and between 5 and 7 on the time base, repeat the visual and ultrasonic inspections and any subsequent rectification as required as detailed in Requirement 3 (a) though (f) of this Directive. 4. (a) In all cases report the results of the ultrasonic inspection (regardless of findings) and of the retraction actuator piston rod draining to the manufacturer. (b) Report the visual inspection results in accordance with the instructions detailed in AIRBUS SB A330-32-3173 R2. Later revisions of the service bulletins listed in this Directive may be used when approved by the French DGAC. Any retraction actuator piston rod PN 114256309 or 114256321, installed as a replacement, new or used, must be submitted to the mandatory actions defined in this Directive. Note: DGAC AD F-2005-098 EASA approval reference No 2005-5887 dated | |
Compliance: | For Requirement 1: (a) For actuators not inspected in accordance with AIRBUS SB 32-3173 at revision 1 or revision 2, prior to 3 years calender period Time In Service (TIS); Thereafter repeat at intervals not to exceed 8 calender days. For actuators previously inspected in accordance with AIRBUS SB 32-3173 at revision 1 or revision 2, within 8 days from the effective date of this Directive or from previous inspection conducted in accordance with AIRBUS SB 32-3173 at revision 1 or revision 2; Thereafter repeat at intervals not to exceed 8 calender days. (b) Before further flight following the inspection detailed in Requirement 1(a) of this Directive. |
| For Requirement 2: For actuators not previously inspected in accordance with AIRBUS SB 32-3173 original issue or revision 1 or revision 2, prior to 3 years calender TIS; Thereafter repeat at intervals not to exceed 4,200 flight hours or 12 months, whichever occurs first. For actuators previously inspected in accordance with AIRBUS SB 32-3173 original issue or revision 1 or revision 2, within 1,750 flight hours, 315 flight cycles or 5 months from the last inspection performed in accordance with AIRBUS SB For Requirement 3: (a) For actuators previously inspected in accordance with AIRBUS SB 32-3173 at original issue, revision 1 or revision 2, within 1,400 flight hours, 250 flights cycles or 4 months from the last inspection, whichever occurs first; Thereafter at intervals not to exceed 1400 flight hours, 250 flights cycles or 4 months, whichever occurs first. For actuators not previously inspected in accordance with AIRBUS SB (b) Before further flight following the inspection detailed in Requirement 3(a) of this Directive. (c) For actuators previously inspected in accordance with AIRBUS SB 32-3173 at original issue, revision 1 or revision 2, within 1,400 flight hours, 250 flights cycles or 4 months from the last inspection, whichever occurs first. For actuators not previously inspected in accordance with AIRBUS SB (d) Before further flight following the inspection detailed in Requirement 3(c) of this Directive. (e) Within the next 10 flights following the inspection as detailed in Requirement 3(c) of this Directive. (f) At intervals not exceeding 1400 flight hours, 250 flights cycles or 4 months from the last inspection, as detailed in Requirement 3(c) of this Directive, whichever occurs first. |
| For Requirement 4: (a) Upon completion of the task. (b) Whenever the retraction actuator is replaced in accordance with the instructions detailed in AIRBUS SB A330-32-3173R2. | |
| This Amendment becomes effective on 1 September 2005. | |
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 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 Directive requires 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. The original issue of this Directive became effective on 15 April 2004. Amendment 1 of this Directive became effective on 30 September 2004. |
James Coyne
Delegate of the Civil Aviation Safety Authority
19 July 2005
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