Airworthiness Directive · Amendment 39-14595 · Airbus Model A310-200 and -300 Series Airplanes
Airbus Model A310-200 and -300 Series Airplanes
Superseded. A later AD replaced this one: AD 2009-06-06. Comply with the one in force.
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category; except for airplanes on which Airbus Modification 12247 has been embodied in production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-200 and -300 series airplanes. This AD requires repetitive inspections for cracking of the flap transmission shafts, and replacing the transmission shafts if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of longitudinal cracks due to stress corrosion in the transmission shafts between the power control unit (PCU) and the torque limiters of the flap transmission system. We are issuing this AD to detect and correct cracking of the flap transmission shaft, which could compromise shaft structural integrity and lead to a disabled flap transmission shaft and reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the earlier of the compliance times specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection for stress corrosion cracking of the flight transmission shafts located between the PCU and the torque limiters in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005. Thereafter, repeat the inspections as required by paragraph (g) of this AD. Before further flight, replace any cracked transmission shaft discovered during any inspection required by this AD with a new or reconditioned shaft, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000.
(1) Within 2,000 flight hours after the last flap asymmetry protection test performed in accordance with Airbus A310 Maintenance Planning Document (MPD) Task 275600-01-1.
(2) Within 8,000 flight cycles after the last flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1 or 800 flight cycles after the effective date of this AD, whichever comes later.
Note 1: Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, refers to Lucas Liebherr Service Bulletin 551A-27-624, Revision 1, dated August 18, 2000, as an additional source of service information for accomplishing the inspections.
Note 2: Airbus Service Bulletin A310-27-2092, Revision 02, refers to Airbus Service Bulletin A310-27-2095, dated March 29, 2000, as a source of service information for replacing the flap transmission shafts.
Note 3: Airbus Service Bulletin A310-27-2095 refers to Lucas Liebherr Service Bulletin 551A-27-M551-05, dated January 12, 2000, as an additional source of service information for replacing the flap transmission shafts.
Repeat the inspection required by paragraph (f) of this AD at the applicable times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(1) Before further flight after any occurrence of jamming of the flap transmission system.
(2) At intervals not to exceed 2,000 flight hours after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-01-1.
(3) At intervals not to exceed 8,000 flight cycles after each flap asymmetry protection test performed in accordance with Airbus A310 MPD Task 275600-02-1.
Replacing any flap transmission shaft with a new or reconditioned transmission shaft in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-27-2095, dated March 29, 2000, ends the inspections required for that transmission shaft only.
(i) Actions performed in accordance with Airbus Service Bulletin A310-27-2092, dated April 9, 1999; or Revision 01, dated December 11, 2001, are considered acceptable for compliance with the corresponding requirements of this AD.
Although Airbus Service Bulletin A310-27-2092, Revision 02, dated April 11, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
