Airworthiness Directive · Amendment 39-11798 · Airbus Model A310 Series Airplanes
Airbus Model A310 Series Airplanes
Model A310 series airplanes, certificated in any category, except those airplanes on which Airbus Modification 10855 or Airbus Service Bulletin A310-27-2075 has been accomplished.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires modification of the position 1 flap screw jack. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane.
To prevent fracture of the lead screw of the position 1 flap screw jack, which could result in failure of the tie bar and possible disconnection of the flap structure from the airplane, accomplish the following:
(a) Within 18 months after the effective date of this AD, modify the position 1 flap screw jack in accordance with Airbus Service Bulletin A310-27-2075, Revision 02, dated February 8, 2000.
Note 2: Modifications accomplished prior to the effective date of this AD, in accordance with Airbus Service Bulletin A310-27-2075, dated November 18, 1994, or Revision 01, dated July 20, 1995, are considered acceptable for compliance with the modification specified by this AD.
Note 3: The Airbus service bulletin references Lucas/Liebherr Service Bulletin 537-27-M537-15, dated May 12, 1994, as an additional source of service information for accomplishing the applicable action required by this AD.
(b) As of the effective date of this AD, no person shall install on any airplane a position 1 flap screw jack having part number 537G0000-02, unless modified in accordance with this AD.
