Airworthiness Directive · Amendment 39-11789 · Airbus Model A300-600 Series Airplanes
Airbus Model A300-600 Series Airplanes
Superseded. A later AD replaced this one: AD 2013-20-10. Comply with the one in force.
Model A300-600 series airplanes, certificated in any category, on which Airbus Modification 10161 has not been installed in production.
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 supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that currently requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment requires revising the compliance thresholds for the inspection and requires that the inspections be repeated at reduced intervals. 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 fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
To prevent fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar, accomplish the following:
(a) Perform an ultrasonic inspection to detect fatigue cracking of the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, in accordance with Airbus Service Bulletin A300-57-6037, dated August 1, 1994, or Revision 1, dated August 31, 1995, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,800 flight cycles or 11,000 flight hours, whichever occurs first.
(1) For airplanes on which Airbus Modification 8842 (reference Airbus Service Bulletin A300-57-6039) has not been installed: Inspect at the earlier of the times specified by paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
(i) Prior to the accumulation of 17,000 total flight cycles, or within 2,000 flight cycles after May 10, 1995 (the effective date of AD 95-07-05, amendment 39-9187), whichever occurs later.
(ii) Prior to the accumulation of 39,000 total flight hours.
(2) For airplanes on which Airbus Modification 8842 has been installed: Inspect at the earlier of the times specified by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
(i) Within 17,000 flight cycles after accomplishment of Airbus Modification 8842, or within 2,000 flight cycles after May 10, 1995, whichever occurs later.
(ii) Within 39,000 flight hours after accomplishment of Airbus Modification 8842.
(b) If any crack is found, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6037, dated August 1, 1994, or Revision 1, dated August 31, 1995. Thereafter, perform the repetitive inspections required by paragraph (a) of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
