Airworthiness Directive · Amendment 39-11661 · Airbus Model A300 Series Airplanes
Airbus Model A300 Series Airplanes
Model A300 series airplanes, as listed in Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998; certificated in any category; except those on which Airbus Service Bulletin A300-53-0282 or Airbus Service Bulletin A300-53-0291 has been accomplished.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 A300 series airplanes, that requires modification of wing center box angle fittings at frame 47. 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 reduced structural integrity of the wing center box angle fittings at frame 47 due to fatigue cracking.
To prevent reduced structural integrity of the wing center box angle fittings at frame (FR) 47, accomplish the following:
(a) Prior to the accumulation of the applicable threshold specified in the “MANDATORY TH” column of the table in paragraph 1.B.(4) of the service bulletin, or within 6,500 flight cycles after the effective date of this AD, whichever occurs later: Except as required by paragraph (b) of this AD, modify the wing center box angle fittings at FR 47 (including removing certain sealant and fasteners, performing rotating probe inspections to detect cracking, cold working certain fastener holes, installing new fasteners and sealant, and repairing damage), in accordance with Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998.
Note 2: Operators should note that the area required to be modified by paragraph (a) of this AD remains subject to the requirements of AD 96-13-11, amendment 39-9679, after modification.
(b) Where Airbus Service Bulletin A300-53-0298, Revision 03, dated November 26, 1998, specifies that Airbus be contacted for repair instructions for certain damage conditions, this AD requires that such damage conditions be repaired prior to further flight in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile (DGAC) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference 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.
