Airworthiness Directive · Amendment 39-11676 · Airbus Model A300-600 Series Airplanes
Airbus Model A300-600 Series Airplanes
Model A300-600 series airplanes, on which Airbus Modification 11044 or Airbus Modification 11045 (reference Airbus Service Bulletin A300-53-6063, dated December 12, 1996) has not been accomplished, certificated in any category.
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 (f) 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 A300-600 series airplanes, that requires repetitive inspections to detect cracking of the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, and corrective actions, if necessary. 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 detect and correct fatigue cracking in the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box. Such cracking and discrepancies could result in reduced structural integrity of the airplane.
To detect and correct fatigue cracking of the doubler angle and discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, which could result in reduced structural integrity of the airplane, accomplish the following:
(a) Perform a detailed visual inspection to detect cracking of the doubler angle, and a detailed external visual inspection to detect discrepancies of the fasteners that connect the doubler angle and the bottom panel of the center wing box, on the left and right sides of the airplane, in accordance with Airbus Service Bulletin A300-53-6110, Revision 01, dated December 10, 1998, at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. Thereafter, repeat the inspections of the doubler angle and fasteners at intervals not to exceed 2,400 flight cycles.
(1) For airplanes on which a detailed visual inspection has been performed within the last 2,400 flight cycles prior to the effective date of this AD, in accordance with Structural Significant Item (SSI) 57-10-19 of the Airbus A300-600 Maintenance Review Board (MRB) Document: Inspect within 2,400 flight cycles after the most recent SSI inspection.
(2) For airplanes on which a detailed visual inspection has not been performed within the last 2,400 flight cycles prior to the effective date of this AD, in accordance with Structural Significant Item (SSI) 57-10-19 of the Airbus A300-600 Maintenance Review Board (MRB) Document: Inspect at the time specified in paragraph (a)(2)(i), (a)(2)(ii), or (a)(2)(iii), as applicable.
(i) For airplanes that have accumulated 6,600 or more total flight cycles as of the effective date of this AD: Inspect within 750 flight cycles after the effective date of this AD.
(ii) For airplanes that have accumulated more than 3,100 total flight cycles, but less than 6,600 total flight cycles as of the effective date of this AD: Inspect within 1,500 flight cycles after the effective date of this AD.
(iii) For airplanes that have accumulated 3,100 total flight cycles or less as of the effective date of this AD: Inspect prior to the accumulation of 4,600 total flight cycles.
Note 2: Accomplishment of inspections or corrective actions prior to the effective date of this AD, in accordance with Airbus Service Bulletin A300-53-6110, dated April 8, 1997, is acceptable for initial compliance with the applicable paragraph of this AD.
Note 3: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(b) If any discrepancy is found in a fastener that connects the doubler angle and the bottom panel of the center wing box during any detailed external visual inspection performed in accordance with paragraph (a) of this AD: Prior to further flight, remove the discrepant fastener, and perform a rotating probe inspection to detect discrepancies of the fastener holes, in accordance with Airbus Service Bulletin A300-53-6110, Revision 01, dated December 10, 1998.
(1) If no discrepancy is found in any fastener hole, prior to further flight, install a new fastener, in accordance with the service bulletin. Thereafter, repeat the inspections required by paragraph (a) of this AD at intervals not to exceed 2,400 flight cycles.
(2) If any discrepancy is found in any fastener hole, prior to further flight, except as provided by paragraph (e) of this AD, repair in accordance with the service bulletin, and accomplish the actions required by paragraph (c) of this AD.
(c) If any crack is found in the doubler angle during any detailed visual inspection performed in accordance with paragraph (a) of this AD, accomplish paragraph (c)(1) or (c)(2), as applicable, at the time specified in that paragraph.
(1) If the cracking is within the limits specified in Figure 1, Sheet 1, of Airbus Service Bulletin A300-53-6110, Revision 01, dated December 10, 1998: Except as required by paragraph (e) of the AD, accomplish the applicable corrective actions (e.g., crack stopping of hole, rotating probe inspection, repetitive detailed visual inspections, eventual modification of doubler angle) specified in Figure 1, Sheet 1; at the times and in accordance with the procedures specified in the service bulletin.
(2) If the cracking is outside the limits specified in Figure 1, Sheet 1 [i.e., 1.181 inches (30 millimeters) or more in length]: Prior to further flight, modify the doubler angle in accordance with Airbus Service Bulletin A300-53-6063, dated December 12, 1996. Accomplishment of the modification constitutes terminating action for the repetitive inspection requirements of this AD.
(d) Accomplishment of the modification in accordance with Airbus Service Bulletin A300-53-6063, dated December 12, 1996, constitutes terminating action for the repetitive inspection requirements of this AD.
(e) If any discrepancy is found during any inspection required by this AD, and the service bulletin specifies to contact Airbus for appropriate action: Prior to further flight, repair 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.
