Airworthiness Directive · Amendment 39-18787 · Wings
Airbus Airplanes
This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) All Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, except those on which Airbus modification 10599 has been incorporated.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a determination that certain inspection thresholds and intervals must be reduced. This AD requires repetitive detailed inspections for corrosion of the lower wing root joint, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, on which Airbus modification 10599 has been incorporated: As of the effective date of this AD, the actions specified in AD 98-21-34 are no longer required. No action is required by this AD.
Within 60 months since the airplane's first flight, or within 60 months since accomplishment of the last inspection specified in Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever occurs later: Do a detailed inspection for corrosion of the rib 1 external lower surface splice between frame (FR)40 and FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable. Repeat the inspection thereafter at intervals not to exceed 60 months. Accomplishment of the initial inspection required by this paragraph terminates the requirements of AD 98-21-34 for Model A300 and A300-600 series airplanes.
If any corrosion is found during any inspection required by paragraph (h) of this AD, do the actions specified in paragraph (i)(1) and (i)(2) of this AD.
(1) Before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(1) of this AD.
(2) At the applicable time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, except as required by paragraph (j)(2) of this AD: Do fatigue inspections to detect cracks of the fasteners and on the surface of the forward and aft lower surface panels, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable. Repeat the fatigue inspections thereafter at the applicable interval specified in paragraph B.(5) of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(2) of this AD. If any cracking is found during any fatigue inspection required by this paragraph: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(i) For Model A300 series airplanes: Do the initial inspection at the applicable time specified in paragraph B.(5) of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999.
(ii) For Model A300-600 series airplanes: Do the initial inspection at the later of the times specified in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
(A) At the applicable time specified in Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011.
(B) Within 500 flight cycles or 1,050 flight hours after the effective date of this AD, whichever occurs first, without exceeding the compliance time specified in Airbus Service Bulletin A300-57-6047, Revision 05, dated May 27, 2008.
(1) Where Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; specifies to contact Airbus for appropriate corrective action, this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
(2) Where Airbus Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011, specifies to contact Airbus for the appropriate threshold or repetitive interval, this AD requires that the compliance time be determined using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
For the purposes of paragraph (i)(2) of this AD, the AFT must be established as specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD.
(1) For the initial inspection, the AFT is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD.
(2) For the first repeated inspection interval, the AFT is the total accumulated flight hours divided by the total accumulated flight cycles at the time of the inspection threshold.
(3) For all inspection intervals onward, the AFT is the flight hours accumulated between the two most recent inspections divided by the flight cycles accumulated between the two most recent inspections.
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.
