Airworthiness Directive · Amendment 39-17668 · Fuselage
Airbus Airplanes
This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes, on which any repair has been done as specified in Airbus Service Bulletin A300-53-0337, dated February 4, 1999; or Airbus Service Bulletin A300-53-0337, Revision 01, dated March 17, 2003.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; and A300 C4-605R Variant F airplanes; on which any repair has been done as specified in any of the service information identified in paragraphs (c)(2)(i), (c)(2)(ii), (c)(2)(iii), (c)(2)(iv), (c)(2)(v), and (c)(2)(vi) of this AD.
(i) Airbus Service Bulletin A300-53-6111, dated February 4, 1999.
(ii) Airbus Service Bulletin A300-53-6111, Revision 01, dated March 17, 2003.
(iii) Airbus Service Bulletin A300-53-6111, Revision 02, dated September 13, 2004.
(iv) Airbus Service Bulletin A300-53-6111, Revision 03, dated September 30, 2009.
(v) Airbus Mandatory Service Bulletin A300-53-6111, Revision 04, dated August 25, 2011.
(vi) Airbus Mandatory Service Bulletin A300-53-6111, Revision 05, dated January 28, 2013.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; 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 report that cracking was found in area 2 of the frame base fittings between frame 41 and frame 46. This AD requires a check of maintenance records to determine if certain repairs were done in area 1 of the frame base fittings, and, for affected airplanes, a detailed inspection for cracking in area 2 of the frame base fittings between frame 41 and frame 46, and repair if necessary. We are issuing this AD to detect and correct cracking in area 2 of the frame base fittings between frame 41 and frame 46, which could adversely affect the structural integrity of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 1,000 flight hours after the effective date of this AD: Check the airplane maintenance records to determine if repairs were done in area 1 of the frame base fittings as defined in Appendix 1 of Airbus Alert Operators Transmission A53W001-12, dated July 4, 2012.
If, during any records check required by paragraph (g) of this AD, it is determined that area 1 of the frame base fittings was repaired: Within 1,000 flight hours after the effective date of this AD, do a detailed inspection of the frame base fittings between frame 41 and frame 46 in area 2 as defined in Appendix 1 of Airbus Alert Operators Transmission A53W001-12, dated July 4, 2012.
If any cracking is found during any detailed inspection required by paragraph (h) of this AD: Before further flight, repair the cracking using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
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.
