Airworthiness Directive · Amendment 39-18024 · Fuselage
Airbus Airplanes
This AD applies to Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers.
(1) Model A300 B4-603 and A300 B4-622 airplanes.
(2) Model A300 B4-605R and A300 B4-622R airplanes.
(3) Model A300 F4-605R and A300 F4-622R airplanes.
(4) Model A300 C4-605R Variant F airplanes.
(5) Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600R and Model A300 F4-600R series airplanes; Model A300 B4-603, B4-622, and C4-605R Variant F airplanes; and Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that a section of the fuselage structure above the forward cargo door is subject to widespread fatigue damage (WFD). This AD requires an inspection for cracks of the fastener and tooling holes at certain locations and a check of the diameter of the holes, and repair or modification of the affected fuselage structure if necessary. We are issuing this AD to address the unsafe condition on these products.
Before exceeding 42,500 flight cycles since the first flight of the airplane, do a check of the diameter of the fastener holes and tooling holes and a rototest inspection for cracks of all holes of removed fasteners and the tooling holes at the locations specified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as applicable.
If any condition specified in paragraph (h)(1) or (h)(2) of this AD is found, prior to further flight, repair in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). Concurrently with the repair, unless the approved repair instructions specify otherwise, modify the affected structure, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as applicable.
(1) Any crack is found during the rototest inspection required by paragraph (g) of this AD.
(2) Any hole diameter greater than or equal to the maximum starting hole diameter specified in the Accomplishment Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as applicable, is found during the check required by paragraph (g) of this AD.
If, during the actions required by paragraph (g) of this AD, no crack is found and the hole diameter is less than the maximum starting hole diameter specified in the Accomplishment Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as applicable: Before further flight, modify the affected fuselage structure, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as applicable.
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.
