Airworthiness Directive · Amendment 39-18995 · Fuselage
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, except airplanes that have been repaired as specified in Airbus Service Bulletin A300-53-0370; or Airbus Service Bulletin A300-53-6144, as applicable.
(1) 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, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
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 reports of cracks initiating at the upper radius of a certain frame and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of the frame. This AD requires repetitive inspections to detect cracking of the upper radius of the forward fitting of a certain frame, and related investigative actions and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
Except as required by paragraph (h) of this AD: Before exceeding 10,000 flight cycles since first flight of the airplane or within 30 days after the effective date of this AD, whichever occurs later, do a special detailed inspection (SDI) for cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,150 flight cycles, except as required by paragraph (j) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016.
(2) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016.
For airplanes previously inspected as specified in the applicable Airbus service information specified in paragraphs (h)(1) through (h)(6) of this AD and on which no cracking was found: Within 4,150 flight cycles after the most recent inspection, do the inspection for cracking of the FR 47 forward fitting upper radius required by paragraph (g) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 06, dated October 19, 2005.
(2) Airbus Service Bulletin A300-53-0246, Revision 07, dated September 9, 2008.
(3) Airbus Service Bulletin A300-53-6029, Revision 08, dated October 19, 2005.
(4) Airbus Service Bulletin A300-53-6029, Revision 09, dated September 9, 2008.
(5) Airbus Service Bulletin A300-53-6029, Revision 10, dated July 9, 2009.
(6) Airbus Service Bulletin A300-53-6029, Revision 11, dated September 28, 2009.
For airplanes on which any crack was found during any inspection done as specified in Airbus Service Bulletin A300-53-0246 or Airbus Service Bulletin A300-53-6029, as applicable, and on which any abnormal load event, such as hard landing or flight in excessive turbulence, occurred within 3 months before the effective date of this AD or occurs on or after the effective date of this AD: Within 3 months after each event, accomplish an SDI for cracking of the FR 47 forward fitting upper radius, left-hand and right-hand sides of the fuselage, in accordance with the applicable Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month period, another abnormal load event occurs, and if no SDI has yet been accomplished, before further flight after the second event, obtain corrective action instructions from the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), and accomplish those instructions accordingly.
If, during any SDI as required by paragraph (g), (h), or (i) of this AD, any crack is found: Before further flight, do the applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (g)(1) or (g)(2) of this AD, and obtain additional corrective action instructions from the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA, and accomplish those instructions accordingly before further flight.
Submit a report of the findings (both positive and negative) of each SDI inspection required by paragraphs (g), (h), and (i) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD.
(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
Accomplishing any inspection required by paragraph (g) or (h) of this AD terminates all requirements of AD 2007-26-14 for the inspected airplane.
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.
