Airworthiness Directive · Amendment 39-18862 · Fuselage
Airbus Airplanes
(1) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, that have accumulated more than 14,600 total flight cycles as of the effective date of this AD.
(2) Airbus Model A300 F4-605R and F4-622R airplanes in the post-Modification 12046 configuration are not affected by the requirements of this AD.
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); and Model A310 series airplanes. This AD was prompted by a report indicating that during inspections to detect corrosion of the bulk cargo doors, several cracks were discovered. This AD requires inspections of the bulk cargo door frame to identify any structural repairs and cracking, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
Within 250 flight cycles or 6 months after the effective date of this AD, whichever occurs first: Do a general visual inspection of the bulk cargo door frame to identify the existence of any structural repairs, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A53W010-15, Revision 01, including Appendixes 1, 2, 3, and 4, dated October 4, 2016. A review of airplane maintenance records is acceptable in lieu of this inspection as long as the existence of any structural repairs can be conclusively determined from that review. If no structural repairs are found or identified during the inspection or maintenance records review, no further action is required by this AD for that airplane.
If, during the general visual inspection required by paragraph (g) of this AD or the maintenance records review specified in paragraph (g) of this AD, any repair is found or identified on the bulk cargo door frame: Before further flight, do a detailed visual inspection for cracking of the frame at the repaired area, in accordance with the instructions of Airbus AOT A53W010-15, Revision 01, including Appendixes 1, 2, 3, and 4, dated October 4, 2016.
If any cracking is found during the detailed visual inspection required by paragraph (h) of this AD: 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).
If no cracking is found during the detailed visual inspection required by paragraph (h) of this AD: Do the actions in paragraphs (j)(1) and (j)(2) of this AD.
(1) At the applicable time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD: Send a report of the inspection results to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/).
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD.
(2) Within 2,800 flight cycles after the detailed visual inspection required by paragraph (h) of this AD: Do applicable post-repair inspections and repairs, using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.
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.
