Airworthiness Directive · Amendment 39-18977 · Wings
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2018-17-10. Comply with the one in force.
This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, on which Airbus Modification 10221 was embodied in production.
(1) Airbus Model A300 B4-605R and B4-622R airplanes.
(2) Airbus Model A300 C4-605R Variant F airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. This AD was prompted by the results of a full stress analysis of the lower area of a certain frame that revealed that a crack could occur in this area after a certain number of flight cycles. This AD requires an inspection of the lower area of a certain frame radius for cracking, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
At the later of the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection of the lower area of the FR 40 radius for cracking, in accordance with paragraph 4.2.2 in Airbus Alert Operators Transmission (AOT) A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13, 2016.
(1) Prior to exceeding 19,000 total flight cycles or 41,000 total flight hours since the airplane's first flight, whichever occurs first.
(2) Within 300 flight cycles or 630 flight hours after the effective date of this AD, whichever occurs first.
For airplanes on which the HFEC inspection required by paragraph (g) of this AD was accomplished before the effective date of this AD using the procedures in Airbus AOT A57W009-16, Rev 00, including Appendices 1 and 2, dated February 25, 2016: Within 300 flight cycles or 630 flight hours after the effective date of this AD, whichever occurs first, do a one-time additional HFEC inspection of the lower area of the FR 40 radius for cracking, in accordance with paragraph 4.2.2 in Airbus AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13, 2016.
If any crack is found during the inspection required by paragraph (g) or (h) of this AD: Before further flight, do the applicable corrective actions in accordance with the procedures in Airbus AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13, 2016. Where AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated July 13, 2016, specifies to contact Airbus for appropriate action, accomplish the corrective actions in accordance with the procedures specified in paragraph (m)(2) of this AD.
Accomplishment of the actions required by paragraphs (g), (h), and (i) of this AD, in accordance with, and at the compliance times specified in, the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017, is acceptable for compliance with the requirements of those paragraphs.
Submit a report of all findings (both positive and negative) from the inspection required by paragraph (g) of this AD to Airbus Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10; or submit the results to Airbus in accordance with the procedures in Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
(1) For airplanes on which the inspection specified in paragraph (g) of this AD is accomplished on or after the effective date of this AD: Submit the report within 30 days after performing the inspection.
(2) For airplanes on which the inspection specified in paragraph (g) of this AD is accomplished before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
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.
