Airworthiness Directive · Amendment 39-19364 · Wings
Airbus SAS Airplanes
This AD applies to Airbus SAS airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, on which Airbus SAS Modification 10221 was embodied in production.
(1) Airbus SAS Model A300 B4-605R and B4-622R airplanes.
(2) Airbus SAS Model A300 C4-605R Variant F airplanes.
(3) Airbus SAS Model A300 F4-605R and F4-622R airplanes.
We are superseding Airworthiness Directive (AD) 2017-15-17, which applied to certain Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. AD 2017-15-17 required an inspection of the lower area of a certain frame (FR) radius for cracking, and corrective action if necessary. This AD requires new repetitive inspections of the forward fitting lower radius of a certain frame for cracking, and corrective actions if necessary. This AD was prompted by a determination that repetitive inspections and applicable corrective actions are necessary. We are issuing this AD to address the unsafe condition on these products.
(1) For the purpose of this AD, the average flight time (AFT) can be established by dividing the flight hours (FHs) by the flight cycles (FCs) counted:
(i) From first flight, for selecting the inspection threshold of the non-repaired area.
(ii) From repair, for selecting the inspection threshold of the repaired area.
(iii) From the last inspection, for selecting the inspection interval.
(2) For the purpose of this AD, Group 1 airplanes are those airplanes already inspected in accordance with paragraph 4.2.2 in Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated July 13, 2016, before the effective date of this AD. Group 2 airplanes are those airplanes not inspected in accordance with paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016, as of the effective date of this AD.
(3) For the purpose of this AD, inspection method A is a high frequency eddy current (HFEC) inspection of the radius and fastener area. Inspection method B is a HFEC inspection of the radius and fastener area and a rototest of the fastener hole. Both are defined as a special detailed inspection (SDI) in this AD.
Within the compliance time values specified in table 1 to paragraph (h) of this AD (Group 1 airplanes) or table 2 to paragraph (h) of this AD (Group 2 airplanes), as applicable, and, thereafter, at intervals not exceeding the values specified in table 3 to paragraph (h) of this AD: Do a SDI for cracking of any non-repaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017; except where Airbus Service Bulletin A300-57-6120, dated April 28, 2017, specifies contacting Airbus SAS for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (m)(2) of this AD and accomplish those instructions.
Within the compliance time values specified in table 4 to paragraph (i) of this AD, and, thereafter, at intervals not exceeding those same values, do a SDI for cracking of the repaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017; except where Airbus Service Bulletin A300-57-6120, dated April 28, 2017, specifies contacting Airbus SAS for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (m)(2) of this AD and accomplish those instructions.
If any crack is found during any inspection required by paragraph (h) or (i) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017.
Submit a report of the findings (both positive and negative) of each inspection required by paragraphs (h) and (i) of this AD to Airbus SAS, in accordance with the instructions of Airbus Service Bulletin A300-57-6120, dated April 28, 2017, 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.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
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.
