Airworthiness Directive · Amendment 39-22201 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as specified in European Union Aviation Safety Agency (EASA) AD 2021-0288, dated December 21, 2021 (EASA AD 2021-0288).
(1) Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes.
(2) Model A300 B4-603 and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R airplanes.
The FAA is superseding Airworthiness Directive (AD) 2000-20- 15, which applied to certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000-20-15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000-20-15, but at reduced compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2021-0288.
(1) Where paragraph (1) of EASA AD 2021-0288 specifies, for certain conditions, using the compliance time and repetitive intervals “in the applicable SB,” and where “the applicable SB” specifies that the “1st inspection will be done within [a specified number of flight cycles] after receipt of the Service Bulletin,” this AD requires compliance within the specified number of flight cycles after the effective date of this AD.
(2) Where EASA AD 2021-0288 refers to its effective date, this AD requires using the effective date of this AD.
(3) The “Remarks” section of EASA AD 2021-0288 does not apply to this AD.
Although the service information referenced in EASA AD 2021-0288 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
For more information about this AD, contact Dan Rodina, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-3225; email dan.rodina@faa.gov.
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.
