Airworthiness Directive · Amendment 39-22144 · Fuselage
Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes
This AD applies to Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.) Model C-212-CB, C-212-CC, C-212-CD, C-212-CE, C-212-CF, C-212-DE, and C-212-DF airplanes, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020-0182R1, dated October 29, 2021 (EASA AD 2020-0182R1).
The FAA is superseding Airworthiness Directive (AD) 2021-16- 07, which applied to certain Airbus Defense and Space S.A. Model C-212- CB, C-212-CC, C-212-CD, C-212-CE, C-212-CF, C-212-DE, and C-212-DF airplanes. AD 2021-16-07 required repetitive inspections of the left- hand (LH) and right-hand (RH) side center wing fairings at a certain frame, around the wing leading edge for discrepancies (cracks), and repair if necessary. This AD was prompted by a modification developed to reinforce the structure in the affected area, providing an optional terminating action for the repetitive inspections required by AD 2021- 16-07. This AD continues to require the actions in AD 2021-16-07 and allows new optional terminating action for the repetitive inspections, 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 paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2020-0182R1.
(1) Where EASA AD 2020-0182R1 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2020-0182R1 refers to refers to August 27, 2020 (the effective date of EASA AD 2020-0182), this AD requires using September 28, 2021 (the effective date of AD 2021-16-07).
(3) Where paragraph (2) of EASA AD 2020-0182R1 specifies to “contact Airbus D&S for approved instructions and accomplish those instructions accordingly” if discrepancies are detected, for this AD if any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus Defense and Space S.A.'s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(4) The “Remarks” section of EASA AD 2020-0182R1 does not apply to this AD.
Although the service information referenced in EASA AD 2020-0182R1 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. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(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 Defense and Space S.A.'s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
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.
