Airworthiness Directive · Amendment 39-21849 · Time limits/maintenance checks
Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.) Airplanes
This AD applies to all Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2018-25- 16, which applied to certain Airbus Defense and Space S.A. Model CN- 235, CN-235-200, and CN-235-300 airplanes. AD 2018-25-16 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2018-25-16, the FAA has determined that additional new or more restrictive airworthiness limitations, including inspections for discrepancies (cracking) of certain structural elements, are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, and repetitive inspections for discrepancies (cracking) of certain structural elements and corrective actions; 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, European Union Aviation Safety Agency (EASA) AD 2020-0251, dated November 11, 2020 (EASA AD 2020-0251).
(1) Where EASA AD 2020-0251 refers to its effective date, this AD requires using the effective date of this AD.
(2) The requirements specified in paragraph (4) of EASA AD 2020-0251 do not apply to this AD.
(3) Where paragraph (5) of EASA AD 2020-0251 specifies actions if discrepancies are found while accomplishing any task “required by paragraph (1), (2), (3) or (4) of this [EASA] AD,” this AD requires actions if discrepancies are found while accomplishing any task “required by paragraph (1), (2), or (3) of EASA AD 2020-0251.”
(4) Where paragraph (5) of EASA AD 2020-0251 specifies actions “in case of finding discrepancies,” for this AD, discrepancies include fatigue cracking.
(5) Paragraph (6) of EASA AD 2020-0251 specifies revising “the approved AMP” within 12 months after its effective date, but this AD requires, for airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before March 20, 2018, revising the existing maintenance or inspection program, as applicable, to incorporate the “limitations, tasks and associated thresholds and intervals” specified in paragraph (6) of EASA AD 2020-0251 within 90 days after the effective date of this AD.
(6) For airplanes with an original airworthiness certificate or original export certificate of airworthiness issued on or before March 20, 2018, the initial compliance time for doing the tasks specified in paragraph (6) of EASA AD 2020-0251 is at the applicable “thresholds” as incorporated by the requirements of paragraph (6) of EASA AD 2020-0251, or within 90 days after the effective date of this AD, whichever occurs later.
(7) The provisions specified in paragraphs (7) and (8) of EASA AD 2020-0251 do not apply to this AD.
(8) The “Remarks” section of EASA AD 2020-0251 does not apply to this AD.
After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) and intervals are allowed unless they are approved as specified in the provisions of the “Ref. Publications” section of EASA AD 2020-0251.
Although the service information referenced in EASA AD 2020-0251 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 (l) 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.
