Airworthiness Directive · Amendment 39-22609 · Flight controls
Deutsche Aircraft GmbH (Type Certificate Previously Held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Airplanes
This AD applies to all Deutsche Aircraft GmbH (Type Certificate previously held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and 328-300 airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH Model 328-100 and 328-300 airplanes. This AD was prompted by a manufacturer's design review, which identified a potential risk of the rudder control rod buckling during operation with one engine inoperative during take-off and landing phases. This AD requires visually inspecting the rudder control rod, performing a one- time functional check of the rudder control rod, performing corrective actions if necessary, and reporting the inspection results, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. 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 2023-0065, dated March 20, 2023 (EASA AD 2023-0065).
(1) Where EASA AD 2023-0065 refers to its effective date, this AD requires using the effective date of this AD.
(2) Replace the entire text of paragraph (2) of EASA AD 2023-0065 with the following text, “If, during the functional check or GVI as required by paragraph (1) of this AD, as applicable, the length of the rudder control rod exceeds the maximum allowable length specified in the ASB, the rudder control rod is bent, both rudder control rod ends are not symmetrically adjusted, or both inspection holes are not fully covered with the threads of the rod end, repair before further flight using a method approved by the Manager, International Validation Branch, FAA; or EASA; or Deutsche Aircraft GmbH's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.”
(3) This AD does not adopt the “Remarks” section of EASA AD 2023-0065.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, 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 International Validation Branch, send it to the attention of the person identified in paragraph (j) 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, International Validation Branch, FAA; or EASA; or Deutsche Aircraft GmbH's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
For more information about this AD, contact Todd Thompson, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-231-3228; email todd.thompson@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.
