Airworthiness Directive · Amendment 39-22648 · Rudder tab control system
Pilatus Aircraft Ltd. Airplanes
Superseded. A later AD replaced this one: AD 2025-10-10. Comply with the one in force.
This AD applies to Pilatus Aircraft Ltd. Model PC-24 Airplanes, as identified in European Union Aviation Safety Agency (EASA) Emergency AD 2023-0219-E, dated December 19, 2023 (EASA Emergency AD 2023-0219-E), certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a determination that the titanium threaded bolts at the forward end of the short rudder trim tab actuating rods could be subject to unexpectedly high oscillating loads due to aerodynamic forces acting on the rudder trim tab. This AD requires periodic replacement of affected titanium threaded bolts, a one-time inspection of the rudder mass balance arm and other elements of the rudder trim tab installation for correct attachment, damage (gouges), cracks, deformation, surface finish, and corrosion on any surrounding parts and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) emergency 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 Emergency AD 2023-0219-E.
(1) Where EASA Emergency AD 2023-0219-E refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA Emergency AD 2023-0219-E requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where paragraph (4) of EASA Emergency AD 2023-0190-E specifies to “contact Pilatus to obtain approved instructions, and within the compliance time(s) specified therein, accomplish those instructions accordingly;” for this AD, replace that text with “accomplish corrective action in accordance with a method approved by the Manager, International Validation Branch, FAA; or EASA; or Pilatus EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.”
(4) Where the service information referenced in EASA Emergency AD 2023-0190-E specifies to “Return bellcrank bolts with damage to Pilatus Aircraft Ltd.” and “Return the two threaded bolts (3) (that you removed) to Pilatus Aircraft Ltd.”, this AD does not require those actions.
(5) Where the service information referenced in EASA Emergency AD 2023-0190-E specifies “Discard the two lock washers (2)”, for this AD, replace that text with “Remove the two lock washers (2) from service.”
(6) This AD does not adopt the Remarks paragraph of EASA Emergency AD 2023-0190-E.
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.
Aircraft
