Airworthiness Directive · Amendment 39-23473 · Aileron control system
Costruzioni Aeronautiche Tecnam S.P.A. Airplanes
This AD applies to Costruzioni Aeronautiche Tecnam S.P.A. (Tecnam) Model P2006T airplanes, certificated in any category, serial numbers (S/N) 001 through 434 and S/N 442.
The FAA is adopting a new airworthiness directive (AD) for certain Costruzioni Aeronautiche Tecnam S.p.A. (Tecnam) Model P2006T airplanes. This AD was prompted by a report of partial detachment of the left aileron due to a missing hinge pin. This AD requires a one- time detailed visual inspection of the affected aileron hinges for damage (cracks, warping of the hinges or hinge pin, scratched paint, missing or broken torque stripe, etc.) and cotter pins for improper installation and, depending on the findings, applicable corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Within 25 flight hours or 30 days, whichever occurs first after the effective date of this AD, perform a one-time detailed visual inspection of the inboard and outboard aileron hinges of the left and right ailerons for damage (cracks, warping of the hinges or hinge pin, scratched paint, missing or broken torque stripe, etc.), and inspect the cotter pins installed at both ends of each hinge pin for improper installation and evidence of looseness, in accordance with steps N 4 and 5 of the Accomplishment Instructions in Tecnam Service Bulletin No. SB 995-CS-Ed. 1 Rev. 2, dated September 18, 2026 (Tecnam SB 995-CS-Ed. 1 Rev. 2).
(2) If, during the inspection required by paragraph (g)(1) of this AD, no discrepancy affecting a cotter pin or crack or damage of an aileron hinge is found, no further action is required by this AD.
(3) If, during the inspection required by paragraph (g)(1) of this AD, any discrepancy affecting a cotter pin is found, before further flight, replace and secure the cotter pin, in accordance with step N 6 of the Accomplishment Instructions in Tecnam SB 995-CS-Ed. 1 Rev. 2.
(4) If, during the inspection required by paragraph (g)(1) of this AD, any crack or damage is found on an aileron hinge, before further flight, contact the Manager, International Validation Branch, FAA; or European Union Aviation Safety Agency (EASA); or Tecnam's EASA Design Organization Approval (DOA) for approved corrective instructions. If approved by the DOA, the approval must include the DOA-authorized signature. Accomplish the approved corrective instructions accordingly.
Although Tecnam SB 995-CS-Ed. 1 Rev. 2 specifies to submit information to the manufacturer, this AD does not require that action.
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.
