Airworthiness Directive · Amendment 39-19804 · Aileron control system
Textron Aviation Inc. (Type Certificate Previously Held by Beechcraft Corporation) Airplanes
This AD applies to the following Textron Aviation Inc. (Type Certificate previously held by Beechcraft Corporation) airplanes, certificated in any category:
(1) Models E33, E33A, E33C, F33, G33, 35-C33, 35-C33A, S35, V35, V35A, and 36, all serial numbers (S/Ns);
(2) Model F33A, S/Ns CE-290 through CE-680;
(3) Model F33C, S/Ns CJ-26 through CJ-128;
(4) Model V35B, S/Ns D-9069 through D-9961; and
(5) Model A36, S/Ns E-185 through E-925.
The FAA is superseding Airworthiness Directive (AD) 2019-21-08 for Textron Aviation Inc. (Textron) Models E33, E33A, E33C, F33, G33, 35-C33, 35-C33A, K35, M35, N35, P35, S35, V35, V35A, 36, and certain Models F33A, F33C, V35B, and A36 airplanes. AD 2019-21-08 required inspecting the right aileron flight control cable end fittings (terminal attachment fittings) and replacing any damaged cable assembly. This AD retains all of the actions of AD 2019-21-08 but removes Models K35, M35, N35, and P35 from the applicability. This AD was prompted by a comment the FAA received that AD 2019-21-08 should not apply to Models K35, M35, N35, and P35 airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
Within 30 days after November 22, 2019 (the effective date retained from AD 2019-21-08) inspect the forward and aft right aileron flight control cable end fittings that thread into the turnbuckle. To gain access to the end fittings, you must remove the front seats and floorboards and, if installed, the rear seats and under-seat closeout. The end fittings are located underneath the heating duct, just forward of the aft carry through spar.
Note to paragraph (g) of this AD: Adjusting the turnbuckle relative to the end fittings will affect cable tension.
(1) Remove any safety wire from the end fittings and turnbuckle, if installed. Remove any sleeving and tape on the shank of the cable end fittings without gouging or scratching the fitting surface.
(2) Using a 10X magnification, a mirror, and a light source, inspect all exposed surfaces of both control cable end fittings for cracks, pitting, and corrosion.
Before further flight after the inspection required by paragraph (g) of this AD, do one of the following actions, as applicable:
(1) If there are no cracks, no pitting, and no corrosion, check cable tension and make any necessary adjustments, and replace safety wire; or
(2) If there is a crack or any pitting or corrosion, replace any damaged cable assembly.
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.
