AUTOMATED PROPELLER FEATHERING TEST

There is described herein systems and method for testing a propeller feathering function, including monitoring over time a torque applied to a rotor shaft assembly (24) operatively connected to a propeller (30) of an aircraft, commanding an angle change of propeller blades of the propeller (30) in response to receipt of a trigger signal generated upon initiation of a task or procedure performed within the aircraft, comparing, in response to the angle change being commanded, a post-angle change torque applied to the rotor shaft assembly (24) to an expected torque without the commanded angle change and obtaining a torque difference, and issuing a test passed signal when the torque difference exceeds a threshold and a test failed signal when the torque difference does not exceed the threshold.