Abstract: An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.

Abstract: Disclosed herein are novel methods of determining and/or adjusting warning thresholds for an aircraft safety system. One exemplary method of adjusting warning thresholds for an aircraft safety system includes determining an acceptable vertical speed range for an aircraft during takeoff or landing and measuring the aircraft's indicated airspeed and true airspeed. The method further includes determining the relationship between the indicated airspeed and the true airspeed, and using such relationship to adjust the acceptable vertical speed range.

Abstract: An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.