Patent ID: 8371523

Claim:
An aircraft rudder authority control system comprising a reversible mechanical system which includes: an actuator operatively connected to the rudder which causes the rudder to pivotally deflect in rightward and leftward directions in response to receiving a rudder command input; right and left stop parts operatively interacting with the rudder to define maximum rightward and leftward rudder deflections, respectively, wherein the right and left stop parts are independently moveable relative to one another between an open position which allows for a greater maximum rightward and leftward rudder deflection and a closed position which allows for a lesser maximum rightward and leftward rudder deflection, respectively; and a controller operatively connected to the right and left stop parts, the controller issuing a control signal to at least one of the right and left stop parts in response to receiving at least one input signal selected from an aircraft engine asymmetry signal indicative of asymmetrical engine traction, an aircraft airspeed signal, an aircraft altitude signal, an aircraft skidding angle signal or an aircraft weight on wheels signal indicative of the aircraft being on ground to thereby cause the at least one right and left stop parts to move between the closed and opened positions thereof which in turn permit greater and lesser maximum rightward and/or leftward rudder deflections, respectively.