Patent ID: 8641154

Claim:
An electric brake system for an aircraft, the electric brake system comprising: a first landing gear comprising a first, fore wheel having a first, fore wheel-brake with a first, fore electric brake actuator, the first landing gear further comprising a second, aft wheel having a second, aft wheel-brake with a second, aft electric brake actuator; a parking brake lever; a throttle control; an instrument configured to sense the position of the throttle control and generate an engine run status control signal indicating an engine run status condition; a brake system control unit (BSCU) coupled to the parking brake lever, the throttle control and the instrument via a digital data communication bus, the BSCU comprising a processor configured to generate a first brake control signal in response to a first engine run status control signal and to generate a second brake control signal in response to a second engine run status control signal; a first electric brake actuator control (EBAC) coupled to and controlled by the BSCU via the digital data communication bus, and also coupled to both the first, fore electric brake actuator and the second, aft electric brake actuator, the first EBAC comprising a processor configured to generate a first brake actuator control signal in response to the first brake control signal received from the BSCU and to generate a second brake actuator control signal in response to the second brake control signal received from the BSCU, wherein the first, fore electric brake actuator and the second, aft electric brake actuator are configured to apply a first clamping force in response to the first brake actuator control signal received from the first EBAC and to apply a second clamping force in response to the second brake actuator control signal received from the first EBAC.