An electrically actuated braking system for an aircraft, including: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a first motor controller for generating a first drive signal for the EMAbrake, and a second motor controller for generating a second drive signal for the EMAbrake, wherein the first motor controller and the second motor controller are dissimilar so as to provide protection against common mode failure of the first and second motor controllers.