Abstract: An actuator assembly provides redundancy to maintain operation when a driver link is inoperable due to jamming or breakage of a prime mover, gear, link, or other drivetrain component. The actuator assembly includes a first motor and a second motor that each generate rotational forces. A first driver link is coupled to the first motor and to a first output link. Similarly, a second driver link is coupled to the second motor and to the second output link. The first output link and the second output link are also coupled to a connecting link. The connecting link exhibits a displacement force to control an angle of a control surface in an aircraft, or other vehicle, or equipment. A controller changes the control mode to enable a desired output state to be achieved in a normal operation or under a fault condition when one of the driver links is non-operational.