Abstract: A flight control system receiving input flight control signals from a flight control computer to manipulate a flight control surface. The dual actuator has an actuating rod connected to the flight control surface, and a pair of pistons are mounted on the actuating rod in respective first and second cylinders. The flow of hydraulic fluid into and out of the first and second cylinders is controlled by the first and second electrohydraulic servovalves, respectively. The electrohydraulic servovalves are, in turn, operated by respective signals applied to a pair of actuating coils. The system includes two controllers that receive the flight control signals and apply respective output signals to the four coils of the two electrohydraulic servovalves. In one embodiment, the controllers each have a primary channel and a secondary channel which are connected to respective actuating coils of the first electrohydraulic servovalve.