A flight control system for actuating a control surface of an aircraft, comprising: a plurality of actuators for redundantly actuating a control surface of the aircraft, actuator control electronics for receiving, calculating and forwarding control signals for the control surface which is to be actuated by the plurality of actuators, a plurality of remote electronic units for each controlling and monitoring a corresponding actuator, and a first data bus system for transferring data between the actuator control electronics and the plurality of remote electronic units, wherein the first data bus system comprises: a first data bus for transferring data between the actuator control electronics and a first one of the plurality of remote electronic units, a second data bus for transferring data between the actuator control electronics and a second one of the plurality of remote electronic units, wherein the first data bus and the second data bus are based on the same bus technology, characterised in that the first data bus system further has a backup data bus for transferring data between the actuator control electronics and the first remote electronic unit, wherein the backup data bus is different in its bus technology from the first data bus and the second data bus and is connected only to remote electronic units which are configured for controlling control surfaces which are necessary for safe flight operation, and wherein the flight control system is designed, in the event of a fault condition or a failure of the first data bus and of the second data bus, to use the backup data bus for transferring data between the actuator control electronics and the first remote electronic unit. a plurality of actuators for redundantly actuating a control surface of the aircraft, actuator control electronics for receiving, calculating and forwarding control signals for the control surface which is to be actuated by the plurality of actuators, a plurality of remote electronic units for each controlling and monitoring a corresponding actuator, and a first data bus system for transferring data between the actuator control electronics and the plurality of remote electronic units, wherein the first data bus system comprises: a first data bus for transferring data between the actuator control electronics and a first one of the plurality of remote electronic units, a second data bus for transferring data between the actuator control electronics and a second one of the plurality of remote electronic units, wherein the first data bus and the second data bus are based on the same bus technology, characterised in that the first data bus system further has a backup data bus for transferring data between the actuator control electronics and the first remote electronic unit, wherein the backup data bus is different in its bus technology from the first data bus and the second data bus and is connected only to remote electronic units which are configured for controlling control surfaces which are necessary for safe flight operation, and wherein the flight control system is designed, in the event of a fault condition or a failure of the first data bus and of the second data bus, to use the backup data bus for transferring data between the actuator control electronics and the first remote electronic unit. a first data bus for transferring data between the actuator control electronics and a first one of the plurality of remote electronic units, a second data bus for transferring data between the actuator control electronics and a second one of the plurality of remote electronic units, wherein the first data bus and the second data bus are based on the same bus technology, characterised in that the first data bus system further has a backup data bus for transferring data between the actuator control electronics and the first remote electronic unit, wherein the backup data bus is different in its bus technology from the first data bus and the second data bus and is connected only to remote electronic units which are configured for controlling control surfaces which are necessary for safe flight operation, and wherein the flight control system is designed, in the event of a fault condition or a failure of the first data bus and of the second data bus, to use the backup data bus for transferring data between the actuator control electronics and the first remote electronic unit.