A method for controlling performance of an aircraft, the method comprising: obtaining, from an electronic control system of the aircraft, an aircraft performance requirement for the aircraft; obtaining, from one or more sensors of the aircraft, a set of aircraft flight data; obtaining main actuator performance data from a main actuator and alternate actuator performance data from an alternate actuator, the main actuator connected to and controlling a main control surface (11,12,13,14,15) of the aircraft and the alternate actuator connected to and controlling an alternate control surface (11, 12, 13, 14, 15) of the aircraft; obtaining, from the electronic control system, a main control law for controlling the main actuator, an alternate control law for controlling the alternate actuator, and a blended control law for controlling the main actuator and the alternate actuator together; implementing the main control law if, based on the main actuator performance data and the set of aircraft flight data, the main control surface can independently be used to meet the performance requirement; implementing the blended control law, based on the set of aircraft flight data and the alternate actuator performance data, if the main control surface cannot independently be used to meet the performance requirement and if the alternate control surface can be used in conjunction with the main control surface; implementing the alternate control law if the main control surface cannot independently be used to meet the performance requirement, if the alternate control surface cannot be used in conjunction with the main control surface, and if the alternate control surface can be independently used to meet the aircraft performance requirement; characterised by automatically implementing the blended control law, before implementing the main control law, if the alternate control law is controlling the alternate control surface and the main control surface can be independently used to meet the aircraft performance requirement. obtaining, from an electronic control system of the aircraft, an aircraft performance requirement for the aircraft; obtaining, from one or more sensors of the aircraft, a set of aircraft flight data; obtaining main actuator performance data from a main actuator and alternate actuator performance data from an alternate actuator, the main actuator connected to and controlling a main control surface (11,12,13,14,15) of the aircraft and the alternate actuator connected to and controlling an alternate control surface (11, 12, 13, 14, 15) of the aircraft; obtaining, from the electronic control system, a main control law for controlling the main actuator, an alternate control law for controlling the alternate actuator, and a blended control law for controlling the main actuator and the alternate actuator together; implementing the main control law if, based on the main actuator performance data and the set of aircraft flight data, the main control surface can independently be used to meet the performance requirement; implementing the blended control law, based on the set of aircraft flight data and the alternate actuator performance data, if the main control surface cannot independently be used to meet the performance requirement and if the alternate control surface can be used in conjunction with the main control surface; implementing the alternate control law if the main control surface cannot independently be used to meet the performance requirement, if the alternate control surface cannot be used in conjunction with the main control surface, and if the alternate control surface can be independently used to meet the aircraft performance requirement; characterised by automatically implementing the blended control law, before implementing the main control law, if the alternate control law is controlling the alternate control surface and the main control surface can be independently used to meet the aircraft performance requirement.