The vehicle specification for all modern fighter aircraft requires some level of flight control system redundancy. The MCAIR approach to meeting the F/A-18 flight control system actuator redundancy requirements is presented. The actuator configurations, servoloops, and redundancy management concepts are described. Early interface compatibility and redundancy management testing of breadboard hardware were used to identify potential problem areas before iron bird testing of flight worthy hardware. The development history and the flight test experience are discussed.