In the last fifteen years, the aerospace industry has been implementing the concept of More Electric Aircraft (MEA). To follow this path hydraulic actuators are replaced by Electromechanical Actuators (EMAs), so as to reduce the complexity and weights associated with the hydraulic system. Electromechanical linear and rotary actuators have an increased probability of failure with respect to hydraulic actuators, due to possible jamming of mechanical parts and possible failure of electronic parts. The increased risk of failure is not acceptable to the safety in critical systems, so redundancy becomes necessary to avoid catastrophic consequences for aircrafts/rotorcrafts and payload. The current stabilization system in helicopters is redundant by placing two identical linear actuators in series, allowing for only partial redundancy after some first failures, leading to halving the actuator stroke and functionality.