With the advent of modern power electronics and the advancement of aircraft system technologies—along with the need for reduced operating costs and emissions—the new concept of More Electric Aircraft (MEA) has gained traction in the aerospace industry. This paradigm aims to replace all non-propulsive systems onboard the aircraft with electrically powered alternatives. In this context, both primary and secondary flight control systems must meet the demanding performance and reliability standards traditionally achieved by high-power hydraulic actuators, adopting instead a new approach based on Electromechanical Actuators (EMAs). The work presented in this thesis aims to implement design modifications on an experimental EMA test bench, enabling it to accurately reproduce various operating conditions typical of these servomechanisms.