Electromechanical actuator for controlling the movement of a moving outer part of an aircraft, and aircraft including one such electromechanical actuator

An electromechanical actuator includes an actuator that is translatable along an axis relative to a case and that is made up of a deployed part and a non-deployed part, which are following one another along the axis and which are respectively deployed and not deployed outside the case. The axial span of the deployed part varies proportionally opposite that of the non-deployed part as a function of the translated position of the actuator. The actuator also includes an electric motor for translating the actuator, which is supported by the case and is connected to the non-deployed part of the actuator by a transmission. The case defines an inner volume inside which the non-deployed part of the actuator, the motor and the transmission are arranged. The inner volume is, during operation of the actuator, pressurized while being filled with a gaseous medium.