System for actuating a control surface of an aircraft

A system for actuating a control surface of an aircraft, comprising:

• a hydraulic actuator comprising a cylindrical cavity containing a piston that is configured to slide within the cylindrical cavity and a rod, the piston separating the cylindrical cavity into a first actuating chamber and a second actuating chamber, the rod being configured to transmit a movement of the piston to a control surface,
• a first servo valve configured to be commanded by a command system, the first servo valve comprising a sheath including a first slider that is configured to slide within a cavity of the sheath in accordance with command signals from the command system, the cavity of the sheath comprising a first command chamber and a second command chamber, respectively on either side of the first slider,
• wherein the first actuating chamber is fluidically connected to the first command chamber, and the second actuating chamber is fluidically connected to the second command chamber, and
• further comprising a second servo valve comprising a second slider that is configured to be controlled by the command system, the second servo valve corresponding to a distributor that includes at least five orifices:
• a first orifice fluidically connected to the first command chamber,
• a second orifice fluidically connected to the second command chamber,
• a third orifice corresponding to a low-pressure outlet orifice,
• a fourth orifice fluidically connected to the first actuating chamber,
• a fifth orifice fluidically connected to the second actuating chamber.