An aircraft actuator hydraulic apparatus that is arranged to supply pressure oil to a hydraulically operated actuator for driving a control surface of an aircraft, the apparatus comprising: a casing; a hydraulic pump suitable for being installed inside a wing at which the control surface of the aircraft is provided; an electric motor suitable for being installed inside the wing and that is arranged to drive the hydraulic pump; a driver for controlling the operational status of the electric motor suitable for being installed inside the wing and that is arranged to drive the electric motor; and a cooling device suitable for being installed inside at least one of the wing and a body of the aircraft and that is arranged to simultaneously cool the hydraulic pump, the electric motor, and the driver; wherein the electric motor is installed in the interior of the casing; characterised in that: the hydraulic pump is a backup hydraulic pump that can supply pressure oil to the actuator when a loss or degradation occurs in a function of an aircraft central hydraulic power source (105, 106) that supplies pressure oil to the actuator; the cooling device is a fan that is arranged to rotate together with a rotating shaft of the electric motor; the fan is installed in the interior of the casing; the backup pump is fixed to the casing in a state in which it projects from the casing; the fan is installed so as to be coupled to the rotating shaft of the electric motor on the side opposite to the backup hydraulic pump side; the fan is configured to take in air from openings at an end of the casing in a portion that the fan faces and to generate cooling air flowing through the interior of the casing towards the backup hydraulic pump; and the electric motor, the backup hydraulic pump, and the driver are installed on a downstream side of the cooling air generated by the fan. a casing; a hydraulic pump suitable for being installed inside a wing at which the control surface of the aircraft is provided; an electric motor suitable for being installed inside the wing and that is arranged to drive the hydraulic pump; a driver for controlling the operational status of the electric motor suitable for being installed inside the wing and that is arranged to drive the electric motor; and a cooling device suitable for being installed inside at least one of the wing and a body of the aircraft and that is arranged to simultaneously cool the hydraulic pump, the electric motor, and the driver; the hydraulic pump is a backup hydraulic pump that can supply pressure oil to the actuator when a loss or degradation occurs in a function of an aircraft central hydraulic power source (105, 106) that supplies pressure oil to the actuator; the cooling device is a fan that is arranged to rotate together with a rotating shaft of the electric motor; the fan is installed in the interior of the casing; the backup pump is fixed to the casing in a state in which it projects from the casing; the fan is installed so as to be coupled to the rotating shaft of the electric motor on the side opposite to the backup hydraulic pump side; the fan is configured to take in air from openings at an end of the casing in a portion that the fan faces and to generate cooling air flowing through the interior of the casing towards the backup hydraulic pump; and the electric motor, the backup hydraulic pump, and the driver are installed on a downstream side of the cooling air generated by the fan.