An aircraft comprising a wing flap system for the aircraft, the wing flap system comprising: a flap movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft; and first (302, 402) and second (310, 404) actuators configured to move the flap relative to the fixed trailing edge, the first actuator being operatively coupled to the second actuator via a shaft (318, 406), the first actuator being actuatable via pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the first actuator via a hydraulic module (326, 408) operatively coupled to the first actuator, the first actuator configured to control movement of the second actuator via the shaft when the hydraulic system and the hydraulic module are functional, the second actuator being actuatable via an electric motor of the second actuator, the electric motor being selectively connectable to an electrical system of the aircraft, the electric motor being connected to the electrical system in response to detection of a failure of the hydraulic system or of the hydraulic module, the second actuator configured to control movement of the first actuator via the shaft when the electric motor is connected to the electrical system, wherein the shaft is a straight shaft or a flexible shaft, and wherein the shaft is configured to rotate in response to actuation of the first actuator via the pressurized hydraulic fluid, wherein the rotation of the shaft is configured to actuate the second actuator, wherein the second actuator can be actuated by either of two independent mechanisms, the second actuator being actuatable via the rotation of the shaft independently of being actuatable via the electric motor; and an electronic motor control unit (340, 412) including a switch, the switch being operatively positioned between the electric motor and the electrical system, the switch being actuatable between an open position and a closed position, the electric motor being connected to the electrical system when the switch is in the closed position, wherein the switch is configured to be actuated into the closed position in response to a command received by the electronic motor control unit from a flight control electronics unit of the aircraft. a flap movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft; and first (302, 402) and second (310, 404) actuators configured to move the flap relative to the fixed trailing edge, the first actuator being operatively coupled to the second actuator via a shaft (318, 406), the first actuator being actuatable via pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the first actuator via a hydraulic module (326, 408) operatively coupled to the first actuator, the first actuator configured to control movement of the second actuator via the shaft when the hydraulic system and the hydraulic module are functional, the second actuator being actuatable via an electric motor of the second actuator, the electric motor being selectively connectable to an electrical system of the aircraft, the electric motor being connected to the electrical system in response to detection of a failure of the hydraulic system or of the hydraulic module, the second actuator configured to control movement of the first actuator via the shaft when the electric motor is connected to the electrical system, wherein the shaft is a straight shaft or a flexible shaft, and wherein the shaft is configured to rotate in response to actuation of the first actuator via the pressurized hydraulic fluid, wherein the rotation of the shaft is configured to actuate the second actuator, wherein the second actuator can be actuated by either of two independent mechanisms, the second actuator being actuatable via the rotation of the shaft independently of being actuatable via the electric motor; and an electronic motor control unit (340, 412) including a switch, the switch being operatively positioned between the electric motor and the electrical system, the switch being actuatable between an open position and a closed position, the electric motor being connected to the electrical system when the switch is in the closed position, wherein the switch is configured to be actuated into the closed position in response to a command received by the electronic motor control unit from a flight control electronics unit of the aircraft.