Distributed trailing edge wing flap systems

A method for operating a wing flap system of an aircraft, the wing flap system including a flap movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft and further including first and second 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, the method comprising:

• commanding the first actuator to control movement of the flap relative to the fixed trailing edge, 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 operatively coupled to the first actuator, the hydraulic module being in fluid communication with the hydraulic system and the first actuator, the first actuator controlling movement of the second actuator via the shaft when the hydraulic system and the hydraulic module are functional;
• detecting a failure of the hydraulic system or of the hydraulic module;
• and
• commanding the second actuator to control movement of the flap relative to the fixed trailing edge, 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 the detecting the failure, the second actuator controlling movement of the first actuator via the shaft when the electric motor is connected to the electrical system.

A wing flap system for an 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 and second 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, the shaft having a first end mechanically coupled to the first actuator and a second end located opposite the first end and mechanically coupled to the second actuator, 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 operatively coupled to the first actuator, the hydraulic module being in fluid communication with the hydraulic system and 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.