DISTRIBUTED TRAILING EDGE WING FLAP SYSTEMS

Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap (112, Fig.3) and first and second actuators (402, 404). The flap (112, Fig.3) is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The first and second actuators (402, 404) are configured to move the flap relative to the fixed trailing edge. The first actuator (402) is operatively coupled to the second actuator (404) via a shaft (406). The first actuator is 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 first actuator is configured to control movement of the second actuator via the shaft (406) when the hydraulic system and the hydraulic module are functional. The second actuator (404) is actuatable via an electric motor (418) of the second actuator. The electric motor is selectively connectable to an electrical system of the aircraft. The electric motor (418) is connected to the electrical system in response to detection of a failure of the hydraulic system or of the hydraulic module. The second actuator is configured to control movement of the first actuator via the shaft when the electric motor is connected to the electrical system.