An aircraft comprising: a wing comprising a fixed trailing edge and a wing flap system comprising: a flap configured to be moved between a deployed position and a retracted position relative to the fixed trailing edge of the wing of the aircraft; and an actuator (302, 402) configured to move the flap relative to the fixed trailing edge, the actuator being configured to be hydraulically driven via first pressurized hydraulic fluid to be supplied by a hydraulic system of the aircraft, the actuator also being configured to be hydraulically driven via second pressurized hydraulic fluid to be supplied by a local power unit, the local power unit being selectively connectable to an electrical system (386, 918) of the aircraft, the electrical system to power the local power unit to supply the second pressurized hydraulic fluid; and wherein: the local power unit includes a compensator, a hydraulic pump in fluid communication with the compensator, and an electrical motor operatively coupled to the hydraulic pump, the second pressurized hydraulic fluid to include a volume of hydraulic fluid contained within the compensator; the wing flap system further comprises a switch (384, 920) positioned between the electrical motor and the electrical system, the switch being configured to be actuated between an open position and a closed position, the electrical motor being connected to the electrical system when the switch is in the closed position; the switch is configured to be controlled via a flight control electronics unit of the aircraft; and the flap is a first flap, and wherein the flight control electronics unit (374, 924) is configured to actuate the switch (384, 920) from the open position to the closed position in response to detecting an asymmetry between the first flap and a second flap that exceeds an asymmetry threshold. a flap configured to be moved between a deployed position and a retracted position relative to the fixed trailing edge of the wing of the aircraft; and an actuator (302, 402) configured to move the flap relative to the fixed trailing edge, the actuator being configured to be hydraulically driven via first pressurized hydraulic fluid to be supplied by a hydraulic system of the aircraft, the actuator also being configured to be hydraulically driven via second pressurized hydraulic fluid to be supplied by a local power unit, the local power unit being selectively connectable to an electrical system (386, 918) of the aircraft, the electrical system to power the local power unit to supply the second pressurized hydraulic fluid; and wherein: the local power unit includes a compensator, a hydraulic pump in fluid communication with the compensator, and an electrical motor operatively coupled to the hydraulic pump, the second pressurized hydraulic fluid to include a volume of hydraulic fluid contained within the compensator; the wing flap system further comprises a switch (384, 920) positioned between the electrical motor and the electrical system, the switch being configured to be actuated between an open position and a closed position, the electrical motor being connected to the electrical system when the switch is in the closed position; the switch is configured to be controlled via a flight control electronics unit of the aircraft; and the flap is a first flap, and wherein the flight control electronics unit (374, 924) is configured to actuate the switch (384, 920) from the open position to the closed position in response to detecting an asymmetry between the first flap and a second flap that exceeds an asymmetry threshold.