A wing flap system for an aircraft including a fly-by-wire flight control system and a power architecture having two independent hydraulic systems (342, 346) and two independent electrical systems (397, 399), 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; an actuator (302, 402, 502) to move the flap relative to the fixed trailing edge; a first hydraulic module (318, 424, 506) located at the actuator; and a second hydraulic module (334, 510) located remotely from the first hydraulic module, the second hydraulic module including a local power unit, the actuator being hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system (346, 518) of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module, the actuator also being hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module, wherein the local power unit is selectively connectable to an electrical system (397, 399, 520, 522) of the aircraft, and when it is connected to the electrical system the local power unit produces and/or supplies the second pressurized hydraulic fluid, 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, and wherein the second pressurized hydraulic fluid is to include a volume of hydraulic fluid contained within the compensator, wherein an electrical load control unit (396, 528), operatively positioned between the electric motor and the electrical system, selectively connects the electrical system to the electric motor, wherein the flap is a first flap of the aircraft, and wherein the electrical load control unit is controlled via a flight control electronics unit (390, 524) of the aircraft, the flight control electronics unit is configured to command the electrical load control unit to connect the electrical system to the electric motor in response to detecting an asymmetry between the first flap and a second flap of the aircraft that exceeds an asymmetry threshold. a flap movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft; an actuator (302, 402, 502) to move the flap relative to the fixed trailing edge; a first hydraulic module (318, 424, 506) located at the actuator; and a second hydraulic module (334, 510) located remotely from the first hydraulic module, the second hydraulic module including a local power unit, the actuator being hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system (346, 518) of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module, the actuator also being hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module, wherein the local power unit is selectively connectable to an electrical system (397, 399, 520, 522) of the aircraft, and when it is connected to the electrical system the local power unit produces and/or supplies the second pressurized hydraulic fluid, 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, and wherein the second pressurized hydraulic fluid is to include a volume of hydraulic fluid contained within the compensator, wherein an electrical load control unit (396, 528), operatively positioned between the electric motor and the electrical system, selectively connects the electrical system to the electric motor, wherein the flap is a first flap of the aircraft, and wherein the electrical load control unit is controlled via a flight control electronics unit (390, 524) of the aircraft, the flight control electronics unit is configured to command the electrical load control unit to connect the electrical system to the electric motor in response to detecting an asymmetry between the first flap and a second flap of the aircraft that exceeds an asymmetry threshold.