Aircraft wing and flight control surface

A swept aircraft wing comprising:

• a movable flight control surface which moves with respect to a hinge line, wherein the hinge line is non-perpendicular to a longitudinal axis of a fuselage attached to the swept aircraft wing;
• an actuator arm configured to actuate the moveable flight control surface, wherein the actuator arm comprises a longitudinal axis substantially parallel to the longitudinal axis of the fuselage attached to the swept aircraft wing, wherein the actuator arm extends at least partially from an outer surface of the aircraft wing, and
• a fairing arranged on the outer surface of the swept aircraft wing and at least partially covering the actuator arm,
• wherein the actuator arm is pivotally attached by a first pivotal connection to a main body portion of the aircraft wing, and the actuator arm is pivotally attached by a second pivotal connection to the movable flight control surface,
• wherein the first pivotal connection and/or the second pivotal connection is configured for rotary movement of the actuator arm in a first plane and in a second plane perpendicular to the first plane,
• wherein at least one of the first pivotal connection and the second pivotal connection is configured such that an axis of the actuator arm is moveable at least five degrees with respect to a line parallel to the longitudinal axis of the fuselage in both a first plane and a second plane perpendicular to the first plane, and
• wherein the actuator arm moves at least five degrees with respect to both the first plane and the second plane while actuating movement of the flight control surface.

An aircraft wing assembly comprising:

• a swept main aircraft wing;
• a flight control surface mounted to a leading or trailing edge of the swept main aircraft wing, and configured to move with respect to a swept hinge line of the swept main aircraft wing;
• an actuator configured to move the flight control surface with respect to the swept hinge line, wherein the actuator includes a longitudinal axis oblique to the swept hinge line and substantially parallel to a longitudinal axis of a fuselage of the aircraft attached to the aircraft wing assembly, and
• a fairing mounted to an outer aerodynamic surface of the swept main aircraft wing and at least partially covering the actuator,
• wherein the actuator is pivotally attached by a first pivotal connection to the swept main aircraft wing, and the actuator is pivotally attached by a second pivotal connection to the flight control surface;
• wherein the first pivotal connection and/or the second pivotal connection is configured for rotary movement of an actuator arm of the actuator in a first plane and in a second plane perpendicular to the first plane
• wherein at least one of the first pivotal connection and the second pivotal connection is configured such that an axis of the actuator arm is moveable at least five degrees with respect to the first plane and at least five degrees with respect to the second plane, and
• wherein the actuator arm moves at least five degrees with respect to both the first plane and the second plane while actuating movement of the flight control surface.