An aircraft wing configured to be fixed to and extend from an aircraft fuselage, the wing having a leading edge and a trailing edge; an aerodynamic control device attached to the trailing edge, an actuator (200, 202) in communication with the control device, and an aircraft input controller in communication with the actuator (200, 202), wherein movement of the control device is subject to the actuator (200, 202) via the input controller; a bell crank mechanism coupled to the control device, and configured to link movement of a hinge panel directly to movement of the control device; a moveable aerodynamic cove lip door proximal to the aerodynamic control device, the cove lip door separately attached to the trailing edge; and wherein the actuator (200, 202) also controls movement of the cove lip door as an indirect function of movement of the control device, and wherein the aircraft wing further comprises an actuator pivot link having first and second ends, the actuator (200, 202) being coupled to the actuator pivot link at the first end, and the actuator pivot link pivotally connected to, but translationally fixed to, the trailing edge at the second end, and wherein the bell crank mechanism includes a center link also pivotally connected to, but translationally fixed to, the trailing edge, wherein the aircraft wing further comprises a cove lip door drive arm, a cove lip door drive link fixed to the drive arm, and a cove lip door hinge connected to the cove lip door, the cove lip door drive arm being secured to the actuator pivot link at a position intermediately of the first and second ends thereof, wherein the cove door drive link also has first and second ends, the first end thereof being rotatably secured to the cove lip door drive arm, and the second end rotatably secured to the cove lip door hinge, and wherein movement of the actuator (200, 202) moves the actuator pivot link, causing pivotal movement of the cove lip door relative to the trailing edge, wherein the actuator pivot link and the drive arm both rotate relative to the trailing edge about the second end of the actuator pivot link. an aerodynamic control device attached to the trailing edge, an actuator (200, 202) in communication with the control device, and an aircraft input controller in communication with the actuator (200, 202), wherein movement of the control device is subject to the actuator (200, 202) via the input controller; a bell crank mechanism coupled to the control device, and configured to link movement of a hinge panel directly to movement of the control device; a moveable aerodynamic cove lip door proximal to the aerodynamic control device, the cove lip door separately attached to the trailing edge; and wherein the actuator (200, 202) also controls movement of the cove lip door as an indirect function of movement of the control device, and wherein the aircraft wing further comprises an actuator pivot link having first and second ends, the actuator (200, 202) being coupled to the actuator pivot link at the first end, and the actuator pivot link pivotally connected to, but translationally fixed to, the trailing edge at the second end, and wherein the bell crank mechanism includes a center link also pivotally connected to, but translationally fixed to, the trailing edge, wherein the aircraft wing further comprises a cove lip door drive arm, a cove lip door drive link fixed to the drive arm, and a cove lip door hinge connected to the cove lip door, the cove lip door drive arm being secured to the actuator pivot link at a position intermediately of the first and second ends thereof, wherein the cove door drive link also has first and second ends, the first end thereof being rotatably secured to the cove lip door drive arm, and the second end rotatably secured to the cove lip door hinge, and wherein movement of the actuator (200, 202) moves the actuator pivot link, causing pivotal movement of the cove lip door relative to the trailing edge, wherein the actuator pivot link and the drive arm both rotate relative to the trailing edge about the second end of the actuator pivot link.