An apparatus for varying a camber of an aircraft wing, comprising: an aircraft wing; a flexible trailing edge connected to an aft end of the wing, said flexible trailing edge comprising; a flexible upper surface, and; a rigid lower surface; at least one slider link having forward and aft ends, wherein the aft end of said slider link is secured to the flexible trailing edge rigid lower surface; a bell crank actuating mechanism arranged internally to the wing, forward of said trailing edge rigid lower surface; wherein said bell crank actuating mechanism is pivotably connected to the forward end of the slider link; and wherein when the bell crank mechanism is actuated, the slider link moves in a forward and aft direction causing the flexible upper surface to bend, selectively varying the wing camber; wherein said bell crank actuating mechanism comprises: an actuation bell crank; a connector bar; an extension bell crank; and a retraction bell crank; the extension bell crank, the retraction bell crank and the actuation bell crank being pivotally attached to the connector bar; and wherein said bell crank actuating mechanism is configured such that: the actuation bell crank is attached to the slider link for rotation by the connector bar; the connector bar is displaceable by the extension bell crank for aft motion of the slider link; and the connector bar is displaceable by the retraction bell crank for forward motion of the slider link. an aircraft wing; a flexible trailing edge connected to an aft end of the wing, said flexible trailing edge comprising; a flexible upper surface, and; a rigid lower surface; at least one slider link having forward and aft ends, wherein the aft end of said slider link is secured to the flexible trailing edge rigid lower surface; a bell crank actuating mechanism arranged internally to the wing, forward of said trailing edge rigid lower surface; wherein said bell crank actuating mechanism is pivotably connected to the forward end of the slider link; and wherein when the bell crank mechanism is actuated, the slider link moves in a forward and aft direction causing the flexible upper surface to bend, selectively varying the wing camber; wherein said bell crank actuating mechanism comprises: an actuation bell crank; a connector bar; an extension bell crank; and a retraction bell crank; an actuation bell crank; a connector bar; an extension bell crank; and a retraction bell crank; the extension bell crank, the retraction bell crank and the actuation bell crank being pivotally attached to the connector bar; and wherein said bell crank actuating mechanism is configured such that: the actuation bell crank is attached to the slider link for rotation by the connector bar; the connector bar is displaceable by the extension bell crank for aft motion of the slider link; and the connector bar is displaceable by the retraction bell crank for forward motion of the slider link. the actuation bell crank is attached to the slider link for rotation by the connector bar; the connector bar is displaceable by the extension bell crank for aft motion of the slider link; and the connector bar is displaceable by the retraction bell crank for forward motion of the slider link.