Patent ID: 7631840

Claim:
A pivoting panel for an aircraft, comprising: a first surface plate and a second surface plate; a front spar at a front edge of the panel and a rear spar at a rear edge of the panel; a frame structure arranged into a space defined by the surface plates and the spars; at least two hinges arranged on a front edge portion of the panel; and at least one actuator connection fitting to which an actuator is connectable for pivoting the panel in relation to the hinges, wherein the frame structure comprises at least one support piece made of a composite material; the support piece comprises at least an extension portion; the position of the extension portion is arranged to correspond to that of the actuator connection fitting; and the extension portion is provided with a first surface and a second surface, the first surface being attached to an inner surface of the first surface plate of the panel and the second surface of the extension portion being attached to an inner surface of the second surface plate, whereby during assembly the support piece is arranged as an integral part of the panel; and wherein the support piece further comprises a first branch and a second branch arranged inside the space defined by the surface plates and the spars, and at a distance from each other, the distance between outermost ends of the branches being greater than that between innermost ends of the first and second branches thereby forming a structure having an inverted V-shape.