Patent ID: 8038093

Claim:
A control mechanism for a control surface ( 3 ) for an aerodynamic lifting surface ( 2 ) of aircraft, characterized in that said mechanism comprises a main closing rib ( 9 ) located at one end of the control surface ( 3 ) having joined thereto a main torsion bar ( 8 ) located at the edge of said control surface and defining an axis about which said control surface is configured to rotate such that it may move from an orientation coplanar with said aerodynamic lifting surface to one that is not coplanar with said aerodynamic lifting surface main torsion bar ( 8 ) being joined at its other end to a lever system ( 14 ) on which at least one actuator ( 15 ) acts, whereby rotation of the mentioned control surface ( 3 ) during the flight of the aircraft may be effected, wherein said control mechanism further comprises a secondary torsion bar ( 11 ), which secondary torsion bar is concentric with the main torsion bar ( 8 ), is located inside the main torsion bar ( 8 ) and is connected with the lever system ( 14 ) and with a secondary closing rib ( 28 ) of the control surface ( 3 ).