Aircraft rudder lock structure

Claim 1

A RUDDER LOCK STRUCTURE FOR AIRCRAFT COMPRISING, IN COMBINATION, A PAIR OF ELONGATED LEG ELEMENTS, EACH OF SAID LEG ELEMENTS HAVING FLATTENED ENDS, ONE OF THE FLATTENED ENDS OF EACH LEG BEING CURVED AWAY FROM THE LEG AXIS, AN APERTURED FASTENING REGION AT EACH FLATTENED END OF THE LEG ELEMENTS, A PLURALITY OF SPRING CLAMP ELEMENTS, MEANS TO SECURE ONE OF SAID SPRING CLAMP ELEMENTS TO THE FASTENING REGION OF THE UNCURVED FLATTENED ENDS OF THE PAIR OF LEG ELEMENTS, THE SECUREMENT BEING ADAPTED TO HOLD THE LEG ELEMENTS IN V FORMATION WITH THE SPRING CLAMP ELEMENTS AT THE V APEX, THE SPRING CLAMP BEING ADAPTED TO BE CLAMPED TO THE TRAILING EDGE OF THE RUDDER ELEMENT OF AN AIRCRAFT IN A CLAMPING POSITION BETWEEN ITS BOTTOM AND TOP, MEANS FOR SECURING THE REMAINING CLAMP MEMBERS OF THE PLURALITY INDIVIDUALLY TO THE FLATTENED CURVED PORTION OF THE LEG ELEMENTS, THE LAST NAMED CLAMP MEMBERS BEING ADAPTED TO BE POSITIONED TO ENGAGE THE TRAILING EDGE OF THE ELEVATOR ELEMENTS OF THE AIRCRAFT AT POINTS THEREON SPACED LATERALLY FROM THE RUDDER WITH THE CURVED FLATTENED ENDS TURNED ANGULARLY RELATIVE TO THE CONNECTION OR THE STRAIGHT ENDS TO ACCOMMODATE THE ELEVATOR CONSTRUCTION OF THE AIRCRAFT SELECTED, AN ELONGATED EXPANSIBLE SPRING MEMBER, MEANS TO ATTACH ONE END OF SAID SPRING TO ONE OF THE LEG ELEMENTS, AND A FASTENING AT THE OPPOSITE END FOR SECUREMENT AT A POINT ON THE AIRCRAFT STRUCTURE TO TIGHTEN THE ASSEMBLY.