Patent ID: 8636121

Claim:
A vibration filter mechanism for aircraft equipment, the mechanism comprising: a pair of filter members for connecting between a first structure connected to a fuselage of an aircraft and a second structure connected to the equipment, each of the pair of filter members including: a lever arm weighted at a free end and hinged at an opposite, anchor end to hinges respectively associated with each of the first and second structures, the lever arm cooperating with a deformable torsion shaft for opposing pivoting movements of the lever arm on the hinges, the lever arm arranged as a one-piece fork having a pair of branches interconnected by a crossbar and individually hinged to the hinges about spaced-apart parallel pivot axes, wherein the torsion shaft extends between the pair of branches at the free end, the torsion shaft defining ends and carrying a first weight placed in a middle zone between the ends of the torsion shaft to filter pitching vibration; wherein the pair of filter members are placed in a head-to-head orientation such that each of the crossbars are adjacent each other; the first weight of each torsion shaft being secured to each other by a junction member; wherein the pivoting movement of the lever arms are limited by the crossbars.