Patent ID: 6129310
Filing Date: 2000-10-10
Classification: B64C

Abstract:
In combination in an aircraft nose landing gear:a nose wheel well web (135);an inboard nose wheel well fitting (130) and an outboard nose wheel well fitting (140) mounted on opposite sides of said nose wheel web (135);said inboard nose wheel well fitting (130) having an inboard cylindrical bore;said outboard nose wheel well fitting (140) having an outboard cylindrical bore;an inboard bushing (132) fitted into said inboard cylindrical bore;an outboard bushing (142) fitted into said outboard cylindrical bore;a trunnion pin (100);said nose wheel web (135) adapted to clear said trunnion pin (100);a shock strut assembly for receiving said trunnion pin (100); said trunnion pin (100) further passing through said inboard cylindrical bore and said outboard cylindrical bore; and,said shock strut assembly shorter than the space between the inboard surfaces of said inboard (130) and outboard (140) nose wheel well fittings .