Patent ID: 6371681
Filing Date: 2002-04-16
Classification: B64C,F16C,Y10T

Abstract:
An improved aircraft comprising:an airframe; a rotating control system carried by the airframe, the rotating control system comprising: a member having at least one clevis defined by a pair of clevis arms disposed in a clevis plane, the at least one clevis having an axis of symmetry disposed in the clevis plane midway between the pair of clevis arms; a shaft member pivotally coupled between the pair of clevis arms, the shaft member having a shaft axis, the shaft axis disposed axially along the shaft member; and an anti-rotation member for limiting a rotation of the shaft member about the shaft axis, the anti-rotation member having at least one restraining member that protrudes toward the shaft member for limiting the axial rotation of the shaft member; wherein the anti-rotation member is a multi-piece clip comprising: a first portion having a center channel, a side member, and a restraining member, the side member having a planar portion and a corner portion, the corner portion being integrated with the center channel and the planar portion, the side member having an inner surface, the restraining member protruding inwardly from the inner surface of the side member; and a second portion identical to the first portion.