Apparatus and system for preventing wear to a component

摘要

In an embodiment, a system may include an aircraft clevis comprising two opposite sides and a longitudinal axis located between the two opposite sides. The longitudinal axis may be parallel to the two opposite sides. The system may include a slider positioned within the aircraft clevis and along the longitudinal axis. The system may include a clip configured to prevent the slider from rotating about the longitudinal axis by having at least a first portion of the clip coupled to one of the two opposite sides of the aircraft clevis and at least a second portion of the clip in contact with the slider.

主权项

1. An apparatus, comprising:
a first member and a second member for positioning the apparatus between a first arm and a second arm of an aircraft clevis, the first member and the second member each positioned on opposite sides of a longitudinal axis, the longitudinal axis being parallel to at least a portion of the first member and the second member and being substantially midway between the first member and the second member, the first member and the second member forming an opening at a first end, the opening configured to receive a slider positioned along the longitudinal axis; a u-shaped member coupling the first member and the second member at second end that is opposite to the first end, the longitudinal axis extending generally between the first and second end; a first prong protruding from a first edge at a top portion of the first member towards the longitudinal axis, the first edge substantially parallel to the longitudinal axis, at least a portion of the first prong for contacting the slider; a second prong protruding from a second edge at a bottom portion of the first member towards the longitudinal axis, the second edge substantially parallel to the longitudinal axis, at least a portion of the second prong for contacting the slider; a first aperture configured to receive a bolt, the first aperture positioned proximate to the first end of the first member; a third prong protruding from a third edge at a top portion of the second member towards the longitudinal axis, the third edge substantially parallel to the longitudinal axis, at least a portion of the third prong for contacting the slider; a fourth prong protruding from a fourth edge at a bottom portion of the second member towards the longitudinal axis, the fourth edge substantially parallel to the longitudinal axis, at least a portion of the fourth prong for contacting the slider; and a second aperture configured to receive the bolt, the second aperture positioned proximate to the first end of the second member; wherein:
at least a portion of the first member is for coupling to the first arm of the aircraft clevis andthe apparatus is operable to prevent the slider from contacting the aircraft clevis.