초록 ▼

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

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.

대표청구항 ▼

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

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; anda 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. 2. The apparatus of claim 1, wherein at least the portion of the first member is for coupling to the first arm of the aircraft clevis using an adhesive or a sealant. 3. The apparatus of claim 1, wherein at least the portion of the first member is for coupling to the first arm of the aircraft clevis using a fastener. 4. The apparatus of claim 1, wherein the first member and the second member each have at least a portion of a surface with an abrasion-resistant finish. 5. The apparatus of claim 1, wherein the first member and the second member are made of steel. 6. The apparatus of claim 1, wherein at least one of the first, second, third, or fourth prongs is shaped as a wave. 7. The apparatus of claim 6, wherein the wave comprises a portion that is straight. 8. An apparatus, comprising: a first member and a second member, 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 positioned between the first member and the second member, the first member and the second member being interconnected at a first end, the first member and the second member forming an opening at a second end opposite to the first end, the opening configured to receive a slider positioned along the longitudinal axis, the longitudinal axis extending generally between the first end and the second end;a first upper 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;a second upper prong protruding from a second edge at a top portion of the second member towards the longitudinal axis, the second edge substantially parallel to the longitudinal axis;a first lower prong protruding from a third edge at a bottom portion of the first member towards the longitudinal axis, the third edge substantially parallel to the longitudinal axis; anda second lower 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;wherein: at least a portion of the first member is for coupling to a first side of an aircraft clevis and at least a portion of the second member is for coupling to a second side of the aircraft clevis; at least a portion of each of the upper and lower prongs are for contacting the slider; and the apparatus is operable to prevent the slider from contacting the aircraft clevis. 9. The apparatus of claim 8, wherein at least the portion of the first member is for coupling to the first side of the clevis using an adhesive or a sealant. 10. The apparatus of claim 8, wherein at least the portion of the first member is for coupling to the first side of the clevis using a fastener. 11. The apparatus of claim 8, wherein the first member and the second member are made of steel. 12. The apparatus of claim 8, wherein the first member and the second member each have at least a portion of a surface with an abrasion-resistant finish. 13. The apparatus of claim 8, wherein at least one of the prongs is shaped as a wave. 14. The apparatus of claim 13, wherein the wave comprises a portion that is straight. 15. A system, comprising: an aircraft clevis comprising two opposite sides and a longitudinal axis located between the two opposite sides, the longitudinal axis being parallel to the two opposite sides;a slider positioned between the two sides of the aircraft clevis and along the longitudinal axis; anda clip comprising the apparatus according to claim 1 or claim 8, the clip configured to prevent the slider from rotating about the longitudinal axis by having at least one of the first and second members of the clip coupled to one of the two opposite sides of the aircraft clevis and at least one prong of the clip in contact with the slider. 16. The system of claim 15, wherein the clip is coupled to one of the two opposite sides of the aircraft clevis using an adhesive or a sealant. 17. The system of claim 15, wherein the clip is coupled to one of the two opposite sides of the aircraft clevis using a fastener. 18. The system of claim 15, wherein the clip has a first surface with an abrasion-resistant finish. 19. The system of claim 15, wherein the clip is made of steel. 20. The system of claim 15, wherein the aircraft clevis is located in an airplane.