Seatback breakover device
AssigneeWeber Aircraft, Inc.
InventorsVahe Bilezikjian, Steve R. Bell
Life of this patent
Estimating the term…
Abstract
A seatback fitting assembly is provided with means to allow the complete forward rotation of the seatback, while remaining anchored to the seat structure, upon an excessive dynamic load or force impact on the seatback. This is accomplished by the use of a structural "breakover" device operating within the fitting assembly, which restrains the seatback within a limited, "forward tilt" range of motion under normal conditions, but allows complete forward rotation once load forces above an allowable level act on the seatback to cause a restraining pin to shear. A friction brake or clutch arrangement is provided to inhibit tilting of the seatback at all times but does not prevent the complete forward rotation of the seatback.
Claims1
An assembly mechanism for anchoring seatbacks to seat structures comprising:
- a circular collar integral with the seatback and inserted through a hole at one end of an arm member, the other end of said arm member being fixed to the seat structure, such that the collar may rotate within the hole and the seatback rotate about the arm member;
- a shear pin mounted on said arm member which abuts a structural element integral with the seatback and restrains further rotation when the seatback has been rotated to a limited forward tilt position relative to the seat structure, wherein
- the shear pin will fail in shear allowing full forward rotation of the seatback once a force of a predetermined magnitude is exerted on the seatback;
- and further comprising
- a cotter-pin retaining the shear pin in place, wherein the cotter-pin may be manually removed for allowing the shear pin to be manually removed.
Dependencies are inferred from the claim text.