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The motivation for this project was to design, and develop an aircraft seat to meet the proposed FAA 32g vertical/longitudinal dynamic test requirements specified in NPRM 93-71. A major goal of the design was to develop a production-quality seat in terms of weight, comfort, appearance, simplicity, and manufacturability. The relevant injury criteria was to obtain an occupant lumbar (spinal) load below 6670 N (1500 1bf). The design incorporated energy absorbing devices in the cushion and chair legs. The seat developed was based on the Beech King Air design and incorporated a modified seat frame, seat back, and reclining mechanism. The seat cushions were provided by Oregon Aero, while the seat pan and seat legs were designed and manufactured at WSU.

The Federal Aviation Administration (FAA)'s analysis of commuter aircraft accidents and ongoing research has indicated that the crashworthiness capabilities of smaller aircraft may be questionable. The small size of these aircraft results in a stiff structure and consequently higher impact loads experienced by the occupants. In 1993, the FAA issued a Notice of Proposed Rule Making (NPRM) 93-71 to increase the deceleration pulse amplitude of the sled tests under the Test-1 conditions (60-degree test) to 32G for the commuter type aircraft. To meet this condition, the seat design must exploit the energy absorption potential for its structural components. Energy absorbing components may include the seat legs, seat pan, and seat cushion. The intent is to design the seat so that it strikes well beyond the elastic limit to absorb the energy of the impact. To date, no seat has yet been able to pass the proposed criteria with an acceptable limit on the lumbar load (1500 pounds).