Emergency landing dynamic conditions.

CFR · 2024-01-01 · US · Title 14

(a) The seat and restraint system in the airplane must be designed as prescribed in this section to protect each occupant during an emergency landing condition when— (1) Proper use is made of seats, safety belts, and shoulder harnesses provided for in the design; and (2) The occupant is exposed to loads resulting from the conditions prescribed in this section. (b) Each seat type design approved for crew or passenger occupancy during takeoff and landing must successfully complete dynamic tests or be demonstrated by rational analysis based on dynamic tests of a similar type seat, in accordance with each of the following emergency landing conditions. The tests must be conducted with an occupant simulated by a 170-pound anthropomorphic test dummy, as defined by 49 CFR Part 572, Subpart B, or its equivalent, sitting in the normal upright position. (1) A change in downward vertical velocity (Δ v) of not less than 35 feet per second, with the airplane's longitudinal axis canted downward 30 degrees with respect to the horizontal plane and with the wings level. Peak floor deceleration must occur in not more than 0.08 seconds after impact and must reach a minimum of 14g. (2) A change in forward longitudinal velocity (Δ v) of not less than 44 feet per second, with the airplane's longitudinal axis horizontal and yawed 10 degrees either right or left, whichever (c) The following performance measures must not be exceeded during the dynamic tests conducted in accordance with paragraph (b) o

official document · source cfr-2024 · id 14:§ 25.562