![]() ![]() The 1964 model 210D introduced a 285 hp (213 kW) engine and two small child seats, set into the cavity that contained the mainwheels aft of the passengers. To compensate for the reduced aileron span, the aileron profile was changed and its chord enlarged. FAA certification regulations state that a single-engined aircraft must have a flaps-down, power-off stall speed no greater than 70 miles per hour (110 km/h). The wing planform remained the same constant 64-inch (160 cm) chord from centerline to 100 inches (250 cm) out, then straight taper to 44-inch (110 cm) chord at 208 inches (530 cm) from centerline, but the semi-Fowler flaps (slotted, rear-moving) were extended outboard, from wing station 100 to Wing station 122, which allowed a lower landing speed. In 1961, the fuselage and wing were completely redesigned: The fuselage was made wider and deeper, and a third side window was added. It was essentially a Cessna 182B to which was added a retractable landing gear, swept tail, and a new wing. The early Cessna 210 (210 and 210A) had four seats with a Continental IO-470 engine of 260 hp (190 kW). ![]() A 1967 Cessna 210G modified with a leading edge cuff and flaperons for improved low speed performance characteristics ![]()
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