Cessna 210 - Design and Development

Design and Development

The early Cessna 210 (210 and 210A) had 4 seats with a Continental IO-470 engine of 260 hp (190 kW). It was essentially a Cessna 182B to which was added a retractable landing gear, swept tail, and a new wing. In 1961 the fuselage and wing were completely redesigned - the fuselage was made wider and deeper, and a third side window was added. The wing planform remained the same (constant 64" chord from centerline to 100 inches (2,500 mm) out, then straight taper to 44" chord at 208 inches 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 (FAA certification regulations state that a single-engine aircraft must have a flaps-down, power-off stall speed no greater than 70 miles/hour). To compensate for the reduced aileron span, the aileron profile was changed and its chord enlarged. The 1964 model 210D introduced a 285 hp (213 kW) engine and 2 small child seats, set into the cavity which contained the mainwheels aft of the passengers.

In 1967 the model 210G introduced a cantilever wing replacing the strut-braced wing. Its planform changed to a constant taper from root chord to tip chord. In 1970 the 210K became the first full 6-seat model. This was achieved by replacing the flat leaf-springs used for the retractable main landing gear struts (undercarriage) with tapered tubular steel struts of greater length. This allowed the tires to be nested farther to the rear of the fuselage, making room for the full size rear seats. In 1979 the 210N model eliminated the folding doors which previously covered the two retracted main wheels. The tubular spring struts retract into shallow channels along the bottom of the fuselage and the wheels fit snugly in closed depressions on the underside of the fuselage. Some models featured de-icing boots as an option.

The aircraft was offered in a normally aspirated version, designated the model 210, as well as the turbocharged T210 and the pressurized P210 versions. The Centurion II was an option introduced in 1970 with improved avionics, and was available in both noramlly aspirated and turbocharged versions (Turbo Centurion II)

On 21 May 2012 the airworthiness authority responsible for the design, the US Federal Aviation Administration, issued an emergency Airworthiness Directive requiring 3,665 of the cantilever wing Cessna 210s to be inspected for cracks in the spar cap, wing spar and wing. Aircraft with more than 10,000 hours of airframe time were grounded immediately pending a visual inspection.