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Cessna 421B Golden Eagle with aftermarket RAM-modified engines A Cessna 421B Golden Eagle, front view A Cessna 421B Golden Eagle 1982 Cessna 421C 421 Type approved 1 May 1967, powered by two Continental GTSIO-520-Ds of 375 hp (280 kW) each, maximum takeoff weight 6,800 lb (3,084 kg). [3] 200 built. [6] 421A
The turbocharged GTSIO-520's most common applications are the twin-engine Cessna 404 and 421, where it is rated at 375 hp (280 kW). The 'G' prefix indicated the incorporation of propeller reduction gearing.
The pressurized 414 was developed to appeal to owners of unpressurized, twin-engined aircraft, and was based on the fuselage of the Cessna 421 and used the wing design of the Cessna 401. The 414 is a low-wing cantilever monoplane with a conventional tail unit and a retractable tricycle landing gear.
Cessna Model A: 1927 70 Single piston engine monoplane utility airplane Cessna Model BW: 13 Single piston engine monoplane utility airplane Cessna CG-2: Glider Cessna CH-1: 1953 ~50 Single piston engine utility helicopter Cessna CH-4: Single piston engine utility helicopter Cessna CR-1: 1 Single piston engine monoplane racer Cessna CR-2: 1930 1
The 425 was introduced in 1980 and was a derivation of the Cessna 421, powered by two 450 hp (336 kW) Pratt & Whitney PT6 engines. In comparison to the King Air C90, "the result was an $875,000 pressurized twin-turboprop that could fly 15 knots to 20 knots faster than the C90, cruise 250 miles farther with four passengers aboard and burn 15 ...
The Cessna Model 411 is an American twin-engined, ... Specifications 3-view line drawing of the Cessna 411A ... Performance. Maximum speed: 268 mph (431 km/h, ...
The Cessna 441 Conquest II is the first turboprop powered aircraft designed by Cessna and was meant to fill the gap between their jets and piston-engined aircraft. It was developed in November 1974, with the first aircraft delivered in September 1977. It is a pressurized, 8–9 passenger turbine development of the Cessna 404 Titan.
In aviation, a balanced field takeoff is a condition where the takeoff distance required (TODR) with one engine inoperative and the accelerate-stop distance are equal for the aircraft weight, engine thrust, aircraft configuration and runway condition. [1]