- Aircraft History, Specification and Information -
Cessna 421

The Cessna 421 Golden Eagle is a development of the earlier Cessna 411 light, twin-engine personal transport aircraft. The main difference between the two models is that the 421 is pressurized.


The 421 uses geared Continental GTSIO-520-D engines. The gearing means that rather than the drive shaft being directly connected to the propeller, it drives through a set of reduction gears.

The 421 was first produced in May 1967. The 421A appeared in 1968 and the aircraft was redesigned in 1970 and marketed as the 421B. In 1975 the 421C appeared which featured wet wings, the absence of wing tip fuel tanks and landing gear that was changed from straight-leg to a trailing-link design. Production ended in 1985 after 1901 had been delivered.

The Cessna 421 was first certified on 1 May 1967 and shares a common type certificate with models 401, 402 411, 414 and 425.

Some 421s have been modified to accept turboprop engines, making them very similar to the Cessna 425, which itself is a turboprop development of the 421.


Cessna 421
Type approved 1 May 1967, powered by two Continental GTSIO-520-Ds of 375 hp (280 kW) each, maximum take-off weight 6,800 lb (3,084 kg).

Cessna 421A
Type approved 19 November 1968, powered by two Continental GTSIO-520-Ds of 375 hp (280 kW) each, maximum take-off weight 6,840 lb (3,103 kg).

Cessna 421C
Type approved 28 April 1970, powered by two Continental GTSIO-520-Hs of 375 hp (280 kW) each, maximum take-off weight 7,250 lb (3,289 kg), later models 7,450 lb (3,379 kg).

Cessna 421C
Type approved 28 October 1975, powered by two Continental GTSIO-520-Ls or Continental GTSIO-520-Ns of 375 hp (280 kW) each, maximum take-off weight 7,450 lb (3,379 kg).

Military Operators



Côte d'Ivoire

New Zealand - Royal New Zealand Air Force, No. 42 Squadron RNZAF




Rhodesia - Rhodesian Air Force - 1

Sri Lanka


Specifications (C 421C)

General characteristics
Crew: One or two
Capacity: Six passengers
Length: 36 ft 9⅝ in (11.09 m)
Wingspan: 41 ft 1½ in (12.53 m)
Height: 11 ft 5⅜ in (3.49 m)
Wing area: 215 ft² (19.97 m²)
Empty weight: 4,501 lb (2,041 kg)
Max takeoff weight: 7,450 lb (3,379 kg)
Powerplant: 2× Continental GTSIO-520-L turbocharged, fuel injected and geared six-cylinder horizontally-opposed air-cooled piston engine, 375 hp (280 kW) each

Maximum speed: 256 knots (475 km/h, 295 mph) at 20,000 ft (6,100 m)
Cruise speed: 240 knots (444 km/h, 276 mph) at 25,000 ft (7,600 m) (75% power)
Range: 1,487 nmi (2,755 km, 1,712 miles)
Service ceiling: 30,200 ft (9,205 m)
Rate of climb: 1,940 ft/min (9.9 m/s)

Last updated March 12, 2010
This article is licensed under the GNU Free Documentation License. It uses material from the Wikipedia article "Cessna 421".
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