Cessna 421
| 421 Golden Eagle |
|
|
| A Cessna 421B Golden Eagle |
| Role |
Light transport |
| National origin |
United States of America |
| Manufacturer |
Cessna |
| First flight |
October 14, 1965 |
| Produced |
1967–1985 |
| Developed from |
Cessna 411 |
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.[1]
Development
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.[1]
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 from the 1981 model year onwards. Production ended in 1985 after 1901 had been delivered.[1]
The Cessna 421 was first certified on 1 May 1967 and shares a common type certificate with models 401, 402 411, 414 and 425[2]
Some 421s have been modified to accept turboprop engines,[3] making them very similar to the Cessna 425, which itself is a turboprop development of the 421.[4]
Variants
- 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).[2]
- 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).[2]
- 421B Golden Eagle/Executive Commuter
- Eight-seat light passenger transport aircraft. 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).[2]
- 421C Golden Eagle/Executive Commuter
- Light passenger transport aircraft. 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).[2]
- Riley Turbine Rocket 421
- Conversion of Cessna 421 aircraft by fitting two Lycoming LTP101 turboprop engines. Formal designation R421BL and R421CL for conversions of 421B and C respectively.[3]
- Riley Turbine Eagle 421
- Conversion of Cessna 421C aircraft by fitting two 750hp Pratt & Whitney Canada PT6A-135 turboprop engines. Formal designation R421CP.[3]
Military operators
- Bahamas
- Bolivia
- Cambodia
- Côte d'Ivoire
- New Zealand
- Nicaragua
- Pakistan
- Paraguay
- Philippines
- Rhodesia
- Sri Lanka
- Turkey
Specifications (C 421C)
Data from Jane's All The World's Aircraft 1976-77 [6]
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
Performance
- 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)
See also
- Related development
- Aircraft of comparable role, configuration and era
References
- Notes
- Bibliography
- Taylor, John W.R. (editor). Jane's All The World's Aircraft 1976-77. London:Jane's Yearbooks, 1976. ISBN 0-354-00538-3.
- Taylor, John W. R. Jane's All The World's Aircraft 1982–83. London: Jane's Yearbooks, 1982. ISBN 0 7106-0748-2.
|
|
|
| Single-engine |
|
|
| Multi-engine |
|
|
Cessna Citation
families |
|
|
| Helicopters |
|
|
| Gliders |
|
|
| Military |
|
|
|
|
|
| General |
|
|
| Military |
|
|
| Accidents/incidents |
|
|
| Records |
|
|