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Cessna 421

 

Cessna 421

421 Golden Eagle
Cessna 421B landing
Role Light transport
National origin United States
Manufacturer Cessna
First flight October 14, 1965
Produced 1967–1985
Number built 1916
Developed from Cessna 411

The Cessna 421 Golden Eagle is an American six or seven seat twin-engined light transport aircraft, developed in the 1960s by Cessna as a pressurised version of the earlier Cessna 411.[1]

Contents

  • Design 1
  • Development 2
  • Variants 3
  • Military operators 4
  • Specifications (C 421C) 5
  • See also 6
  • Notes 7
  • References 8
  • External links 9

Design

The 421 is an all-metal low-wing cabin monoplane with a retractable tricycle landing gear, and powered by two geared[1] Continental GTSIO-520-D tractor engines. The cabin is accessed from a door, on the left hand side behind the wing, and has seating for six on the basic 421, or up to ten on later variants.

Development

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 wingtip 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 1,901 aircraft 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.[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

Cessna 421B Golden Eagle with aftermarket RAM-modified engines
A Cessna 421B Golden Eagle, front view
A Cessna 421B Golden Eagle
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).[2] 200-built.[1]
421A
Type approved 19 November 1968, powered by two Continental GTSIO-520-Ds of 375 hp (280 kW) each, maximum takeoff weight 6,840 lb (3,103 kg).[2] 158-built.[1]
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 takeoff weight 7,250 lb (3,289 kg), later models 7,450 lb (3,379 kg).[2] 699-built.[1]
421C Golden Eagle/Executive Commuter
Model with new wing and landing gear. Type approved 28 October 1975, powered by two Continental GTSIO-520-Ls or Continental GTSIO-520-Ns of 375 hp (280 kW) each, maximum takeoff weight 7,450 lb (3,379 kg).[2] 859-built.[1]
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]
Excalibur 421
Re-engined 421C with Pratt & Whitney Canada PT6A-135A or PT6A-112 turboprops, supplemental type certificate held by Excalibur 421 LLC of Paso Robles, California.[5] In 2013 it was announced that Aviation Alliance are acting as program managers for the Excalibur 421 updagrade programme.[6]
Advanced Aircraft Regent 1500
Production of the Riley Turbine Eagle 421 conversion by Advanced Aircraft Corporation.[7]

Military operators

"Golden Eagle" logo on the fin of a 421B
 Bahamas
 Bolivia
 Cambodia
 Ivory Coast
 New Zealand
 Nicaragua
 Pakistan
 Paraguay
 Philippines
 Sri Lanka
 Turkey
 Zimbabwe

Specifications (C 421C)

1982 Cessna 421C
Cessna 421C Golden Eagle, typical pilot's instrumentation
Cessna 421C Golden Eagle, typical copilot's instrumentation

Data from Jane's All The World's Aircraft 1976–77 [15]

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
  • Pressurised 6-8 seat cabin twin.

Performance

See also

Related development
Aircraft of comparable role, configuration and era

Notes

  1. ^ The gearing means that rather than the driveshaft being directly connected to the propeller, it drives through a set of reduction gears.

References

  1. ^ a b c d e
  2. ^ a b c d e
  3. ^ a b c Taylor 1982, p. 455.
  4. ^ Taylor 1982, p. 352.
  5. ^
  6. ^
  7. ^ Taylor 1988, p. 321.
  8. ^ Andrade 1982, p. 27
  9. ^ http://www.flightglobal.com/pdfarchive/view/2001/2001%20-%203767.html
  10. ^ Andrade 1982, p. 126
  11. ^ Andrade 1982, p. 165
  12. ^ Andrade 1982, p. 174
  13. ^ Andrade 1982, p. 229
  14. ^ Andrade 1982, p. 346
  15. ^ Taylor 1976, pp. 272–273.
Bibliography

External links

Media related to at Wikimedia Commons

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