Cessna 421

Development

The Cessna 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 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.

Design

The 421 is an all-metal low-wing cabin monoplane with a retractable tricycle landing gear, and powered by two geared Continental GTSIO-520-D engines, wing-mounted in tractor configuration. 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.

Variants

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). 200-built.

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). 158-built.

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). 699-built.

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). 859-built.

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.

Riley Turbine Eagle 421

Conversion of Cessna 421C aircraft by fitting two 750hp Pratt & Whitney Canada PT6A-135 turboprop engines. Formal designation R421CP.

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. In 2013 it was announced that Aviation Alliance are acting as program managers for the Excalibur 421 updagrade programme.

Advanced Aircraft Regent 1500

Production of the Riley Turbine Eagle 421 conversion by Advanced Aircraft Corporation.

Military operators

 Bolivia

Bolivian Air Force at least one 421B was in use.

 Cambodia

Royal Cambodian Air Force

 Ivory Coast

Ivory Coast Air Force

 New Zealand

Royal New Zealand Air Force three 421C.

No. 42 Squadron RNZAF

 Pakistan

Pakistan Army Aviation at least one 421 in use.

 Turkey

Turkish Army Aviation at least three 421Bs in use.

 Zimbabwe

Air Force of Zimbabwe at least one 421A in use.

Specifications (C 421C)

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

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)

Pressurised 6-8 seat cabin twin.

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)