Cessna 414 Chancellor

Pressurized twin utility aircraft.

Overview

Cessna United States ICAO: C414 1968–1985 Active $500,000 (1981)

The Cessna 414 Chancellor is a light, pressurized, twin-engine transport aircraft with a pressurized cabin in service since 1969. It is a less powerful and lighter evolution of the Cessna 421.

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Specifications

Units
Engine
2 × Continental TSIO-520-NB
Engine type
Piston
Power
2 × 310 hp · 231 kW
Avionics
—
Wing tips
No winglets
Seats
10
Crew
—
Cabin width
4 ft 7 in  ·  1.40 m
Cabin height
4 ft 3 in  ·  1.30 m
Cabin length
11 ft 6 in  ·  3.50 m
Exterior length
36 ft 5 in  ·  11.10 m
Tail height
11 ft 6 in  ·  3.50 m
Fuselage diameter
4 ft 11 in  ·  1.50 m
Wing span
44 ft 2 in  ·  13.46 m
Baggage volume
85 ft³  ·  2.4 m³
Gross weight
—
Empty weight
—
Max takeoff weight
6,750 lb  ·  3,050 kg
Max landing weight
5,950 lb  ·  2,700 kg
Max payload
1,750 lb  ·  800 kg
Fuel capacity
210 gal · 800 L · 600 kg (AvGas)
Max cruise speed
235 kt  ·  270 mph  ·  435 km/h
Maximum speed
—
Cruise speed
—
Approach speed
68 kt  ·  78 mph  ·  126 km/h
Range
1,328 nm  ·  1,530 mi  ·  2,460 km
Fuel burn
—
Ceiling
30,800 ft  ·  9,400 m
Rate of climb
1,520 ft/min  ·  8 m/s
Takeoff distance
2,200 ft  ·  670 m
Landing distance
2,350 ft  ·  720 m
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Cessna 414AW Chancellor

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Operational Context

On November 1, 1968, the prototype registered N7170C, conducted its maiden flight. Production aircraft were accessible in several optional seating configurations and avionics packages. The aircraft was labeled the Chancellor in 1976. In 1978, an enhanced version was launched, designated as the 414A Chancellor. It featured major modifications, including a restructured and increased wingspan, incorporating integral fuel tanks, and a stretched nose to allow more space for baggage. The Cessna 414 Chancellor was produced from 1968 to 1985.

The original 414 was developed out of the fuselage of the Cessna 421 and of the wing of the Cessna 401. It has an exterior length of 11.1 meters, a height of 3.5 meters, and a fuselage diameter of 1.5 meters. The wingspan is 13.46 meters, the wing area is 20.97 square meters, and the wheelbase is 3.3 meters. The 414 is a low-wing cantilever monoplane with a conventional tail section and a retractable tricycle undercarriage. The cabin length is 3.5 meters, height is 1.3 meters, and width is 1.4 meters. The aircraft can seat up to eight passengers and one or two crew.

The aircraft is powered by two Continental TSIO-520-NB piston engines. This piston engine is a six-cylinder, horizontally-opposed, direct drive, turbocharge, air-cooled, and fuel-injected type that produces a maximum thrust of 310 horsepower each. The fuel system composed of a pair of main tanks and fuel selectors, emergency cross-feed shutoff valves, and other crucial parts to complete the system. The two main tanks were essential sections of the sealed wet wing. Auxiliary fuel pumps were placed outside the tanks, while the fuel flow gauge together with the fuel quantity gauge and the fuel low-level warning light is in the cockpit. The aircraft also featured a 28V, negative ground, direct current electrical system charged by an alternator on each engine, and a 24V battery.

The Chancellor has a service ceiling of 30,800 feet and a maximum speed of 235 knots. It has a range of 1,328 nautical miles and a climb rate of 1,520 feet per minute. It has a take-off distance of 665 meters and a landing distance of 718 meters.

The aircraft has a maximum takeoff weight of 3,061 kg and a maximum landing weight of 2,697 kg.