Canadair CL-44

Canadian airliner and transport aircraft introduced in 1960

Overview

Bombardier Canada ICAO: CL44 1960–1965

The Canadair CL-44 was built and manufactured by Canadair during the late 1950s until the early 1960s as a turboprop airliner and cargo aircraft developed from the British Bristol Britannia medium-to-long-range airliner. The aircraft performed its maiden flight in November 1959 and was introduced in July 1960 by Royal Canadian Air Force. It was retired in 1971 and has a total number of 39 aircraft built.

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Specifications

Units
Engine
4 × Rolls-Royce Tyne 515/50
Engine type
Turboprop
Power
4 × 5,730 shp · 4,273 kW
Avionics
—
Wing tips
No winglets
Seats
189
Crew
—
Cabin width
11 ft 0 in  ·  3.35 m
Cabin height
6 ft 9 in  ·  2.05 m
Cabin length
98 ft 5 in  ·  30.00 m
Exterior length
136 ft 10 in  ·  41.70 m
Tail height
36 ft 8 in  ·  11.18 m
Fuselage diameter
12 ft 2 in  ·  3.70 m
Wing span
142 ft 3 in  ·  43.37 m
Baggage volume
999 ft³  ·  28.3 m³
Gross weight
—
Empty weight
—
Max takeoff weight
209,500 lb  ·  95,000 kg
Max landing weight
—
Max payload
66,000 lb  ·  30,000 kg
Fuel capacity
9,800 gal · 37,000 L · 29,600 kg (Jet A)
Max cruise speed
360 kt  ·  414 mph  ·  667 km/h
Maximum speed
—
Cruise speed
—
Approach speed
—
Range
4,856 nm  ·  5,590 mi  ·  8,990 km
Fuel burn
—
Ceiling
30,000 ft  ·  9,100 m
Rate of climb
—
Takeoff distance
—
Landing distance
—
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‘N122AE’ Canadair CL-44D-4 – Air Express International

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Operational Context

From the late 1950s until the early 1960s, the Canadian manufacturing company Canadair started to develop the CL-44 transport aircraft. It was based on the British Bristol Britannia medium-to-long-range airliner. On November 15, 1959, the aircraft prototype designated as Yukon took to the air for the first time at the Cartierville Airport. Several problems arose during flight testing such as an entire electrical failure to engines slipping up and nearly falling off. On July 19, 1960, the aircraft was introduced with the Royal Canadian Air Force and was retired in 1971.

The CL-44D-4 version can carry two pilots, one flight engineer plus loadmasters as required, and up to one hundred and sixty passengers and 29,959 kg of useful load. It has an external length of 41.73 meters, an external height of 5.6 meters, and a fuselage diameter of 3.7 meters. It has a tail height of 11.18 meters and a wheelbase of 16 meters. The wingspan is 43.47 meters and the wing area is 192.7 square meters. The cabin has a length of 30 meters, a height of 2.05 meters, and a width of 3.35 meters. The aircraft has an empty weight of 40,348 kg, a maximum takeoff weight of 95,000 kg, a maximum payload of 30,000 kg, and a fuel tank capacity of 9,775 US gal.

The aircraft is powered by four Rolls-Royce Tyne 515/50 turboprop engines. It is a twin-spool turboprop with an axial six-stage low-pressure nine-stage high-pressure compressor, ten cannular flame tubes combustors, a three-stage low-pressure single-stage high-pressure turbine, and a pressure spray/splash with dry sump oil system. The engine produces a maximum takeoff thrust of 5,730 shaft horsepower each and drives four-bladed variable pitch propellers. The CL-44 has a maximum speed of 360 knots and a cruise speed of 349 knots. It has a travel range of 4,856 nautical miles and can fly up to 30,000 feet.