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  • de Havilland Canada DHC-3 Otter

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    Description

    The de Havilland Canada DHC-3 Otter is a single-engined, high-wing, propeller-driven, short take-off and landing (STOL) aircraft developed by de Havilland Canada.

    General Information

    It was conceived to be capable of performing the same roles as the earlier and highly successful Beaver, including as a bush plane, but is overall a larger aircraft.

     

    The rugged single-engined, high-wing, propeller-driven DHC-3 Otter was conceived in January 1951 by de Havilland Canada as a larger, more powerful version of its highly successful DHC2 Beaver STOL utility transport. Dubbed the "King Beaver" during design, it would be the veritable "one-ton truck" to the Beaver's "half-ton" role.

     

    The Otter received Canadian certification in November 1952 and entered production shortly thereafter. Using the same overall configuration as the Beaver, the new, much heavier design incorporated a longer fuselage, greater-span wing, and cruciform tail. Seating in the main cabin expanded from six to 10 or 11. Power was supplied by a 450-kW (600 hp) Pratt & Whitney R-1340 geared radial. The version used in the Otter was geared for lower propeller revolutions and consequently lower airspeed. The electrical system was 28 volts D.C. Many Otters have been modified with turboprop engines.

     

    Like the Beaver, the Otter can be fitted with skis or floats. The Otter served as the basis for the very successful Twin Otter, which features two wing-mounted Pratt & Whitney Canada PT6 turboprops. A total of 466 Otters were manufactured.

     

    For details of the many modifications and eight variants, click here.

     

    Specifications below are for the landplane version. For specifications of the skiplane and seaplane versions, see above link.

    dhc3 Otter amphibian N98T.jpg

    DHC-3 Otter VH-OTR Photo by Edwin van Apstal.jpg

    DHC-3-Otter-2 CF-APQ.jpg

    DHC-3-Otter-2 C-FUKN Northway Aviation.jpg

    De Havilland Canada DHC-3 Otter Turboprop N90422 floatplane.jpg

    Specifications

    Seats:
    Crew: 1 or 2 Capacity: 9-11 passengers (optional 10th seat in main cabin) / 6 stretchers with 4 seats / 23 stretchers with 7 seats
    Length:
    41 ft 10 in (12.75 m)
    Wingspan:
    58 ft 0 in (17.68 m)
    Height:
    12 ft 7 in (3.84 m),
    Wing Area:
    375 sq ft (34.8 sq m)
    Empty Weight:
    4,108 lb (1,863 kg)
    MTOW:
    Gross weight: 8,000 lb (3,629 kg)
    Fuel Capacity:
    Total fuel 178 imp gal (214 US gal; 809 l) in :- 51 imp gal (61 US gal; 232 l) front tank ; 85 imp gal (102 US gal; 386 l) middle tank group (two cells) ; 42 imp gal (50 US gal; 191 l) rear tank
    Powerplant:
    1 × Pratt & Whitney R-1340-S1H1-G Wasp 9-cylinder air-cooled radial piston engine, 600 hp (450 kW) or -S3H1-G (lower supercharger gearing)
    Vne:
    Maximum speed: 160 mph (260 km/h, 140 kn) at 5,000 ft (1,524 m)
    Cruise Speed:
    138 mph (222 km/h, 120 kn) 66% power at 5,000 ft (1,524 m)
    Range:
    960 mi (1,540 km, 830 nmi) full internal fuel at 5,000 ft (1,524 m)
    Takeoff Dist.:
    to 50 ft (15 m): 1,310 ft (399 m)
    Landing Dist.:
    from 50 ft (15 m): 975 ft (297 m)
    Rate of Climb:
    735 ft/min (3.73 m/s) at sea level
    Service Ceiling:
    18,800 ft (5,700 m) S1H1-G engine 17,400 ft (5,304 m), S3H1-G engine

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