TYPE: Twin-turboprop light transport.
PROGRAMME: Design started in January 1964 and construction in November of that year. Prototype (CF-DHC-X) flew in May 1965; Canadian certification 7 April 1966; first delivery in July 1966. Main production series were 100 (115 built, including prototypes), 200 (117 built) and 300 (612 built), last of which completed in December 1988. Some 550 remain in service.
Production rights acquired from Bombardier in 31 January 2006 and new Series 400 version offered. Assembly of first aircraft targeted for third quarter of 2008; work shared between facilities in Calgary and Vancouver.
CURRENT VERSIONS: Series 400: Revised version offered by Viking in 2006. P&WC PT6A-34 engines, upgraded avionics and systems.
CUSTOMERS: Production of first three series covered 844, including prototypes. No orders accepted for Viking version, pending formal launch.
COSTS: USD2 million (2007).
DESIGN FEATURES: High-set, constant-chord wing with streamlined strut bracing; cruciform empennage with sweptback fin and constant-chord tailplane.
Wing-section NACA 6A series mean line; NACA 0016 (mod) thickness distribution. Dihedral 3°.
FLYING CONTROLS: Conventional and manual. Double-slotted full-span trailing-edge flaps. Ailerons also droop for use as flaps. Electrically actuated tab in port aileron; geared trim tabs in port and starboard ailerons. Manually operated trim tabs in rudder and elevators. Geared tab is fitted to the rudder to lighten control forces and a tab fitted to the starboard elevator is linked to the flaps to control longitudinal trim during flap retraction and extension.
STRUCTURE: Generally of aluminium alloy. All-metal safe-life structure, each wing being attached to the fuselage by two bolts at the front and rear spar fitting and braced by a single streamline section strut on each side. Light-alloy riveted construction is used throughout except for the upper skin panels which have spanwise corrugated stiffeners bonded to them. Fuselage is a conventional semi-monocoque safe-life structure, in three sections. Primary structure of frames, stringers and skin of aluminium alloy. Windscreen and cabin windows of acrylic plastics. Cabin floor is of low-density aluminium-faced sandwich construction and is designed to accommodate distributed loads of up to 976 kg/m² (200 lb/sq in). Tail unit of high-strength aluminium alloys. Fin and fixed-incidence tailplane are bolted to rear fuselage.
LANDING GEAR: Tricycle type; fixed. Single wheel on each unit. Fully steerable nosewheel. Urethane compression-block shock-absorption on main units. Oleo-pneumatic nosewheel shock-absorber. Mainwheel tyre size 11.00-12; pressure 2.62 bars (38 lb/sq in). Nosewheel tyre size 8.9-12.50; pressure 2.28 bars (33 lb/sq in). Independent, hydraulically operated disc brakes on mainwheels. Alternatively, high-flotation wheels and tyres, for operation in soft field conditions, also available at option size 15-0-12.0 for nosewheel and mainwheels. Provision for alternative wheel-ski landing gear. Twin-float gear accompanied by added wing fences and small auxiliary fins.
POWER PLANT: Two 559 kW (750 shp) Pratt & Whitney Canada PT6A-34 turboprops, each driving a Hartzell HC-B3TN-3DY three-blade, reversible-pitch fully feathering metal propeller with Beta control (zero-pitch propeller on floatplane). Four-blade propellers under development in 2006. Two underfloor fuel tanks (eight cells), total capacity of 1,442 litres (381 US gallons; 317 Imp gallons). Long-range tank optional in fuselage, providing 337 litres (89.0 US gallons; 74.1 Imp gallons). Refuelling point for each tank on port side of fuselage. Oil capacity 9.1 litres (2.4 US gallons; 2.0 Imp gallons) per engine. Optional electric de-icing system for propellers and air intakes.
ACCOMMODATION: Two pilots on flight deck and up to 20 passengers, or equivalent freight. Flight deck access via forward-opening car-type door on each side or via passenger cabin. Dual controls standard. Windscreen demisting and defrosting standard. Cabin divided by bulkhead in top main passenger cabin for freight compartment and baggage compartment.
Standard interior is 20-seat commuter layout with Douglas track, carpets, double windows, individual air vents and reading lights and airstair door. Optional layouts include 18- or 19-seat commuter versions, and 13/20-passenger utility version with foldaway seats and double cargo doors with ladder. Access to cabin by door on each side of rear fuselage; airstair door on port side. Optional double door for cargo on port side instead of airstair door. Compartments in nose and aft of main cabin, each with upward-hinged door on port side, for 136 kg (300 lb) and 227 kg (500 lb) of baggage respectively; rear baggage hold accessible from cabin in emergency. Emergency exits near front of cabin on each side.
Heating of flight deck and passenger cabin by engine bleed air; ventilation via a ram air intake on the port side of the fuselage nose. No pressurisation. Oxygen system for crew and passengers optional. Executive, survey or ambulance interiors optional. Tie-down cargo rings standard for the freighter role.
SYSTEMS: Hydraulic system, pressure 103 bar (1,500 lb/sq in), for flaps, brakes, nosewheel steering and (where fitted) ski retraction mechanism. Hand pump in crew compartment provides emergency pressure for standby or ground operation if the electric pump is inoperative. Accumulators smooth the system pressure pulses and provide pressure for parking and emergency braking. Optional low-pressure pneumatic system (1.24 bars; 18 lb/sq in) for operation of autopilot or wing and tail de-icing boots, if fitted.
Primary electrical system is 28 V DC with one 24 A starter/generator on each engine. One 40 Ah 20-cell Ni/Cd battery (optional 36 Ah lead-acid battery) for emergency power and engine starting. Separate 3.6 Ah battery supplies independent power for engine starting relays and ignition. 250 VA main and standby static inverters provide 400 Hz AC power for instruments and avionics. External DC receptacle aft of port side cabin door permits operation of complete system on the ground. Optional boot de-icing equipment on wing. Optional pneumatic-boot de-icing of tailplane leading-edge.
DIMENSIONS, EXTERNAL:
- Wing span: 19.81 m (65 ft 0 in)
- Wing chord, constant: 1.98 m (6 ft 6 in)
- Wing aspect ratio: 10.1
- Length overall: Landplane: 15.77 m (51 ft 9 in)
- Floatplane: 15.09 m (49 ft 6 in)
- Height overall: Landplane: 5.94 m (19 ft 6 in)
- Floatplane from waterline: 6.05 m (19 ft 10 in)
- Tailplane span: 6.30 m (20 ft 8 in)
- Wheel track: Landplane: 3.71 m (12 ft 2 in)
- Wheelbase: Landplane: 4.53 m (14 ft 10½ in)
- Length of floats: Floatplane: 9.65 m (31 ft 8 in)
- Width over floats: Floatplane: 5.18 m (17 ft 0 in)
- Seaplane track (c/l of floats): 4.06 m (13 ft 4 in)
- Propeller diameter: 2.59 m (8 ft 6 in)
- Passenger door (port): Height: 1.27 m (4 ft 2 in)
- Width: 0.76 m (2 ft 6 in)
- Height to sill: 1.32 m (4 ft 4 in)
- Passenger door (stbd): Height: 1.16 m (3 ft 9½ in)
- Width: 0.77 m (2 ft 6¼ in)
- Height to sill: 1.32 m (4 ft 4 in)
- Baggage compartment door (nose)
- Mean height: 0.69 m (2 ft 3¼ in)
- Width: 0.76 m (2 ft 6 in)
- Height to sill: 1.32 m (4 ft 4 in)
- Baggage compartment door (port, rear):
- Max height: 0.97 m (3 ft 2 in)
- Width: 0.65 m (2 ft 1½ in)
- Height to sill: 1.32 m (4 ft 4 in)
DIMENSIONS, INTERNAL:
- Cabin, excl flight deck, galley and baggage compartment:
- Length: 5.64 m (18 ft 6 in)
- Max width: 1.61 m (5 ft 3¼ in)
- Max height: 1.50 m (4 ft 11 in)
- Floor area: 7.45 m² (80.2 sq ft)
- Volume: 10.87 m³ (384 cu ft)
- Baggage compartment (nose):
- Volume: 1.08 m³ (38 cu ft)
- Baggage compartment (rear):
- Length: 1.88 m (6 ft 2 in)
- Volume: 2.49 m³ (88 cu ft)
AREAS:
- Wings, gross: 39.02 m² (420 sq ft)
- Ailerons (total): 3.08 m² (33.2 sq ft)
- Trailing-edge flaps (total): 10.42 m² (112.2 sq ft)
- Fin: 4.46 m² (48.0 sq ft)
- Rudder, incl tabs: 3.16 m² (34.0 sq ft)
- Tailplane: 9.29 m² (100 sq ft)
- Elevator, incl tabs: 3.25 m² (35.0 sq ft)
WEIGHTS AND LOADINGS:
- Basic weight: 3,121 kg (6,881 lb)
- Max payload:
- for 100 n miles (185 km; 115 miles): 1,941 kg (4,280 lb)
- for 400 n miles (740 km; 460 miles): 1,474 kg (3,250 lb)
- Max T-O weight: 5,670 kg (12,500 lb)
- Max landing weight:
- wheels and skis: 5,579 kg (12,300 lb)
PERFORMANCE:
- Max cruising speed: at S/L: 170 kt (315 km/h; 196 mph)
- at FL50: 181 kt (335 km/h; 208 mph)
- at FL100: 182 kt (337 km/h; 209 mph)
- Stalling speed: flaps up: 74 kt (138 km/h; 86 mph)
- flaps down: 58 kt (108 km/h; 67 mph)
- Max rate of climb at S/L: 488 m (1,600 ft)/min
- Rate of climb at S/L, OEI: 104 m (340 ft)/min
- Service ceiling: 8,140 m (26,700 ft)
- Service ceiling, OEI: 3,530 m (11,600 ft)
- T-O run: STOL: 213 m (700 ft)
- CAR Pt 3: 262 m (860 ft)
- T-O to 15 m (50 ft): STOL: 366 m (1,200 ft)
- CAR Pt 3: 457 m (1,500 ft)
- Landing from 15 m (50 ft): STOL: 320 m (1,050 ft)
- CAR Pt 3: 591 m (1,940 ft)
- Landing run: STOL: 157 m (515 ft)
- CAR Pt 3: 290 m (950 ft)
- Ferry range: normal tankage: 775 n miles (1,435 km; 891 miles)
- long-range tankage: 980 n miles (1,815 km; 1,127 miles)