PZL Kania
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| PZL Kania | |
|---|---|
 PZL Kania of Polish Police |
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| Type | Helicopter |
| Manufacturer | WSK "PZL-Świdnik" |
| Maiden flight | 3 June 1979 |
| Primary user | Poland |
| Produced | 16 (including prototypes) |
| Developed from | Mil Mi-2 |
The PZL Kania (Polish Kitty Hawk) is a follow-up to the Mi-2.
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[edit] Design and development
PZL Kania helicopter is featuring lot of changes, redesigned hull, new engines (Rolls-Royce Allison 250-C20B turboshaft engines each rated at 426hp (313 kW), new composite rotors blades, new, western avionics. Work on the version was started in 1969. The first prototype was flown on 3 June 1979. Test conducted during early 1980s led to certification according to FAR-29 in February 1986. Produced in small numbers (also as upgrade of original Mi-2) in Poland, in the PZL Świdnik factory.
[edit] Variants
- Passenger Standard
- Seats for pilot and 9 passengers, individual vents and lighting.
- Passenger Executive
- Seats for pilot and 5 passengers, luxury finishing, silenced cockpit, individual vents, lighting and audio system.
- Cargo
- Ability to carry external loads as a flying crane or to carry up to 1200 kg of load in the cabin.
- Medevac / Air ambulance
- Equipment and space for up to 4 stretchers or less with paramedic crew onboard.
- Agricultural
- Ability to carry up to 1000 kg of chemicals or agro loads (grains, seeds etc.) and ability to carry on one of following aerial application methods: LV spraying, ULV spraying, dustring and spreading.
- Spitfire Taurus
- American version of the PZL Kania built under licence in the USA[citation needed].
[edit] Operators
[edit] Technical Data
[edit] Powerplants
Two 315kW (720shp) RR Allison 250C20B turboshafts driving a three blade main and two blade tail rotor.
[edit] Performance
Max cruising speed 215km/h (116kt), economical cruising speed 190km/h (102kt). Initial rate of climb 1722ft/min. Service ceiling 13,120ft. Hovering ceiling out of ground effect 4510ft. Range with max fuel and reserves 435km (234nm), with auxiliary fuel and reserves 800km (432nm). Endurance with auxiliary fuel 4hr.
[edit] Weights
Basic empty 2000kg (4410lb), max takeoff 3550kg (7826lb).
[edit] Dimensions
Main rotor diameter 14.50m (47ft 7in), length overall 17.48m (57ft 4in), fuselage length 12.03m (39ft 6in), height (no tail rotor) 2.70m (8ft 10in). Main rotor disc area 166.4m2 (1791.1sq ft).
[edit] Capacity
Pilot and eight passengers in passenger configuration, pilot and five passengers in corporate configuration. Two stretchers, one seated patient and two medical attendants in ambulance configuration. Ag version capacity 1000kg (2205lb) of chemicals.
[edit] Specifications
General characteristics
- Crew: One
- Capacity: 9 passengers or 700 kg (1,540 lb) internal, 1000 kg (2205 lb) external cargo
- Length: 12.03 m (39 ft 6 in)
- Rotor diameter: 14.50 m (47 ft 7 in)
- Height: 2.70 m (8 ft 10 in)
- Disc area: 167 m² (1,797 ft²)
- Empty weight: 2,000 kg (4,410 lb)
- Max takeoff weight: 3,550 kg (7,826 lb)
- Powerplant: 2× Allison 250C20B turboshafts, 315 kW (720 shp) each
Performance
- Maximum speed: 220 km/h
- Range: 435 km (234 NM) (with external fuell 800 km (432 NM))
- Service ceiling 4,000 m (13,120 ft)
- Rate of climb: 8.748 m/s (1722 ft/min)
[edit] See also
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