|PZL-105 at the Polish Aviation Museum|
|First flight||9 November 1989|
|Primary user||Polish civilian aviation|
|Number built||2 (prototypes)|
The PZL-105 was designed as a successor to the successful utility aircraft PZL-104 Wilga, being more modern and economical and offering increased transport capacity. The design was initially called Wilga 88. It retained the high-wing layout of the PZL-104 and the upward-opening side doors, but it was a completely new aircraft. Compared with the Wilga, it has a six-seat cabin instead of four seats and the wings are supported by single struts instead of a cantilever design. The plane was intended for a variety of purposes, like glider towing, parachute training, transport, air ambulance, patrolling and crop dusting (with 500 kg of chemicals). Also, a seaplane variant was intended.
The first prototype, powered by a 265 kW (360 hp) Russian M-14P radial engine, was first flown on 9 November 1989 (markings SP-PRC). An intended designation of a serial variant was PZL-105M. The second prototype, designated PZL-105L, was fitted with a flat engine 298 kW (400 hp) Lycoming IO-720. It was flown on 27 July 1991 (markings SP-PRD). There was also made one prototype for static trials.
Problems with funding at the outbreak of the 1980s and 1990s, connected with a change of political system in Poland, and the priority of the PZL-130 Orlik trainer program, had caused the Flaming program to be suspended, and production of the type has yet to have started. The company developed a new variant of the PZL-104, the Wilga 2000 with Lycoming I0-540 flat engine instead.
Metal construction braced high-wing monoplane, conventional in layout, duralumin covered. Semi-monocoque fuselage. Rectangular single-spar wings, fitted with Fowler flaps and slotted flaperons. Six-seat cabin with three rows of seats, with large side doors opening upwards. Conventional fixed landing gear with tail wheel, the main gear is made of composite spring legs. Two-blade or three-blade (PZL-105L) metal propeller. Fuel tanks in wings (270 l).
Data from Jane's All The World's Aircraft 1993-94
- Crew: 1 pilot
- Capacity: 5
- Length: 8.67 m (28 ft 5¼ in)
- Wingspan: 12.97 m (42 ft 6½ in)
- Height: 2.87 m (9 ft 5 in)
- Wing area: 16.90 m² (182 ft²)
- Empty weight: 1,150 kg (2,535 lb)
- Max. takeoff weight: 1,850 kg (4,078 lb)
- Fuel: 270 L (71.3 US Gallons)
- Powerplant: 1 × Lycoming IO-720-A1B air-cooled flat engine, 298 kW (400 hp)
- Never exceed speed: 306 km/h (165 knots, 190 mph)
- Maximum speed: 260 km/h (140 knots, 162 mph)
- Cruise speed: 216 km/h (117 knots, 134 mph) (econ cruise)
- Stall speed: 102 km/h (55 knots, 64 mph)
- Range: 981 km (529 nm, 609 mi) at econ cruise speed
- Service ceiling: 5,070 m (16,625 ft)
- Rate of climb: 5.6 m/s (1,100 ft/min)
- Wing loading: 109 kg/m² (22.4 lb/ft²)
- Power/mass: 0.161 kW/kg (0.0982 hp/lb)
- Related development
- Lambert 1993, pp. 241–242.
- Andrzej Glass: Samoloty '94, Grupa IMAGE, Warsaw 1994, ISBN 83-85461-19-1
- Lambert, Mark (ed.). Jane's All The World's Aircraft 1993-94. Coulsdon, UK: Jane's Data Division, 1993. ISBN 0-7106-1066-1.
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