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PZL Warszawa-Okecie PZL-104 Wilga


Designed as a successor to the Polish-built Yak-12 and the P.Z.L. 101 developed from it, the original P.Z.L. 104 Wilga 1 (Thrush) prototype, powered by a 134kW Narkiewicz WN-6 flat-six engine, was flown for the first time on 24 April 1962.

A cantilever high-wing monoplane with fixed tailwheel landing gear and an enclosed cabin, it was followed by prototypes of the Wilga 2P and Wilga CP, powered by the 138kW Narkiewicz WN-6RB2 and 168kW Continental O-470-13A or O-470-L flat-six engines respectively. Intended as a general-purpose aircraft, the P.Z.L. 104 was offered initially in versions equipped for use as a four-seat passenger-carrying or liaison aircraft; for club flying, glider towing or parachuting; for agricultural use with a 500-litre hopper for dust or liquid application; and as an air ambulance carrying pilot, doctor, two stretcher patients and medical equipment.

Following construction of a number of prototypes, the type entered production initially as the Wilga 3A club aircraft and the Wilga 3S air ambulance. In 1967 the design was revised to give better cabin accommodation and with improved landing gear, production beginning in 1968 of the Wilga 35 which, powered by a 194kW Ivchenko AI-14R engine, had flown for the first time on 28 July 1967, and of the Wilga 32 with a 172kW Continental O-470-K flown on 12 September 1967. This last version was built under licence in Indonesia as the Lipnur Gelatik 32 (rice bird) with a Continental O-470-R engine of similar output. The Wilga 35 first flew on 28 July 1967.

The later versions have automatic wing leading-edge slats, an all moving tailplane and a detachable under-fuselage cargo container.




The Wilga's design incorporates an air-powered starting system for one. It looks complex, but it has one advantage in that batteries are almost worthless in extreme cold. The landing gear incorporates a short trailing beam at the end of each main gear strut so that its wheels recoil up and rearward, enhancing its ability to handle rough, off-airport landings. Engine cooling is designed to cope with wide air-temperature extremes, long climbs and rapid descents. The cowl shutters, manually operated by a knob in the cockpit open fully to cool the 620-cubic-inch radial on a climb, then close tightly so the airplane can perform its patented 4,000fpm descents without warping the cylinder heads. The airplane is not only adapted very nicely to hauling sailplanes aloft but also to winter operations without fancy cold-weather kits. The engine will run on anything from 70-octane fuel up. A gear-driven supercharger provides a constant boost of about three inches, and it has a two-blade constant-speed prop.

The wing is strut-less, fully cantilevered; the ailerons droop with full flaps for landing, and there's a fixed, full-span leading-edge slot. The tail-cone carries its structural members outside the skin, giving the impression of widely spaced corrugations; Four low bucket seats occupy the cabin, with an aft cargo compartment under glass. It has dual flight controls except for trim, and both rudder pedals carry toe brakes. The throttle and prop controls are designed to be operated with one hand; their rates are nicely matched so that for a go-around, you grab both handles and push.

The Wilga demonstrates excellent STOL performance, accelerating crisply and lifting off at a radical climb angle. At sea level, the airplane is said to produce a climb of 1,240 feet per minute at its gross weight of 2,711 pounds, which is lighter than a Cessna 180 but with more horsepower to heft it. This airplane's empty weight is 1,874 pounds, and it carries 252 pounds of fuel; its payload, after allowing for oil and incidentals, is probably around 550 pounds. The Wilga is slow, producing only 104 knots at maximum cruise on about 15 gallons per hour.


Wilga 35


Developments of the Wilga 35 have included the Wilga 35A intended for aeroclub use; the Wilga 35H floatplane fitted with Airtech (Canada) LAP-3000 floats; the multi-purpose Wilga 35M fitted with a 260kW M-14P radial engine, flown in prototype form in 1990; the Wilga 35P tourer or air-taxi version; and the Wilga 35R agricultural variant. A version generally similar to the Wilga 35, but meeting US FAR Part 23 requirements, is designated the Wilga 80. The first of these flew on 30 May 1979, and is available in three versions, the 80A, for aeroclub use, the 80H floatplane, and as the 80R for agricultural use. A more radical redesign, originally identified as the Wilga 88, has become the P.Z.L. 105 Flamingo. The Wilga 35 and 80 remain in production in 1993, by which time P.Z.L. had sold around 900 variants to countries around the world.

Certification of the PZL-104 Wilga 35A is under European Aviation Safety Agency EASA A.061.

Some 800 PZL 104 have been manufactured, but was no longer in production in 1991.

Wilga 1
Wilga 2
Redesigned prototype
Wilga 2P
Seats: 4
Wilga 2R
Agricultural version
Wilga C
Export version prototype
Wilga 3P
Initial production
Seats: 4
Wilga CP / Gelatik
As 3P, with engine change
Wilga 3A
Parachuting, glider towing
Wilga CA
As 3A, with engine change
Wilga 3C
As CP, new tailplane, tailwheel and forward inclined gear legs
Wilga 3D
Dual control version of 3P
Wilga CD
As 3D with engine change
Wilga 3R
Ag version of 3P
Wilga CR
As 3R with engine change
Wilga 3S
Ambulance version of 3P
Wilga CS
As 3s with engine change
Wilga 32 / Gelatik 32
1967 improved version
Wilga 32A
Aeroclub version
Wilga 32P
Passenger version
Wilga 32S
Ambulance version
Wilga 35
As 32
Engine: Ivchenko AL-14R, 260 hp
Wingspan: 36 ft 5 in / 11.13 m
Length: 25 ft 6.75 in / 8.10 m
Empty weight equip: 1874 lb / 850 kg
MTOW: 2755 lb / 1250 kg
Max cruise: 104 kt / 120 mph / 193 kph
ROC SL: 1245 fpm / 380 m/min
Service ceiling: 15,025 ft / 4580 m
Range max fuel, 30min res: 366 nm / 422 mi / 680 km
Seats: 4
Glider tow weight: 1433 lb / 650 kg
Multi-glider max combined tow weight: 2480 lb // 1125 kg
Cabin length: 7 ft 2.5 in / 2.20 m
Cabin width: 3 ft 10 in / 1.20 m
Cabin height: 4 ft 11 in / 1.50 m
Wilga 35
Engine: 260 hp PZL‑built Ivchenko IA‑14RA radial
Prop: 8 ft 8 in (2,65 m) dia two‑blade wood
Wing span: 36 ft 4.75 in (11.14 m)
Length: 26 ft 6.75 in (8.10m)
Wing area: 166.8 sq.ft. (15.50 sq.m)
Gross weight: 2,711 lb (1,230 kg)
Max cruising speed: 120 mph (193 km/h)
Max range: 410 miles (660 km)
Seats: 4
Wilga 35A
Engine: 1 x Ivchenko AI-14RA radial, 194kW / 256 hp
Max take-off weight: 1300 kg / 2866 lb
Loaded weight: 900 kg / 1984 lb
Weight empty: 1830.2 lb / 830.0 kg
Wingspan: 11.12 m / 37 ft 6 in
Length: 8.1 m / 27 ft 7 in
Height: 2.96 m / 10 ft 9 in
Wing area: 15.5 sq.m / 166.84 sq ft
Max. speed: 195 km/h / 121 mph
Cruising speed: 104 kts / 193 km/h
Ceiling: 4040 m / 13250 ft
Range: 670 km / 416 miles
Crew: 1
Payload: 3 Pax
Wilga 35P
Wilga 35S
Wilga 40
1969 experimental
Automatic leading-edge slats, all-moving tailplane,
detachable cargo or fuel pack
Wilga 43
Experimental, similar to 40 with engine change
Wilga 80
Engine: AI-14R, 260 hp
First flew 30 May 1979
Seats: 4
Payload: 400 kg
PZL-104 MA WILGA 2000
Base price: $211,595
Horsepower on takeoff: 300
TBO: 2000 hr
Fuel type: 100LL
Propeller type: 3-blade Hartzell
Landing gear type: Tailwheel/Fixed
Max ramp weight: 3306 lb
Gross weight: 3306 lb
Empty weight, std: 1980 lb
Useful load, std: 1326 lb
Useful fuel, std: 100 USG
Payload, full std. fuel: 726 USG
Oil capacity: 12 qt
Wingspan: 37 ft
Overall length: 28 ft. 4 in
Height: 8 ft. 6 in
Wing area: 167 sq. ft
Seating capacity: 4
Cabin doors: 2
Cabin width: 3 ft. 7 in
Cabin height: 3 ft. 10 in
Baggage capacity: 66 lbs
Cruise speed 75% power: 114 kt
Max range 75% power: 1000 nm
Fuel consumption 75% power: 14.4 USG
Vs: 60 kt
Vso: 50 kt
Best rate of climb, SL: 925 fpm
Service ceiling: 11,500 ft
Takeoff ground roll: 676 ft
Takeoff over 50-ft obstacle: 1145 ft
Landing ground roll: 282 ft
Landing over 50-ft. obstacle: 764 ft

PZL 104 Wilga


Wilga 35






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