Aviamilano Scricciolo

The Aviamilano P.19 Scricciolo (Italian: "Wren") was a light civil trainer aircraft built in Italy in the 1960s.

P.19 Scricciolo
Aviamilano P.19 Scricciolo at Milan's Bresso general aviation airfield in 1965
Role Trainer
Manufacturer Aviamilano
Designer Ermenegildo Preti
First flight 13 December 1959
Primary user Aero Club d'Italia
Number built 50 + 1 prototype

Design and development

The Scicciolo was designed at the Centro Volo a Vela del Politecnico di Milano to compete in a competition arranged by the Aero Club d'Italia for a light civil trainer. The aircraft was evaluated by the Milan Aero Club. The CVV P.19 emerged victorious and two batches of twenty-five were produced at the Aviomilano factory.

The Scricciolo was a low-wing monoplane with tailwheel undercarriage (although some were fitted with tricycle gear and designated P.19Tr). The pilot and instructor sat side by side under a large bubble canopy. The fuselage was of fabric-covered steel tube construction while the wings and tail surfaces were made of wood with plywood covering.[1]

After 1964, a few examples were fitted with 112 kW (150 hp) Lycoming O-320 engines for use as glider tugs and designated P.19R

Variants
CVV P.19 Scricciolo
The prototype designed and built at the Centro Volo a Vela del Politecnico di Milano for the Aero Club d'Italia competition for a new light civil trainer.
P.19 Scricciolo
The main production version of the Scricciolo
P.19Tr Scricciolo
Production aircraft fitted with tricycle undercarriage.
P.19R
(R - Rimorchio - tug) Rebuild with 150 hp (112 kW) Lycoming O-320 for use as a glider tug.

Specifications (P.19)

Data from Jane's All The World's Aircraft 1965–66[2]

General characteristics

  • Crew: 2
  • Length: 7.03 m (23 ft 1 in)
  • Wingspan: 10.24 m (33 ft 7 in)
  • Height: 2.02 m (6 ft 8 in)
  • Wing area: 14.0 m2 (151 sq ft)
  • Aspect ratio: 7.5:1
  • Empty weight: 525 kg (1,157 lb)
  • Max takeoff weight: 725 kg (1,598 lb)
  • Fuel capacity: 95 L (25 US gal; 21 imp gal)
  • Powerplant: 1 × Continental O-200-A air-cooled flat-four engine, 75 kW (100 hp)
  • Propellers: 2-bladed Sala fixed-pitch propeller, 1.90 m (6 ft 3 in) diameter

Performance

  • Maximum speed: 210 km/h (130 mph, 110 kn) at sea level
  • Cruise speed: 170 km/h (110 mph, 92 kn) (econ. cruise, 60% power)
  • Stall speed: 70 km/h (43 mph, 38 kn) (flaps down)
  • Endurance: 5 hr (at 60% power)
  • Service ceiling: 3,100 m (10,200 ft)
  • Rate of climb: 2.8 m/s (550 ft/min)
  • Takeoff distance to 15 m (50 ft): 350 m (1,148 ft)
  • Landing distance from 15 m (50 ft): 300 m (984 ft)

References
  1. Green & Pollinger, 1965, p.84
  2. Taylor 1965, pp. 90–91.
  • Green & Pollinger, William & Gerald (1965). The Aircraft of the World. London: McDonald & Co (Publishers) Ltd. p. 84.
  • Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing. p. 407.
  • Taylor, John W. R. (1965). Jane's All The World's Aircraft 1965–66. London: Sampson Low, Marston & Company.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 88.
  • World Aircraft Information Files. London: Bright Star Publishing. pp. File 889 Sheet 88.


See also

Aircraft of comparable role, configuration, and era

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