The SM.1019 light STOL aircraft is suitable for observation, light ground attack or utility duties. Its design was started in January 1969, and construction of a prototype began two months later. This aircraft (I-STOL) flew for the first time on 24 May 1969, with an Allison 250-B15C engine, and was granted Normal and Utility category certification by the RAI on 25 October 1969.
A second prototype (I-SJAR), which flew for the first time on 18 February 1971, was designated SM.1019A. It had an improved fuel system, two doors and two instrument panels, and received RAI civil certification in the Normal and Utility categories.
Production began in 1974 of an initial series of 80 SM.1019EIs for the Aviazione Leggera dell'Esercito (ALE, or Italian Army Light Aviation), and all of these had been delivered by the Summer of 1978.

TYPE: Two-seat STOL light aircraft.

WINGS: High-wing monoplane, braced by single strut on each side. Wing section NACA 2412. Dihedral 2° 8'. Incidence 1° 30'. Washout 3°. Conventional all-metal structure, with detachable tapered outer panels. Metal Frise-type ailerons and electrically-actuated trailing-edge slotted flaps. Trim tab in starboard aileron. Tiedown point at each wingtip.

FUSELAGE: Conventional all-metal stressed-skin structure.

TAIL UNIT: Conventional cantilever all-metal structure, with horizontal surfaces mounted on top of fuselage. Dorsal fin. Fixed-incidence tailplane. Elevators and rudder horn-balanced. Manually-operated mechanically-actuated trim tab in starboard elevator; servo tab in port elevator. Ground-adjustable trim tab on rudder.

LANDING GEAR: Non-retractable tailwheel type, with cantilever leaf-type spring steel main-wheel legs. Goodyear 511960 main wheels, with low-pressure tyres, size 7.00-6, pressure 2.07 bars (30 lb/sq in); Scott 3200A tailwheel, with size 8-3.00 tyre, pressure 2.41 bars (35 lb/sq in). Goodyear independent hydraulic single-disc brakes on main wheels, controllable from either seat. Parking brake. Combined wheel/ski gear, with hydraulic retraction and extension of skis, is optional.

POWER PLANT: One 298 kW (400 shp) Allison 250-B17 turboprop engine, driving a Hartzell HC-B3TF-7/T10173-11R three-blade constant-speed reversible-pitch metal propeller. Fuel in two tanks in each wing, each of 80 litres (17.5 Imp gallons) capacity; total capacity 320 litres (70 Imp gallons). Refuelling point for each tank on top of wings. Provision for two 80 litre (17.5 Imp gallon) auxiliary underwing tanks. Oil capacity 8 litres (1.75 Imp gallons).

ACCOMMODATION: Pilot and co-pilot or observer/systems operator seated in tandem in fully-enclosed and extensively-glazed cabin. Two forward-hinged doors on starboard side. Cabin heated, by engine bleed air, and ventilated. Dual controls standard.

SYSTEMS: 28V DC electrical power provided by 30V 150A Lear Siegler P/N230320020 engine-driven starter/generator and 24V 25Ah nickel-cadmium battery. External ground power receptacle. Windscreen defrosting and engine compressor inlet heating standard. Oxygen system optional.

AVIONICS AND EQUIPMENT: Choice of VHF/UHF/HF communication systems. VLF/Omega navigation. ADF; IFF; high-performance intercom and compass system. Provision for specialised avionics (VHF/FM, radar warning, Tacan and microwave landing system) to customer's requirements. Twin taxying and landing lights in port outer wing leading-edge. Anti-collision light on top of rudder.

ARMAMENT AND OPERATIONAL EQUIPMENT (SM.1019EI): Two hardpoints beneath each wing for 2.75 in rocket launchers, gun pods, missiles, bombs, auxiliary fuel tanks or a reconnaissance pod. Electronic, photographic and navigation equipment for use as day or night reconnaissance aircraft.