TYPE: Aerobatic two-seat sportplane.

PROGRAMME: Designed by former Sukhoi personnel, also responsible for Su-26, Su-29 and Su-31 aerobatic types. Batch of 50 I-3s begun by Tushinsky Mashinostroitelnyi Zavod AO (Tushino Machine-Building Plant Ltd), Moscow, in early 1990s to order of Chechnya, but embargoed by Russian government. Five were completed as Technoavia SP-91s, but definitive SP-95 version failed to materialise; however, four SP-91s exported to USA, where one incorrectly registered as an SP-95. Fifth (RA-44496) retained as demonstrator, but subsequently to Skydance Aero Team in Germany. Sixth, designated SP-91L, built in 2000 and also based in Germany with Yak Team (as RA-44522).
Prototype I-3 exhibited at Moscow Air Show in 1993. Exports to USA began in 1996, some being registered as E-3s. Production transferred from Tushino to Repikhovo, with final assembly at Myachkovo; now at Lukhovitsy.

CURRENT VERSIONS: SP-91/95: Built by TMZ for Technoavia as two-seaters.
I-3: Built by Radonezh for Interavia.
I-3M: Built by RSK ‘MiG’ for Interavia. Increased fuel capacity; 50 kg (110 lb) decrease in empty weight; flush rivets; revised instrument panel with improved (Western) navaids; lightened canopy (including green tinted transparency); lightweight electrical system; wing/fuselage fairings; Western (Cleveland) wheels and (Parker) brakes; MT propeller; option of smoke system, strobe lights and 294 kW (394 hp) M-14PF engine.
As described.
Manufacture of I-3M began at Lukhovitsy in 2004, deliveries being due from March 2005, although subsequently delayed. In July 2006, announced that first I-3M due for delivery by end of 2006.

CUSTOMERS: Total of 23 built at Radonezh plant; last in 2004 for South African customer. I-3M had “15 or 16” orders by mid-2006.

COSTS: USD150,000 to 180,000 (2006).

DESIGN FEATURES: Conventional low-wing monoplane, capable of unlimited aerobatics; roll rate 345 °/s; tapered multispar wings of symmetrical section, without dihedral or anhedral; unswept tail surfaces with pointed rudder tip; clear-view blister canopy over one or two seats. At least two modified by removal of rudder tip. Convertible from two-seater to single-seater in 1 hour by removal of front cabin bay with control panel, installation of top fuselage panel and changing of canopy.
Wing incidence 0°; dihedral 0° at chord line.

FLYING CONTROLS: Manually actuated conventional horn-balanced elevators and horn-balanced rudder; 80 per cent span flaperons. Ground-adjustable tab on rudder; two suspended balance tabs on each flaperon. Control surface deflections: ailerons ±25°; elevators ±25°; rudder ±25°.

STRUCTURE: All-metal; semi-monocoque fuselage; fluted skin on fin, tailplane and all control surfaces.

LANDING GEAR: Tailwheel type, fixed; cantilever mainwheel legs. Mainwheel tyres size 400x150; tailwheel tyre size 200x80. Cleveland wheels and Parker brakes.

POWER PLANT: One 265 kW (355 hp) VOKBM M-14P nine-cylinder air-cooled radial engine driving an MT-Propeller MTV-9 three-blade, variable-pitch propeller. Fuel tank in each wingroot, combined capacity 120 litres (31.7 US gallons; 26.4 Imp gallons), of which 110 litres (29.0 US gallons; 24.2 Imp gallons) usable. Oil capacity 20 litres (5.3 US gallons; 4.4 Imp gallons).

ACCOMMODATION: One or two seats in tandem. Seats adapted for Western style flat parachutes and with Hooker harness.

SYSTEMS: Pneumatic system pressure 49 bar (711 lb/sq in).


  • Wing span: 8.10 m (26 ft 7 in)
  • Wing aspect ratio: 5.7
  • Length overall: 6.72 m (22 ft 0½ in)
  • Tailplane span: 2.72 m (9 ft 2¼ in)
  • Propeller diameter: 2.40 m (7 ft 10½ in)


  • Wings, gross: 11.54 m² (124.2 sq ft)
  • Ailerons (total): 1.76 m² (18.94 sq ft)
  • Fin: 0.425 m² (4.57 sq ft)
  • Rudder, incl tab: 0.915 m² (9.84 sq ft)
  • Tailplane: 1.05 m² (11.30 sq ft)
  • Elevators (total, incl tab): 1.25 m² (13.45 sq ft)


  • Weight empty: single-seat: 748 kg (1,648 lb)
    • two-seat: 767 kg (1,692 lb)
  • Max T-O weight: ferry: 1,200 kg (2,645 lb)
    • solo aerobatic: 1,057 kg (2,330 lb)
  • Max wing loading, aerobatic: 92.1 kg/m² (18.86 lb/sq ft)
  • Max power loading, aerobatic: 4.02 kg/kW (6.60 lb/hp)


  • Never-exceed speed (VNE): 250 kt (463 km/h; 288 mph)
  • Max level speed: 175 kt (324 km/h; 201 mph)
  • Manoeuvring speed: 215 kt (398 km/h; 247 mph)
  • Stalling speed, flaps up, power on: 33 kt (60 km/h; 38 mph)
  • Service ceiling: 5,000 m (16,400 ft)
  • T-O run: paved runway: 200 m (660 ft)
    • unpaved runway: 262 m (860 ft)
  • Landing run: paved runway: 452 m (1,485 ft)
    • unpaved runway: 514 m (1,685 ft)
  • g limits: single seat: +12/-10
    • two seats: +10/-8