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Commercial offer for delivery of airplanes MAI-407
Commercial offer for delivery of airplanes MAI-407 (PDF)...

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MAI-407 > Our Products > MAI-407
The four-seater plane

MAI-407 multi-purpose four-seat twin engine airplane has been designed according to AP—23 Aviation Rule requirements, analog of European CS—23 and American FAR—23.

In addition, while designing the following features were put to airplane concept:

  • spacious cabin allowing to house a crew and passengers dressed in winter clothes but herewith all the rest is achievement of maximum aerodynamic efficiency: a cantilever wing, retractable landing gear, etc.;
  • boarding and deboarding comfort: four car-type doors, the cabin floor height demanding neither step-ladders nor footboard;
  • ability to operate from unprepared runway as well as to have ski or float-type landing gear mounted;
  • proven, including testing in Russia, engine with a qualified dealer accompaniment;
  • efficient ventilation and heating systems.

MAI-407 airplane application may be promising in the following fields:

  • air transportation;
  • initial training and professional selection of pilot personnel;
  • oil and gas pipeline, power lines, forest tract, water reservoirs, etc. air patrol;
  • aerial photographing, instrument monitoring;
  • air tourism.

An important feature is an ability of a multi-purpose single-type airplane employment for all the above tasks. This is provided by a reasonable combination of conflicting factors:

  • maximum cruise and minimum landing speeds;
  • easy flying and sufficient maneuverability;
  • long range and ability of landing on unprepared runways.

Besides the afore-said, there are other distinguishing features:

  • operation by cheap and available (e.g., automotive) fuels and lubricants;
  • fuel consumption compared with that of a car;
  • manufacturability and series-production worthiness;
  • competitive cost.

The standard crew and passenger seating is side-by-side in two rows. The cabin height is 1220 mm, crew and passenger seating area width is 1275 mm, which provides comfortable conditions of housing the people dressed in winter clothes. Seat pitch is 1060 mm. This allows to have the backs of the front seat row reclined 25˚ with no damage for those passengers who take seats in the back row. The backs of an aft row can also recline 25˚ that allows long flight duration tolerance with no painful tiredness.

The cabin has ventilation and heating systems efficient within the whole range of operating conditions (-25...+40˚C). The luggage section is located behind the backs of the 2nd row seats.

A vertical tail includes a fin integrated with a fuselage, and a rudder.

A horizontal tail comprises a cantilever stabilizer and an elevator. Both stabilizer and an elevator are made one-piece tailplane by span, which lowers the weight and improves efficiency.

Airplane have a tricycle retractable landing gear with a nose wheel. Large diameter wheels (445 mm) are applied. Landing gear have gas-liquid shock-absorbers. In nose leg compressing the wheel travels into an open well for its retraction that allowed to decrease a landing height of the cabin floor from the ground and herewith employ a wheel of a large diameter. The airplane has an ability of a float-type and ski landing gear mounted.

A power plant includes two ROTAX 912S piston engines closed in engine nacelles and located on the wing symmetrically to the fuselage. The main fuel tanks are in the center-wing section. Additional (ferry) fuel tanks are possible to install in the outer wing plane.

The airplane is of a double control. A pilot's seat is on the left.

The control consists of mini-handles and pedal posts.

For airplane control convenience the pilots' seats have an adjustment ability.

The airplane is fitted with a full set of up-to-date navigation equipment to provide for instrument flight rule requirements.


Author of design: N. Goryunov, V. Demin, V. Luchak, S. Svinin

Head of project: V. Demin.

Senior Design Engineer: V. Luchak.

  • The beginning of designing: 2008
  • The end of designimg: 2010

The prospective supplier of the plane — REMZ-Avia company.

Total wing area, sq. m2 14.3
Wing span, m 11.4
Wing aspect ratio 9.1
Wing profile GA(W)-1
Fuselage height, m 1.48
Fuselage width, m 1.28
Fuselage length, m 7.75
Parking height, m 2.73
Landing gear base, m 2.12
Wheel track, m 1.90
Wheels, mm Ø445x160
Engine number, pcs 2
Engine type Rotax 912S, 100 h. p.
Max takeoff weight, kg 1250
Useful load, kg 325
Passenger capacity, man 3
Crew, man 1
Maximum speed of level flight, km/h 290
Maximum cruising speed, km/h 270
Maximum rate-of-climb, m/s 6
Maximum cruising altitude, m up to 3000
Maximum payload range, km 1500
Take-off run, m 150
Take-off distance, m 400
Landing run, m 180
Landing distance, m 400
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