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"АС-5К" - the single glider-paritel equipped with withdrawable and letting out in flight screw-engineinstal lation, providing independent launch, and as if necessary flight continuation in a motor mode in the absence of ascending streams. A fuselage of type "monocook" and as all steering aerodynamic surfaces are made of fiber glass fabric, polyfoam and epoxide pitches. The cabin has the raised safety factor, is equipped regulated, in conformity with growth of the pilot, pedals and a moved back of sitting. The glider wing is executed from the facilitated multilayered composite, on modern technology in precision matrixes with use of curing in vacuum. The wing has scope of 12,6 m and is executed from 2 demountable parts (the left and right consoles) which can be removed for transportation or storage. On the wing ends winglets are located. On the top part of a wing air brakes (inceptors) the sliding design, executed under the scheme "Schempp-Hirth" are placed. The Control system of flight consists of usual management on three axes and managements interceptors, made for management of a trajectory and speed. The wing is equipped by flaps. An elevator, elerons and inceptors cope with the help of metal pipes. Drafts of management by elerons, intercepters and flaps will be automatically connected in an installation time of wings. A metal cable is used for management of a direction wheel. Chassis are equipped with pnevmo-gidroammortizators. The glider "АС-5К" is designed according to the norms which are meeting the requirements of standard JAR-22.
At flight with the engine the screw is coming from a fuselage, but thus the engine remains inside a fuselage. It is the basic difference from glider АС-5М. 


Aircraft performance AC-5k

Wing area

7.7 sc.m.

82.9 sc.f

Wing aspect ratio


Tare weight

175 kg

386 lbs

Maximum flight weight 

300 kg

661 lbs

Maximum disposable load

115 kg

254 lbs

Range operating overload


Wing loading with flight weight 300 kg 

40 kg/sc.m.

8.1 lbs/sc.f.

Climb of rate

5.5 m/sec

1083 f/m


Main dimensions


12.6 m

41 f

Length of a plane

5.3 m

17.2 f

Height of a plane

1.3 m

4.3 f


Speed measures in a gliding flight

Flight weight



300 kg

Stall speed

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- [knots]






Minimum descent altitude

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- [f/min]

at a speed of

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Maximum speed of aerodynamic quality

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- [miles/h]

- [knots]

Sink rate

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Declining in speed 130 км/ч

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Restrictions and the basic modes of flight

The maximum aerodynamic quality Кmax (relative range of planning L/H) and value of speeds of the basic modes of flight:



Max. additional speed (Vne)

Max. add. maneuver speed (Va)

220 km/hour (137 miles/hours, 119 knots)

160 km/hour (99 miles/hours, 86 knots)

Corkscrew and figures of difficult pilotage

Deliberate performance of a corkscrew, flights on performance of figures of difficult pilotage are forbidden until the special permission of the Manufacturer

Speed of prelanding planning under normal weather conditions, not less   

100 km/hour (60 miles/hours, 55 knots)


The trapezoid wing of the big lengthening (20,6) has laminar profile FX60-157 with high value of the maximum carrying power. Specific loading on a wing is in limits from 33 kg / sq. m to 39 kg / sq. m depending on weight of useful loading. The glider possesses properties: time of a rerun for spirals–45 degrees in 45 degrees makes of a list no more than 3,5 seconds. The sinuosity of a surface of a wing along a profile makes 0,1 mm (under the American standard) that corresponds to the higher range of quality of a surface under the American standard. Wing consoles it is powerful 38 kg incorporate in the center one adjusting finger having on the end the eccentric for tightening of consoles at joining. Automatic connection of control system by elerons and air brakes is realized thanks to system of cross-section drafts with funneled edge lines, incorporating to spherical tips of onboard swigs.


Motor-glider AC-5К is equipped by a withdrawable basic wheel of chamber type. Shock-absorbers pneumo-hydraulic. A cylinder of a wheel in diameter of 360 mm on an external contour of a tire cover in a combination with ammortizators reliably work on absorption of shock loadings; a tail wheel in diameter of 220 mm. In a design of the basic wheel ball bearings, and as the brake of "drum" type put in action by means of a hydraulic actuator are built in. The brake copes the lever of bicycle type established on the handle of management.


The spacious cabin of a glider allows to take place conveniently in it even to broad-shouldered pilots growth 180 - 190 sm, thus remain enough empty seat in the space of a head and high knees of legs;the pilot cabin is equipped by pedals of a wheel of a direction regulated on length and a back of sitting moved largely. The lantern of a cabin consisting of 2 parts, gives to the pilot the full review outside spaces within corners not less than 300 degrees: "at the left-upwards-to the right". The lantern Windshield is fixed, and its central part can open and lean back to the right thanking to a "ball-type"suspension bracket. Emergency dump of a lantern can be executed by moving of two red handles conveniently located on both boards of the bottom contours of a lantern. The compact control panel has enough free space for placing of the standard complete set of pilot-navigating devices, plus possibility of a custom-made configuration, including an additional variometer or other devices. The standard 4 dot fastened system is applied. VHF aerial is placed in keel.


Firm — the manufacturer: Simonini Racing S.r.l.
Mark of the engine: Simonini Victor 1
The engine 2 tacts, one-cylinder, air cooling the carburetor. For installation on a motor-glider the engine is modified: the exhaust system and the muffler is changed.
One of the basic parts of impellent installation is a wedge-rope reducer serving for decreasing of speed of rotation of the air screw. The reduction factor makes size 1:270. 
The engine is started by an electrostarter.
The electrostarter engine eats from a source of a direct current pressure 12В.
Devices of control of impellent installation: the electronic tachometer and the thermoelectric indicator are established directly on instrument to a board in a cabin of the pilot.
The fuel system is placed in a special compartment, in a forward part of an impellent compartment and consists of a fuel tank, the fuel crane, the pipelines providing giving of fuel to the carburetor, the drain pipeline and a drainage tube.
Fuel structure: gasoline of mark АИ 95 and synthetic oil for 2-h-taktnyh engines, 3 volume % of oil for gasoline without lead.
Engine key parameters:
Capacity of 32,3 kw/44 h.p. (DIN)
Number of rpm of the engine at макс. Capacities of 6200 rpm
Fuel consumption on turns 5400 — 5 l/hour.


Wooden 2 blades screw of the fixed step.