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- Flying lessons for both military and civilian students;
- Participation in aviation sports competitions.
 
2.3 ENGINE TYPE AND QUANTITY
2.3.1. The helicopter uses one piston liquid-cooled engine produced by the Japanese Subaru, EJ-25 model, which is installed behind the cockpit.
 
2.4. DEVELOPER AND MODEL
2.4.1 The developer is Аэрокоптер Ltd., Ukraine.
 Model: AK1-3 helicopter.
 
2.5. CREW PERSONNEL AND HELICOPTER’S TRANSPORTING CAPABILITIES 
2.5.1. Depending on its mission, the helicopter crew may include one or two persons: - A pilot;
- An observer (operator, trainee).

 

2.5.2. The helicopter is capable of transporting one passenger.
 
2.6       OUTER COATING Coating and proofing of the helicopter’s outer surfaces, engine, and components are carried out according to the existing norms and guarantee successful exploitation under different climatic conditions.
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 

 

 
 
Figure 2.1. General View of the Helicopter
 
 
 
 
MAIN FEATURES
 
3.1. ESTIMATED WEIGHTS
 3.1.1. Maximum takeoff weight      650 kg
3.1.2.  Maximum weight of loaded helicopter without fuel   590 kg
3.1.3. Maximum payload weight (including pilot and fuel)  270 kg
3.1.5. Empty helicopter weight       380 kg
3.1.6. Helicopter equipment weight, including:
 - crew parachutes (2)       20 kg
- crew (2 persons)       160 kg
- protective helmets (2)      2.3 kg
- engine oil        3 kg
- unusable fuel        0,5 kg
 
З.2.  REGULATION CURVES
Table 3.1
 REGULATING DATA 
#
 Item 
 Deflecting direction
 Deflection
 Note
 
degrees
 mm
 
1.
 Slope angle of rotor axis
 Forward
Left
Right
 0
0
0
 --
 --
 
2.
 Angle of rotor pitch
 min
 
max
 0
 
14°
 --
 Crosshead traverse 24±1mm
 
3.
 Slope angles of wobble plate and control rod traverses that correspond to them
 Forward
Backward
Right
Left
 5°±20′
4°±20′
4°±20′
4°±20′
 130
110
110
110
 --
 
4.
 Angle of incidence of anti-torque rotor 
a) with right pedal stopped
b) with both pedals in neutral
c) with left pedal stopped
 --
 
 
+20°±20′
 
+5°±20′
-10°±20′
 --
 --
 
5.
 Deflection of pedals from neutral
 --
 --
 
60±2
 --
 
6.
 Control rod labor not more than 3 kg.
 
 --
 --
 --
 Labor measurements are taken in the middle part of rods and footboards with TNV
 
7.
 Foot pedals labor with anti-torque rotor attached not more than 7 kg.
  --
 --
 --
 
8.
 Labor for the Lead/Gas shift, with normal shifting from one extreme position to the other taking no less than 20 seconds, not more than 5 kg.
 --
 --
 --
 > +15°.
 

 
 
 
3.3. CENTERING CHARACTERISTICS
 3.3.1 Centering capacity during takeoff, flight, and landing:
  - noseheaviness,  before the rotor axis   38 mm
- bowheaviness, behind the rotor axis   59 mm
3.3.2. Longitudinal centering for an empty helicopter   173mm
 3.4. FLIGHT CHARACTERISTICS
 3.4.1. Maximum ground airspeed       186 km/h
3.4.2. Ground cruising airspeed      160 km/h
　
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