YAK-52W ( Western Version of Yak-52 )

520000-00W

These SPECIFICATIONS were issued following a marketing study , as well as the specific requirements of YAK UK Ltd, England , Termikas, Lithuania and from Gessco in the USA.

The YAK-52W aircraft is designed for civil aviation use and in the standard design is intended for the following missions:

• flight instruction
• aerobatic training and competition
• pleasure flying

Optional equipment may be fitted on the aircraft according to customer specifications.

5.1. The characteristics and performance of the YAK-52W aircraft are similar to YAK 52 aircraft.

5.2. Dimensions:

• wing surface: 15 mp - 161 sq. ft
• wing span: 9,3 m. - 30 ft. 6 in.
• length: 7,7 m. - 25 3 in. ft.
• height: 2,5m. - 8 ft. 2 in.
• track wheel: 2,7 m. - 8 ft. 7 in.

5.3. Weight ( preliminary to be revised after completion of the prototype aircraft)

5.4. Aircraft performances

• - max. speed: 295 Km./ h. 160 Knots
• - max. ceiling: 4,000 m 13,000 ft.
• - stall speed: 105 Km./h 56 Knots
• - climb rate: 6m/s 1,200 ft/min.
• - take off distance:
• - with 120 l. fuel : 200m. 660 ft.
• - with 240 l. fuel : 300m. 990 ft.
• - with 200 l. fuel : 230m. 755 ft.
• - landing distance: 260 m. 855 ft.
• - max. flight range:
• - with 120 l. fuel : 500 Km. 270 Nm.
• - with 240 l. fuel : 1000 Km. 540 Nm.
• - with 200 l. fuel : 650 Km. 350 Nm.
• - max. g-limit +7g to -5g

5.5. The above data and performance specifications are based on standard atmospheric conditions.

5.6. The aircraft design shall include ability to take off and land on grass fields.

5.7. The aircraft design shall allow take off and landing with cross wind component of 11Knots.

5.8. The aircraft will have an angle of attack ( stall ) waning system, a Vne warning system, and a gear up when landing warning system.

5.9. The aircraft is expected to be easy to manoeuvre, without unexpected departure from normal flight while close to the critical flight conditions.

6.1. The aircraft shall be fitted with a 360 Hp. M14-P piston engine and a Mulbauer MTV-9 three blade propeller. Optionally it may be equipped with a Hoffman or Whirlwind three blade propeller.

6.2. The following are the significant modifications as compared to the standard existing YAK 52.

6.2.1    THE FUSELAGE

• The aircraft shall be fitted with a externally accessible baggage compartment and battery compartment located on the left side behind the rear cockpit;
• The aircraft shall be fitted with a permanent mounted and retractable ladder for the pilots and passenger convenience to enter the cockpit.

6.2.2. THE WING

• In order to increase the fuel capacity, the wing shall be fitted with an additional integral fuel tank between ribs no 5-9 on both left and right wings.
• In the right and left leading edge, between ribs 6-7, the wing shall be fitted with recessed landing and taxi lights for night operations.
• The wing shall be strengthened in the tip area, for optional wing-tip tanks.
• Tip Rib no. 15 shall be fitted with strobe and navigational lights.
• Tubing shall be added for fuel supply system and for the electric installation.

6.2.3. CONTROL SURFACES

- The fabric skins of aileron, elevator and rudder shall be replaced with aluminium skins and the attach brackets and balance weights shall be modified for the different skins.

6.2.4. THE LANDING GEAR

6.2.5. CONTROLS

- The aircraft shall be fitted with rudder steering bars that allow a wider adjustment range for pilot comfort.

- The aileron and elevator centring springs will be eliminated.

6.2.6. THE PNEUMATIC SYSTEM

- The starting system of the engine shall remain as currently on the Yak-52.

- The landing gear retract and flap operating system will be retained and operable from both cockpits.

- The pneumatic system water drain shall be operable from the cockpit.

6.2.7. THE HYDRAULIC SYSTEM

- The hydraulic brake system shall be added, and shall include toe brakes for both cockpits.

6.2.8. THE PVD SYSTEM ( Fault simulation system )

- The system for instructors simulation of failures or the front cockpit shall be eliminated.

6.2.9. THE POWER UNIT

- Following the aircraft fitting with additional tanks, the fuel system shall be supplemented with the required lines, valves and the fuel pump to transfer fuel from the auxiliary tanks into the main tanks.

- The engine shall be modified with a drain system to avoid the hydraulic lock. ( clean Kit )

- The oil dilution system will be eliminated.

- The aircraft shall be fitted with a three blade propeller and the governor shall be modified to allow the higher pressures required.

- The cowl flaps and the oil cooler door shall be controlled from both cockpits.

- The fuel lines in the engine compartment shall have fire sleeves.

- The start switch shall be located in the front cockpit only. Both cockpits shall be equipped with magneto switches.

6.2.10. THE SEATS

- Both cockpits shall be equipped with Hooker Harness seat belt systems.

6.3.1. Both cockpits shall be equipped as follows:

1. Engine instruments
2. light signals
3. basic flight instruments
4. All markings and tags shall be in English and, optionally, in another languages.

6.3.2. The minimum equipment for flight and navigation instruments shall be in compliance with the requirements of FAR 23.1303:

1. speed-indicator
2. altimeter
3. magnetic compass

1. g- factor indicator
2. turn and slide indicator
3. accelerometer
4. gyro- horizon
5. gyro- compass or compass system

6.3.4. The standard YAK-52W will have the following radio equipment. At the customer request other equipment may be substituted.

1. ICOM IC-A200 Com radio
2. Garmin GTX Transponder with AmeriKing Altitude Encoder
3. NAT intercom AA80-20 with both VOX and PTT activation

1. Portable and storable hand tow bar
2. Canopy Cover
3. Tool roll with special tools for the engine