YAK-52TD Data

YAK 52TD the upgrade and major modification of the YAK 52 offering a cheaper option to that of the "Aerostar" YAK-52TW (Romanian YAK 52TW).

  1. PRODUCT NAME:

    YAK-52TD (Tail Dragger Version of Yak-52 )

    Serial number 000000

  2. PRODUCT CODE NO.:

    520000-00TD

  3. DEVELOPMENT BASIS:

    These SPECIFICATIONS were issued following a marketing study, after the launch of the YAK 52TW in the USA it was shown there is great demand for a cheaper version of the YAK 52 tail dragger type of aircraft. Termikas, Lithuania, have undertaken a design study to convert during overhaul or to supply as a "kit" the necessary parts for conversion of the standard YAK 52 to Tail Dragger configuration.

  4. DESTINATION AND FIELD OF APPLICATION:

    The YAK-52TD 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's specifications.

  5. AIRCRAFT CHARACTERISTICS AND PERFORMANCES:

    5.1. The characteristics and performance of the YAK-52TD aircraft are similar to the YAK 52 aircraft, however the 52TD is lighter and has fully inward "Clean" retracting u/c.

    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 at propeller 2.7 m. - 8ft 7 in.

    5.3. Weight:

    • Weight, empty-equipped: 980 Kg.
    • Max. take off weight: with 90 ltrs. 1315 kg., with 180 ltrs.(integral auxiliary wing tanks) 1415 kg.

    NOTE: aerobatic maneuvers prohibited with fuel in auxiliary tanks

    5.4. Aircraft performances:

    • max. speed: 320 Km./ h. 172 Knots (estimated)
    • max. cruising speed 270 km/h (estimated). Might be bigger after test flights
    • max. ceiling: 4,000 m 13,000 ft. (without oxygen)
    • stall speed: 105 Km./h 56 Knots
    • climb rate: 8m/s 1,800 ft/min.
    • take off distance: with 160 lts. fuel : 200m. 660 ft., with 230 lts. fuel : 300m. 990 ft.
    • landing distance: 260 m. 855 ft.
    • max. flight range: with 230lts 5.5hrs @ 210kph = 1100KM
    • 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 has the ability to take off and land on grass fields.

    5.7. The aircraft design allows take off and landing with cross wind component of 10 Knots.

    5.8. The aircraft is easy to manouver, without unexpected departure from normal flight while close to the critical flight conditions (as the YAK 52 is).

  6. REQUIREMENTS REGARDING THE AIRCRAFT CONSTRUCTION:

    6.1. The aircraft is fitted with a 360 or 400 Hp. M14-P piston engine, propeller types B530 TA D35 two blade or a Muellbauer MTV-9 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 same like standard YAK-52.

    6.2.2. THE WINGS:

    • In order to increase the fuel capacity, the wing have been fitted with an additional integral fuel tank both left and right wings (wet wing technology 78 ltr. each ).
    • Tip Rib no. 15 is fitted with strobe and navigational lights (optional).

    6.2.3. CONTROL SURFACES: The fabric skins of aileron, elevator and rudder remain "Ceconite 101" covered.

    6.2.4. THE LANDING GEAR: The wheels of the main landing gear, with pneumatic drum brakes, remain as per YAK 52.

    6.2.5. CONTROLS: The aileron and elevator centering springs have been eliminated.

    6.2.6. THE PNEUMATIC SYSTEM:

    • The starting system of the engine is as currently on the Yak-52.
    • The landing gear retract and flap operating system will be retained and operable from both cockpits.

    6.2.7. THE PVD SYSTEM ( Fault simulation system ):The system for instructors simulation of failures or the front cockpit has been eliminated.

    6.2.8. THE POWER UNIT:

    • The engine has been modified with a drain system to help avoid the hydraulic lock (Oil Drain Kit, optional).
    • The oil dilution system will be retained for use in temperatures.
    • The aircraft have been fitted with a three blade propeller and the governor have been modified to allow the higher pressures required (optional).
    • The front shutters are retained, optionally the SU style of shutter may be fitted.
    • Cowl shutter, oil cooler & exit doors can be controlled from both cockpits.
    • Both cockpits can be equipped with magneto switches.

    6.2.9. THE SEATS: Both cockpits are equipped with Hooker Harness seat belt systems (optional).

    6.3. INSTRUMENTATION, COMMUNICATION AND NAVIGATION EQUIPMENT:

    6.3.1. Both cockpits are equipped as follows:

    1. engine instruments
    2. light signals
    3. basic flight instruments
    4. all markings and tags are in English and, optionally, in another languages.

    6.3.2. The front cockpit has the following flight and navigation instruments (in compliance with the requirements of FAR 23.1303): Gyro Horizon, Altimeter, Rate of Climb, Wet Compass, Clock, Airspeed, Turn coordinator, “G” meter, Air pressure gauge, Fuel Gages, Oil Temperature, Oil Pressure, Fuel Pressure, Carb. Air Temperature, Manifold Pressure, Cylinder Head Temperature, Tachometer.

    6.3.3 The rear cockpit is equipped with the following instruments: Altimeter, Airspeed, Rate of Climb, Wet Compass, Manifold Pressure, Oil Pressure, Oil Temperature, Fuel Pressure, Tachometer, Cylinder Head Temperature.

    6.3.4. The standard YAK-52TD will have the following radio equipment ( at the customer request other equipment may be substituted ):

    1. Baklan 5 radio
    2. SPU 9 PTT intercom

    6.4. ELECTRICAL SYSTEM:

    6.4.1. The basic electric source is a 100 amp 28 volt engine driven generator.

    6.4.2. The battery system will be sealed lead acid (gel) batteries of sufficient capacity to allow 25 minutes of flight with an inoperable generator.

    6.4.3. The electric installation is protected against over voltage variations and short - circuit conditions.

    6.4.4. The electric installation ensures power, control and protection for the following:

    1. Radio
    2. Night Navigation and anti-collision strobe lights at the wing tips
    3. Engine and navigation instruments

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