1. PRODUCT NAME
YAK-52TD
(Tail Dragger Version of Yak-52 )
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.
The YAK-52TD aircraft is designed for
civil aviation use and in the standard design is intended for the following
missions:
o
flight instruction
o
aerobatic training and
competition
o
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:
o
wing surface: 15 mp - 161
sq. ft
o
wing span: 9,3 m. - 30
ft. 6 in.
o
length: 7,7 m. - 25 3 in.
ft.
o
Height at propeller 2.7
meters - 8ft 7"
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
o - max. speed: 320 Km./ h. 172 Knots (estimated)
o - max. cruising speed 270 km/h (estimated). Might be bigger after test flights
o
- max. ceiling: 4,000 m
13,000 ft.
o
- stall speed: 105 Km./h
56 Knots
o
- climb rate: 8m/s 1,800
ft/min.
o
- take off distance:
o
- with 160 lts. fuel :
200m. 660 ft.
o
- with 270lts. fuel :
300m. 990 ft.
o
- landing distance: 260
m. 855 ft.
o
- max. flight range:
o
- with 270lts 5.5hrs @
210kph = 1100KM
o
- 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
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
o Fuselage is the same like standard YAK-52.
6.2.2. THE WING
o
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 )
o
Tip Rib no. 15
is fitted with strobe and navigational lights
6.2.3. CONTROL SURFACES - The fabric skins of aileron, elevator and rudder remain "Ceconite 101" covered.
-
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.
- 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 Gyro Compass
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
Rate of Climb Wet Compass
Manifold Pressure Oil Pressure
Oil Temperature Fuel Pressure
Tachometer Cylinder Head Temperature
1.
Baklan 5 radio
2.
SPU 9 PTT intercom
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
8. TECHNICAL DOCUMENTATION AND GROUND EQUIPMENT
8.1. The following documents will be provided in English:
a) Aircraft, engine and propeller parts and maintenance manuals
b) Aircraft wiring diagrams
c) Pilots operational flight manual and technical description of the
aircraft
8.3. The following Ground Support
equipment:
1.
Canopy and
Pitot covers
2.
Ground air charge adapter
3.
Full set of leather
cushions
For more information please visit contacts page and contact us
