The below is available for historic reasons, we no longer manufacture the kits or convert the aircraft.
YAK 52TD
(Tail Dragger) pictures, the upgraded and modified YAK 52 offering a cheaper option to that of the “Aerostar YAK-52TW” from Romania, the YAK 52TW (aimed at the American market) YAK 52TW pictures of the Aerostar version from Romania who refuse to certify the aircraft in Europe, unfortunately the aviation authorities will not register the aircraft as a result. Pilot magazine report. TheYAK 52TD is approved and flying in Europe. Prices below for the “must have YAK!!”
We are offering 3 options.
1. Modified, fully overhauled a/c with 400hp at 130,000 Euro (standard a/c) or the YAK-52TD special with the following options available, MT prop, Nav/ strobe lights, spinner, P1 front or rear seats as required, extra baggage, rounded wing tips, mode S transponder. Please enquire regarding price.
2. Upgrade of existing flying YAK-52 to TD specification, fly to us and fly away with 3 weeks later at 65,000 Euro
3. Kit of parts with exchange wings for “local” fitting, approx 120 hrs labour at 50,000 Euro primarily for USA market.
If the YAK 52 was being designed today for the general aviation market place this is how it would turn out !! 2 seats, fully aerobatic, long range fuel, baggage carrying ability and fighter pilot appeal all in a tail dragger that’s faster than the “original” 52. On 4th June a “race” was conducted with Nick Barnard in his YAK-50 (www.yakovlevs.com/ display team) and the YAK-52TD, with 2 people on board the TD was faster at all power settings even though it was 280 kgs heavier!! On 8th June a race with Bob Davy in his CJ6 was conducted, again the YAK 52-TD is faster. All prices plus European/ state tax as applicable.
| YAK – 52 TD data sheet. | (data below is the results of actual flight testing) |
| 1. PRODUCT NAME; YAK-52TD (Tail Dragger Version of Yak-52 ) | Prototype serial number 888907 |
| 2. DEVELOPMENT BASIS: |
These SPECIFICATIONS were issued following a marketing study , following 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: |
| o Flight instruction |
| o Aerobatic training and competition |
| o Pleasure flying |
| o Airshow flying |
| o Air combat sorties (ACM) |
Optional equipment may be fitted on the aircraft according to customer specifications. eg smoke systems, 400 hp, MT propeller, rounded wing tips, strobe/ nav lights etc.
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 resulting in a much faster aircraft.
| 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 hub 1.92meters and 3.12meters prop vertical | |
| 5.3. Weight | o – Weight, empty-equipped: 990 Kg. |
| o – Max. take off weight: | |
| o – with 90 lts aerobatic 1315 Kg. | |
| o – with 180 lts. (integral auxiliary wing tanks) 1415 Kg. | |
| o – note: aerobatic maneuvers prohibited with fuel in auxiliary tanks | |
| 5.4. Aircraft performances, 400hp and 2 blade prop | o – 100% full throttle 330 kph 2 persons. |
| o – max. continuas speed @ 82% WOT : 310 Km./ h. | |
| o – suggested max. cruising speed 250 km/h @70% | |
| o – stall speed: 105 Km./h 56 Knots | |
| o – climb rate: 10m/s 1,980 ft/min. | |
| take off distance: | o – with 160 lts. fuel : 150 meters |
| o – with 270lts. fuel : 200 meters | |
| o – landing distance: 260 m. 855 ft. | |
| max. flight range: | o – with 270lts 5:30 hrs @60% 220kph = 1200KM |
| o – max. ceiling: 4,000 m 13,000 ft. (without oxygen) | |
| o – max. g-limit +7g to -5g @1315kgs and +6 to -3g @ 1415 kg’s |
5.5. The above data and performance specifications are based on actual flight tests..
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 maneuver, 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 Mulbauer 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 – The nose wheel has been removed and the redundant space may be used as a smoke tank |
| 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 85 ltr. each ) |
| o – Tip Rib no. 15 is fitted with rounded wing tips and strobe / 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. Tyres made in USA, brake pads made in Germany |
| 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 are retained and operable from both cockpits. |
6.2.7. Depending upon customer specification and requirements it is possible to make P1 the rear cockpit
6.2.8. THE PVD SYSTEM ( Fault simulation system )
– The system for instructors simulation of failures or the front cockpit has been eliminated.
6.2.9. THE POWER UNIT
– The engine has been modified with a drain system to help avoid the hydraulic lock. (optional clean Kit )
– The oil dilution system is retained for use in low (+5-20′c) temperatures.
– The aircraft can be fitted with a three blade propeller.
– The front shutters are retained, optionally the SU style of shutter may be fitted at additional cost.
– Cowl shutter, oil cooler doors are controlled from both cockpits.
– Both cockpits are equipped with magneto switches.
6.2.10. THE SEATS
– Both cockpits are equipped with 5 point harness, optionally a Hooker 7 point Harness belt system can be fitted.
6.3. INSTRUMENTATION, COMMUNICATION AND NAVIGATION EQUIPMENT
6.3.1. Both cockpits are equipped as follows:
- Engine instruments
- light signals
- basic flight instruments
- 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) Instruments subject to change dependant upon customer requirements regarding P1 position.
| Gyro Horizon | Rate of Climb |
| Altimeter | Clock |
| Wet Compass | Turn coordinator (optional) |
| Airspeed | Air pressure gauge |
| “G” meter | Oil Temperature |
| Fuel Gages | Manifold Pressure |
| Oil Pressure | Fuel Pressure |
| Carb. Air Temperature | Tachometer. |
| Cylinder Head Temperature | Airspeed |
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 |
| Cylinder Head Temperature | Tachometer |
6.3.4. The standard YAK-52TD will have the following radio equipment. At the customer request other equipment may be substituted.
– Baklan 5 radio
– SPU 9 PTT intercom with hot mike switch.
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
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:
- Portable and storable hand tow bar
- Canopy Cover
- Ground air charge adapter
- Full set of leather cushions
Specifications may change as a result of customer requirements. Items mentioned on this page do not form part of a contract. Aircraft specification may change.
