|
Core
details
|
|
|
No. Of cyl
and arrangement
|
V12 – 80°
|
|
Fuel type
|
Jet A1, kerosene type fuels acc. To
ASTM D1655, Def Stan 91-91 and GOST 10227 up to a maximum ignition delay time of 8.06 ms/minimum derived cetane number of 27.9 (determined according EN 15195/ASTM D6890)
|
|
Power A03-x03
|
500 hp – 378 kW/4,000 rpm
|
|
Power A03-x05
|
550 hp – 405 kW/4,000 rpm
|
|
Power A03-non aviation use (project
state)
|
600 HP – 441 kW
|
|
Displacement
|
372 CUI – 6.1 l
|
|
Bore & stroke
|
3.38″x3.46″ – 86×88 mm
|
|
Valves per cylinder
|
4
|
|
Camshaft system
|
gear driven dual overhead camshaft
|
|
Turbocharger
|
Single or 2-stage system
|
|
Fuel system
|
Common rail high preasure system 1,600 bar – 23,206 psi
|
|
Electrical system
|
2x28V 3.5 kW alternator
|
|
Reduction gear
|
1:1.88
|
|
Dry mass w/o gearbox
|
290 kg – 640 lbs
|
|
Dry mass with normal/utility
gearbox
|
363 kg – 800 lbs
|
|
Dry mass with aerobatic gearbox
|
357 kg – 787 lbs
|
|
Fuel Flow take-off power
|
85 KG/H – 187 lbs/h
|
|
Fuel Flow MCP
|
77 KG/H – 169 lbs/h
|
|
Fuel Flow 400 hp
|
65 KG/H – 143 lbs/h
|
|
Fuel Flow 300 hp
|
47 KG/H – 103 lbs/h
|
|
Engine control system
|
FADEC, EECU, EECS, sensors, Design Assurance Level B cert. ompliant RTCA DO-254,
DO-178B, DO-160G
|
RED Aircraft