Flight manual
MD3
RIDER
Page 7-17
WARNING:
This aircraft engine does not comply with federal safety regulations for
standard aircraft.
This engine is for use in experimental and ultralight uncertified aircraft only and
only in circumstances in which an engine failure will not compromise safety.
TECHNICAL DATA:
performance for standard conditions (ISA)
ENGINE
Type:
912 ULS
D.C.D.I.
performance
69,0 kW (95,0 hp) @ 5500 1/min(rpm)
Max. 5 min.:
73,5* kW (100,0* hp) @ 5800 /min(rpm)
torque
128 Nm (94,0 ft.lbf.) @ 5100 1/min (rpm)
Max. RPM:
5800 1/min (rpm)
Bore:
84,0 mm (3,31 in.)
stroke:
61 mm (2,40 in.)
displacement:
1352,0 cm3 (82,6 cu.in.)
compression ratio:
10,5:1
ignition unit:
DUCATI double CDI
ignition timing:
4° up to 1000 1/min (rpm) / ab ove 26°
spark plugs:
ROTAX part no. 297 940
generator performance:
250 W DC @ 5500 1/min
voltage:
13,5 V
OPERATING MEDIA:
Fuel:
min. RON 95*- min. AKI 91* or AVGAS 100 LL
Oil:
API SF or SG
cooling liquid:
50% BASF
Glysantin-Antikorrosion
/ 50% water
WEIGHTs:
Standard engine with gearbox i=2,43:
56,6 kg (124,8 lb.)
oil radiator 886 029:
0,5 kg (1,1 lb.)
radiator 995 697:
1,0 kg (2,2 lb.)
slipping clutch:
1,0 kg (2,2 lb.)
air guide hood:
0,8 kg (1,8 lb.)
vacuum pump:
0,8 kg (1,8 lb.)
external alternator 40 A/ 12 V DC:
3,0 kg (6,6 lb.)
fuel pump with installed fuel lines:
0,2 kg (0,4 lb.)
