M106 aircraft, UL260i engine hyperflite
M106 aircraft, UL260i engine
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M106 aircraft, UL260i engine
Terms and Conditions
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M106 aircraft, UL260i engine
Engine Description

4 stroke, 4 cylinder, horizontally opposed
Dual (redundant) electronic spark ignition (variable timing)
Electronic multipoint fuel injection (pressure and temperature compensated)
Electronic RPM limiter
Direct propeller drive
5 bearing crankshaft with surface hardening treatment and additional large thrust bearing (ball bearing type)
Single central camshaft
Push rods, tappets and OHV (hydraulic compensators have not been used)
Wet sump forced lubrication with integrated pressure regulator
Ram air cooled cylinders and cylinder heads
Integrated permanent magnet AC generator, external rectifier-regulator
Electric starter
Electric fuel pump and pressure regulator to eliminate vapor lock and facilitate starting even under adverse conditions


2592 cc [158.17 cu in]
105.6 mm [4.157 in]
74 mm [2.913 in]
Compression Ratio*
8.16 : 1
Firing Order
1 - 3 - 2 - 4
Direction of Rotation
Clockwise - Pilot's view - tractor configuration
Maximum Torque
(ISA conditions)*
207 Nm [152.7 ft.lbf] @ 2500 rpm
Power rating
(ISA conditions)*
95 hp @ 3300 rpm  /  82 hp @ 2800 rpm
All up dry weight*
72 kg [158.7 lbs] (including all accessories such as electric fuel pump, filters, lines, alternator and exhaust system)
DC output*
35 Amp (+/- 20 Amp available above engine/fuel pump needs)
Oil capacity*
2.5 L [0.66 US gal]
Unleaded gasoline (or AVGAS) min. 98 octane - use of lower octane fuel will be possible with reduced compression

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