Rotax 912 i series Operator's Manual

Effectivity: 912 i Series BRP-Powertrain page 7-11
OM Edition 1/Rev. 0 January 01/2012
d05871.fm
ECU The ECU is a digital engine control unit which contains the
LANE A and the LANE B in a single housing. In principle, each
LANE represents an independent computer.
In the “AUTO“ (both LANE select switch “ON“) setting, the ECU
decides which LANE takes control (redundancy management) ac-
cording to the health level of the EMS.
Any errors or values outside the operating limits are indicated by
an EMS lamp for each lane.
NOTE: The ECU also contains an databus system
(CANaerospace). A large number of engine pa-
rameters and warnings can be displayed on a
separate display. Usage is up to the aircraft
manufacturer.
Warning lamps
Error messages
All the information messages, warnings and displays below relate
to the lamps and not to databus information messages.
ON = permanently on
Main functions of
the ECU
Other main functions of the ECU include:
- Ignition control
- Fuel injection control
- Indication of faults and values that are outside operating limits
- Storing faults
- Power supply monitoring
LANE A LANE B Action
OFF Flashing Limited flight operation
Flashing OFF Limited flight operation
OFF ON Land the aircraft
Flashing Flashing Land the aircraft
Flashing ON Land the aircraft
ON OFF Land the aircraft
ON Flashing Land the aircraft
ON ON Land the aircraft

Rotax 912 i series Specifications

General

Number of Cylinders	4
Max Power	100 hp (73.5 kW)
Max Power Output RPM	5800 rpm
Ignition System	Dual electronic ignition
Oil System	Dry sump, forced lubrication with separate oil tank
Reduction Gear Ratio	2.43:1
TBO	2000 hours
Engine Type	4-stroke, horizontally opposed
Displacement	1352 cm³
Bore x Stroke	84 mm x 61 mm
Max Torque	128 Nm
Fuel Type	Avgas 100LL or unleaded automotive gasoline
Fuel System	Electronic fuel injection
Cooling System	Liquid/air-cooled