Rotax 912 i series Installation Manual

d05395.fm
INSTALLATION MANUAL
BRP-Powertrain
Effectivity: 912 i Series
Edition 1/Rev. 1
74-00-00
Page 1
July 01/2012
Chapter: 74-00-00
IGNITION SYSTEM
Introduction The ignition system is powered by the ECU and has fully mapped varia-
ble timing. It is completely doubled up. Either of the ECU‘s can operate
the double ignition coils. If a fault occurs with the ignition system the ECU
informs the pilot by warning lamps through the display in the instrument
panel.
NOTE: All components are installed on the aircraft engine as stan-
dard.
Table of contents This section of the Installation Manual contains information on the aircraft
engine ignition system.
Subject Page
Connection to rectifier regulator Page 3

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