Rotax 912 i series Installation Manual

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INSTALLATION MANUAL
BRP-Powertrain
Effectivity: 912 i Series
Edition 1/Rev. 2
76-00-00
Page 1
January 01/2014
Chapter: 76-00-00
ENGINE MANAGEMENT
Introduction The main components of the EMS are:
- ECU
- ECU actuators
- ECU sensors
- EMS current supply
- FUSE BOX
- Switches
-Wiring
Table of contents This section of the Installation Manual describes the management of the
aircraft engine.
The core of the EMS is the engine control unit (ECU), which consists of
two modules. These modules will be denoted by LANE A and LANE B,
each one capable of taking over control, regulation and monitoring of the
engine. In error-free engine operation, both LANES are turned ON.
During engine control by LANE A, LANE B ensures that the engine ope-
ration can be maintained even after a failure or reduced functionality of
LANE A. Depending on the activity and the failure status of the two
LANES, the ECU automatically selects a LANE to take over control of the
engine.
Subject Page
ECU
Technical data
Connector
Connections
Installation of the engine control unit assy.
Page 5
Page 5
Page 6
Page 6
Page 6
FUSE BOX assy.
Technical data
Connections
Fitting the AMP connector
Installation position of the FUSE BOX assy.
Page 7
Page 7
Page 8
Page 8
Page 9
Ambient air, pressure, temperatur sensor (AAPTS) Page 11
Maintenance tool
Pin assignment of maintenance and diagnostic in-
terface
Page 11
Page 11
Display
Pin assignment of display interfaces
Page 13
Page 13

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