Effectivity 912/914 Series
Edition 1 / Rev. 0
71-00-00
page 3
May 01/2007
d02621
BRP-Rotax
Maintenance Manual
2) System description
2.1) Description of design
All ROTAX engines of the 912/914 Series consist of several main components
and additional aggregates which are described in the following sections.
On the 912 Series: 4-cylinder horizontally opposed 4 stroke engine with a
central camshaft pushrods OHV.
On the 914 Series:4-cylinder horizontally opposed 4 stroke engine with turbo-
charger and electronic control of boost pressure control
(TCU = turbocharge control unit) and a central camshaft -
push-rods OHV
Liquid cooled cylinder heads
Ram air cooled cylinders
Dry sump forced lubrication
Dual breakerless capacitor discharge ignition
2 constant depression carburetors
On the 912 Series:1 mechanical fuel pump
On the 914 Series:2 electric fuel pumps (12V DC)
Propeller drive via reduction gearbox with integrated mechanical shock ab-
sorber and overload clutch
â—† NOTE: The overload clutch is fitted in serial production on both
certified aircraft and uncertified aircraft engines of
configuration 3.
On the 914 Series:Stainless steel exhaust system
On the 912 Series:Individual parts of the exhaust system (optional),
usually fitted by aircraft manufacturer
On the 912 Series: engine suspension frame, optional
On the 914 Series: engine suspension frame in serial production
Electric starter (12 V 0,6 kW / optional: 12 V 0.9 kW )
Integrated AC generator with ext. rectifier-regulator (12V 20A DC)
External alternator (12V 40A DC), optional
Vacuum pump: (only possible for Type 2 and Type 4), optional
Hydraulic constant speed propeller governor: (only for Type 3), optional
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