Pilot Operating Handbook
Cavalon Pro
SECTION 7
SYSTEM DESCRIPTION
RotorSport_POH_Cavalon Pro
Revision 1.0 – Issue 2 Date 16 03 2016
7-4
7.6
Power Plant
Engine
There is only one engine variant available, being the ROTAX 914F turbo charged version
certified according to FAR 33 and JAR-E. The configuration is a 4 cylinder, horizontally
opposed, 4 stroke featuring
Liquid cooled cylinder heads
Ram air cooled cylinders
Dry sump forced lubrication
Dual breakerless capacitor discharge ignition
2 constant depression carburettors
Hydraulic tappets
Electric starter
Internal generator (Alternator) with external regulator
Reduction gearbox with integrated shock absorber and overload clutch
This turbo charged engine offers a maximum take-off power of 115 horse power. For
technical details refer to the engine manufacturer’s manual.
Oil system
The oil reservoir with dipstick is accessed through a cover on the left hand side of the
fuselage. The cover is held by 3 cam lock fasteners which can be locked or unlocked by a
quarter turn. The type of lubrication system requires a special procedure for accurate oil
level checking and to prevent overfilling, which is described in SECTION 8 of this manual.
Engine cooling
Engine cooling is provided by ram air cooled cylinders and liquid cooled cylinder heads.
Therefore, cylinder head temperature (CHT) indication in the cockpit corresponds to water
temperature, or on later engines a direct reading of Coolant Temperature (CT) is provided.
Sufficient cooling air flow is provided by a ram air duct. The water cooling system comprises
of engine driven pump, radiator with thermo-activated electrical blower fan, expansion tank
with radiator cap, overflow bottle, and hoses.
A single, large area radiator is mounted above the engine so that cooling air from the ram
air duct passes through the cooler, is directed around the engine’s cylinders, and finally
escapes through an opening at the lower rear end of the engine cowling. Force cooling is
ensured by an electrically driven ducted fan controlled by a thermo switch. A push button in
the cockpit allows manual activation temporarily which is typically used to avoid possible
heat build-up after shut-down.
For the relevant checking and replenishing procedures, refer to SECTION 8 of this manual
and also the engine manufacturer’s manual.
7.7
Propeller
The propeller fitted is a Woodcomp KW-31 in-flight adjustable variable pitch design, certified
with type certificate EASA.P.177.
The propeller pitch is adjusted by means of a Woodcomp CS 3-5 solid-state controller that
can be used in both Manual and Constant-Speed modes. Operation of this propeller is fully
described in SECTION 9 of this manual.
