Engine Controls; Power Control / Choke; Engine Shutdown / Emergency; Chapter77 - AUTO GYRO Cavalon Maintenance Manual

CHAPTER 76 - ENGINE CONTROLS
Engine control consists of engine power lever / throttle and related cockpit switches for engine shut-
down and test.
76-10-00 Power Control
Engine power / throttle is controlled by a control column installed in the centre console between the crew
seats. The unit combines a lever for activation of the wheel brake.
Throttle control (1) is conventional with IDLE in aft
(or pulled) and full throttle in most forward position.
The throttle lever is linked with cable controls to
the intake butterfly valve. A mechanical spring
applies tension to the control cable and brings the
engine to full throttle in case of a cable break. The
throttle lever has a pre-set friction brake which
holds the throttle in the selected position.
76-20-00

Engine Shutdown / Emergency

For normal and emergency shutdown, a pair of LANE switches (LANE 1 + LANE 2) is installed in the
cockpit centre panel. These switches are also used for testing the individual ignition circuits. The
switches are protected against inadvertent operation by sheet metal safety plates.
CHAPTER 77 - ENGINE INDICATING
All relevant engine parameters are displayed in the cockpit, using analogue-type instruments in standard
version. In case of integrated cockpit systems (option), engine data may be displayed in the integrated
instrumentation system (glass cockpit). An hour meter (Hobbs Meter) is installed in the cockpit to count
engine operating time with an accuracy of two decimals (1/100 hrs). Although the 'engine operating time'
is also used for total aircraft hours counting, the hour meter is allocated to this chapter as the main
function.
CAN-Bus note:
The engine parameters (Coolant temp, coolant led, oil temp, oil pressure and engine rpm) are provided
via the Rotax CAN-Bus system to the gauges, via a digital to analogue Convertor. On start up the gauges
initially go to full scale deflection, the normal Road gauge manufacturer's process.
The AutoGyro Convertor then self-checks by displaying the red line indication, dropping to the green
line indication.
The Convertor compares the information provided by the two CAN-Bus inputs.
If one input fails the unit will display the information from the other CAN-Bus.
If both fail the indication is zero, but the gauge internal warning light illuminates.
If the information provided shows a significant discrepancy the gauge will go to FSD and the internal
warning lamp will illuminate.
In the event of both, CAN-Bus input failure or Convertor failure, no information will be displayed on the
gauges.
In this situation provided the Lane A or B lamps are unlit, the engine will run normally.
77-10-00

Power

With a piston engine with fixed pitch propeller, engine power indication normally solely consists of an
engine RPM indicator. In this case, regardless of whether a fixed pitch or a variable pitch propeller is
installed, a fuel flow rate indicator is provided. This provides the pilot with clear information regarding
fuel burn versus engine rpm.
See CHAPTER 31 for different cockpit layouts.
AMM-CV-915iS/916iS-EN-
C-2023-12
Aircraft
Maintenance Manual
1 – Throttle lever
2 – Brake lever with locking pawl
4 – Cabin heating (if installed)
Part C – System Description Section
(Chapter 21 – 90)
Cavalon 915 iS / 916 iS
Throttle and brake panel
AutoGyro
Page 66 of 67