Calidus
SYSTEM DESCRIPTION
AutoGyro_POH_Calidus Revision 4.0 – Issue Date 17.JAN.2019 7-25
Note re Rotor bearing temp indicator. The purpose of this is to advise the pilot of an unusual
rise in temperature of the bearing. In general use it may be used to indicate the outside air
temperature in the region of the rotor head.
7.15 Intercom
The standard intercom system features standard headset sockets (TSR Tip Ring Sleeve)
with additional optional XLR-3 socket for active headset power supply. Sockets are provided
in each station, on the left hand side of the pilots respectively co-pilots seat. The intercom
amplifier and VOX control is integrated in the respective radio.
In case of ATR 833, an audio in socket is provided in the instrument panel right beside the
radio. Audio sources can be connected to the intercom system using a standard 3.5 mm
audio jack.
See manufacturer’s manual for additional information.
7.16 Pitot Static
Total pressure is picked up by a pitot tube located in the nose section of the fuselage. The
tube is connected to the integrated cockpit instruments by a plastic line. The static pressure
is measured across two ports, one on either side of the fuselage.
7.17 Indicators and Sensors
Rotor speed is measured by a magnetic pick-up, located directly at the geared ring of the
rotor head. Rotor bearing temperature is measured by a temperature sensor which is glued
into the rotor bearing sleeve.
If Rotorhead II is embodied then an additional indicator “Clutch” is provided. Comparison of
rotor RPM with engine RPM governs the CLUTCH indication that informs the pilot about a
slipping clutch (continuous light) or warns of an attempted take-off run with the risk of blade
flapping (blinking).
CLUTCH is on with engine speeds above 2200 RPM and rotor speed
not matching while pre-rotator is depressed (slipping clutch)
CLUTCH is blinking with engine speeds above 5000 RPM and rotor speed
below 200 RPM (attempted take-off run with the risk of blade flapping)
NOTE
If the stick is pulled back more than 5degrees the pre rotator clutch will
automatically disengage. In this case the CLUTCH lamp will indicate a
continuous light until the pre rotator button is released.
Rotor bearing temperature is measured by a temperature sensor which is glued into the
rotor bearing sleeve. This is deleted when rotorhead III is installed, and replaced by an OAT
sensor located under the aircraft body rear of the nosewheel.
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