Pilot Operating Handbook
Cavalon
SECTION 3
EMERGENCY PROCEDURES
AutoGyro_POH_Cavalon 915iS
Revision 1.0 – Issue Date 08.MAY.2019
3-7
A reduction in vibration may be caused by increased flexibility between the rotor head and
the occupant. This may be control system looseness, so check all system joints for
tightness, and also for cracks at the base of the mast. Check security of all fastenings
between the rotor and the pilot
3.11 Other equipment failure
Good judgement must be used in monitoring instruments, and timely action taken should a
reading be in doubt. If in doubt, make a precautionary landing and resolve the issue rather
than continuing a flight.
Actions recommended:
ASI failure
In level flight fly with an engine rpm of 4,200 lightly laden to 5,000 heavily laden which will
give approx 105 to 130kmh (45-55 KIAS, 60 to 80mph). When descending (nose down)
throttle back to approx 3,000 to 3,500rpm to prevent overspeed. Continue to your
designated landing site, maintaining speed for a flare on landing in the final descent. Leave
plenty of space to land in should the flare be prolonged. Experience will aid judgement of
the best engine rpm to maintain to match the desired flight speed and payload.
Altimeter failure
In a gyroplane it is reasonably easy to judge height. If in controlled airspace ensure the
controlling authority is informed to prevent traffic conflict. Otherwise continue to a safe
landing using navigational skills to avoid potential collisions.
NOTE
The configuration menu on the electronic ASI and ALT devices can be
accessed to change between different units of measure.
If a device turns off when uncommanded, this could signify a software reset
has been signalled internally. Attempt to manually restart the unit by
depressing the power button. If the device does not restart assume the
instrument has failed.
Compass
Resort to map, aided by GPS if available, fly at a speed to suit navigational requirements or
make a precautionary landing if unable to identify position.
Rotor RPM gauge
This is not essential for safe flight, and rotor rpm cannot normally be affected in flight unless
significant “g” or negative “g” is exerted – and then will only provide an indication of the rpm.
If failed in flight, repair on landing.
Engine RPM
The engine is rpm self-limiting by propeller pitch in flight. If the gauge fails, replace on
landing. Use audio cues to establish rpm
Oil pressure, oil temp and water temp
. A failure of one gauge can indicate an engine fault
or simply a gauge fault. Watching the other gauges will indicate the likely failure mode.
For example,