P&M QUIK-GTR Manual, ref. QUIK-GTR Man 1.0.doc
Page 26
3.9. ELECTRICAL SYSTEM SPECIFICATION
The Alternator
Rotax 912S/912
: the alternator gives a nominal maximum current of 18 amps AC or voltages up to about 75 volts
RMS with very low current. The nominal power rating is 250 Watts DC.
Power Wiring
The power wiring loom consists of insulated conductors inside a woven nylon sheath with a rubber connector at
the rear end and spade terminals at the front. A 2-core cable and switch for engine ignition control is also
included for each ignition circuit.
Note that airworthiness requirements specify that all electrical equipment attached to the wiring system must be
protected by overload protection devices and that no protective device may protect more than one circuit
essential to flight safety. To this end a multiway fuseholder is provided at the front of the aircraft for the
attachment of electrical equipment.
Operators wishing to fit equipment themselves must contact their dealer with a modification scheme, the dealer
will obtain modification authorisation from the factory.
Battery State Monitor.
A single LED Battery State Monitor (BSM) may be fitted. When power is switched on, it conducts a brief check
sequence. It indicates as follows:
No power
(0-5v)
Neutral
GREY
Low volts
( 6- 11.5v)
Slow flashing
RED
Good battery off charge
(11.5-12.5v)
Steady
ORANGE
Battery on charge
(12.5-14.5v)
Steady
GREEN
Over voltage
(14.5v +)
Fast flashing
RED
Any fault condition should be investigated before further flight. It may be wise to turn the master switch off.
Sensor Wiring
The sensor wiring system comprises a multicore cable intended for transmission of signals not involving
significant power levels. No items requiring significant power with an alternating component should have their
supply lines attached to this cable as electrical interference with sensor signals may occur.
CAUTION
When the aircraft is stored for an extended period of
time, remove the battery and charge it fully. Then
store it in a warm dry place. Never leave the battery
discharged.
It is important to understand that the data recorded during stall tests
were ascertained using the CAA requirement of a reduction of airspeed
of not more than 1 knot per second. If accelerated and therefore
unauthorised stalls are undertaken, the aircraft may then lose significant
height before recovery is made, or in extreme cases, may become
unstable to the extent of being unrecoverable.
WARNING
!
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