POH/EUR/02
Issue 5
Page 33 of 37
7.9
Fuel system
The fuel system consists of a 65 litre (
14.3 Imp. gals
) tank, fuel cock, filter and
mechanical fuel pump on the engine. The tank is positioned in a separate space
behind the seats and has a drain sump and drain valve. The outlet is situated below
on the starboard side of the fuselage.
Fuel quantity is measured by a resistive float sensor located in the top of the tank.
The sensor indicates the relative quantity of fuel in the tank (the corresponding
quantity in litres is shown in table 6.2). and is displayed either on a separate fuel
gauge on the analogue panel or on the digital display as a guide only. It is
recommended that you always dip the tank and work on fuel burn of 15ltr per hour for
a safe operation.
WARNING
Verify fuel quantity before flight by using a dip stick or other means
7.10 Electrical system
The aeroplane is equipped with a 12v DC electrical system; most services use
aircraft frame return (-ve).
The engine does not require the aeroplane’s DC system to function, except for
starting. Its ignition system derives its power from an independent generator built into
the engine. Full details of the engine’s electrical system can be found in the Rotax
Operator’s Manual.
DC Supply
A 7.5 amp hour Aliant X3 lithium iron phosphate battery is installed on the firewall
and receives charge from the engine’s alternator via an electronic rectifier/regulator
unit and a 30 amp fuse. The regulator is a switched mode unit and a large (22,000
μF) electrolytic capacitor is connected across i
ts output to provide smoothing for
avionics and other services sensitive to electrical noise. It also protects services from
over-voltage in the event of battery disconnection.
WARNING
The battery will be damaged if allowed to completely discharge or if it is jump started.
Only use recommended charger. See battery manufacturers’ maintenance manual
Pull the "Master" and "Charge" Circuit breakers if the engine is not run for more than
48 hours to prevent the battery from becoming discharged.
An analogue or electronic voltmeter mounted on the instrument panel monitors the
battery voltage. Normal readings lie in the range 12 to 14.4 volts.
Distribution and Services
The battery is connected via a 30 amp circuit breaker to a +ve bus bar mounted
behind the instrument panel, and switched by the Master Switch. The bus bar feeds
all services via circuit breakers. The circuit breakers are designed to trip if there is an
overload on the circuit. To reset, push the circuit breaker in. If it trips again do not
reset
Electric Starter System
The high starter motor current is switched by a relay mounted on the firewall. The
starter relay is energised when the Master switch is ON and the starter key switch,
mounted on the instrument panel, is turned.
A warning lamp in the instrument panel, is connected to the starter relay secondary
and warns if the starter relay remains closed after the starter is released.
