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Page Date: 19. February 2014
Section 7
Description and Operation of Aircraft and Systems
Pilot´s Operating Handbook US
EXTRA 330LX
Wing Tank:
The root section of each wing - in front of main spars forms an integral fuel tank providing two
interconnected tanks with 120 liters (31,7 US GAL.) total capacity. Each side of the wing has
a 2" diameter filler cap for gravity refueling. The wing tank can be completely emptied in flight.
Acro & Center Tank:
An Acro tank 9 liters (2,3 US Gal.) is mounted in the fuselage just behind the firewall and the
Center tank 60 liters (15.9 US Gal.) in front of the main spar of the wing. The Acro tank is
connected with the center tank in a gravity feed system. The center tank has a 2" diameter
filler cap for gravity refueling. Unusable fuel is 2 liters (0.5 US Gal.).
Adequate venting is provided in each tank to a main ventilation-tube, ending outside the
fuselage at the right side.
In addition to the engine driven fuelpump an electrically driven auxiliary fuel pump (boost
pump) with by-pass and having sufficient capacity to feed the engine at take-off power is fitted
as a safety device against failure of the engine-driven pump. The boost pump switch is
located on the instrument panel.
A fuel filter with drain is installed between the fuel selector valve and the boost pump.
Separate drains are located at the lowest point of each tank system.
Normal float type transducers and electrically operated fuel indicators are used.
7.12
ELECTRICAL SYSTEM
The electrical system (refer to Figure 4) is supplied by a 12 V alternator with integrated
rectifier, transistor voltage regulator. The alternator is mounted on and belt-driven by the
engine.
The field current is controlled by the voltage regulator to nominal 14.5 V under all load
conditions. The ALTERNATOR switch is located on the rear instrument panel.
Circuit protection against overvoltage is provided by the voltage regulator.
Depending on the alternator installed the maximum alternator output varies from 55 to 65 A.
Refer to the Equipment List in Section 6 for identification of alternator installed.
A 12 V leak proof battery is connected across the alternator output to stabilize the supply
and to maintain all essential services in the event of an alternator failure and when the engine
is not operating. The battery is mounted behind the firewall. The BATTERY switch is located
on the rear instrument panel.
All electrical circuits are protected by circuit breakers located on the rear instrument panel
and they are easily accessible to the pilot during flight.
The electrical system features adequate noise suppression to ensure satisfactory operation of
the radio equipment.
All wires, switches, circuit breakers etc. are manufactured to related aeronautical
specifications.
7.13
CABIN ENVIRONMENT CONTROL
A ventilation system in the canopy on the left side is provided for the supply of fresh air to the
cabin. Left and right at the rear seat are eyeball-type adjustable vents.
Summary of Contents for 330lx
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