8
CARBURETOR
The Bing pressure compensating carburetor is mounted at the rear of the engine. There is no
mixture control and the carburetor automatically adjusts for altitude.
PROPELLER
The propeller is a 58 x 42” Jabiru fixed pitch wooden unit.
FUEL SYSTEM
The fuel system consists of a single wing tank located in the right hand wing with a vented fuel
cap (and forward facing vent tube) running through a filter into a small header tank located
behind the passenger seat. There is a quick drain valve at the bottom of the wing tank. Fuel is
fed into the header tank through an inlet at its top. The header tank has a vent line with spring
operated valve. This vent valve is depressed when the header tank is filled, and on a periodic
basis to purge air from the header. There is a spring mounted fuel drain at the bottom of the
header, exiting under the right side bottom of the fuselage. The fuel outlet is located several
inches above the bottom of the header tank in order to trap water and debris. Fuel passes
through a second filter under the seat and through an on-off valve mounted adjacent to the
throttle control. From this valve, it passes through a fuel flow transducer and into the engine
driven fuel pump. The fuel line then diverts into a main line into the carburetor and secondary
line, which attaches to a fuel pressure transducer. In the case of a mechanical fuel pump
failure, the system is will continue to feed due to gravity
The capacity of the fuel tank is 18 Gallons. At the inboard rib of the right wing is a clear
fiberglass panel that displays the quantity of fuel remaining.
ELECTRICAL SYSTEM
A 12 volt, direct current system, supplies electrical power. The system includes a 12 volt 10
ampere alternator, regulator and 17 ampere hour battery to produce electrical power. The
battery is located immediately behind the firewall.
The Rocky Mountains Engine Monitor indicates system voltage and amperage. A positive
ammeter reading and a voltage between 13 and 14.5 volts indicate charging.
There is a single Master Switch located on the left half of the instrument panel, which
energizes the master solenoid to provide power to the main bus and circuit breakers. There
are five switches and six circuit breakers for lights, instruments and avionics. These switches
control the aircraft [spare]; Transponder/Encoder/GPS; Radio; Strobe Light; [Position Lights].
Each circuit is protected by a circuit breaker. The sixth circuit breaker protects the Hobbs
meter. The circuit breakers automatically break the electrical circuit if an overload should
occur. To reset the circuit breaker simply push in the reset button. It may be necessary to
allow approximately two minutes for cooling before resetting a circuit breaker. Corrective
action should be taken in the event of continual circuit breaker popping or a circuit breaker that
will not stay reset.
The magneto switches are located to the left of the master switch. The engine starter solenoid
is located at the front of the firewall on the passenger side and is activated by a momentary
push button switch.
PITOT and STATIC SYSTEM
Static air is provided from within the aircraft cabin. As such, it is sensitive to the effect of
opening cabin cooling vents. Pitot pressure is supplied by the unheated pitot tube located
under the left wing. Pitot pressure is provided to the airspeed indicator and static pressure is
provided to the airspeed indicator, vertical speed indicator and encoding altimeter.
AVIONICS
An Icom A-22 is located centrally at the top front of the cabin and provided with power from
the aircrafts electrical system. A spare battery should be carried to enable handheld
operation. The radio has 720 communication channels (118.000 to 135.975) and a power
output of ?? watts. The unit plugs into a Pilot intercom located centrally at the top rear of the
cabin. The radio provides a basic CDI Navigation function with has ???? channels (108.00 to
117.95).
Up to 20 frequencies can be stored and the emergency frequency 121.?? can be obtained
with a single button push. Frequencies are selected either directly using the front push button
panel or by dialing the appropriate frequency using the knob located on the right top the unit.
Memories can be scrolled and selected using the same controls. Volume and on/off is
controlled using the knob located on the left top of the unit. A squelch knob is co-located with
the volume control.
A 9 volt battery powers the intercom. It contains an on-off-volume knob and a squelch knob.
Two headphone and mic jacks are available and a push to talk cable jack is also available.
The associated push to talk buttons is on each pilot’s control stick.
ENGINE MONITOR
The aircraft contains a Rocky Mountains Engine Monitor that displays a wide range of engine
and other aircraft parameters. These include:
• CHT and EGT (cylinders 1-4 selected
via rotary switch on the panel)
• Clock – GMT/LMT/Flight
Timer/Countdown Timer
• Oil Temperature • Oil Pressure
• Fuel Pressure • Engine RPM
• Outside Air Temperature (displayed in
the MAP portion of the display)
• Fuel consumption
• Fuel available
The operating controls are of two types, rotary switches and pushbutton switches. The power
switch and the clock mode selector are rotary switches. The white pushbuttons are
momentary switches that have to be held in to accomplish their function. The two yellow
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