Jabiru Aircraft
SECTION 7
Model J160-C
AIRCRAFT AND SYSTEMS
JP-FM-06
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1 Dec 2008
Page 7-15
7.17 COCKPIT VENTILATION
Ventilation air is provided by vents located beside the rudder pedals. The volume of the air
supply can be regulated by sliding the vent shutters as desired using your foot.
7.18 PITOT-STATIC SYSTEM AND INSTRUMENTS
The pitot-static system supplies ram air pressure to the airspeed indicator and static pressure to
the airspeed indicator and the altimeter. The system is composed of a Pitot probe mounted on
the right wing strut.
7.18.1
Airspeed Indicator
The airspeed indicator is calibrated in knots. Limitations and range markings (in KIAS) are
incorporated on the instrument as specified in Section 2 sub-section 2.3.
7.18.2
Altimeter
Aircraft altitude is depicted by a barometric type altimeter. A knob near the lower left portion of
the altimeter allows the ambient barometric pressure sub-scale to be adjusted to the current
value. This sub-scale has a dual calibration of millibars (mb) and inches of Mercury (in Hg).
7.18.3
Vertical Speed Indicator
The vertical speed indicator indicates the aircrafts rate of climb or descent in feet per minute.
The pointer is actuated by changes in ambient barometric pressure as sensed by the static
source.
7.19 STALL WARNING SYSTEM
The aircraft is equipped with an air operated artificial stall warning system. A vent is located on
the leading edge of the left wing with a small lip protruding below. As the aircraft approaches the
stall the angle of the airflow flowing past the lip produces a suction in the vent which sucks air
through a reed “squawker” located in the wing root area of the cabin. The “squawker” produces
an audible note which increases in volume as the stall deepens. The speed at which the warning
activates is adjusted by changing the height f the lip below the vent on the wing, and is set to go
of 5-10 knots below the stall. The system will operate reliably in any loading condition or flap
setting.
7.20 AVIONICS
The aircraft may be fitted with a variety of avionics equipment. Refer to Section 9 for information
on the avionics fitted to each aircraft.
All avionic services are powered from the instrument bus that is energised by turning ON the
Master and Instrument Switches on the instrument panel.
Summary of Contents for J160-C
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