Mahindra GIPPSAERO GA8-TC 320 - Avionics; Stall Warning System; Vacuum System and Instruments

Section 7
Aircraft & Systems
Model GA8-TC 320 Description
Page 7-16 5 Feb 2009 C01-01-08
7.19 VACUUM SYSTEM AND INSTRUMENTS (If Fitted)
An engine driven vacuum pump provides suction for the articial horizon and direction indicator.
A vacuum system pressure indicator and an amber caution light is provided on the instrument
panel.
7.20 STALL WARNING SYSTEM
The aircraft is equipped with an electrically operated articial stall warning system. A vane type
lift transducer is located on the leading edge of the right wing. As the aircraft approaches the
stall the angle of the airow lifts the transducer vane activating a warning horn in the cockpit.
The system is set to warn of an impending stall when the airspeed falls to within 5 to 7 knots of
the stalling speed. The system will operate reliably in any loading condition or ap setting. The
warning horn requires electrical power and operates independently of the master switch. The
circuit breaker for the stall warning is found in front of the pilot’s seat.
7.21 AVIONICS
The aircraft may be tted with a variety of avionics equipment. Refer to Section 9 for information
on the avionics tted to each aircraft.
All avionic services are powered from the dual bus system that is energised by turning ON the
Bus 1 and Bus 2 Master Switches on the overhead panel. The Bus 1 and Bus 2 Avionics Master
Switches must also be selected ON to activate the services on the respective bus. Figure 7-3
provides information of which services are on each bus.
01 Aug 2011