Airplane Flight Manual Supplement

Hawker Beechcraft C90A and C90GT King Air 190-00682-02 Rev. D
Page 102 of 117
FLIGHT INSTRUMENTS
G1000 FLIGHT INSTRUMENTS
The flight instruments are an integrated part of the G1000 system. For system descriptions, operating
instructions, and abnormal failure indication refer to the Cockpit Reference Guide.
STANDBY FLIGHT INSTRUMENTS
There are three 2 ¼ inch standby instruments that are located directly to
the right of the pilot’s Primary Flight Display arranged vertically, standby
attitude indicator, standby altimeter, and standby airspeed indicator.
A standby attitude indicator located at the top of the stack is normally
powered by the triple fed buss. In the event of total loss of aircraft
electrical power, there is a standby battery that will power the standby
attitude indicator for at least 30 minutes.
A standby altimeter is the next instrument in the stack. It is a
mechanical instrument that requires no electrical power to operate.
Electrical power is used to power an internal vibrator, used to minimize
indicator pointer sticking, and instrument internal lighting. The vibrator
is normally powered from the triple fed buss. In the event of total loss
of normal aircraft electrical power, the vibrator and internal lighting is
powered by the standby battery. The standby altimeter uses the
copilot’s static system for its source of static air pressure.
The bottom instrument is a mechanical airspeed indicator. It is a
mechanical instrument that requires no electrical power to operate.
Electrical power is used for internal lighting. In the event of a total loss
of aircraft electrical power, the standby battery will power the
instrument’s internal lighting. The standby airspeed indicator uses the
copilot’s static system for its source of static air pressure, and the
copilot’s pitot system for its source of impact air pressure.
Figure 14, Standby Flight Instruments
3
5
7
8
ALT
2992 1013
28
inHg
mb/ hPa
KNOT S
AIRSPEED
300
50
100
150
200
250
30