Instruction Manual

Page 2-14 G1000 / GFC 700 System Maintenance Manual - 300/B300 Series King Air
Revision 4 190-00716-01
2.1.24 Signal Conditioner (2)
Each GEA 71 receives signals from its on-side engine turbine speed sensor, propeller speed sensor and
fuel flow sensors via a Meggitt Signal Conditioner, p/n 85-292-4. This unit converts the signals from the
engine sensors to a signal usable by the GEA 71. These units are installed behind the instrument panel.
Electrical power to the No. 1 Engine Signal Conditioner is provided from No. 1 Triple Fed Bus and to the
No. 2 Engine Signal Conditioner from No. 2 Triple Fed Bus. Both signal conditioners will power-up
immediately with external or aircraft power or battery operation.
2.1.25 Standby Airspeed Indicator
A Standby Airspeed indicator, Aerosonic part number 25030-0184, or Mid-Continent Instruments part
number MD25-300 is installed between PFD 1 and the MFD. The standby airspeed indicator does not
require electrical power for normal operation except for internal instrument lighting, which is powered
from No. 3 Triple Fed Bus and the emergency standby battery. This unit is connected to the right-side
pitot/static system.
2.1.26 Standby Altimeter
A standby altimeter, Aerosonic part number 16650-1172, or Thommen part number
3A43.22.35F.28.1.FU, is installed between PFD 1 and the MFD. This unit incorporates a vibrator to
ensure accurate display altitude information. The vibrator is powered by No. 3 Triple Fed Bus and the
emergency standby battery. Internal lighting of this unit is powered from Left Gen Bus and the
emergency standby battery. This unit is connected to the right-side static system.
2.1.27 Standby Attitude Indicator
The Mid-Continent Model 4200-11 Electric Attitude Indicator is used as the standby attitude indicator. It
is powered by No. 3 Triple Fed Bus and the emergency standby battery. Gyro power and internal lighting
of this unit is powered from Left Gen Bus and the emergency standby battery.
2.1.28 L-3 PS-835(C or D Model) Emergency Standby Battery
In the event of loss of all normal electrical power, the battery is designed to provide 24 Vdc (nominal)
emergency power source for the following items:
• standby attitude indicator (operation and internal lighting)
•
standby altimeter (vibrator and internal lighting)
•
standby airspeed indicator (lighting only)
•
pilot side glareshield lighting
•
magnetic compass
The aircraft power buss provides a trickle charge to the PS-835 under normal conditions. This battery is
installed in the nose avionics bay. It is controlled using the standby battery switch indicator on the
instrument panel.
2.2 G1000 Optional Interfaces
Optional equipment interfaces include lightning detection, traffic, transponder, radar altimeter, ADF and
DME systems. The G1000 also provides a general purpose ARINC bus for use with third party
entertainment and cabin equipment. Refer to wiring diagram listed in Table 1-2, for specific interface
information.