System Maintenance Manual

G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-11
190-00915-01 Revision 7
2.1.20 Standby Airspeed Indicator
A Standby Airspeed indicator, Aerosonic part number 25030-0184, is installed between PFD 1 and the MFD.
Due to varying airspeed marking requirements, four marking options are used. To determine the appropriate
option for a specific aircraft configuration, refer to the General Arrangement drawing, Garmin Document
005-00421-03. The standby airspeed indicator does not require electrical power for normal operation except
for internal instrument lighting, which is powered from Dual Fed No. 1 Bus and the emergency standby
battery. This unit is connected to the right-hand pitot/static system.
2.1.21 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 the new Standby Instrument Bus and the emergency standby
battery. Internal lighting of this unit is powered from Dual Fed No. 1 Bus and the emergency standby
battery. This unit is connected to the right-hand static system.
2.1.22 Standby Attitude Indicator
The Mid-Continent Model 4200-11 Electric Attitude Indicator is used as the standby attitude indicator. It is
connected to the new Standby Instrument Bus and the emergency standby battery. Gyro power and internal
lighting of this unit is powered from Dual Fed No. 1 Bus and the emergency standby battery.
2.1.23 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
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.
2.1.24 Safe Flight Lift Computer
For the optional Electronic Stability and Protection (ESP) feature with Angle Of Attack modes, a new Safe
Flight lift computer, part number C-05606-1, that is a direct replacement for the existing lift computer is
installed to provide an additional Low Airspeed Awareness (LAA) output to support the Angle of Attack
modes of Electronic Stability and Protection. The lift computer is located in the same location as the original
lift computer, under the forward cabin floor. Note: this unit is not used for the “ESP – no AOA” option.
2.2 G1000 Optional Interfaces
Optional equipment interfaces include L-3 WX-500 Stormscope, traffic systems, radio altimeter, ADF
systems 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.