Instruction Manual

G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-13
190-00915-01 Revision 9
2.1.22 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 (Vibro-Meter) Signal Conditioner. 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 Dual Fed Bus No. 1 and to the
No. 2 Engine Signal Conditioner from Dual Fed Bus No. 2. Both signal conditioners will power-up
immediately with external or aircraft power or battery operation.
NOTE
On serial numbers BB-1484, 1486 and subsequent, the electrical system includes the L
ENG INSTR and R ENG INSTR buses which (after this STC) are powered from Dual
Fed Bus No. 1 and No. 2 respectively. On these aircraft, the No. 1 Engine Signal
Conditioner receives power from Dual Fed Bus No. 1 via the L ENG INSTR bus and the
No. 2 Engine Signal Conditioner receives power from Dual Fed Bus No. 2 via the R ENG
INSTR bus.
2.1.23 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.
2.1.24 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.
2.1.25 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.
2.1.26 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.