Figure 2-19, Gsa 9000 / Gsm 9100 - Garmin G1000 System Maintenance Manual

2.1.19
GSA 9000 Servo and GSM 9100 Servo Gearbox
The Garmin GFC 700 AFCS uses a GSA 9000 servo to control aircraft yaw damper/turn coordination and
rudder boost. The GSA 9000 contains a motor-control and monitor circuit board, as well as a solenoid and a
brushless DC motor. The GSA 9000 servo receives serial RS-485 data packets from the GIA 63Ws. The
GSA 9000 yaw servo is located in the tail. Power to the servo is received from No. 2 Triple Fed Bus. The
servo mounts to a Garmin GSM 9100 Servo Gearbox. The GSM 9100 is responsible for transferring the
output torque of the GSA 9000 servo actuator to the mechanical flight control surface linkage.
2.1.20
Garmin G36 and 37 GPS/WAAS Antennas
This installation uses one G36 GPS/WAAS antenna and a G37 GPS/WAAS/XM antenna. The antennas are
located in the upper, forward cabin.
2.1.21
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.
2.1.22
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.
2.1.23
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.
G1000 / GFC 700 System Maintenance Manual - 300/B300 Series King Air
190-00716-01

Figure 2-19, GSA 9000 / GSM 9100

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Revision 1