Cirrus Garmin GFC 700, Руководство по обслуживанию

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CIRRUS A
IRPLANE
M
AINTENANCE
M
ANUAL
C
HAPTER
22-10: GFC 700 A
UTOMATED
F
LIGHT
C
ONTROL
S
YSTEM
MODELS SR22
AND
SR22T G
ENERAL
3
For additional information on the autopilot system integration, see Pers Integrated
Avionics System Pilot’s Guide.
(Refer to 5-00)
The GFC 700 AFCS is integral to the Pers Integrated Avionics system. For an over-
view of the Pers system, see Core System section of Integrated Modular Avionics.
(Refer to 42-20)
B. GMC 707 Automatic Flight Control System (AFCS) Mode Controller
The GMC 707 AFCS Mode Controller, located in the upper section of the center console,
provides primary control of autopilot modes and, if installed, yaw damper engagement. A
pitch wheel is included for adjustment of pitch mode reference. Through the mode
controller, the GIA 63W Integrated Avionics computer serves the function of converting
operator commands to logic signals for the roll and pitch computer functions.
28 VDC for mode controller operation is supplied through the 5-amp KEYPADS/AP CTRL
circuit breaker on Main Bus 1.
C. GTA 82 Pitch Trim Adapter
The Pitch Trim Adapter, located below the passenger seat, takes input from the trim
switches, Integrated Avionics Units, and the pitch servo to allow the GFC 700 to drive the
pitch servo. The trim adapter interfaces with the dual GIA 63W Integrated Avionics
computers through serial communication on separate RS-485 ports. Trim commands from
the yoke switches are routed through the GTA 82 when autopilot is disconnected.
28 VDC for pitch trim adapter operation is supplied through the 2-amp PITCH TRIM circuit
breaker on Essential Bus 2.
D. Pitch Servo
The pitch servo, located below the baggage compartment at access panel CF5, provides
automatic control of the pitch axis. The pitch computer receives signal inputs to compute
pitch commands for stabilization, turns, radio intercepts, heading and tracking.
The pitch servo is an electromechanical unit that provides automatic control of the pitch
flight axis. The pitch servo receives data from dual GIA 63W Integrated Avionics computers
containing Autopilot/Flight Director algorithms. The GSU 75 ADAHRS is fed inputs used to
drive autopilot. The pitch servo consists of a GSA 81 Servo Actuator and GSM 86 Servo
Mount.
The servo actuator contains a motor-control circuit board, monitor circuit board, solenoid,
and motor. The motor-control board processes data and drives the motor as required for
axis control. The monitor board monitors servo speed, monitors output torque, and
controls engagement of the drive-clutch solenoid.
The servo mount contains a capstan and slip-clutch. The capstan transfers the output
torque of the servo actuator to the mechanical flight control surface linkage for pitch axis.
23 Dec 2016