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When the autopilot is disengaged for whatever reason, it sends a signal to LS10 autopilot buzzer. In the event of a trim fault detection, it disengages the servo actuators and causes "TRIM FAIL" annunciation to illuminate on M6 advisory panel.
A82 flight computer is electrically supplied by "BUS 2" bar and protected by CB 11 "A/P CMPTR" circuit breaker. It also gets and electrical supply (AP ALERT) from "BUS 1" bar, protected by CB 12 "A/P ALERT" circuit breaker and an electrical supply (AP DISC) from "BUS 2" bar, protected by CB 10 "A/P SERVOS" circuit breaker.
The + 15-VDC, - 15-VDC and + 5-VDC supplies necessary for certain autopilot components are provided from the 28-VDC supply.
It is mounted in PL30 radio rack.
B. B35, B36 and B38 pitch, roll, pitch trim servo actuators
The servo actuators enable to transmit the piloting commands computed by A82 flight computer to the flight controls.
Each servo actuator consists of a CW/CCW electric motor, a clutch mechanism and a capstan on which a cable attached to the main flight control is wound.
As long as the autopilot is engaged, the capstan remains integral with the electric motor, the commands from A82 flight computer are transmitted to the flight controls.
When the autopilot is disengaged, the drive capstan rotates freely.
NOTE : Each capstan is equipped with a calibrated slip clutch that enables the pilot to manually override the autopilot with flight controls when the autopilot is engaged.
 
The servo actuators are electrically supplied by "BUS 2" bar and protected by CB 10 "A/P SERVOS" circuit breaker.
B36 roll servo actuator is located under the cowling under hull on the left side between C1 and C2 frames.
B35 pitch servo actuator and B38 pitch trim servo actuator are located in the rear fuselage behind C6 frame.
C. Control switches and pushbuttons
"AP DISC TRM INT", "CWS" pushbuttons and "TRIM UP-DN" split rocker switch are located on the L.H. portion of the pilot's control wheel.
- When depressed momentarily, "AP DISC TRM INT" pushbutton disengages the autopilot and cancels all previously selected modes.
- When depressed and held, "CWS" pushbutton allows aircraft manual control (disengagement of the servo actuators) without cancelling the selected modes.
- When both sides of "TRIM UP-DN" split rocker switch are kept depressed in the same direction, the pitch trim operates in manual mode in the desired direction. When the autopilot is engaged, activation of the manual electric trim causes the autopilot to automatically disconnect.
- S145 GO-AROUND pushbutton is mounted on the control pedestal front cover.
When depressed, it disengages the autopilot and engages the flight director in climb mode (nose-up, wings-level attitude).
- "AP/MASTER" switch is mounted in the radio rack or in variant on the L.H. panel strip of the instrument panel. It allows energization of the system.
　
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本文鏈接地址：TB20 MAINTENANCE MANUAL 22 AUTO FLIGHT TB20飛機維護手冊 22 自動飛行(29)