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B36 roll servo—actuator is located beneath the under—hull cowling on the left side between frames C1 and C2.
B38, B35 pitch trim and pitch servo—actuators are located on the rear fuselage behind frame C6.
C. A81 altitude / vertical speed selector (Optional)
A81 altitude / vertical speed selector provides the data necessary for the autopilot to maintain the vertical speed (climb or descent rate) selected by the pilot or to reach the altitude selected by the pilot. It also ensures the altitude warning function ("ALERT" indicator and audio tone).
Altitude or vertical speed parameters are selected by means of two concentric knobs located on the R.H. side of the display.
"ENG" and "ARM" pushbuttons located on the L.H. side of the display allow selection of the "VS" and "ALT ARM" modes.
A81 altitude / vertical speed selector receives the altitude coding and barometric correction from the encoding altimeter.
Aircraft equipped with the printed circuit
A printed circuit equipped with diodes makes it possible to isolate the altitude coding inputs of the transponder from the inputs of the altitude / vertical speed selector.
The printed circuit is equipped with a protection cover and is secured on the front R.H. table. All
The altitude / vertical speed selector is electrically supplied by BJ6 bus bar and protected by "ALT. SEL" circuit breaker.
The altitude / vertical speed selector is mounted on the R.H. instrument panel but it may be mounted in an alternate location.
AHAG
Validity : KAP 150 without EFIS 22 12-00Page 7
(DE) DEC 99
 
D. M80 mode annunciator (Optional)
M80 mode annunciator provides a parallel annunciation display of the modes within the pilot's main sight field.
Mode annunciations illuminate when the respective mode has been selected on the flight computer. "TRIM" annunciation illuminates when the preflight test has not been carried out, in the absence of power to the servo actuator or in the event of a servo actuator malfunction.
M80 mode annunciator is electrically supplied by BJ6 bus bar. It is mounted on the L.H. instrument panel.
E. Control pushbuttons
"AP DISC TRM INT", "CWS" pushbuttons and "TRIM UP—DN" split rocker switch are located on the pilot 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.
— "TRIM UP—DN" split rocker switch is composed of a L.H. portion which provides electrical power to the pitch trim servo actuator clutch and a R.H. portion which controls the servo actuator rotation direction. Both sides of "TRIM UP—DN" split rocker switch must be simultaneously depressed to operate the manual pitch trim servo in the desired direction. When the autopilot is engaged, activation of the manual electric trim causes the autopilot to automatically disconnect.
　
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本文鏈接地址：TB20 MAINTENANCE MANUAL 22 AUTO FLIGHT TB20飛機(jī)維護(hù)手冊 22 自動(dòng)飛行(22)