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- Selecting "HDG" (Heading), "NAV" (Navigation), "APR" (Approach), "REV" (Back course), "ALT"
(Altitude hold) modes is obtained by depressing the respective pushbuttons on the flight computer.
- Concentric knobs and "ARM", "VS", "UP" and "DN" pushbuttons of the flight computer permit to select the vertical speed hold mode, or the capture and altitude hold mode. The flight computer is connected to the aircraft static circuit and also uses altitude encoding information and barometric correction information issued from the encoding altimeter.
- Aural alerts generated by the flight computer are transmitted to headsets or to loudspeaker via the audio control panel.
- "TRIM FAIL" warning annunciation of advisory panel illuminates when pitch trim fault is detected during preflight test or during flight.
 
AUTOPILOT
DESCRIPTION AND OPERATION
1. GENERAL (Figure 1)
The optional autopilot allows the control with regard to both pitch and roll axes. It is equipped with an electric pitch trim, which ensures an automatic compensation when the autopilot operates. This pitch trim can also be manually operated by the pilot when the autopilot is not engaged.
The autopilot consists of :
— an A82 flight computer,
— a B36 roll servo—actuator,
— a B35 pitch servo—actuator,
— a B38 pitch trim servo—actuator,
— an optional A81 altitude / vertical speed selector in conjunction with an Alt. alert sonalert,
— an optional M80 mode annunciator,
— control push—buttons,
— an AUTOPILOT MASTER switch,
— a warning buzzer (autopilot sonalert).
The autopilot also uses information from :
— the flight director indicator — refer to 34-24-00,
— the heading reference system — refer to 34-21-00.
— the Marker system — refer to 34-31-00,
— the VOR / ILS navigation system — refer to 34-51-00,
— the Global Positioning System (GPS) (Only if the aircraft is equipped with HSI — NAV 1 / GPS switching option) — refer to 34-57-00.
It sends information to the flight director indicator.
The pressure from the static pressure ports is applied to the flight computer.
The system also uses the radio installation cooling fan.
The autopilot is supplied by "BUS 2" bar, which electrically supplies a specific autopilot "BJ6" bus bar.
AIAH
Validity : KFC 150 without EFIS 22-12-00 (FM) Page 1
DEC 99
 
B36 B35 B38
SERVOMOTEUR DE ROULIS SERVOMOTEUR DE PROFONDEUR SERVOMOTEUR COMPENSATEUR
ROLL SERVO ACTUATOR PITCH SERVO ACTUATOR DE PROFONDEUR
　
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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(31)