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F. BJ6 bus bar
BJ6 bus bar is electrically supplied by "BUS 2" bar via the autopilot master switch. It distributes 28 VDC to the different components constituting the autopilot system.
BJ6 bus bar is protected by the "A / P" circuit breaker.
BJ6 bus bar is located behind the circuit breaker panel.
4. OPERATION
NOTE : For equipment operation and maintenance, refer to the supplier's Maintenance Manual.
AHAG
Validity : KAP 150 without EFIS 22-12-00Page 8
(DE) DEC 99
 
Variante de localisation Alternate location
 
 
14221400AAAAWZ5001 ® 

Autopilot — Identification and location of components
Figure 2
 

  A — "AP DISC TRM INT push—button"
B — "TRIM UP DN" dual inverter
C — "CWS" push—button

14220000AAA0YZ5004 

Autopilot — Identification and location of components
Figure 3
 
®
 
®
14221400AAABWZ5000 

Autopilot — Identification and location of components
Figure 4
AHAG
Validity : KAP 150 without EFIS 22-12-00Page 1 I
(DE) DEC 99
 
Variante de localisation Alternate location
 
 
Autopilot — Identification and location of components
Figure 5
AHAG
Validity : KAP 150 without EFIS 22-12-00Page 12
(DE) DEC 99
 
AUTOPILOT
DESCRIPTION AND OPERATION
1. GENERAL (Figures 1 and 1A)
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 A111 demodulator,
— control push—buttons of the pilot control wheel,
— an AUTOPILOT MASTER switch,
- a warning buzzer (autopilot sonalert).
The autopilot system also uses the K103 relay, the K109 relay (if installed) and the R82 equipped resistor plate located on PL100 panel — refer to 34-28-00.
The autopilot system also uses information from :
— either the Attitude Director Indicator or 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,
　
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