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preselect. Pitch information is derived from a pressure sensor and accelerometer. The KAP 140
Autopilot System operates independent of the airplanes´s attitude gyro (artificial horizon). Internal
monitors keep constant track of the KAP 140´s status and provide for automatic shutdown of the
autopilot or trim system in the event of a malfunction.
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 2
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
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Figure 1: Autopilot System Schematic
AIRCRAFT
DA 40 Series
AMM
Auto Flight
Doc # 6.02.01
Rev. 5 22-10-00 Page 3
20 Sep 2007
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% Figure 2: Autopilot System Schematic Diagram (if OÄM-40-267 is carried out)
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 4
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
A. Bendix/King KAP 140 Flight Control Computer
% Figure 3 shows the Bendix/King KAP 140 flight control computer. It is located in the avionics rack
in the instrument panel, see Section 31-10.
The Bendix/King KAP 140 has the following annunciators on the front panel, above the AP button:
) 'P' (pitch axis) annunciator. It indicates failure of the pitch axis and will either disengage the
autopilot or does not allow engagement of the pitch axis. The 'P' annunciator may illuminate with
the autopilot disengaged. This condition can occur during maneuvering flight when g thresholds
are exceeded. The autopilot monitor will not allow engagement during illumination.
) 'R' (roll axis) annunciator. It indicates failure of the roll axis and will disengage the autopilot or
does not allow engagement.
The Bendix/King KAP 140 controls the following annunciator on the annunciator panel (also see
Section 31-50):
) TRIM FAIL annunciator. It illuminates whenever the automated preflight self test detects a pitch
trim fault or a continuous monitoring system detects a pitch trim fault in flight. (Located on the
White Wire annunciator panel.) Refer to the EMERGENCY PROCEDURES for proper response
to a pitch trim fault.
The Bendix/King KAP 140 has a display which shows the following:
) Pitch and roll mode displays. Displays the active pitch modes (VS, ALT, ARM, ALT, GS ARM,
GS) and roll modes (ROL, HDG, NAV ARM, NAV, APR ARM, APR, REV ARM, REV). Also
displayed will be a flashing AP annunciation (5 seconds) at each autopilot disconnect,
accompanied by an aural alert (for 2 seconds).
) PT (pitch trim) annunciation. It indicates the direction of required pitch trim. With electric trim
installed, the annunciation simply provides status to the autopilot request for auto trim. A solid
indication represents the lowest demand level for trim, whereas a flashing annunciation implies
a greater demand. A solid PT annunciation without an arrow head is an indication of a pitch trim
fault. During MET operation, this annunciation can be caused by a stuck MET switch. If the
stuck switch fault clears, trim operation will resume.
AIRCRAFT
DA 40 Series
AMM
Auto Flight
Doc # 6.02.01
Rev. 5 22-10-00 Page 5
20 Sep 2007
APR VS 10.500
GS A
R
M
A
R
M
PT
ALT ALERT FT
P R
BENDIX/KING
KAP 140
Pitch Axis
Annunciator
Roll Axis
Annunciator
Autopilot
Engage/Disengage
Button
Navigation Mode
Selector Button
Back Course
Approach Mode
Selector Button
Vertical Trim
Buttons
Baro Set
Button
Altitude Arm
Button
Altitude Alert
Annunciation
Pitch and Roll
Mode Displays
Altitude Alerter/
Vertical Speed/
Baro Setting
Display
Pitch Trim
Annunciation
Heading Mode
Selector Button
Mounting
Screw
Approach Mode
Selector Button
Altitude Hold
Mode Selector
Button
Rotary Knobs
% Figure 3: Bendix/King KAP 140 Flight Control Computer
AIRCRAFT
Auto Flight DA 40 Series
AMM
Page 6
20 Sep 2007 22-10-00 Doc # 6.02.01
Rev. 5
) ALERT (altitude alert) annunciation. This annunciation is only used when the altitude preselect
option is installed.
) It illuminates continuously in the region of from 200 to 1000 feet from the selected altitude
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钻石40系列AMM 1(84)
