Honeywell Bendix/King KFC 225 Pilot's Manual page 8

System Operation
14. SELECTED ALTITUDE/VERTI-
CAL SPEED DISPLAY - Normally
displays the selected altitude. The
display indicates the reference verti-
cal speed in FPM for 3 seconds after
the CWS button or the UP or DN
button is pressed and the VS mode
is engaged.
15. ALTITUDE ALERT (ALERT)
ANNUNCIATION - Illuminates as a
solid alert in the region from 1000 to
200 feet from the selected altitude if
the airplane was previously outside
of this region. Flashes (1) for two
seconds the first time the airplane
crosses the selected altitude and (2)
flashes continuously in the 200 to
1000 feet region if the airplane was
previously inside of this region (i.e.
at the selected altitude). An aural
alert consisting of five short tones is
associated with the visual alerting.
This aural alert occurs 1,000 feet
before a selected altitude while
approaching it and 200 feet after
leaving a selected altitude.
16. PITCH TRIM (PT) ANNUNCIA-
TION - A flashing PT with an
accompanying arrow head is an indi-
cation that the request for auto trim
has lasted longer than 16 seconds.
A solid PT without an arrowhead is
an indication of a pitch trim fault. A
trim runaway will generate the solid
PT annunciation, a remote TRIM
FAIL annunciation and a continuous
alert tone. Refer to the EMER-
GENCY PROCEDURES in the air-
plane Flight Manual Supplement for
proper response to a pitch trim fault.
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KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
17. PITCH AND ROLL MODE,
AUTOPILOT AND YAW DAMPER
ANNUNCIATIONS - Displays the
active flight director pitch modes
(PIT, VS, ALT ARM, ALT CAP, ALT,
GS ARM, GS, GA, and roll modes
(ROL, HDG, NAV ARM, NAV, APR
ARM, APR, REV ARM, REV).
Displays when the autopilot (AP)
and yaw damper (YD) are engaged.
Also displayed will be a flashing AP
annunciation (5 seconds) at each
autopilot disconnect accompanied
by an aural tone (for 2 seconds).
18. YAW DAMPER (YD) BUTTON
(optional) – When pressed will
engage or disengage the yaw
damper independent of autopilot
operation. (The yaw damper
engages automatically when the
autopilot is engaged; however, the
yaw damper may then be disen-
gaged or reengaged as desired.)
19. AUTOPILOT DISCONNECT
(AP DISC/TRIM INTER) SWITCH
(not shown) - When pressed will
disengage the autopilot and yaw
damper if installed, and interrupt
electric trim power. (Located on the
left horn of the pilot's control wheel.
The switch is red in color.) May also
disengage the flight director depend-
ing on how the system is configured.
20. MANUAL ELECTRIC TRIM
SWITCHES (not shown) - When
both switches are pressed in the
same direction, will activate pitch
trim in the selected direction. If only
one switch is moved, the trim system
Rev. 0
Apr/99
will not operate. If one switch fails or
is moved and held for 3 seconds, the
trim monitoring system will detect a
switch failure resulting in a PT
annunciation on the autopilot display
and the disabling of the electric trim
system. Use of manual electric trim
during autopilot operation will disen-
gage the autopilot. (Located on the
pilot's control wheel.)
21. CONTROL WHEEL STEERING
(CWS) MODE BUTTON (not shown)
- When pressed and held, disen-
gages the pitch, roll, yaw, and pitch
trim clutches allowing the pilot to
maneuver the airplane by hand.
Pressing the CWS button will also
sync the automatic flight control sys-
tem PIT, ROL, ALT or VS com-
mands to the actual attitude, altitude
or vertical speed present at the time
the button is released. ROL will
maintain wings level if CWS is
released at less than 6° bank angle.
(Located on the left horn of the
pilot's control wheel.)
22. GO AROUND (GA) MODE
BUTTON (not shown) – When
pressed will engage the flight direc-
tor in a pitch up attitude and wings
level (ROL mode). GA will disen-
gage the autopilot, and cancel all
armed modes including an armed
altitude preselect. Lateral modes
such as HDG or NAV ARM may
subsequently be added. The autopi-
lot may subsequently be engaged.
Modification to the commanded pitch
attitude such as through the UP/DN
button or CWS, etc. will cancel GA
and revert to pitch altitude hold.
(Located on the engine throttle).
Rev. 0
KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM
Apr/99
System Operation
23. OMNI BEARING SELECT
KNOB - Selects the desired course
to be tracked by the autopilot
(Located on the HSI.)
24. HEADING SELECT KNOB -
Positions the heading bug on the
compass card (Located on the HSI.)
25. TRIM FAIL ANNUNCIATOR
(not shown) - Illuminates whenever
the automated preflight self-test
detects a pitch trim fault or a continu-
ous monitoring system detects a
pitch trim fault in flight. (Located on
the instrument panel. The annuncia-
tor is red in color.) Refer to the
EMERGENCY PROCEDURES in
the airplane Flight Manual
Supplement for proper response to
a pitch trim fault.
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