KING KFC 200 - KFC 200 Operating Modes and Procedures

KFC 200 System Integration
The adjacent system diagram shows
the components of the KFC
200 integrated
Flight Control Systemand their relationships.
The system has a number of input-
outputs: Sensor
ouv ’ ; Com-
putation input shown in blue; Display out-
puts shown in orange; Aircraft control
shown in green. All sensor information
(pitch and roll reference; Heading error or
course datum; RNAVNORlLOClGS de
viation and flags; Marker receiver and
static pressure (altitude) is fed into the
KC
295 Flight Computer.
The Flight Computer computes roll and
pitch steering commands. These
two com-
mands are routed to the KI 256 Flight Com-
mand Indicator, where they are displayed
on the V-bar as visual guidance commands.
These steering commands are also fed to
the Autopilot computation circuits con-
of pitch and roll commands.
Using the same pitch and roll com-
mands for Flight Director and Autopilot pro-
vides totally consistent Flight Director
steering command and Autopilot control.
There is no disagreement in computation.
The Autopilot simply converts the pitch and
roll steering commands from the Flight
Computer, displayed on the V-bar in the
FCI, into the required elevator and aileron
position commands.
Full integration of Flight Director and
Autopilot allows the pilot to delegate the
manual effort of flying the aircraft to the
Autopilot while monitoring its activity with
the Flight Director.
Modes of Operation Flight Director System
Headlng (HDG) , fly Director (FD) 7 Hdd (ALT)
Vertical
Trim
(Pitch Attitude/
Altitude)
-AutOpllOt (AP)
‘Approach (APPR)
/ (ILS, VOR or RNAV)
Navigate (Nk
(VORIRNAV) REV LOC (BC)
Flight Director Mode Flight Director Guidance-. .
Attitude Reference
and Command to Autopilot
Power on and no modes selected. FCI
displays aircraft attitude and PNI dis-
plays aircraft heading. Command V-bar
is biased out of view. Aircraft engine must
be running for pressure to be applied to
FCI attitude gyro.
Flight Director (FD)
Command V-bar will appear and com-
mand wings level and pitch attitude of the
aircraft at the time of mode selection.
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