FLIGHT
DIRECTOR
Mode
(FD)
The Flight Director mode is activated by
depressing the "FD" button on the Mode
Controller
The FCI Command V-bar will appear
and provide the pilot with steering com-
mands to maintain wings level and the pitch
attitude that existed at the time of Flight Di-
rector engagement To fly the Command
V-bar, the pilot will bank and pitch the aircraft
to put the orange delta wing 'aircraft" into the
V-bar The command is satisfied when the
V-bar aligns symmetrically at the top of the
orange delta wing
If
pitch attitude is changed, recycling
the FD button will synchronize the Com-
mand V-bar to the new pitch attitude
If
a change only in the commanded pitch
attitude is desired, the Control Wheel Steer-
ing (CWS) button installed on the pilot's con-
trol wheel allows the pilot to synchronize the
Command V-bar (in the FD mode with Au-
topilot disengaged) without removing his
hand from the control wheel
The Flight Director can also be activated
by direct selection of any specific mode
which will activate the Command V-bar Such
selection will illuminate both FD and the ap-
propriate annunciator mode
Special note: The
FD
mode must be acti-
vated before the Autopilot can be engaged
The Vertical Trim switch may be used
to
adjust the selected pitch attitude up or down
at
1
degkecond
AUTOPILOT ENGAGEMENT (AP)
The Autopilot is engaged by movin the
solenoid-held AP switch on the Mode Eon-
troller to the
"ON"
position
CAUTION Prior
to
Autopilot engagement,
the pilot should make sure the V-bar com-
mands are satisfied This
wll
prevent any
hanges
in
the aircraft's flight path
e Autopilot
IS
engaged
The Autopilot provides two-axis (pitch
and roll) stabilization and automatic elevator
trim as well as automatic response to all
selected Flight Director commands
Installation of optional 3rd axis (rudder
command) will damp out yaw oscillations
and provide automatic tum coordination
Upon Autopilot disconnect, an Aural
Alerter will sound a Sonalert
for
2
to
2Y2
seconds while the AP light on the Annun-
ciator Panel flashes
FO
'Fi"
NAV
ARM
ALT
&''
HOG APPR
CPtD
GS
.
GA
m
I
ON
U
UP
AUTION: Overpowering the Autop
pitch axis
in
flight for periods of
3
seconds or
more will result in the autotrim systemoperat-
ing in the direction to oppose the pilot and
will, therefore, cause an increase in the pitch
overpower forces,
and
if
Autopilot is disen-
?aged, will result
in
a
pitch transient control
orce. Operation of the Autopilot
on
the
ground may cause the autotrim
to
run be-
cause of backforce generated by elevator
downsprings
or
pilot induced forces.
28
NOTE: For system limitations refer to your
Flight Manual Supplement.
Attitude Gyro Operation Note: When shut-
ting down the aircraft for short periods of
time, make sure the Attitude Gyro has com-
pletely spun down before starting opera-
tions again. Gyro spin down occurs when the
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