d
As
the aircraft approaches the select&
altitude, an “adaptive” pitch rate command
will automatically guide the pilot through it at a
low
rate.
As
the aircraft reaches the selected
altitude, ALT HOLD
will
automatically engage,
“ALT
”
will light on the Annunciator Panel and
“ARM” will disappear on the
KAS
297.
The
command bars on the FCI will call for level
flight at the selected altitude.
If
autopilot is
engaged, the system will perform the required
maneuvers.
ALT ARM is disengaged by depressing
the ALT ARM button, by engaging ALT HOLD,
by
GS
capture, or selecting FLT DIR to OFF.
ALTITUDE HOLD (ALT HOLD)
Mode
This mode will cause a computed visual
pitch command on the FCI command bars to
hold the aircraft at the pressure altitude ex-
isting at the time it was activated.
The mode is activated either automa-
tically by the ALT ARM function, or manually
by depressing the ALT button
on
the Mode
Controller.
If
the autopilot is engaged,
it
will
auto-
matically hold the aircraft at that altitude.
The Vertical Trim switch may
be
used
to
adjust the selected altitude up or
down
at a
constant rate of
600
fpm without disengaging
the mode.This enables the
pilot
to conveniently
adjust the aircraft altitude
to
match resetting
of the altimeter, or
to
make short descent
segments during a nonprecision approach.
The ALT HOLD mode is cancelled by
automatic GlidesloDe caDture
or
selection of
ALT ARM, or GO-AROUND modes, or selec-
tion
of
FLT DIR to OFF.
MANUAL ELECTRIC
TRIM
Manual Electric Trim switch on the yoke
automatically disengages the AP (roll and
pitch, but not yaw) in all installations, but will
not affect the FD.
Use of the AP DlSClTRlM INTERRUPT
switch on the control wheel will disengage
the AP, Yaw Damper and, in some installa-
tions, the Flight Director.
It is important that you consult the
Flight Manual Supplement for your par-
ticular aircraft for detailed instructions.
CONTROL WHEEL STEERING
(CWS)
Mode
When the Autopilot is engaged, Control
Wheel Steering provides the pilot with the
capability for natural and convenient manual
maneuvering of the aircraft without the need
to
disengage and reengage the Autopilot, or
reselect any modes of operation.
The
CWS
mode is engaged by contin-
uous pressure on the CWS button, normally
located on the Ihft-hand horn of the control
wheel. Operation of the CWS button causes
immediate release of Autopilot servos and
allows the pilot to assume manual control,
FO
ALT
P
m
ru
t
I
t
d
while Autopilot control funsio6s and Pitch
Command and Altitude Hold modes are syn-
chronized
so
that, upon release of the CWS
mode button, the Autopilot will smoothly
reassume control of the aircraft
to
the
original lateral command and existing ver-
tical command.
Since all engaged modes remain coupled
(in synchronization) during operation of the
CWS mode, their annunciator lights will con-
tinue
to
show on the Annunciator Panel. The
CWS mode is not separately annunciated.
NOTE:
For system limitations refer to
your Flight Manual Supplement.
33
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