mode selector. If VS or IAS are
not selected, the pitch wheel
works as described above. The
pitch wheel is always disabled
during a coupled glide slope.
BANK LIMIT PUSHBUTTON/
Selection of the Bank Limit mode
on the autopilot controller pro-
vides a lower maximum bank
angle while in the Heading Select
mode. LOW will illuminate on
the Bank Limit switch. The lower
bank limit is inhibited and LOW
is extinguished during NAV mode
captures. If Heading Select is
again engaged, Bank Limit will
again be illuminated. Pressing
Bank Limit when illuminated will
return autopilot to normal bank
SOFT RIDE PUSHBUTTON/
ANNUNCIATOR SWITCH. Soft
ride reduces autopilot gains while
still maintaining stability in rough
air. This mode may be used with
a n y F l i g h t D i r e c t o r m o d e
TURN KNOB. Rotation of the
turn knob out of detent results in
a roll command. The roll angle is
proportional to and in the direc-
tion of the turn knob rotation. the
turn knob must be in detent (cen-
ter position) before the autopilot
can be engaged. Rotation of the
turn knob cancels any other previ-
ously selected lateral mode.
YAW DAMP SWITCH. When
the autopilot is not engaged, the
yaw damper may be utilized by
depressing the YD ENGAGE
AP ENGAGE PUSHBUTTON/
ANNUNCIATOR SWITCH. The
AP ENGAGE switch is used to
engage the autopilot. Engaging the
autopilot automatically engages
the yaw damper. The autopilot
may be engaged with the airplane
in any reasonable attitude.
ELEV TRIM ANNUNCIATORS.
The elevator trim annunciator
indicates UP or DN when a
sustained signal is being applied
illuminated when engaging the
(3.) Autopilot Disengagement. The autopi-
lot is normally disengaged by momentarily depress-
ing the control wheel AP DISC switch. The autopilot
may however be disengaged by any of the following:
Actuation of the control wheel AP
DISC button. Disengagement is
confirmed by 5 flashes of the AP
Pressing the respective vertical
gyro FAST ERECT button.
Actuation of respective compass
Selection of Go-Around mode.
Disengagement is confirmed by
the AP ENG annunciator flashing
5 times and illumination of the
GA and YD ENG annunciators.
Pulling the autopilot CONTROL
& AFCS DIRECT circuit breaker.
Actuation of the manual electric
Any of the following malfunctions
will cause the autopilot to auto-
Vertical gyro failure.
b. Directional gyro failure.
Autopilot power or circuit
d. Torque limiter failure.
Disengaging under any of the previous
four conditions will illuminate the AP
DISC annunciator and the MASTER
WARNING light. Pressing the control
wheel AP DISC switch will extinguish the
AP DISC annunciator.
(4.) Pitch Sync & Control Wheel Steering
(CWS). The CWS push button located on the control
wheel (fig. 2-17) allows the pilot to manually change
aircraft attitude, altitude, vertical speed and/or air-
speed without disengaging the autopilot. After com-
pleting the manual maneuver, the CWS pushbutton
is released, and the autopilot will automatically