Beechcraft C-12C Operator And Technical Reference Manual page 407

i. Disengaging the Autopilot. The autopilot is
normally disengaged by momentarily pressing the
control wheel AP DISC switch. The autopilot may,
however, be disengaged by any of the following:
1. Actuation of the control wheel AP DISC
button. Disengagement is confirmed by
five flashes of the AP ENG annunciator.
2. Pressing the respective vertical gyro
FAST ERECT button.
3. Actuation
INCREASE / DECREASE switch.
4. Selection
Disengagement is confirmed by the AP
ENG annunciator flashing five times and
illumination of the GA and YD ENG
annunciators.
5. Pulling the autopilot AP POWER circuit
breaker.
6. Pressing the autopilot AP ENGAGE push
button.
7. Transferring between pilot and copilot
flight directors.
Any of the following malfunctions will cause the
autopilot to automatically disengage.
8. Vertical gyro failure.
9. Directional gyro failure.
10. Autopilot power or circuit failure.
11. Torque limiter failure.
Disengaging under any of the last four conditions
will illuminate the AP DISC annunciator and the
flashing MASTER WARNING light.
control wheel AP DISC switch will extinguish the AP
DISC annunciator.
j. Elevator TRIM Annunciators. The elevator
trim annunciator indicates UP or DN when a sustained
signal is being applied to the elevator servo.
annunciator should not be illuminated when engaging
the autopilot.
of respective compass
of go-around mode.
Pressing the
Only the TCS button on the side that has
control of
changing the autopilot without canceling
the other pilot's GA mode.
k. Touch Control Steering (TCS). The TCS
push button located on the control wheel allows the
pilot to manually change aircraft attitude, altitude,
vertical speed, and/or airspeed without disengaging
the autopilot. After completing the manual maneuver,
the TCS push button is released, and the autopilot will
automatically resynchronize to the vertical mode. For
example, with IAS mode selected, the pilot may press
the TCS push button and manually change airspeed.
Once trimmed at the new airspeed, the TCS push
button is released and the autopilot will hold this
airspeed. If a large pitch attitude change is made, the
pilot should trim the aircraft normally before releasing
the TCS button while in the ALT hold mode.
3C-25. FLIGHT MANAGEMENT SYSTEM NO. 1
(FMS-800).
a. Description.
(1) System Overview.
management system provides global autonomous
guidance using GPS navigation. This FMS guidance
may be used to fly published airways, direct routing,
TACAN emulation procedures, and published non-
precision or autonomous GPS approaches, as well as
various mission patterns.
The FMS-800 permits pre-flight loading of 40
complete mission plans using a data cartridge. It also
permits the crew to generate or modify mission plans
on the aircraft, using a global International Civil
Aviation Organization (ICAO) data base of waypoints
and automatic flight plan calculations.
The FMS-800 also provides simplified crew
control of the communication radios.
The C-12 installation uses a single Control
Display Unit (CDU).
"designated pilot" in this manual refer to
pilot only.
The
(2) System Architecture.
shows a simplified diagram of the FMS-800 system.
The CDU provides access to all system functions for a
single crewmember.
between the FMS-800 and MIL-STD-1553B and non-
1553B aircraft systems.
TM 1-1510-218-10
NOTE
the autopilot will
The FMS-800 flight
NOTE
Any references to
Figure 3C-22
It also provides user interface
permit
3C-53