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provides the flight guidance signals to drive the servos. Both flight guidance computers must be operational for the autopilot
to function.
Upon occurrence of any single failure, the autopilot will not:
- Cause significant displacement of the aircraft from its approach path or altitude loss below the nominal glide path
- (Upon system disconnection) Involve any out-of-trim condition not easily controlled by the pilot
- Cause any action to occur with the flight control system that is not readily apparent to the pilot, either by control
column movement or advisory display
The automatic flight-control system (AFCS) consists of dual-independent flight directors, a three axis autopilot, and automatic
pitch trim and yaw damper system.
The AFCS operates with the integrated-avionics processor system (IAPS). The IAPS collects the data for the avionics systems.
The AFCS gives the course, heading, and preselected altitude data to the electronic flight instrument system (EFIS).
The AFCS calculates the vertical and lateral flight-guidance commands to keep the aircraft on the correct pitch/roll attitude.
The flight directors show the flight-guidance commands on the primary flight displays.
ENGAGEMENT PARAMETERS
The autopilot can be engaged using the AP switch on the FGP, if the following conditions exist:
- Yaw damper is operable
- Both flight guidance computers (FGCs) are serviceable
- At least one channel of the horizontal stabilizer trim is engaged and the FCCs detect no faults with the horizontal
stabilizer trim system
- No significant instability of the aircraft exists
COMPONENTS AND OPERATION
AUTOPILOT ENGAGEMENT
The autopilot is engaged by pressing the AP switch located on the flight guidance panel. When the autopilot is engaged,
both channels of the autopilot are coupled to the onside flight guidance computer. Autopilot engagement is indicated on the
PFD by a green AP indication.
Pressing the AP switch on the FGP when the autopilot is engaged will cause the autopilot to disengage.
AUTOPILOT SERVO MOTORS
When the autopilot is engaged, the controlling FGC directs pitch and roll commands to the aileron and elevator servos.
When a change in roll or pitch attitude is required, the FGC signals the aileron servo or elevator servo to bias the control
cables to move the associated control surface.
The aileron servo is located on the control cable run for the right aileron. Since the left and right ailerons are normally interconnected,
the servo is capable of moving both ailerons. The elevator servo is located in the left elevator cable run. The
servo moves both elevators when the elevators are interconnected.
When an out-of-trim condition is sensed in the pitch axis, the FGC signals the horizontal stabilizer trim control unit to reposition
the horizontal stabilizer.
AUTOMATIC FLIGHT CONTROL SYSTEM
Volume 2 Flight Crew Operating Manual May 06/2005
04-01-22 CSP 100-6 REV 2
AUTOPILOT (Cont)
20
DUAL RVDT (A)
(B)
DUAL RVDT (A)
(B)
DUAL RVDT (A)
(B)
SINGLE RVDT
SINGLE RVDT
LVDT (ANALOG)
LVDT (ANALOG)
LVDT (ANALOG)
LVDT (ANALOG)
RDC
CH A CH B
FCU-2
FLAPS OVERRIDE
(FROM FCU)
28VDC
TRIM SELECT
SWITCH
RELAY
PILOT MANUAL
TRIM SWITCH
COPILOT MANUAL
TRIM SWITCH
PILOT MASTER
DISCONNECT
COPILOT MASTER
DISCONNECT
PRI/OFF/SEC
SWITCH
MCU
CH 1
MCU
CH 2
RELAY
HSTECU
(COMMAND)
HSTECU
(MONITOR)
SECONDARY
R AHC R ADC
R DCP
B-DCU-1(HS) SVO
R-MFD-1(HS)
R-PFD-1(HS)
R-IOC-1(HS)
R-GPBUS-5 (HS)
R AFD
B-RDC-5
B-RDC-1/2
A-RDC-5
A-RDC-1/2
DCU
CH
A
CH
B
L AFD
R IOC R FGC
YD
SVO
SVO
L IOC L FGC
L AHC L ADC
FGP
CH
A
SPC
PILOT'S PITCH
DISCONNECT
(HANDLE ON
THROTTLE)
THROTTLE
QUAD/
CONTROL
WHEEL
PILOT'S ROLL
DISCONNECT
(HANDLE ON
CONTROL WHEEL)
FCU
FCU-2
TO RDC
CH
B
SPC
L DCP
L ELEVATOR
SURFACE POS
L AILERON
SURFACE POS
RUDDER
SURFACE POS
R AILERON
SURFACE POS
R ELEVATOR
SURFACE POS
PILOT CONTROL
WHEEL FORCE
PILOT RUDDER
PEDAL FORCE
COPILOT RUDDER
PEDAL FORCE
COPILOT CONTROL
WHEEL FORCE
A-DCU-1(HS)
L-PFD-1(HS)
L-IOC-1(HS)
L-MFD-1(HS)
PRIMARY PITCH
PRIMARY ROLL
PRIMARY YAW
PRIMARY PITCH
PRIMARY ROLL
PRIMARY YAW
　
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