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AP ENG
PUSH
CANCEL
PUSH
DIRECT
P604_04_030
Turbulence Mode Button
AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03
4-9
P I LOT T R A I N I N G GU I D E
Autopilot Disengagement
Manual (Pilot Action) Disengagement
The autopilot is normally disengaged by pressing the red autopilot/stick pusher (AP/
SP DISC) disconnect button on the outboard horn of either control wheel.
The autopilot may also be manually disengaged by any one of the following actions:
• lowering the AP DISC switch-bar on the FCP
• pushing the AP ENG button on the FCP
• selecting Takeoff or Go-Around (TOGA) button
• operating either stabilizer trim switch
• pressing the Yaw Damper DISC switch, or
• switching the AFCS SEL selector to the other AFCS (1 or 2)
Whenever the autopilot is manually disengaged (by pilot action) the PFD green
engage annunciation turns red and flashes for 5 seconds, the green status indicator
lights beside the AP button extinguish, and the autopilot disconnect (cavalry charge)
aural sounds. The autopilot disconnect warning will automatically cancel, after a few
repetitions of the cavalry charge.
Monitored Disengagement
The FCCs continually monitor aircraft sensors, servo data, the automatic pitch trim
system and internal parameters for faults. The autopilot will automatically disengage if
any of the following conditions occur:
• internal monitors detect a failure in any axis
• any power source to the FCCs is lost
• loss of either inertial reference system (IRS) system input
• dual yaw damper failure
• aircraft is at an excessive attitude (pitch angle beyond +25° or -17°, roll angle
beyond ± 45°), or
• either stick shaker activates
A monitored disengagement is annunciated in the same manner as a manual
disengagement with the exception that the flashing on the PFD and the aural warning
will continue until canceled by the flight crew. Pressing either pilot’s AP/SP DISC
switch or TOGA button, or reengaging the autopilot will cancel the flashing on the
PFD and the aural warning.
AUTOMATIC FLIGHT CONTROL SYSTEM
4-10 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Yaw Damper System
Description
Each yaw damper is a dual-channel, fully independent yaw damper system providing
yaw damping, turn entry, steady-state turn coordination, and turn exit for the full flight
envelope.
The yaw dampers operate independently of the autopilot.
The yaw damper will not compensate for a sustained adverse
yaw created by an engine power asymmetry or improper rudder
inputs.
Components and Operation
Yaw Damper Engagement
The yaw dampers are engaged by pushing both YD 1 and YD 2 switch/lights on the
YAW DAMPER Panel. Selective engagement of the switch/lights activates the
corresponding yaw damper channel. Yaw damper engagement is indicated by the
absence of yaw damper (status and caution) EICAS messages and PFD indications.
Normally, both yaw dampers are engaged for all phases of flight. One yaw damper
channel will provide adequate yaw damping and turn coordination during flight.
Yaw Damper Disengagement
The DISC button on the YAW DAMPER Panel disengages both yaw damper channels
when pressed. When both yaw damper channels are disengaged, an amber YD
annunciation is displayed on the upper left side of the PFDs, and a YAW DAMPER
caution EICAS message appears.
A single disengaged (or inoperative) yaw damper channel is indicated by a YD 1(2)
INOP status EICAS message.
NOTE
AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
Jan 04
4-11
P I LOT T R A I N I N G GU I D E
Yaw Damper Panel
Figure 4-6
Yaw Damper Disengage Annunciation
Figure 4-7
ENGAGE
YAW DAMPER
DISC
YD 1 YD 2
P604_04_032
7000
5000 1.0
10
10
MDA
A
A
HDG
A
DR ALTS
A
YD
2500M 4
4
2
2
1
1
200
29.92 IN
P604_04_034
0 FT
60
40
VT 150
V2 133
VR121
V1 113
0
200
300
000
100
2
1
100
AUTOMATIC FLIGHT CONTROL SYSTEM
4-12 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Flight Directors (FDs)
Description
The flight directors (FDs) are the visual representation of the commands generated by
the flight control computers.
The flight directors provide pitch and roll guidance by means of inverted V-shaped
　
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