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AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual
CSP A--013
MASTER
The autopilot can be disengaged manually by any of the following:
S Pushing either AP/SP DISC switch on the control wheels
S Pushing the AP ENG switch on the flight control panel
S Lowering the AP DISC switch-bar on the flight control panel (a red line becomes visible)
S Operating either stabilizer trim switch on the control wheels
S Pressing either TOGA switch on the thrust levers
S Switching to the standby FCC
S Pressing the yaw damper DISC pushbutton on the yaw damper panel.
Disengagement of the autopilot causes a cavalry charge aural alert to sound and the AP
indication on the primary flight display (PFD) turns red. The autopilot disengage warning will
automatically cancel, after approximately two repetitions of the cavalry charge, when a
disengagement is mutually induced.
REV 56, Jan 31/03
Vol. 1 03--30--4
AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual MASTER
CSP A--013
Autopilot --- Controls
Figure 03---30---2
Flight Control Panel
AP DISC Center Glareshield
Lowering bar disengages autopilot.
Red line becomes visible.
Pilot’s Control Wheel
(Copilot’s Opposite)
AP / SP DISC (red)
When pressed, disengages
autopilot and deactivates
stick pusher. When
released, stick pusher
system is immediately
reactivated, but autopilot
remains disengaged.
CAVALRY
CHARGE
Take--Off/ Go--Around
(TOGA) Switches
Momentary pushbutton
switches associated with
the take--off/ go--around
mode of the flight director.
Yaw Damper Panel
Center Pedestal
DISC
Used to disengage
yaw dampers.
Vol. 1 03--30--5
REV 56, Jan 31/03
AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual
CSP A--013
MASTER
Automatic AP disengagement occurs if:
S Both yaw dampers are disengaged or fail
S A failure condition is detected by the FCC monitoring circuits
S Stick shaker is activated
S Excessive attitude occurs (roll beyond 45 degrees or pitch beyond 25 degrees nose--up
or 17 degrees nose--down)
S Two seconds after a windshear warning (if the autopilot has not already been
disengaged). During those two seconds, the autopilot will follow the windshear
commands.
In the event that the autopilot is disengaged due to a system fault, pressing the AP/SP DISC
switch or either TOGA switch will cancel the red flashing AP indication on the PFD and
silence the aural warning.
The automatic flight control system monitors both axes of the autopilot when engaged. If a
control surface is detected to be significantly out of trim, an indication will appear on the PFD
and a caution message will be displayed on the EICAS primary page to indicate in which
direction that the control surface is out of trim.
Autopilot --- PFD Flags <MST>
Figure 03---30---3
Primary Flight Display
Pilot’s and Copilot’s Instrument Panels
Aileron Mistrim Indicator (yellow)
Iindicates that the ailerons are in a
mistrim condition, when the autopilot
is engaged.
Elevator Mistrim Indicator (yellow)
Indicates that the horizontal stabilizer
is in a mistrim condition, when the
autopilot is engaged.
<0015>
E
A
REV 56, Jan 31/03
Vol. 1 03--30--6
AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual MASTER
CSP A--013
Autopilot --- EICAS Messages <MST>
Figure 03---30---4
CONFIG AP
Primary Page
<0039>
<0006>
Status Page
YD 1 INOP
YD 2 INOP
YAW DAMPER
AP TRIM IS LWD
AP TRIM IS NU
AP TRIM IS RWD
AP PITCH TRIM
AP TRIM IS ND
YD 1, 2 INOP Status
(white)
Comes on to indicate
that either yaw damper
channel is inoperative.
AP PITCH TRIM Caution (amber)
Comes on to indicate a failure in the
autopilot pitch trim system.
AP TRIM IS LWD Caution (amber)
Comes on to indicate an out--of--trim
condition in the roll axis (left wing down).
AP TRIM IS NU Caution (amber)
Comes on to indicate an out--of--trim
condition in the pitch axis (nose up).
AP TRIM IS ND Caution (amber)
Comes on to indicate
an out--of--trim condition
in the pitch axis (nose down).
AP TRIM IS RWD Caution (amber)
Comes on to indicate an out--of--trim
condition in the roll axis (right wing down).
YAW DAMPER Caution (amber)
Comes on when both yaw damper channels
(1 & 2) are off or when all IAPS input busses
　
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