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from selected PFD symbol generator. The data received includes:
IRS:
Roll angle Normal acceleration
Pitch angle Ground speed
Roll rate True track angle
Pitch rate Flight path angle
Yaw rate Magnetic heading
Longitudinal acceleration True heading
Lateral acceleration Inertial vertical speed
ADC:
Baro-corrected altitude True airspeed
Pressure altitude Dynamic pressure
Vertical speed VMO
Mach MMO
Calibrated airspeed
FMS:
Lateral steering command and flags VNAV submode selection flags
VNAV targets
FWC:
Preselected altitude
Display Controller (DC):
Speed references
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-6 For Training Purposes Only
Sept 04
AUTOPILOT ENGAGEMENT
Autopilot is engaged via the AP button on the guidance panel. When there are no
vertical or lateral mode active, the autopilot will engage in (PIT) and (ROL) FD
modes.
Autopilot control authority:
• Roll rate is limited to ± 7.5°/sec.
• Pitch rate
• ± 0.3 g’s in straight and level flight
• maximum 0.7 g’s pitch up in a turn
The autopilot can engage throughout the range:
• Pitch = ± 50°
• Roll = ± 75°
• Once engaged, the autopilot will reduce the pitch and roll angles below control
limits
Autopilot control limits:
• Roll = ± 35° except in Approach (APP) mode. When in APP mode, the roll limits
are reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at zero feet
radio altitude
• Pitch = ± 20°. In APP mode, the nose-down pitch limit is reduced below 300 feet,
programmed by vertical rate and radio altitude
CRS 2
PUSH DCT
Honeywell
AP FD
CPL
YD
AP
AP
CRS 2
PUSH DCT
Honeywell
AP FD
CPL
YD
GX_02_004
AP1
AP2
When selected, or will flash for
approximately 5 seconds, then steady.
AP1 AP2
20 20
10 10
ROL AP1 PIT 0.88 30000
23500
220
200
For Training Purposes Only
Sept 04
2-7
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
AUTOPILOT DISENGAGEMENT
Autopilot disengagement is accomplished by activating any of the following:
• AP button on guidance panel
• Autopilot quick-disconnect (DISC) button on either control wheel
• Manual stabilizer trim when touch control steering (TCS) not active
• YD button on FGC panel
• TCS button on either control wheel (while depressed).When the TCS button on
either control wheel is activated, the aileron and elevator servo clutches are
released, the autopilot is disengaged and the flight director is resynchronized.
Releasing the TCS button reengages the servo clutches and autopilot is engaged, if
within normal pitch and roll limits. Where applicable, the flight director modes
will react as if the autopilot had just been engaged
• Takeoff/Go Around (TOGA) buttons on thrust levers
• Motor trip/failure or AFCS failure
• Stick shaker acuation
The AP1 or AP2 annunciator will flash red continually and an aural “cavalry charge”
will sound repeatedly. The annunciation and aural can only be canceled by depressing
DISC on either control wheel.
NOSE
DN
NO SE UP
DISC
MASTER
TCS
GX_02_005
Stabilizer
Trim
Autopilot Quick
Disconnect Button
(DISC)
Touch Control
Steering (TCS)
PILOT’S CONTROL WHEEL
IC
R/T
GX_02_006
Takeoff/Go Around
(TOGA) Buttons
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-8 For Training Purposes Only
Sept 04
YAW DAMPER
The yaw damper provides stability augmentation and turn coordination for the
airplane yaw axis via two linear actuators, in series with the rudder control system.
The yaw damper function will automatically engage on the ground, within 3 seconds
after successful completion of AFCS power-up test. As with the autopilot, the yaw
damper operates in an active/standby configuration. When engaged, the active yaw
damper will center both linear actuators.
The YD will not automatically engage once the airplane is airborne. The YD button,
located on the guidance panel, may be used to reengage the YD. When YD is engaged,
the associated arrow on the guidance panel is illuminated.
One yaw damper must be engaged for autopilot operation. Autopilot engagement
without YD will occur only when both YDs have failed in flight.
　
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