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CRS 2
PUSH DCT
210
Autopilot control authority:
· Roll rate is limited to ± 7.5°/sec.
· Pitch rate is ± 0.3 G in straight and level flight and maximum 0.7 G 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 Track (APPT) mode. When in APPT mode, the roll limits are
reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at 0 feet radio altitude.
· Pitch = ± 20°. In APPT mode, the nosedown
pitch limit is reduced below 300 feet programmed
by vertical rate and radio altitude.
AUTOMATIC FLIGHT CONTROL SYSTEM
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
04−10−7
AUTOPILOT DISENGAGE
Normal disengagement of the autopilot is accomplished by activating any of the following:
· AP button on guidance panel. AP
· 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.
Autopilot Quick
Disconnect Button
(DISC)
Touch Control
Steering (TCS)
Stabilizer
Trim Pilot’s Control Wheel GF0410_015
· TakeOff/
Go Around (TOGA) buttons on thrust levers.
Take−Off/Go Around
(TOGA) Button
GF0410_016
For a normal autopilot disengagement, AP1 or AP2 annunciator will change to a steady AP1 or AP2
for 2 seconds, then flash continuously and an aural “cavalry charge” will sound once. The
annunciation and aural can only be cancelled by depressing DISC button on either control wheel.
For an abnormal autopilot disengagement, (motor trip/failure or AFCS failure), AP1 or AP2 will flash
continuously and an aural “cavalry charge” will sound repeatedly. The annunciation and aural can
only be cancelled by depressing DISC button on either control wheel.
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
04−10−8
PFD ANNUNCIATION
The PFD will display the following AFCS information:
GF0410_017
AP engage status
Touch control steering (TCS) status
Flight director commands and status
Flight director data source (CPL)
Vertical speed reference
0.88 AP1 300 00
20 20
220
210
23500
0.88 TCS 300 00
20 20
220
210
23500
0.88 AP2 300 00
20 20
220
210
23500
160 ROL 3 000
20 20
AP1 WSHR
WIND
SHEAR
180
170
160
150
145
6
1500
1000
HDG
330
W
0 1000
1
1
2
3
12
E
24
21
s
15
33
30
3
VS 1000
2
3
N
6
AP1 AP
TCS
CPL
UP
PITC
H
VNAV
VS
DN
VS Speed
Readout
Pitch
Wheel
VS Target
Readout
VS Target
Bug
VS
Pointer
1000
VS 1000
0
1
2
3
1
ROL AP1 WSHR
Windshear
Windshear
Windshear
TOGA Buttons
AUTOMATIC FLIGHT CONTROL SYSTEM
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
04−10−9
PFD ANNUNCIATION (CONT'D)
GF0410_022
Overspeed warning
Armed lateral mode
Active lateral mode
Armed vertical mode
Active vertical mode
0.84 AP1 300 00
20 20
220 23500
VOR
VOR NAV
HDG
0.84 AP1 300 00
20 20
220 23500
VOR
VOR
VPTH
0.84 AP1 300 00
20 20
220
210
23500
VPTH
0.84 AP1 300 00
20 20
220
210
23500
VPTH
FLC
VPTH
VNAV
Active mode flashes
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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