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COMPONENTS AND OPERATION
There is a stick shaker on each control column and a single stick pusher mechanism attached to the left pitch control system.
A dual-channel stall protection system (SPS) computer monitors the following inputs:
- Angle of attack - L, R Angle-of-Attack (AOA) transducers (vanes)
- Lateral acceleration - Attitude Heading Reference Systems (AHRS)
- Flap position
- Weight-on-wheels - WOW 1 and WOW 2
- Mach and airspeed - ADC 1, ADC 2, and standby instrument
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual May 06/2005
10-02-14 CSP 100-6 REV 2
STALL PROTECTION SYSTEM (Cont)
The ADCs supply primary Mach data to the SPS computer for Mach compensation of the aircraft’s stall margin.
The SPS uses the above inputs to calculate the angle-of-attack trip points. The stick shaker activation and ignition activation
are simultaneous.
In the event of an AOA increase rate greater than 1 degree per second, the stall protection computer lowers the activation
trip point. This prevents the aircraft’s pitching momentum from carrying it through the stall warning/stick pusher sequence
to deep into the stall.
LH ANGLE OF
ATTACK SENSOR
CFO1006002_001
ANGLE OF ATTACK SENSOR
(TYPICAL)
RH ANGLE OF
ATTACK SENSOR
EV 2
FLIGHT CONTROLS
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6 10-02-15
STALL PROTECTION SYSTEM (Cont)
STICK PUSHER DISCONNECT FEATURES
The stick pusher can be stopped by pressing and holding either control wheel master disconnect switch (MSW). The stick
pusher is capable of operating immediately when the MSW switch is released. This function is inoperable on JAA approved
aircraft.
Should the SPS incorrectly activate the stick pusher, the stick pusher may be disabled by selecting the STALL PUSHER
switch to OFF.
MASTER DISCONNECT
SWITCH FOR AP, TRIM
& STALL PUSHER
MIC ID
CFO1006002_002
STALL
PUSHER
STAB
PRI
OFF
SEC
L R
RUD
TRIM
OFF
REV 2
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-02-16 CSP 100-6 REV 1
CONTROLS AND INDICATIONS
FLAP CONTROL LEVER
EICAS TRIM STATUS DISPLAY
CFO1005002_007
FLAPS
VFE
210
VFE
210
VFE
175
10
20
30
0
CFO1001002_010
TRIM
STAB AIL
LWD RWD
RUD
L R
NU
ND
6.6
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-02-17
CONTROLS AND INDICATIONS (Cont)
FLIGHT CONTROL SYNOPTIC PAGE
CFO0305002_012
CAS
CKLST SKIP
FRMT TFC TR/WX ENTER SUMRY
A/ICE FUEL HYD
L R
ECS
600 600
NI
MACH
HOLD
ITT
N2
OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM
APU EGT
FUEL QTY LBS
TOTAL 12000
6000 6000
START
START
STAB AIL
LWD RWD
RUD
NU
ND
6.6
GEAR
SPOILERS
CAB ALT
CAB RATE
7300
1000
UP
85.0 MCT 85.0 MCT TRIM
COM1 NAV1 ATC1/TCAS ADF1 HF1 COM3 COM2
118.000 108.00 1799.5 118.000 118.000
118.000 108.00 STBY 190.0 2.0000 118.000 118.000
ABV
TX
2.0000 AM
25 25
ELEC
1200
FLT
MFD CONTROL
FLIGHT CONTROLS
AILERON AILERON
ELEVATOR ELEVATOR
RUDDER
AUTO PLAN
SHLDR SIDE
UP
UP
L R
FLAPS 0
90.0 90.0
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-02-18 CSP 100-6 REV 1
EICAS MESSAGES
The flight controls messages are shown on the EICAS. The flight control messages, inhibits and aural alerts are listed below.
A brief explanation of each message is provided.
MESSAGE INHIBITS MEANING
AURAL
WARNING
CONFIG AILERON
TRIM
Aileron trim is not in the takeoff range (green
band)
“Configuration”
CONFIG AUTOPILOT Autopilot not configured for takeoff “Configuration”
CONFIG FLAPS Flaps not in takeoff position “Configuration”
CONFIG RUDDER
TRIM
Rudder trim is not in the takeoff range (green
band)
“Configuration”
CONFIG SPOILERS Spoilers is not in takeoff position “Configuration”
CONFIG STAB TRIM Elevator trim is not in the takeoff range (green
band)
“Configuration”
PARK/EMER BRAKE
ON
Emergency brake is engaged with throttles at
or above climb. The CAS will be accompanied
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