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both channels of the SPS computer are in agreement.
NOTE
The crew should initiate approved recovery techniques at the first
indication of an impending stall (i.e., recognition of proximity of
low-speed cue at airframe buffet, at autoignition, or any time the stick
shaker or pusher activates).
In the event of an AOA increase rate greater than one degree per second, the SPS computer
lowers the AOA trip points to activate the aural, visual and tactile indications at a lower AOA. This
prevents the aircraft’s pitching momentum from carrying it through the stall warning/stick pusher
sequence into the stall.
Stick Pusher Disconnect
The stick pusher subsystem is armed when both STALL PROT PUSHER switches, located on the
pilot and copilot side panels, are ON. An acceleration switch will disconnect the stick pusher to
prevent an unusual attitude, if less than +0.5 ’G’ is reached during pusher operation. The pusher
may also be disabled momentarily by pushing the AP/SP DISC button on the pilot’s or copilot’s
control wheels. This will disconnect the pusher only as long as either button is held in. In the event
of a malfunction, the stick pusher may be deactivated by switching either STALL PROT PUSHER
switch to OFF (located on the side panels). To enable pusher operation, both switches must be
returned to the ON position.
FLIGHT CONTROLS
Description
Vol. 2 10−10−18
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
STALL PROTECTION SYSTEM (CONT'D)
Stall Protection System − Schematic
Figure 10−10−12
NOTE
The stick shaker is always armed. The STALL PROT PUSHER
switches affect only the stick pusher function.
FLIGHT CONTROLS
Description
Vol. 2 10−10−19
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
STALL PROTECTION SYSTEM (CONT'D)
SPS Ground Testing
Preflight testing of the system is accomplished by SPS TEST switches on the miscellaneous
test panel, located on the center pedestal. Either L (R) SPS TEST switch will cause the system
to progressively sweep through the AOA range from no stall to full stall, as indicated on the SPS
test indicator, activating ignition (blue arc) and shaker/autopilot disconnect (yellow arc). This is
followed by red flashing STALL lights on the glareshield, and an aural warbler warning. If both
switches are activated simultaneously, the stick pusher will activate (red arc).
Pusher disconnects can then be tested by pushing, in sequence, the pilot’s AP/SP DISC, the
copilot’s AP/SP DISC and the G-switch.
CAUTION
See the Airplane Flight Manual for full testing procedures. Ignition
is activated during the test, and may pose a hazard in enclosed
areas.
CONTROLS AND INDICATORS
Primary and secondary flight controls and indicators are accessible from both pilot seats. Warning,
caution, advisory and status messages are presented on the primary flight display (PFD) and primary
and status pages of the engine indication and crew alerting system (EICAS).
FLIGHT CONTROLS
Description
Vol. 2 10−10−20
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Primary Flight Controls
Pitch, Roll and Yaw Controls
Figure 10−10−13
FLIGHT CONTROLS
Description
Vol. 2 10−10−21
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Stab Trim, Aileron Trim, Rudder Trim
Trim Controls
Figure 10−10−14
FLIGHT CONTROLS
Description
Vol. 2 10−10−22
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Flaps, Spoilers
Flap and Spoiler Controls
Figure 10−10−15
FLIGHT CONTROLS
Description
Vol. 2 10−10−23
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
Stall Protection System
Stall Protection System
Figure 10−10−16
FLIGHT CONTROLS
Description
Vol. 2 10−10−24
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
EICAS Flight Controls Indications
EICAS Flight Controls Indications (Ground Spoilers)
Figure 10−10−17
FLIGHT CONTROLS
Description
Vol. 2 10−10−25
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
CONTROLS AND INDICATORS (CONT'D)
　
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