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disconnect button is held for longer than 2 to 3 seconds.
The stick pusher will not be stopped by pressing and holding the autopilot/stick pusher disconnect
(AP/SP DISC) switch.
NOTE
The remaining stall warning functions are available with the disconnect button held. All other SPS
functions operate normally.
· Airplanes 9002 thru 9999 not incorporating Service Bulletin:
· SB 700−27−025, Stall Protection − Disable Stick Pusher Cancel Function from Autopilot
Master Disconnect Switch for JAA Aircraft.
The stick pusher may be stopped by pressing and holding the autopilot/stick pusher disconnect
(AP/SP DISC) switch.
The SPC will remove power to the actuator as long as either switch is activated and the push will
be cancelled. The stick pusher is capable of operating immediately once the AP/SP DISC switch
is released and a stall push is requested by the computer.
The remaining stall warning functions are available with the disconnect button held. Only the
pusher function is disabled with either switch held. All other SPS functions operate normally.
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−53
STALL PROTECTION COMPONENTS (CONT'D)
Stall Pusher On/Off Switches
The stall pusher “ON/OFF” switches are used for long term disabling of the pusher system. The
switches are located on the pilot and copilot side panels.
NOTE
Selecting either stall pusher switch to “OFF” will cause a “STALL
PROTECT FAIL” caution message to be displayed.
STICK
PUSHER
SYSTEM
PILOT’S SIDE PANEL COPILOT’S SIDE PANEL
In the event of a malfunction, the stick pusher may be disabled by selecting the PUSHER switch to
the “OFF” position on the pilot or copilot’s stall protection panel. When either or both switches are
selected to “OFF” the SPC cannot command a push.
STALL PROTECTION OPERATION
In flight the stall protection computer uses numerous system inputs to calculate the angle of attack
trip points. As a high angle of attack is approached:
· Ignition is activated.
If the angle of attack continues to increase:
· The stick shakers are activated.
· Autopilot disengages.
·
" STALL "
· Voice advisory sounds.
If the angle of attack continues to increase:
· The pitch disconnect system will lock.
· The stick pusher mechanism is activated.
FLIGHT CONTROLS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
10−10−54
STALL PROTECTION OPERATION (CONT'D)
This results in both control columns advancing to the full forward limit to correct the stall condition.
· The word “STALL” appears in a red box on the attitude sphere during the push phase.
Stall Annunciation
Primary Flight Display
GF1010_068 The stall annunciation shall initially blink at a
rate of 1
second on and ½
seconds off for 5
seconds
and then shall remain steady.
When stall has been corrected the SPC will cancel:
· The push and pitch disconnect locking mechanism.
· “STALL” on the attitude sphere.
· Voice advisory.
· Stick shakers.
· Ignition.
FLIGHT CONTROLS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
10−10−55
STALL WARNING ADVANCE
In specific conditions the SPC will cause warnings to occur sooner than normal. The stall warning
advance system will advance the stick shaker firing angles through the SPC when these conditions
are sensed. Events which may lead to a stall warning advance are icing conditions during antiice
fail
(indicated from the bleed management controller), slats failed in or stall protection system failure
cases.
The pilot has an interface through the Electrical Management System (EMS)/Control Display Unit
(CDU) to select the stall warning advance for undetected failures (example: damage of slat panel due
to bird strike). Either pilot’s EMS/CDU can command mode changes from the control page 1/2. Once
selected it can only be canceled by pilot input. The two modes of operation selectable on the
EMS/CDU are “NORM or ADVANCE”.
SWITCH CONTROL 1/2
NORM
ON
STALL WARN ADVANCE
RIGHT FOOTWARMER
SLAT/FLAP RESET
LEFT FOOTWARMER ON
OFF
STALL WARN ADVANCE:
from control page 1/2.
Select the mode " N O R M o r A D V A N C E "
Select the SYSTEM CONTROL page
　
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