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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 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−56
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 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−57
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. Examples of conditions leading to a stall warning advance are listed below.
· Slat malfunction
· Flap malfunction
· Flight in icing conditions with wing anti−ice off or failed.
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 or ice accumulation on the wing which cannot be dispersed). 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
to display the STALL WARN ADVANCE
mode of operation.
NOTE
Only pilot action can return the SPS from advance mode to normal
mode.
Pilot command interface on EMS/CDU:
· Command mode change from the control page.
· Either pilot’s EMS/CDU can command mode changes.
NOTE
The pilot cannot override advanced mode for detected failures.
Advanced mode indication on EICAS and EMS/CDU:
· “STALL WARN ADVANCE” EICAS advisory message.
· “ADVANCE” on EMS/CDU.
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−58
STALL SYSTEM PILOT ACTIVATED TEST (ON GROUND ONLY)
The pilot activated test is initiated by the pilot during preflight.
It takes approximately 20 seconds to
complete the test. The test is initiated through the EMS/CDU. Refer to Chapter 7 ELECTRICAL
SYSTEM for the pilot activated testing procedure.
SWITCH CONTROL 1/1
TEST
OFF
STALL TEST
AURAL WARNING TEST 2
FIRE TEST
AURAL WARNING TEST 1 OFF
OFF
STALL TEST:
button to initiate test. Test duration
Press the STALL TEST activation
approximately 20 seconds.
LAMP TEST 1 OFF
LAMP TEST 2 OFF
GF1010_070
The pilot activated test will accomplish the following:
　
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