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As the trip point is approached, continuous ignition is activated. If the AOA continues to increase, the stick shaker activates and the autopilot disengages. If the AOA still continues to increase, the stick pusher activates, along with red STALL annunciation displayed left of the ADI, and Master Warning lights on the glareshield, and a warbler aural warning. The stick pusher only activates when the signals from 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.
NOTE
The stick shaker is always armed. The STALL PROT PUSHER switches affect only the stick pusher function.
FLIGHT CONTROLS Description Vol. 2 10.10.18
Oct 05/06
Stall Protection System . Schematic
Figure 10.10.12
FLIGHT CONTROLS Description Vol. 2 10.10.19
Oct 05/06
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 the 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 annunciation on the PFD, 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.
See the Airplane Flight Manual for full testing procedures. Ignition is activated during the test, and may pose a hazard in enclosed areas.
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