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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.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
STALL SYSTEM PILOT ACTIVATED TEST (ON GROUND ONLY)
The pilot activated test is initiated by the pilot during pre-flight. 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.
The pilot activated test will accomplish the following:
.
Checks each shaker individually.
.
Checks audio and visual warnings.
.
Activates and monitors pitch disconnect lock for proper operation.
.
Checks pusher for activation only under correct conditions (computer logic).
.
Simulates a stall event and verifies AOA serviceability electronically (no AOA movement).
.
Pushes both columns forward at the end of test.
Stall Protection Computer
A dual-channel stall protection computer (avionics bay) monitors the following inputs:
.
LH, RH Angle-of-attack (AOA) transducers . Angle of attack
.
LH, RH Lateral accelerometers . Lateral acceleration
.
LH, RH Flap/slat . Flap/slat position
.
#1, #2 weight on wheels (WOW) . WOW and SPS inhibit
.
#1, #2 and #3 ADC, MACH Transducer . Airspeed, altitude and Mach
.
Inertial Reference Unit (IRU) . Normal and lateral acceleration
.
WOW Fail . Weight on wheels
The SPC receives data input from the bleed management controller, landing gear electronic control unit, heater brake monitor unit and EMS CDU through the data acquisition units. The EGPWS uses the AOA for windshear requirements.
Low speed awareness output is a function of the SPC to the Electronic Flight Instrument System (EFIS).
. Red line . Shaker or stall warning speed.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
STALL PROTECTION COMPUTER SCHEMATIC
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
STALL PROTECTION EICAS MESSAGES
STALL PROTECT FAIL
STALL WARN ADVANCE
STALL WARN BASIC
PITCH DISC FAULT
MACH XDUCER FAIL
(on airplane 9002 thru 9158). SHAKER 1-2 FAIL
SHAKER 1-2 FAIL
GF1010_072a
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
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Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
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