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COMPONENTS AND OPERATION The warning system is armed when the airplane is on the ground. If one or more of the monitored systems is in an unsafe takeoff configuration and both throttles are at or above the climb (CLB) detent, the master warning lights flash, aural alerts sound and warning messages are presented. The configuration warning indications are canceled by correctly positioning the applicable control or retarding the thrust levers. PROXIMITY SENSING SYSTEM DESCRIPTION The proximity sensing system (PSS) consists of the proximity sensing electronic unit (PSEU), proximity sensors and prox-imity switches. The proximity sensing system monitors aircraft systems for correct operation and configuration. COMPONENTS AND OPERATION PROXIMITY SENSING ELECTRONIC UNIT The proximity sensing electronic unit (PSEU) processes information received from landing gear position, WOW position, thrust reverser position and fuselage door position and provides instructions to other aircraft systems. Proximity switches and sensors measure the physical relationship between two aircraft components. If the components are close together, the sensors and/or switches provide a “near” signal. If the components are separated, a “far” signal is gen-erated. The PSS uses this information to generate appropriate signals for use by other aircraft subsystems. The PSEU receives inputs from sensors and controls the takeoff configuration warning system. Failure of the proximity sensing system is indicated on the EICAS. STALL PROTECTION SYSTEM DESCRIPTION The stall protection system (SPS) provides the flight crew with aural, visual, and tactile (stick shaker) indications of an impending stall. If the pilot does not take corrective action, the system activates the stick pusher mechanism. COMPONENTS AND OPERATION There is a stick shaker on each control column and a single stick pusher mechanism attached to the left pitch control system. A dual-channel stall protection system (SPS) computer monitors the following inputs: -Angle of attack - L, R Angle-of-Attack (AOA) transducers (vanes) -Lateral acceleration - Attitude Heading Reference Systems (AHRS) -Flap position -Weight-on-wheels - WOW 1 and WOW 2 -Mach and airspeed - ADC 1, ADC 2, and standby instrument Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 10-02-13 STALL PROTECTION SYSTEM (Cont) The ADCs supply primary Mach data to the SPS computer for Mach compensation of the aircraft’s stall margin. |
