(2)
The ground proximity data includes: sink rate, pull up, terrain, don't sink, too low gear, too low flap, too low terrain, glideslope minimum, terrain pull up, windshear warning, and windshear alert. All of the GPWC data is transmitted through the EIU to the MAWEA. In addition, the windshear and pull up data is transmitted through the EIU for display on the PFD.
M. Yaw Damper System Interface (Fig. 31)
(1)
The yaw damper modules transmit an analog discrete yaw damper fault signal to the EIUs. These analog fault signals are used to enable the YAW DAMPER UPR and YAW DAMPER LWR messages which are displayed on the main EICAS.
(2)
The YAW DAMPER UPR message indicates that the upper yaw damper module has failed or its power is off, the IRU is off or in align, the upper rudder yaw damper actuator has failed, or the upper yaw damper engage switch is in the OFF position. Similarly, the YAW DAMPER LWR message indicates that the lower yaw damper module has failed or it's power is off, the IRU is off or in align, the lower rudder yaw damper actuator has failed, or the lower yaw damper engage switch is in the OFF position.
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(P3-2)
B140 R-WXR (E30-1)
Weather Radar Interface
Figure 29
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SINK RATE PULL UP TERRAIN DON'T SINK TOO LOW GEAR TOO LOW FLAP-DH SELECT
EFICP4-
TOO LOW TERRAIN
L-A-1
GLIDESLOPE GLIDESLOPE INHIBIT MINIMUMS -EFIS DISCRETE
M7354 CAPT EFIS CP
(P55) TERRAIN PULL UP WIND SHEAR WARN WIND SHEAR ALERT WIND SHEAR CAUTION WIND SHEAR INOP GPWS ALERT GPWS WARN
GPWC-L-A-1
GPWS INOP R/A BUS ADC BUS IRS BUS FLAPS DISCRETE GEAR DISCRETE ILS BUS
-DH SELECT
CFDIU INPUT BUS EFICP4-
G/S DISCRETER-B-1-EFIS DISCRETE STALL WARN L BUS STALL WARN R BUS
M7364 F/O EFIS CP
FMC BUS (P55)
PRO PIN CONFIG CHG GPWC LRU FAILURE BITE TEST INHIBIT COMMAND WORD ANKNW
X85 GROUND PROXIMITY WARNING
COMPUTER (E1-4) M7351 R-EIU (E2-6)
Ground Proximity Warning Computer (GPWC) Interface Figure 30
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M7351 R-EIU (E2-6)
Yaw Damper System Interface
Figure 31
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8. Engine Indicating and Crew Alerting System Overview
___________________________________________________
A. General (Fig. 1)
(1)
The EICAS performs the functions of engine indicating and crew alerting. Additionally, the EICAS monitors major airplane systems and displays and/or stores system information related to airplane maintenance, dispatch status, and overhead panel configuration.
(2)
The EICAS is the integration of the engine indicators and the caution and warning system. The two center Display Units (DUs) normally display EICAS information.
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