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System detects an internal fault or the MFD detects invalid data.
Lightning/Weather Fault Annunciation
Table 17-7
NAVIGATION SYSTEMS
For Training Purposes Only
Jan 04
17-27
P I LOT T R A I N I N G GU I D E
Pilot and Copilot MFD - Weather Radar Fault Annunciation
Figure 17-17
ADF1 ADF2
UTC11 : 42
TTG11 : 07
VOR1
CID
CRS 350 FMS2 DTK 333
TAS 250 GS 254 SAT 12C TAT–15C
TGT
30.0NM YUL 12.7NM
TTG11 : 04
50
100
340
LX/WX+TRB+GCS G+3 USTB T+10.7
CID
LX/WX FAULT
RADAR NOT AT TCAS RANGE
RADAR NOT AT THIS RANGE
RADAR CONTROL FAULT
WXR Range/Control
Fault Annunciation
LX/WX Fault
Annunciation
P604_17_012
NAVIGATION SYSTEMS
17-28 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Enhanced Ground Proximity Warning System (EGPWS)
Description
The EGPWS alerts and warns the flight crew when the airplane’s flight path and
position relative to terrain requires immediate crew attention and action. EGPWS
alerts the flight crew when predetermined thresholds are exceeded using the following
modes:
• Mode 1 - Excessive Descent Rate
• Mode 2 - Excessive Terrain Closure Rate
• Mode 3 - Altitude Loss after Takeoff or Go-Around
• Mode 4 - Unsafe Terrain Clearance when not in a Landing Configuration
• Mode 5 - Below Glideslope Deviation Alert
• Mode 6- Callouts
• Mode 7 - Windshear Detection and Alerting
• Terrain/Obstacle Awareness Alerting and Display (TAAD)
• Terrain Clearance Floor (TCF)
Modes 1 through 6 are installed in all aircraft (basic GPWS). Mode 7, TAAD, and
TCF are installed in the aircraft equipped with “Enhanced” GPWS. Consult your
Airplane Flight Manual supplement for individual aircraft installation.
NAVIGATION SYSTEMS
For Training Purposes Only
May 03
17-29
P I LOT T R A I N I N G GU I D E
EGPWS Functional Schematic
Figure 17-18
ENHANCED
GROUND
PROXIMITY
WARNING
SYSTEM
COMPUTER
FLIGHT COMPARTMENT SPEAKER
AND HEADPHONE UNITS
Voice Logic:
• Only 1 message at a time
• Highest priority takes
precedence and will interrupt
lower priority messages
• Once a message starts, it
will complete unless
overridden by higher priority
message, even if
alert/warning condition no
longer applicable
• Pause (approx. 3/4 second)
at end of each message.
GLARESHIELD
RADIO
ALTITUDE
ACCELERATION, HEADING,
ATTITUDE, INERTIAL,
VERTICAL SPEED,
INERTIAL ALTITUDE,
ROLL ANGLE,
TRACK ANGLE,
LATITUDE, LONGITUDE
GLIDESLOPE
INHIBIT/SELF-TEST
COMPUTED AIRSPEED
TRUE AIRSPEED,
ALTITUDE (RATE,
CORRECTED/
NOT CORRECTED)
STATIC AIR
TEMPERATURE
VERTICAL SPEED
VHF NAVIGATION
RECEIVERS
(NAV 1 & NAV 2)
LOCALIZER DEVIATION,
GLIDESLOPE DEVIATION
AIR DATA REFERENCE PANEL
DECISION
HEIGHT
FLAP CONTROL
UNIT
FLAP POSITION AND
OVERRIDE
GEAR UP/
GEAR DOWN
LANDING GEAR
CONTROL UNIT
AC
BUS 1 CBP1-B13
ANGLE-OFATTACK
PROBE 3
ANGLE-OF-ATTACK
ADC 1 & 2
IRS 1 & 2
RADIO ALTIMETER
FLAP
45°
SIMULATED
FLAP OVERRIDE SWITCH
P604_17_013
PUSHSET
OFF
SEL
SPEED REFS
TGT VSPDS
BARO
DH MDA HPA/IN
RA TEST
PUSHSET
OFF
PUSH
STD
0
20
30
45
0
20
30
45
FLAPS
LAT/LONG
RAIM
GPS 1 & 2
UP DN
LDG GEAR
DN LCK
REL
PULL UP
GND PROX
GPWS
TERR
TERRAIN INHIBIT INHB
NAVIGATION SYSTEMS
17-30 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Components and Operation
EGPWS Computer (EGPWC)
The EGPWC receives inputs from the air data system, radio altimeters, VHF Nav
receivers, GPS, IRS, Angle-of-Attack vanes, gear and flap selector levers and
glareshield switch/lights. These inputs are used to compute potential terrain conflicts.
Mode 1 - Excessive Descent Rate
Mode 1 provides aural and visual alerts and warnings in the event that the EGPWC
determines that the rate of descent is excessive with respect to airplane altitude. The
mode is active when the airplane is less than 2500 feet AGL. Mode 1 requires radio
altitude and rate of descent data.
The annunciation envelope consists of two areas: alert and warning.
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