Weather Radar Auto-Tilt; Aural Message Priority - Honeywell EGPWS MK V Pilot's Manual

Geometric The blending algorithm gives the most weight to altitudes
with a higher estimated accuracy, reducing the effect of less
Altitude
accurate altitudes.
Continued
Each component altitude is also checked for reasonableness
using a window monitor computed from GPS Altitude and its
VFOM. Altitudes that are invalid, not available, or fall outside
the reasonableness window are not included in the final
Geometric Altitude value.
The Geometric Altitude algorithm is designed to allow
continued operation when one or more of the altitude
components are not available. If all component altitudes are
invalid or unreasonable, the GPS Altitude is used directly. If
GPS Altitude fails or is not present, then the EGPWS reverts
to using Corrected Barometric Altitude alone.
The Geometric Altitude function is fully automatic and
requires no pilot action.
Weather In -210-210 and later versions, the EGPWC computes a
optimum Weather Radar tilt angle based on the aircraft
Radar
altitude (ASL) and the terrain elevation ahead of the aircraft.
Auto-Tilt
This is output and available to a compatible Weather Radar
system so that the tilt angle may be automatically set for
optimum operation.
Aural
Two or more alert envelopes may be opened simultaneously,
so a message priority has been established. The following
Message
table reflects the priority for these message callouts. Messages
Priority
at the top of the list will start before or immediately override a
lower priority message even if it is already in progress. Only
one message may be generated at a time.
MESSAGE
"Windshear, Windshear, Windshear"
"Pull Up"
"Terrain, Terrain" ............................................................................... 2
"V1"
"Engine Fail"
"Terrain, Terrain Pull Up"
"Obstacle, Obstacle Pull Up"
"Terrain" ............................................................................................ 2
"Minimums"
"Caution Terrain, Caution Terrain"
"Caution Obstacle, Caution Obstacle"
"Too Low Terrain" .................................................................... 4, TCF
System Description
38
k
...................................................................................................................................................
c
........................................................................................... ANN
c
.............................................................................. ANN
a, c
.............................................................................................................................................
Mark V and Mark VII EGPWS Pilot's Guide
d, j
...............................................................................
h, k
...................................................................................................
c, i, k
........................................................................................
c, f
.............................................................................
c, g
.....................................................................
MODE
7
1, 2
TA
TA
6
TA
TA
060-4241-000
Rev H, August 2011