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discrete to the GPWC.
The gear inhibit switch in the inhibit position sends a discrete to
the GPWC that simulates the landing gear in the extended
position. GPWC uses gear position for these modes:
* Mode 2
* Mode 3
* Mode 4
* Mode 5.
When the flap inhibit switch on the GPWM is in the inhibit
position, a flap inhibit discrete signal goes to the GPWC. This
simulates a flaps landing position in the GPWC.
The GPWM terrain inhibit discrete prevents the enhanced
function of the GPWS. The discrete does not affect the operation
of modes 1 thru 7. These items are inhibited:
* Terrain cautions
* Terrain warnings
* Terrain displays
* Terrain aural messages.
The GPWM also sends a test discrete signal to the GPWC. The
GPWC uses the test discrete to start a self-test of the GPWS.
The GPWC sends a GPWC INOP discrete to the GPW control
module to turn on the amber INOP light.
The PSEU sends air/ground discrete data to the GPWC for in-air
logic. This logic is used in these modes:
GPWS - POWER AND ANALOG INTERFACES
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* Mode 2
* Mode 3
* Mode 4
* Inhibit BITE in air
* Flight leg counting.
The GPWC sends an inhibit discrete to the TCAS computer
when the GPWC has a highter priority alert. This discrete
inhibits the TCAS aural messages and downgrades TCAS
resolution advisories (RAs) to traffic alerts (TAs).
GPWC aural messages have a higher priority than the TCAS
aural messages with the exception of mode 6 aural messages.
Mode 6 aural messages can occur at the same time as TCAS
aural messages.
The GPWC also sends a predictive windshear inhibit discrete to
the weather radar receiver transmitter when the GPWC has a
higher priority alert. This discrete inhibits the PWS aural
messages.
The program switch module supplies program pin selections to
the GPWC. The options determine such parameters as:
* Airplane type
* Mode 6 callouts
* High or low audio volume.
The GPWC sends discretes to the captain and first officer
glideslope inhibit switches. The lights come on for GPWC mode
5 alerts. When you push the light assemblies, a discrete goes to
the GPWC to turn off the lights and stop the aural warnings.
GPWS alert and warning aural messages go to the remote
electronics unit (REU). The REU sends the aural messages to
the flight compartment.
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General
The GPWC interfaces with other airplane systems on ARINC 429
data buses. These systems have digital interfaces with the
GPWC:
* Left and right air data inertial reference units
* Radio altimeter 1 and 2
* Multi mode receivers 1 and 2
* Flight management computer (FMC)
* DFCS mode control panel
* Stall management yaw damper 1 and 2
* Weather radar (WXR)
* Display electronics unit (DEU) 1 and 2
* Terrain/weather relays
* Flight data acquisition unit (FDAU).
Air Data Inertial Reference Unit
The left and right ADIRU ADR buses send this data to the
GPWC:
* Computed airspeed
* True airspeed
* Barometric altitude rate
* Uncorrected altitude
* Barometric altitude.
This air data is used to determine cautions and warnings for
GPWS modes 1, 2, 3, 4, and 7. The GPWC uses the data from
from the left ADIRU. If the left ADIRU data is invalid, it uses data
from the right ADIRU.
The left and right ADIRU IR bus sends these inputs to the
GPWC:
* Latitude
* Longitude
* Inertial altitude
* Inertial vertical speed
* Track angle magnetic
* Pitch attitude
* Roll attitude
* Body longitudinal acceleration
　
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