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MAINTENANCE MANUAL
CAS-100 COLLISION AVOIDANCE SYSTEM
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D. Aircraft Equipment Required But Not Supplied By Honeywell
Table
3. lists aircraft equipment not supplied by Honeywell, but required for CAS-100
operation.
Table 3. Aircraft Equipment Required But Not Supplied By Honeywell
Aircraft Equipment
Description
115 V 360-800 Hz or 28 V dc Power Source
The primary power source for TA/VSI, RA/VSI,
dedicated TCAS traffic display, and Mode S
Transponder System.
The primary power source for TCAS Processor (115
V 360-800 Hz or 28 V dc)
26 V 400 Hz Reference Power Source
Synchro reference voltage for attitude (pitch and roll)
and heading gyros.
5 V ac or dc or 28 V dc Lighting Bus
Panel lighting power source for TA/VSI, RA/VSI, and
dedicated TCAS traffic display.
5 V ac or 28 V dc Power Source (separate)
Fault lamp power for Mode S transponder/TCAS
control unit.
ARINC 429 Attitude/Heading Reference System
(digital)
Supplies the aircraft pitch, roll, and heading on an
ARINC 429 digital input to the TCAS processor.
OR
Magnetic Compass Unit, Pitch Gyro, and Roll Gyro
(synchro)
Supplies the aircraft heading, pitch, and roll on three
isolated 3-wire, synchro input to the TCAS processor
for each ARINC 407.
Radio Altimeter, digital type (one or two)
Supplies the aircraft altitude on an ARINC 429 digital
input to the TCAS processor.
OR
Radio Altimeter, analog type (one or two)
Supplies the aircraft radio altitude on a 2-wire, dc
analog input to the TCAS processor (see Figure
2015 in the MAINTENANCE PRACTICES section for
all types of altimeters that may be connected).