TCAS Block Diagram - Data Acquisition Figure 003
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 TCAS Block Diagram - Maintenance and Display Figure 004
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 D. Associated Items
 (1)
 ATC/Mode S transponders Two ATC/Mode S transponders, one active and the other on standby, are used with their antennas. Each transponder is linked to the TCAS by one high-speed ARINC 429 bus for transmission and another one for reception. Apart from the specific transponder functions (response to ATC ground station interrogations) they permit communication between the TCAS and a TCAS-equipped detected aircraft.

 (2)
 Displays Advisories are displayed by the Electronic Instrument System (EIS) by high speed transmission of ARINC 429 messages on the buses linking the TCAS to the DMCs 1 on one hand and to the DMC2 on the other hand. Depending on the EFIS DMC selection, the DMC 3 receives either the TA/RA display bus 1 (CAPT3/NORM positions) or the TA/RA display bus 2 (FO3 position). The FWCs connected in parallel on these buses monitor the validity of the information. The NDs provide indications on the location of intruders in the traffic area. The PFDs provide the flight crew with vertical speed correction information to avoid them. The ECAM system also presents warning messages.

 E. Peripherals The TCAS receives information from the following equipment:
 (1)
 Radio altimeter The radio altitude is an essential parameter for the TCAS. In the 0 to 2500 ft range it permits modulation of system sensitivity and triggering of inhibit orders. For this reason, two radio altimeters, one active and the other in standby, are linked to the TCAS via the low speed ARINC 429 bus.

 (2)
 Air data system Barometric altitude information fulfils the same functions as radio altitude information but for the range over 2500 ft. The ADIRU, which is not directly linked to the TCAS computer, transmits this information to the computer across the transponders via the ARINC 429 buses.

 (3)
 Inertial reference system The TCAS is linked by a high speed ARINC 429 bus to the aircraft ADIRU1 which supplies it with magnetic heading and pitch and roll attitude information.

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 (4)
 Landing Gear Control and Interface Unit (LGCIU) The LGCIU provides the TCAS with the following discrete signals:

 -ground/flight signal
 -landing gear extended signal.

 (5)
 Centralized Fault Display Interface Unit (CFDIU) The TCAS computer communicates with the Centralized Fault Display System (CFDS) via two low speed ARINC 429 buses.

 (6)
 Data loader It is possible to load software data into the TCAS computer by means of a mobile data loader with remote loading capability linked by two low speed ARINC 429 buses to a dedicated connector in the aircraft.

 (7)
 Flight Data Interface Unit (FDIU) The FDIU receives TCAS data from the DMC. The following parameters are recorded by the FDIU:

 -RA related information (label 270):
 *
 advisory rate to maintain

 *
 combined control

 *
 vertical control

 *
 up advisory

 *
 down advisory

 -manual sensitivity level (SL 0, 1, 2)
 -TA issued or not.

 (8)
 Various discrete signals Discretes are used for the inhibition of certain advisories by equipment with higher priority than the TCAS:

 -
advisory inhibit by the windshear signal

 -
advisory inhibit by the stall warning

 -
advisory inhibits by the ground proximity warning.

 (9)
 Pin programming Discrete pin program inputs are used:

 -audio level to set the audio level of the synthetic voice output
 -all traffic/threat traffic display at Threat Traffic indicates that intruders are only displayed if a TA or RA is presented
 -ground display mode: specifies that the display mode, when the aircraft is on the ground, is the TA mode only
 -display intruder limit: indicates the maximum number of intruders that can be displayed (8)
 -aircraft altitude limit, configured at 48,000 ft informs the TCAS computer that it must inhibit climb orders above this altitude.
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 4. Power Supply____________ The TCAS is supplied with 115VAC, 100 watt power rating. The ATC/TCAS control unit, common to the transponders and the TCAS, is also supplied with 115VAC: - the 115VAC BUS1 101XP supplies the TCAS via circuit breaker 4SG - the 115VAC SHED ESS BUS 801XP supplies the ATC1 system via circuit breaker 5SH1 - the 115VAC BUS2 204XP supplies the ATC2 system via circuit breaker 5SH2. The ATC/TCAS control unit is energized through the two circuit breakers 5SH1 and 5SH2. The system is supplied through these circuit breakers:
　
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