User's Manual

SYSTEM DESCRIPTION AND INSTALLATION MANUAL
TCAS 3000 Traffic Alert and Collision Avoidance System
34−43−23
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Page 1−24
15 Dec 2005
(n) Altitude Alerter Interface
The TCAS 3000 computer contains an ARINC 429 low speed input bus that is
reserved for receiving selected altitude information from an altitude control
source or flight control computer. The TCAS computer uses the selected altitude
information to inhibit the weakening of a resolution advisory by determining the
selected altitude limits for the aircraft.
(o) Reserved ARINC 429 Bus Interface
The TCAS 3000 computer has four sets of reserved ARINC 429 input busses
that can be configured as either high speed or low speed. These busses allow
for future upgrades to the TCAS 3000 system without hardware modification.
(2) Discrete Inputs
The TCAS 3000 has various discrete inputs available for implementing various TCAS
functions. The input logic status is defined according to ARINC 735 definition.
(3) Program Inputs
The TCAS 3000 has various program inputs available for unit configuration and
installation programming. Input logic status is defined according to ARINC 735
definition.
(4) Discrete Outputs
The TCAS 3000 has a number of discrete outputs that are used for unit status
annunciation and data output functions. The output logic status is defined according
to ARINC 735 definition.
(5) Self−Test Function
By momentarily pushing the TEST switch on the front panel of the TCAS Computer
Unit, maintenance personnel can display fault data for the current and preceding
flight legs. When TEST is initially activated, all annunciators (pass/fail lamps on front
of unit) are ON for a 3−second lamp test, then current fault data is displayed for 10
seconds. If no further activations of the TEST switch are made, the LRU display
cycle is terminated at the end of the 10−second fault display period, and all
annunciators are extinguished.
If during the 10−second fault display period, the TEST button is activated again, the
fault display period is aborted, a 2−second lamp test cycle is done, and the fault data
recorded for the preceding flight leg is displayed for 10 seconds. This procedure can
be repeated up to 10 times to obtain recorded data from the previous 10 flight legs.
If the TEST button is not activated again during the fault display period, the fault
display cycle is terminated at the end of the 10−second fault display period and all
annunciators are extinguished. If an attempt is made to display fault data for the
preceding flight leg when the tenth preceding flight leg fault data is displayed, all
annunciators flash for a 3−second period at a 2.5−Hz rate, after which all
annunciators are extinguished.