User's Manual

SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T
3
CAS/Part No.9005000
7 Weight and Balance System (WBS)
The TAWS/RWS function obtains current aircraft weight from an
A429 digital weight and balance system source.
(d) Transponder System Interfaces
1 ADLP Interface
The transponder is a Level 3 Transponder per the definitions in ICAO
Annex 10 Volume IV Section 2.1.5. The Transponder is capable of
processing COMM-A/B/C Data Link messages, and interfaces to an
external Mode S Airborne Data Link Processor (ADLP).
(4) Discrete Inputs
The T
3
CAS has various discrete inputs available for implementing various TCAS
and TAWS/RWS functions. For the TCAS function, the input logic status is
defined in accordance with ARINC 735B. For the TAWS/RWS function, the input
definition is defined by the ASDB for the specific aircraft type. These discrete
inputs default to open when power is removed.
(5) TCAS Program Inputs
The T
3
CAS has various program inputs available for TCAS unit configuration and
installation programming. Input logic status is defined according to ARINC 735B
definition.
For Part Numbers 9005000-11801 and -55801, the T
3
CAS also utilizes the ASDB
database for unit configuration and installation programming. ASDB software is
stored on the Airplane Personality Module (APM).
The ASDB defines the assignment of the connector pins to each signal, the
criteria for determining the value and status of each signal and the signal specific
filtering and processing requirements.
(6) Discrete Outputs
The T
3
CAS TAWS function contains 7 discrete outputs that are used to provide
annunciation of alerts and system status. For the TCAS function, the output logic
status is defined in accordance with ARINC 735B. For the TAWS/RWS function,
the output definition is defined by the ASDB for the specific aircraft type. These
discrete outputs default to open when power is removed.
(7) Self-Test Function
(a) TCAS, TAWS/RWS and Transponder Maintenance Self-Test
By momentarily pushing the TEST switch on the front panel of the T
3
CAS
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, and 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.
Pub. No. 8600200-001, Revision 004
34-45-29
1-59
04 Nov 2014
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