User's Manual
Table Of Contents
- T3CAS_Section_5
- 5 Adjustment/Test
- 1. General
- 2. Equipment
- 3. Initial Harness Checkout (New Installations Only)
- 4. System Self-Tests
- 5. Return-to-Service Test
- 6. Operational Software Loading Using an ARINC 615A Portable Data Loader or Compact Flash Card
- 7. Downloading Information from the TP3PCAS Using a CF Card
- 1. Obtain a New or Blank Compact Flash (CF) card.
- 2. Copy to the New or Blank CF card the appropriate ‘Header File’
- a) Header files are files copied to the New or Blank CF card that will instruct the computer unit what is desired to be downloaded.
- b) Header files needed to download Maintenance Data, Event Data and CRC Part Numbers can be obtained from ACSS Customer Services at +1-623-445-7070 or crc.acss@l-3com.com.
- 3. For downloading Maintenance Data, Event Data or CRC Part Numbers the aircraft does not need to be in an on-ground configuration.
- 4. Apply power to the computer unit.
- 5. Insert the CF card.
- 6. For ACSS part numbers 9005000-10000, -10101, -10202, and -10204 the DATA STATUS LED will UblinkU green once; this indicates the unit recognized that a CF card was inserted.
- 7. For ACSS part numbers 9005000-11203, -11801 and -55801 the DATA STATUS LED will UblinkU green while reading the header file and performing the action defined in the header file.
- 8. Flight Data Recording
- 1. T3CAS part numbers 9005000-10000, -10101, -10202, and -10204 only support FAT16 CF card formatting. T3CAS part numbers 9005000-11203, -11801 and -55801 support both FAT16 and FAT32 CF card formatting.
- B. Flight Data
- 1. Obtain a New or Blank CF Card.
- 2. Copy to the New or Blank CF Card the Appropriate Header File.
- 3. Header files are files copied to the New or Blank CF card that will instruct the computer unit what is desired to be downloaded.
- 4. For Flight Data Recording, the aircraft does not need to be in an on-ground configuration.
- 5. Apply power to the computer unit.
- 6. Insert the CF card.
- B. Flight Data
- 9. Downloaded Maintenance Data, Event Data And Flight Data May Be Sent To ACSS Customer Services For Analysis
- 5 Adjustment/Test
- T3CAS_Section_6
- T3CAS_Section_7
- 7 Maintenance Practices
- 1. General
- 2. Equipment and Materials
- 3. Procedure for the TP3PCAS Computer Unit
- 4. Procedure for the APM (Not applicable for part numbers 9005000-10000, -10101, -10202, -10204, or -11203)
- 5. Procedure for the Directional Antenna
- 6. Procedure for the Omnidirectional Antenna (Applicable to part numbers 9005000-11203, -11801 and -55801)
- 7. Procedure for the Control Panel
- 8. Procedure for the VSI/TRA Display
- 9. Instructions for Continued Airworthiness, FAR Part 25.1529
- 7 Maintenance Practices
- T3CAS_Section_8
- T3CAS_Section_9
- T3CAS_Section_10
- T3CAS_Appendix_A
SYSTEM DESCRIPTION AND INSTALLATION MANUAL
T
3
CAS/Part No.9005000
● The following aural annunciation will occur:
“TERRAIN AWARENESS TEST COMPLETE”
If the TAWS standard test fails, execute the T
3
CAS Computer Unit Self-Test
procedures referenced in paragraph 4.C. to determine which subsystem is not
functioning properly. Execute the Extended Test Mode in paragraph 4.B.(2) to
determine which external LRU has failed. To troubleshoot the system, refer to the
procedures in the FAULT ISOLATION section.
(2) Extended Test Mode
The TAWS Extended Test Mode provides a flight deck initiated aural
annunciation for all active external faults. This test mode will be useful in isolating
standard self-test failures annunciated as “TERRAIN AWARENESS LRU PASS,
REQUIRED EXTERNAL INPUT UNAVAILABLE (or FAIL), TERRAIN
AWARENESS SYSTEM UNAVAILABLE (or FAIL)”. The extended self-test can
only be activated while on the ground.
The Extended Test Mode is initiated under the following conditions:
● The ACD entry for BITE_FAULT_AURALS is enabled and the TAWS flight
deck self-test pushbutton/switch transitions from not initiated to initiated twice
within a 3-second period.
AND
● No other self-test operation (self-test, past fault annunciation, maintenance
pages) is currently active.
The Extended self-test provides aural annunciation of the Active External Faults
after the standard self-test has completed as shown in Figure 5-2.
NOTE:
Further definition and execution detail on the self-test discrete input is
defined in the ASDB and may vary from aircraft to aircraft.
Pub. No. 8600200-001, Revision 004
34-45-29
5-9
04 Nov 2014
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