User's Manual

GTS Processor Installation Manual Page 3-17

190-00587-50 Revision A

3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and

Configuration

For configuration of the displays, refer to their respective manuals.

· 500 Series Installation Manual (190-00181-02)

· GMX 200 Installation Manual

· (190-00607-04)

· GDU 620 Installation Manual

· (190-00601-04)

· GTS Processor System Maintenance Manual (190-00587-51)

· G1000 System Maintenance Manual LJ/VLJ (190-00903-00)

3.9.5 Calibration/Self Test

A self-test feature tests the (aural) alarm, attempts self calibration, and activates each display element in a

pre-determined sequential pattern to allow visual verification that display outputs issued by the digital

processor can be correctly interpreted by the pilot.

Self tests may be performed indoors but signal multi-path from building walls

may be a factor. If problems are experienced, self tests should be performed

outside away from buildings, and where local traffic is not a factor.

With the GTS Processor powered up and Standby indicated on the CDTI, cycle the GTS Processor to Self

Test. The self test feature of the GTS Processor tests the following internal parameters as well as performs

calibration of various components in the GTS Processor:

For helicopter installations without a squat switch, and wired as described in Note

6 of Appendix B, select standby mode on the CDTI and initiate the self test within

8 seconds before the unit changes back to operate mode.

a) Calibration Data fault – Stored factory calibration parameters are invalid. Return unit to Garmin

for service.

b) Configuration Data fault – Stored system configuration parameters are invalid or Mode S address

is invalid (All 0’s or F’s ). Fault will persist until configuration is corrected. Attempt

configuration per the Configuration Section 3.8.2. Download the assert log and send to Garmin

for diagnosis per Assert Tab info in Section 3.8.2.

c) FPGA fault – Check of the FPGA image failed. Fault will persist until valid FPGA image is

loaded. If upload of FPGA image was recently attempted, retry the upload. Otherwise, return unit

to Garmin for service.

d) ROM fault – Internal non-volatile memory failure, or invalid data image detected. If upload of

audio image or IGRF magnetic field image was recently attempted, retry the upload. Otherwise

return unit to Garmin for service.

e) Execution fault – CPU execution fault has occurred. Cycle power and retry self test. Download

the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault

persists, return unit to Garmin for service.

f) Electrical fault – One of the internal electrical voltages are out of range. Fault will persist until

power is cycled. Check aircraft power supply. Download the assert log and send to Garmin for

diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.

NOTE

DRAFT