GDL 90 System ICA, Helicopter STC
Garmin AT
2345 Turner Rd SE
21 December 2005
Salem, OR 97302
Part #: 560-0255-00 Rev A
©
Copyright 2005 Garmin AT All Rights Reserved
Page 8 of 13
2.3
Control, Operating Information
The GDL 90 does not have a direct pilot interface. If the GDL 90 is interfaced to optional
external controllers or display systems, consult the appropriate controller or display User’s
Guide for system operation and self-test information. If an external controller is used other than
the GSL 71 or the MX20 MFD the system includes an external GDL 90 failure annunciator.
Some GDL 90 UAT Data Link Sensor units are controlled by the optional GSL 71. Consult the
GSL 71 User’s Guide listed in Section 2.1 of this document for system operation and self-test
information for GSL 71 installations.
Rotorcraft-specific configuration information for the GDL 90 is stored in the MicroAPM. This
information may be accessed using a PC as described in the GDL 90 Installation Manual listed in
Section 2.1 of this document.
2.4
Servicing Information
None. In the event of system failure, return the unit to the manufacturer or an approved repair
station.
2.5
Periodic Maintenance Instructions
The GDL 90 is designed to detect internal failures. A thorough self-test is executed
automatically upon application of power, and built-in test is continuously executed. Detected
errors are indicated by failure LEDs on the GDL 90, and maintenance is on-condition. If the
GDL 90 is interfaced to an optional external controller or MFD, detected errors may also be
indicated by annunciation on the interfaced controller or MFD.
The GSL 71 UAT Control Panel is also designed to detect internal failures. A self-test is
executed automatically upon application of power, and built-in test is continuously executed.
Detected errors at start-up are indicated by “TEST” “FAIL” on the GSL 71 LED display.
Detected errors during use are indicated by “UAT” “FAIL” on the display. At an aircraft annual
inspection, conduct a visual inspection on the GSL 71 UAT Control Panel and its wire harness to
insure continued installation integrity. Visually inspect wiring harness to insure no chafing or
wire routing problems.
At an aircraft annual inspection, conduct a visual inspection on the GDL 90 Data Link Sensor,
GSL 71 Control Panel, and their wire harness to insure continued installation integrity. Visually
inspect wiring harness to insure no chafing or wire routing problems. The MicroAPM is
installed in the wiring harness near the GDL 90 unit.
2.5.1
Equipment Calibration
The GDL 90 and GSL 71 designs require no adjustments or calibration.
2.5.2
GDL 90 Battery Replacement
The GDL 90 has an internal keep-alive battery that will last about 10 years. The battery is
used for retention of internal ram memory data and GPS system information. Regular
