190-00207-02 GTX 330/330D Installation ManualRev. U Page 4-34.2 Power and Lighting FunctionPower Input requirements and Lighting Bus input are listed in the following tables. The power-input pinsaccept 14/28 Vdc. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as onaircraft with two electrical buses. Switched Power Out is a power source available for devices such as aremote digital altitude encoder. Refer to Figure D-1 and Figure D-2 for power and lightinginterconnections.4.2.1 Aircraft Power4.2.2 Lighting BusThe GTX 330 unit can be configured to track a 28 Vdc, 14 Vdc, 5 Vdc or 5 Vac lighting bus using theseinputs. The GTX 330 can also automatically adjust for ambient lighting conditions based on the photocell.Refer to Section 5.2.5 and Section 5.2.6 for lighting configuration.4.3 Temperature InputsTemperature input is used for Outside Air Temperature (OAT) display and Density Altitude computations.The type of temperature probe required is a current sensor type, such as an EDMO P/N 655-PROBE orDavtron P/N C307PS. Connect the red wire to pin 41 and the black wire to pin 44. The GTX 330 is notconfigurable for different types of temperature sensors. The temperature-input specification is 1 microampper degree Kelvin (1 μA/°K). Refer to Figure D-6 for the temperature probe interconnect and to Section5.2.12 for probe configuration.Table 4-2 Aircraft Power Pin AssignmentsPin Name Pin Number I/OAIRCRAFT POWER 1 21 InAIRCRAFT POWER 1 42 InAIRCRAFT POWER 2 56 InAIRCRAFT POWER 2 60 InSWITCHED POWER OUT 62 OutPOWER GROUND 27 --POWER GROUND 43 --Table 4-3 Aircraft Lighting Pin AssignmentsPin Name Pin Number I/O14 V/5 V LIGHTING BUS HI 45 In28 V LIGHTING BUS HI 14 InTable 4-4 Temperature Probe Pin AssignmentsPin Name Pin Number I/OCURRENT TEMPERATURE PROBE OUT 41 OutCURRENT TEMPERATURE PROBE IN 44 In
