SYSTEM INSTALLATION MANUAL
89000016
Table 1016. ARINC 429 Ports (Cont)
Pin
Signal
Electrical
I/O
Description
J1-35
429 IN 1A
ARINC 429
I
ARINC 429 input Port 1A
J1-36
429 IN 2B
ARINC 429
I
ARINC 429 input Port 2B
F.
Discrete Inputs
(1)
Three discrete inputs are available to supply control inputs to the UAT. Discrete input
connection pins are shown in Table 1017.
NOTE:
Input pins are pre-configured active low. Refer to SYSTEM INTERCONNECT
DIAGRAMS, Figure 2011 thru Figure 3014 for a wiring diagram reference.
Table 1017. Discrete Inputs
Pin
Signal
Electrical
I/O
Description
J1-15
TRAF TEST
Open/ground
I
Traffic test
J1-27
AIR/GRND
Open/ground
I
Air/ground in (squat switch - configurable)
J1-12
ANONYMOUS
MODE
Open/ground
I
Anonymous mode
(2)
Air/Ground Input
NOTE:
Automatic air/ground determination is required for transceiver and transmitter
installations.
(a)
The air/ground discrete input connects to an open/ground squat switch or other air/ground
discrete indication. The air/ground discrete is configurable to be either:
• Not connected
• High when airborne
• Low (ground) when airborne.
(b)
Deleted.
(c)
Airborne or on ground status affects ADS-B message transmission behavior.
(d)
Light Aircraft Installations: The KGX automatically determines the air/ground status if
configured to the light aircraft (<15500 lbs) emitter category (refer to CONFIGURATION,
CALIBRATION, AND CHECKOUT, Paragraph 4.E. Step (9) and Paragraph 5.C. (5))
without the use of the external air/ground input discrete.
(e)
Other Aircraft Installations: The KGX validates the air/ground status of the external
air/ground input for all other Emitter Categories including Rotorcraft utilizing available
GPS and air (pressure altitude, airspeed, etc.) data.
(f)
Rotorcraft Installations: The KGX sufficiently validates an air/ground input discrete based
on collective position or collective position combined with oil pressure, no/low engine
RPM, airspeed, etc. to ensure false On Ground indications are not transmitted during
auto-rotation training and other unusual conditions
EFFECTIVITY
ALL
Page 1015
22 Dec 2016
© Honeywell International Inc. Do not copy without express permission of Honeywell.