Revision G
October 14, 1996 13
3.3.5 SUMMARY
The paragraphs above are not intended to be highly technical, completely thorough,
or extensive, but serve as a reminder for certain precautionary or follow-up
procedures for general avionics installations. Trimble is prepared to assist at any
point with additional information, hints, or literature. Simply call 1-800-487-4662
and ask for technical assistance.
3.4. MECHANICAL INSTALLATION
The TRI NAV will mount in either a standard 3 1/8" panel hole or a 3ATI instrument mount.
Do not use mounting screws longer than 5/8 inch. Failure to comply will result in internal
damage to the unit.
3.5. ELECTRICAL INSTALLATION
The TRI NAV connector diagram is shown on Page 11. SWITCHED POWER from receiver
1 is wired to Pin 1. SWITCHED POWER from receiver 2 is wired to Pin 2. The TRI NAV
will operate directly on 11 to 32 volts DC.
The COMPOSITE SIGNAL from radio 1 is attached to Pin 8. The COMPOSITE SIGNAL
from radio 2 is wired to Pin 15.
A standard glide slope receiver (
+ 150 uV full scale up, down deflection and a 250 uA full
scale on flag deflection) is attached to Pins 4, 12, 13 and 14 as shown in Figure 3-2. The
internal resistance of both up-down and on-off inputs is 1000 ohms.
TRI NAV MOD 4 and below, when using Terra by Trimble’s TN 200, TN 200D, and other
similarly phased composite outputs, pins 6 and 7 are grounded to pin 9 for proper phase
programming. No other source of ground for pin 7 should be used. On Nav receivers with
composite signals 180 degrees out, pin 6 and 7 are left open.
TRI NAV MOD 5 and above, when using Terra by Trimble’s TN 200, TN 200D, and other
similarly phased composite outputs, pins 6 and 7 are
internally grounded (factory installed)
for proper phase programming. On Nav receivers with composite signals 180 degrees out,
cut the jumpers shown on Figure 3-1.
Pin 3 output to an autopilot’s coupler. The output level is 15 millivolts per degree of VOR
course error, or 90 millivolts for a .093 DDM localizer signal. The autopilot output will drive
any coupler with an input impedance greater than 100 ohms.
Grounding Pin 5, NAV 1 Fail, causes information from the NAV 2 receiver to be channeled
to the NAV1 display. This pin can be wired to an external switch for use in case of a receiver
failure or to transfer NAV 2’s VOR/LOC information instantaneously to displayed flight
information. This capability is only available with dual NAV installations. It is also used
during calibration.
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