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.
Summary of Contents for TRI NAV
Page 9: ...6 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 10: ...Revision G October 14 1996 7 Figure 2 1 TRI NAV Display ...
Page 11: ...8 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 17: ...14 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 18: ...Revision G October 14 1996 15 Figure 3 1 TRI NAV TRI NAV C Jumper Wire Location ...
Page 19: ...16 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 20: ...Revision G October 14 1996 17 18 Figure 3 2 Tri Nav Interconnect Diagram ...
Page 22: ...20 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 23: ...Revision G October 14 1996 21 Figure 3 3 TRI NAV ADJUSTMENT ...
Page 24: ...22 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...
Page 26: ...24 Revision G October 14 1996 THIS PAGE INTENTIONALLY LEFT BLANK ...