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Pressing the key a second time will initiate self-test. Self test cannot
be canceled once it has began.
SCALE - This line select key commands scale factor changes
between SEA and LAND. Pressing the key once will bring the
cursor over the field. Pressing the key a second time will change the
scale factor.
XMIT MODE - This line select key commands the transmit mode
between SILENT and NORMAL. Pressing this key once brings the
cursor over the field. Pressing the key a second time will change the
transmit mode.
FMS1 - FMS velocity.
DVS1 - Doppler velocity.
SELECT DOPPLER - This line select key is used to deselect and
reselect the Doppler. When Doppler is deselected, a (D) will appear
after the STATUS description.
Section VII
Sensors & Interfaces
7-14 2423sv602
Change 1
LONG-RANGE SENSORS
GPS Sensors
The FMS uses GPS as a heavily weighted position sensor in its
Kalman Filter. The FMS complies with all aspects of TSO C-129
Class B1 and C1 in regards to waypoint displays, scaling, integrity
monitoring, predictive RAIM, etc. using its internal GPS or when
interfaced to a TSO C-129/B1/C1 GPS sensor such as the GPS-
1000 and GPS-1200. In a multi-sensor configuration, the GPS
position is monitored the same as DME-DME, OSS, IRS and LCS in
relation to the average of all sensors currently selected. A position
difference greater than 50 nm or a divergence at greater than 50
knots will cause automatic deselection of the GPS from the position
solution.
GPS Management
GPS sensors are automatically selected at power up on the ground
or any time while on the ground. Additionally, GPS is selected at
power up in the air and at approach mode cancellation if it had been
automatically deselected at approach mode arming. GPS is
automatically deselected 1) at approach mode arming of a non-GPS
overlay or GPS approach, or 2) if the GPS is not approved under
TSO C-129, or 3) whenever the GPS position or divergence rate fails
the sensor monitor test. The GPS can be manually selected or
deselected at any time.
On aircraft equipped with a GPS-1000, GPS satellites can be
manually deselected by the crew. A page is available which
presents a list of deselected satellites. Individual satellites may be
added to or removed from the deselection list.
GPS Operation in Remote/Oceanic Areas
With GPS software SCN 10 or later (GPS-1000 or internal GPS),
The FMS can be approved for use as primary means of navigation in
remote and oceanic areas in accordance with FAA Notice 8110.60
without use of any other long range navigation sensors (VLF
Omega, IRS or Loran-C). In addition to the airborne hardware
requirements, an off-line Windows based PC program (available for
Universal) must be used to perform RAIM prediction analysis to
assure that sufficient GPS integrity will exist for the proposed route
of flight.
Section VII
Sensors & Interfaces
2423sv602 7-15
Change 1
Operators must obtain a Letter of Authorization from FAA in order to
conduct flights in remote/oceanic airspace. A data package is
available from Universal Avionics (reference Universal’s Service
Letter No. 2738 for more information).
GPS Integrity
Receiver Autonomous Integrity Monitoring (RAIM)
A key element of C-129 approval for GPS equipment is Receiver
Autonomous Integrity Monitoring (RAIM). RAIM requires that
additional usable satellites be available to the system.
RAIM provides a function analogous to the flag for VOR or ILS
equipment. In these systems, the system integrity is provided by
ground station equipment, which continuously monitors the
transmitted signal. If the ground monitor equipment detects an outof-
tolerance condition, it shuts down the transmitter (or effects a
transfer to standby equipment). The signal loss causes the flag to
be set in the cockpit instruments. Since GPS does not incorporate
this type of signal monitoring, the airborne equipment must be
capable of detecting out-of-tolerance conditions itself.
RAIM requires at least 5 usable satellites. RAIM is implemented by
dropping one satellite at a time out of the navigation solution to
permit evaluation of its pseudo-range data. Position is calculated
using the remaining 4 satellites. Range to the satellite under
evaluation is then calculated on the basis of that position and the
current almanac data for the satellite in question. Received pseudorange
is compared to the calculated data for a validity test.
The FMS implements the functions required to provide a GPS
Integrity monitor which meets the requirements of TSO C129
categories B1 and C1. The GPS Integrity monitor is implemented
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