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within the FMS as a separate function from the FMS sensor monitor.
It will independently monitor and display the Integrity status for each
configured stand-alone and hybrid GPS sensor using criteria based
upon the current phase of flight. It will also alert the aircrew with
messages, annunciators, and, under some conditions, the nav flag
when the monitor data for the GPS that is currently being used for
navigation is either unavailable or in and alarm state.
Section VII
Sensors & Interfaces
7-16 2423sv602
Change 1
The GPS integrity monitor is defined for three phases of flight, each
with a specified Alarm Limit and Time to Alarm. The Enroute phase
is the default phase, and is active whenever the Terminal and
Approach phases are not active. The Terminal and Approach
phases are defined the same as for the POSN UNCERTAIN
message. Each phase of flight limit and alarm time is specified as:
Phase of Flight Alarm Limit Time to Alarm
Enroute 2.0nm 27 seconds
Terminal 1.0nm 7 seconds
Approach 0.3nm 7 seconds
The RAIM based integrity monitoring function provides the status of
each configured GPS sensor when the GPS sensor is transmitting
valid Horizontal Integrity Limits (HIL) and that data less than or equal
to 15.9 nm. If RAIM is available, the GPS Integrity status will be
RAIM when the HIL data is less than the phase of flight criteria (see
above chart) and the Satellite Failure Detected bit is not set. The
GPS Integrity status will be ALARM when the Satellite Failure
Detected bit is set for the time specified for the phase of flight.
Radio Based (DME, VOR, TACAN) Integrity
In installations with DME or TACAN as a position input, GPS
integrity is further monitored by the DME-DME position solution. In
those cases where satellite-based RAIM is insufficient due to poor
geometry or unhealthy satellites, the integrity monitoring will revert to
RADIO on the GPS Status page (assuming a good DME-DME
position). Under this condition, GPS will continue to be used as the
primary position sensor, with no associated messages to the pilot.
TEMPORARY CHANGE
Page 1 of 1
25 February 2002
MANUALS AFFECTED: Universal Avionics Systems
Corporations’ Operator’s Manual, Report No. 2423sv602,
dated January 5, 1998.
FILING INSTRUCTIONS: Insert this Temporary Change into
2423sv602, Section 7 adjacent to page 7-16.
INSTRUCTIONS: Add the paragraph below so that it follows
the last paragraph under “Receiver Autonomous Integrity
Monitoring (RAIM)”.
Fault Detection and Exclusion (FDE)
If six or more satellites are received, the GPS can determine
whether errors exist and which satellite is providing faulty data. The
GPS can then exclude that satellite from the position solution, still
leaving five satellites available to protect RAIM. This process is
known as FDE (Fault Detection and Exclusion). Remote/Oceanic
operations certification requires that FDE be provided and
continuously monitored by the GPS.
Section VII
Sensors & Interfaces
2423sv602 7-17
Change 1
The Radio Based integrity monitoring function provides the status of
each configured GPS sensor when the RAIM data from the particular
GPS sensor is not available and the Radio monitor is available. The
Radio monitor is based upon the difference between the GPS sensor
position and the independent radio position solution within the FMS.
The radio position solution is derived from the DME, VOR and
TACAN receivers. In order for the Radio monitor to be available, the
radio solution must meet the following conditions:
1. There must be a minimum of two DMEs received and used for
updating the DME position.
2. The DME positions must be valid.
3. The variance in the DME positions must meet minimum
requirements for the phase of flight.
If the RAIM function is unavailable, radio monitor is available and is
currently being used for monitoring; the GPS Integrity status will be
RADIO when the above criteria are satisfied. The GPS Integrity
status will be ALARM when the above criteria are exceeded for the
time specified for the phase of flight.
GPS INTEG Annunciator
The FMS provides a logic signal to annunciate GPS INTEG
whenever the integrity of the GPS position cannot be assured to
meet minimum requirements for the particular phase of flight
(enroute, terminal or approach).
NOTE: Whenever the GPS INTEG annunciator is illuminated, the
first pilot action should be to verify that GPS is in nav and
the Q factor is on the GPS Status Page. GPS position
should be monitored against other sensors. If available,
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