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• Make sure HGS symbology is positioned accurately (Critical Symbol
Monitoring, see “Built-In Tests”)
• Make sure an AIII or AII approach is flown successfully (Approach
Monitoring).
If the System Monitor detects an HGS or sensor fault, a configuration
problem, or a data problem, AIII, AII, or AI capability is lost. Below 500
feet AGL an approach warning (APCH WARN) is given in AIII or AII
Mode.
The Approach Monitor is active in AIII or AII Mode when aircraft altitude
is less than 500 feet AGL. In AII Mode, the monitor is not active below 80
feet AGL. The Approach Monitor operates as both a tracking monitor and a
flare monitor (AIII only). If the Approach Monitor finds an out of tolerance
condition, an approach warning is given.
The tracking monitor evaluates the state of the approach relative to:
• Airspeed error
• Localizer deviation
• Glideslope deviation
• Crosstrack rate.
The flare monitor evaluates (AIII only):
• The aircraft sink rate
• Lateral displacement from the centerline of the runway
• Pitch rate
• Airspeed error
• Crosstrack rate
• Late flare initiation
• Flare guidance tracking
• Roll angle
• Touchdown distance from the threshold (long landing).
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
A-6 November 2002 9701-1153 Rev A
The System Monitor automatically starts a functional test of the Approach
Monitor when the system is AIII or AII capable and the glideslope and
localizer are captured. If the HGS fails this test, it loses AIII or AII
capability.
Ground Guidance Monitoring
During TO or RO Mode, the System Monitor has two functions:
• Determine the status of the systems, configuration and data required for
ground guidance
• Make sure HGS symbology is positioned accurately (Critical Symbol
Monitoring, see “Built-In Tests”).
If the System Monitor detects an HGS or sensor fault, a configuration
problem, or a data problem, TO or RO capability is lost. If TO capability is
lost and ground speed is between 20 and 80 knots, a takeoff warning is
given. If RO capability is lost during rollout, a rollout caution is given.
Built-In Tests
The HGS contains extensive self-test hardware and software, which
continuously analyze the HGS’s operational status. When the Built-In Test
(BIT) detects a fault in portions of the HC or OHU, the HGS blanks the
Combiner to prevent the display of misleading data. The HCP FAULT light
comes on as an additional indication of a BIT-detected fault. The HGS
shows these faults as a two-digit number on the HCP while in TEST. On the
HC a light comes on to indicate which LRU has a fault.
The subsection that follows contains data related to HGS BIT.
Background BITs
The HC continuously performs BIT functions in the background as it does
normal display and guidance calculations. The HGS does all tests in
approximately two seconds during system power-up and an operatorinitiated
test (see “HGS TEST”).
The background tests done as a function of BIT include:
• Critical Symbol Monitor: verifies certain critical symbols are
positioned properly by comparing the display output back to expected
aircraft sensor input numbers
• Window Comparator Test: verifies video deflection signals against
references for deflection position monitoring
• Power Supply Monitors: verifies required power supply voltages
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
9701-1153 Rev A November 2002 A-7
• CRT Deflection Circuitry: monitors CRT operation
• Input Converters: verifies HGS Computer and HCP input converters
• Processors: verifies basic arithmetic and logical functions of each
processor and its activity
• Processor Memory: verifies all processor RAM and program memory
• Program Execution: verifies proper execution of software programs
• Combiner Alignment determines the proper alignment of the
Combiner when in the normal position.
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
A-8 November 2002 9701-1153 Rev A
HGS Test
HGS Test functions apply primarily to maintenance. Therefore, flight crews
are not required to use HGS Test during normal operations. The subsections
in the list that follows give data related to HGS Test because the operator
starts the test from the cockpit.
NOTE: An operator-initiated test may clear a fault by resetting the
HGS, returning the system to normal operation.
• HGS Test Parameters
• HGS Test Start
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