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and 30 feet RA, the Flare Cue symbol (+ +) flashes continuously.
NOTE: The Flare Cue is fixed to the Flight Path Symbol and is not
used to command or provide guidance for the flare maneuver.
Figure 5-23:
VMC Mode—Flare and Landing
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
9701-1153 Rev A November 2002 5-31
Basic Rollout
Figure 5-24 shows basic rollout symbology. This display shows after
touchdown after a VMC Mode approach. This display also shows after PRI,
AII, AI, or F/D approaches if RO Mode is enabled.
Figure 5-24:
Basic Rollout
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
5-32 November 2002 9701-1153 Rev A
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HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
9701-1153 Rev A November 2002 A-1
Appendix A:
Reference Information
This appendix presents information related to the topics listed below:
• HGS Interface
• Right-Side Monitoring Requirements
• Approach Monitoring
• Built-In Tests
• HGS Test
• HCP Display Test.
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
A-2 November 2002 9701-1153 Rev A
HGS Interface
The subsections that follow give data related to the HGS interface:
• HGS Interface Block Diagram
• HGS Interconnect
• Sensor and Equipment Inputs.
HGS Interface Block Diagram
Figure A-1 gives the HGS interface block diagram.
Figure A-1:
HGS Interface Block Diagram
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
9701-1153 Rev A November 2002 A-3
HGS Interconnect
The HGS interconnect consists of video signals between the HC and OHU.
The HC and HCP transmit bi-directional data about HGS modes, functions,
data entry, and system status. The HC also receives video feedback signals
and LRU status (Built-In Test) data and gives outputs to the EFIS.
Sensor and Equipment Inputs
The HGS receives inputs from redundant sensor and equipment systems to
meet the requirements of a fail-passive CAT III approach and landing
system. The HGS receives these inputs through dual independent input/
output subsystems contained within the HC. These inputs include digital
and analog data and related status signals from these sensors and
equipment:
• Dual Inertial Reference System (IRS) for primary attitudes, headings,
body accelerations, body rates, inertial vertical speed, ground speed and
environmental data
• Dual Air Data Computers (ADC) for altitude and airspeed data
• Dual VHF Navigation Receivers for VOR, ILS and Marker Beacon
data
• Dual Radio Altimeter Systems for altitude above ground data
• Dual Flight Control Systems (FCS) for command signals, modes and
status
• Dual Distance Measuring Equipment (DME) for station slant range
distance
• TCAS for traffic avoidance data
• IAPS for ARP, RSP, EGPWS, FCP, and FMS data.
Below is a list of parameters the HGS uses or displays that the flight crew
can select manually.
• Use the Flight Control Panel (FCP) or power lever GA switches to
select FCS modes and to enter selected altitude, selected airspeed,
selected heading and selected course
• Use the left-side Air Data Reference Panel (ARP) to enter the Decision
Height and barometric altitude.
• Use the Reversionary Switching Panel (RSP) to make reversion
selections.
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
A-4 November 2002 9701-1153 Rev A
Right-Side Monitoring Requirements
Low-visibility operations require a high degree of safety. The HGS helps
the flight crew assess the approach to the runway, centerline tracking, and
the performance of the HGS and associated systems. The right-side pilot
analyzes the takeoff, approach, and rollout procedures and monitors the
performance of the HGS system and its related sensors. The right-side pilot
also uses data on the EFIS system (PFD and EICAS).
Expanded Localizer
HGS low-visibility operations require the expanded localizer to allow the
right-side pilot to monitor lateral deviations during TO, AIII, and RO
Modes. The scaling represents the limit for lateral deviation when the
pointer is just going out of view on either side of the scale.
HGS® Pilot Guide for the Bombardier CRJ 700 Model 4200
9701-1153 Rev A November 2002 A-5
Approach Monitoring
The HC contains an independent processor called the System Monitor.
During approach, the System Monitor has three functions:
• Determine the status of the systems, configuration and data required for
an AIII, AII or AI approach
　
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