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difference between the selected/targeted airspeed and the indicated airspeed. It is displayed when
the Radio Altitude is greater than 50 feet.
The speed tape error is limited to 15 knots and a tick mark is displayed at every 5 knots. The
speed error tape is removed during excessive airplane attitude to prevent display clutter.
If the system is unable to compute a speed error, the speed error tape is replaced by 2 parallel
lines indicating a speed error invalid.
Flight Path Angle Reference Cue
The Flight Path Angle Reference Cue consists of 2 dashed lines corresponding to the selected
Approach Flight Path Angle displayed. This symbol is conformal, is referenced to the flight path
vector and is derived from the FMS database.
The Flight Path Angle Reference Cue is displayed when the following conditions are met:
· A FMS approach or an ILS approach has been selected from the FMS and the aircraft is
less than 7 NM from the runway threshold.
· The Horizon Line is displayed,
· Selected Flight Path Angle is valid and
· The FMS is providing a vertical Flight Path Angle.
GF1110_110a
LNAV
EVS ON
Horizon Line
Flight Path Angle
Reference Cue
FLIGHT INSTRUMENTS
Rev 7, Dec 01, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
11−10−67
HUD SYMBOLOGY (CONT'D)
Acceleration Cue
The acceleration cue is located to the left of the FPV and represents the longitudinal
acceleration/deceleration of the airplane. If the FPV is not displayed, the acceleration cue is
displayed in relation to the airplane reference symbol, for example during takeoff
roll. The
acceleration cue is displayed when the airspeed is greater than 60 knots.
The acceleration cue indicates inertial acceleration independent of airspeed trend. When climbing
into an increasing headwind for example, at constant airspeed, the inertial acceleration cue will
indicate a deceleration because the airplane groundspeed is decreasing. Also, during turns at
constant airspeed, the acceleration cue will indicate an acceleration or deceleration as the
headwind/tailwind component changes. The inertial acceleration cue can be used effectively for
precise airspeed control when the airplane is straight and level under constant wind conditions.
NOTE
The basic flight instruments remains the primary reference and the
acceleration cue must be interpreted with caution especially when
the airplane is under dynamic wind conditions.
Acceleration Cue
Speed Error T ape
Speed Error
Invalid 10
GF1110_069
Flare Cue
The Flare Cue indicates a flight path to touch down at approximately minus one degree. The Flare
Cue is displayed vertically in relation to the horizon line at a fixed pitch attitude and laterally in
relation to the flight path vector.
The flare cue is displayed when the FD is in Approach mode, the radio altitude is lower than 50
feet, and the main wheels are weightoffwheel.
Decision Height (DH) Readout
The Decision Height (DH) indication is located at the left of the BARO set readout. The DH readout
is displayed in 10 foot increments and labeled RAD when the selected DH is valid and greater than
20 feet.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual Rev 7, Dec 01, 2005
CSP 700−5000−6
Volume 2
11−10−68
HUD SYMBOLOGY (CONT'D)
Minimum Alert Indication
When the minimum alert indication is armed, a window is displayed to the right of the radio altitude
readout. When the DH or the MDA is reached, a MIN annunciation appears inside the window.
The MIN annunciation is removed when the Radio Altitude readout is removed as the airplane
transition to weight on wheel condition.
The minimum alert indication cannot be displayed when:
· The minimum alert is not set ON, or
· The selected DH/MDA is invalid, or
· A BARO altitude miscompare exists for DH/MDA annunciation.
Decision Height
Minimum Alert
Indication
Flare Cue
200 RAD
GF1110_070
AP Status Annunciation
The status of the Autopilot is displayed above the altimeter tape. When the autopilot is engaged,
AP1 or AP2 annunciation is displayed.
This annunciation blinks for a 10−second time period when the AP source is changed.
In the case of an autopilot abnormality, the annunciation blinks until the fault is rectified, the pilot
manually disengages the autopilot or the other autopilot is selected.
In case of an uncommanded autopilot disengagement, the annunciation is boxed and blinks until
the pilot acknowledges the fault by pressing the Autopilot Disengage switch.
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