Indicated Airspeed Comparison Monitor; Mach Display; Airspeed Rolling Digit Display; Low Speed Awareness - Honeywell PRIMUS 1000 Pilot's Manual

When the FGS enters the MAX SPEED mode, the annunciator MAX
SPEED is displayed in amber to the left of the ADI.
Takeoff V
D
SPEED
V are displayed in digital tabular form inside the lower portion of the
2
airspeed tape. As the airspeed tape increases and the values come
into view on the airspeed tape, the tabular display is removed and
subsequently replaced by the appropriately positioned V
Indicated Airspeed Comparison Monitor -- If the on--side and
D
cross--side calibrated airspeed differ by 5 knots or more for greater
than 2 seconds, an amber IAS is displayed vertically near the top of
the airspeed tape. When initially activiated, the display flashes for
ten seconds, then goes on steadily.
Mach Display -- The digital Mach speed display is of the present
D
Mach number and is shown below the airspeed tape. The color of
the digits always agrees with the digital airspeed display. Mach
speed is displayed when the airspeed increases beyond 0.45M and
is removed when airspeed drops below 0.40M.
Airspeed Rolling Digit Display -- A rolling digit display of the actual
D
current IAS value is contained within the display window. This data
is a magnification of the digits on the scale and they are readable to
a one--knot resolution. The digits within the pointer are green. When
the current airspeed value is equal to or exceeds the maximum
allowable airspeed (V
vector exceeds V
red is required.
Low Speed Awareness (LSA) -- LSA (not shown) is indicated by
D
the three segment bar on the lower right side of the airspeed tape.
The bar indicates angle of attack (AOA) relative to V
for the bar is the airspeed reference line. The top of each segment
is defined in table 4--16.
A28--1146--112--00
Display -- If the aircraft is on the ground V
) the digits turn red. When the airspeed trend
MO
by one knot, the rolling digits turn amber unless
mo
Segment
White
Amber
Red
Low Speed Awareness Color Logic
Table 4--16
PRIMUSr1000 Integrated Avionics System
V Reference (V
S
1.23
1.13
1.0
Electronic Flight Instrument System (EFIS)
, V , and
1 R
bug.
SPEED
. The reference
s
)
SO
4-47