Specifications

SECTION III
MODEL 560 INSTRUMENTATION AND AVIONICS
ALTIMETER AND AIRSPEED INDICATIONS
Altitude and airspeed data to the primary flight displays (PFD) are provided by information generated
by the AZ-850 micro air data computers which is transmitted in digital form through the IC-600 Display
Guidance Computers to the pilots’ primary flight displays. The altitude and airspeed are then presented in
color on the display in the PFDs. The micro air data computers also generate the altitude information which
is used by the mode C function of the transponders, and for the optional Traffic Collision Avoidance
System(TCAS) if it is installed.
AIRSPEED INDICATION
The indicated airspeed display is to the left of the attitude display on the primary flight display. The
display consists of a “rolling digit” window in the center of an airspeed vertical tape. The resolution of the
rolling digits is one knot. The moving vertical tape moves behind the window and displays digital airspeed
at 20 knot intervals, with the larger numbers at the top of the scale. The range of the airspeed scale is 40
to 400 knots with tick marks at 10-knot intervals. An airspeed trend vector, which displays an indication of
the direction and rate of airspeed change, extends vertically from the apex of the current airspeed value
display window. It extends upward for acceleration and downward for deceleration. The trend vector
represents a prediction of what the airspeed will be in approximately 10 seconds if the current change in
airspeed is maintained.
“Bugs” for six V-speeds are provided to allow pilot selection of key airspeeds by means of the
multifunction display (MFD) bezel buttons. The bugs are labeled 1, (V
1
) R (V
R
), 2, (V
2
)and E (V
ENR
) (this
airspeed is automatically displayed whenever V
1
, V
R
, or V
2
is selected for display; V
ENR
is permanently
selected to 160 knots) and RF (V
REF
) and AP (V
APP
). When the speeds are selected digital indications
appear at the bottom of the PFD display as well as the bugs being placed into position. The bugs are
positioned on the right outside edge of the airspeed tape. They consist of a horizontal T-shaped symbol
with its respective label positioned to the right of the symbol. All the takeoff set bugs will be removed from
the display when that airspeed has been attained and the airspeed exceeds 230 knots and the landing
speed bugs are removed upon touchdown.
When the airspeed is below 40 knots, V
1
, V
R
, V
2
, and V
E
are displayed in the bottom portion of the
airspeed tape in the form of a digital readout. The digital readout of the set value is displayed along with
the bug symbol and are labeled in ascending order, starting with V
1
. Upon power up, the digital readouts
for the set bugs will be amber dashes. As the V speeds are set on the MFD menu, the digital readouts will
follow the readout on the MFD and set accordingly. The digital readouts are removed from the display
when the first V speed value comes into view on the airspeed tape.
Standby altitude and airspeed are available, in case of main electrical system failure, from the standby
altimeter and the standby airspeed indicator, which are located in the standby flight display. These
indicators receive their data from a standby micro air data computer (MADC). The standby MADC, powered
by its own battery source, obtains its pneumatic data from the standby pitot-static system and converts it to
digital electrical outputs for the indicators.
OVERSPEED INDICATIONS
Below 8000 feet altitude the limiting airspeed (V
MO
) is 260 KIAS; between 8000 feet and 28,907 feet
the limiting airspeed is 292 KIAS. When one of these limits is exceeded, the airspeed indication in the
window to the left of the attitude display in the PFD will be changed to red and an amber annunciation, also
to the left of the attitude sphere, will announce MAX AIRSPEED. A red thermometer type tape is also
presented on the inside of the airspeed scale. The thermometer extends from V
MO
/M
MO
to larger airspeeds
on the tape and appears in the indication as the airspeed reaches into the range near V
MO
/M
MO
. When the
limiting airspeed is exceeded the overspeed warning horn will sound, and will continue to sound until the
airspeed is reduced below the limit speed.
NOTE
• The aural warning system consists of two separate units which receive input from
airplane anomalies of overspeed, autopilot off and altitude alert. The units will
output aural signals to both the headphones and speakers.
I 56OMB-01 Configuration AA 3-5