Specifications

SECTION III
MODEL 560 INSTRUMENTATION AND AVIONICS
INCLINOMETERS
Conventional inclinometers (slip indicators) are fixed to the bezel of each primary flight display. In
addition, the primary flight displays also show split sky pointers.
ENGINE INSTRUMENTS (For non-AMLCD equipped Aircraft)
Each engine is equipped with the following instruments located on the center instrument panel:
Fan RPM
Inter-Turbine Temperature (ITT)
Turbine RPM
Oil Temperature
Oil Pressure
Fuel Flow
Fuel Quantity
All engine instruments are of the vertical tape readout design except for the turbine RPM and fuel flow,
which are digital readout only The gages are powered by 28 VDC through circuit breakers on both cockpit
circuit breaker panels. The fan tachometer also has a digital RPM display as well as the vertical tape. The
digital display is provided above the N
1
tape for a more accurate readout. The loss of DC power or
instrument failure is indicated by OFF flags in each instrument, except the fan (N
1
) and turbine (N
2
) digital
tachometers.
The fan RPM (% RPM N
1
) and turbine RPM (% RPM N
2
) are calibrated in percent from 0-115%
(100% Fan RPM = 15,850; 100% Turbine RPM = 33,970). The fan (N
1
) tachometers are powered from
the emergency bus and are thus available in case of electrical system failure. They are powered by engine
monopoles (magnetic speed sensors) mounted on the applicable engine shaft and require airplane electrical
power for operation. The N
2
gage will illuminate the small red lights beside the digits and flash the display if
a turbine overspeed occurs.
The ITT gage is calibrated in degrees centigrade from 150-800. The temperature displayed is a
synthetic inter-turbine temperature which is computed by measuring the exhaust gas temperature and then
adding to it three times the temperature rise across the fan.
The FUEL FLOW gage displays fuel flow in pounds per hour. Readings are accurate at stabilized
power settings.
The FUEL QUANTITY gage is calibrated in pounds of fuel and accurately displays fuel remaining in the
left and right tanks.
The OIL TEMPERATURE gage, in degrees centigrade and the OIL PRESSURE gage in PSI, show
system limitations on the face of the instrument with red, yellow and green markings.
RAM AIR TEMPERATURE INDICATOR
A ram air temperature (RAT) indicator, located on the upper left side of the left instrument panel
displays air temperature uncorrected for ram rise. Either Celsius or Fahrenheit readings may be selected by
a switch on the face of the instrument.
FUEL TEMPERATURE INDICATOR
A fuel temperature indicator, located on the upper right side of the center instrument panel, displays
the temperature, in degrees centigrade, of the fuel in either the left or right wing fuel tank. A switch on the
face of the instrument allows selection between left and right fuel tank.
TRUE AIRSPEED PROBE
A true airspeed (TAS) probe is located below the windshield on the fuselage right side. The TAS
probe temperature reading is fed directly into the Air Data Computers for computational purposes only and
does not provide a viewable readout.
I 56OMB-01 Configuration AA 3-9