Specifications

SECTION III
INSTRUMENTATION AND AVIONICS
MODEL 560
INSTRUMENTATION
The Citation Encore is equipped with a Primus 1000 Integrated Avionics System which includes
display, flight director guidance, autopilot, yaw damper and pitch trim functions. The system consists of the
following components:
• IC-600 Integrated Avionics Computer (IAC) that includes:
- Flight Guidance System (FGS)
- Electronic Flight Instrument System (EFIS)
• AZ-850 Air Data System (ADS)
• Primus 880 Weather Radar
• Attitude and Heading Reference System
The IAC system is a fail-passive autopilot/flight director and display system that has full complement of
horizontal and vertical flight guidance modes. These include all radio guidance modes, long range
navigation system tracking modes, and air data vertical modes. Either pilot’s flight director (FD) can be
coupled to control the airplane.
The IAC is the focal point of information flow in the system. It converts input data and information to
the pilot-selected formats, and displays then on the attitude director indicator (ADI) and the horizontal
situation indicator (HSI) within the confines of the primary flight display tube(s). The IAC also generates
information that is displayed on the multifunction display (MFD), and it computes the flight director steering
information for the autopilot function.
The two IACs are connected with high level data link control lines. This and other interconnects are
used so that the flight guidance functions and symbol generator functions share, compare, and
communicate blocks of information. When engaged and coupled to the flight director commands, the
system’s autopilot controls the aircraft using the same commands that are displayed on the attitude director
indicator. When the autopilot is engaged and uncoupled from the flight director commands, manual pitch
and roll commands can be entered using the touch control steering (TCS) button or the autopilot PITCH
wheel and TURN knob.
A standby flight display is installed, which displays the airplane attitude, altitude, and airspeed, as well
as Mach number. All of this information is displayed in one DC powered cathode ray tube instrument,
which is powered by its own battery. It receives its data from a small standby air data computer connected
to the standby pitot-static system.
PITOT-STATIC SYSTEMS
The airplane is equipped with three separate and independent pitot-static systems. The two primary
systems serve the pilot’s and copilot’s systems. The third (backup) system provides pitot and static air
pressure to the backup airspeed indicator/altimeter on the center instrument panel and to the landing gear
warning horn pressure switch, and provides a source of static pressure for the cabin pressure differential
pressure gage.
Pitot pressure from the tube on the left side of nose of the airplane supplies pressure to the pilot's
AZ-840 micro air data computer which, after converting the information into digital information, forwards
the data through the system to the pilot’s primary flight display. The pitot tube on the right side of the nose
of the airplane serves the same function in the copilot’s system. The pitot tube on the right side of the
fuselage, below and forward of the emergency exit hatch, provides pitot pressure to the backup airspeed
indicator/altimeter and the landing gear warning horn pressure switch.
Three static ports are located on each side of the airplane at approximately fuselage station 150. The
lower port on the left side and the upper port on the right side provide the static source for the pilot's
system. The upper port on the left side and the lower port on the right side provide the static source for
the copilot's system. The center ports on each side provide static pressure for the backup pitot-static
system. The two pitot tubes and four static ports of the primary pitot-static systems, as well as the two
static ports and single pitot tube of the backup system, are electrically heated for ice protection.
I 3-4 Configuration AA 56OMB-01