INSTRUMENTATION
The Citation XLS is equipped with a Honeywell Primus 1000 Control Display System which includes
display, flight director guidance, autopilot, yaw damper and pitch trim functions. The system consists
of the following components:
IC-615 Integrated Avionics Computer (IAC) that includes:
• Flight Guidance System (FGS)
• Electronic Flight Instrument System (EFIS)
AZ-950 Air Data System (ADS)
Primus 880 Weather Radar
Attitude and Heading Reference System (AHRS)
Primus II Radio System
The IAC system is a fail-passive autopilot/flight director and display system that has a 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, then displays on the attitude direction 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 multi-function 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 GH-3000 standby flight display is installed which displays the airplane attitude, altitude, airspeed,
Mach number, and magnetic heading. All of this information is displayed on an LCD display which is
powered by its own battery. It receives data from a small standby air data computer connected to the
standby pitot-static system.
A mechanical standby HSI is also installed to provide heading, short range navigation and approach
information. It is comprised of a course deviation indicator (CDI or localizer) and a glide slope
indicator.
Cessna Citation XLS - Instrumentation & Avionics
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