The course deviation bar moves laterally in the HSI, in relation to the course cursor. Course deviation
dots in the HSI act as a displacement reference for the course deviation bar. When tracking a VOR,
the outer dot represents 10°, while on an ILS localizer it represents 2.5°. White TO-FROM flags point
to or from a station along the VOR radial when operating on a VOR. A red warning flag comes into
view when power is OFF, when NAV information is unreliable, or when signals from the NAV receiver
are not valid. The standby HSI displays only NAV 1 information.
The glideslope deviation pointer is located to the right side of the display. When receiving glideslope
information during an ILS approach, the green deviation pointer will be uncovered by the red VERT
warning flag which will otherwise be in evidence. If an ILS frequency is not tuned and being received,
or the ILS signal is unusable or unreliable, the deviation pointer will be covered by the red warning
flag.
STANDBY FLIGHT DISPLAY
The GH-3000 ESIS (Electronic Standby Instrument System) standby flight display is located on the
center instrument panel. This active-matrix liquid crystal display provides airplane attitude, slip/skid,
airspeed, mach, heading, and altitude on a single display. Airplane attitude is provided by an internal
3-axis inertial sensor cluster. Airspeed and altitude are provided by a dedicated Air Data Unit.
Heading reference is provided by a magnetometer mounted in the tailcone stinger.
Power to the system is controlled by a switch marked STBY PWR ON/OFF/TEST located on the
lower right of the pilot's instrument panel. A separate 10.5 Ampere-hour sealed lead acid battery
pack is located in the nose of the aircraft. When fully charged, the battery allows for at least 3.5 hours
of operation in the event of total loss of airplane electrical power. The battery pack is constantly
charged by the airplane's electrical system, and should therefore be fully charged in the event of an
electrical power failure. The STBY PWR switch must be ON for automatic transfer of battery power
to occur. An amber ON light next to the STBY PWR switch illuminates when the SFD is turned ON
and the airplane's electrical system is not charging the emergency power supply battery. When the
SFD switch is held to the spring loaded TEST position, a self-test of the battery and circuits is
accomplished. The application of 28V DC power to the display system initiates the attitude
initialization process, which is identified by the display of the message "attitude initializing" on the
SFD. The duration of the initialization process is usually less than 180 seconds.
A light sensor is located on the bottom left side of the instrument case. It provides ambient light level
data to the backlight control system to optimize display brightness.
Cessna Citation XLS - Instrumentation & Avionics
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