GO-AROUND MODE
A go-around mode (GA) is available through buttons on the left and right throttles. Depressing one of
the buttons will cancel all other FD modes and disconnect the autopilot except for the yaw damper.
The FD command bars will command a wings level and a 10° nose up climb attitude. GA will
illuminate in green on the ADI. After go-around has been selected, the selection of any lateral mode
will cancel the wings level roll command but the pitch-up command will remain. The go-around mode
is canceled by selecting and entering a vertical mode, pressing the TCS button, transitioning to
altitude preselect capture mode, engaging the autopilot, or by changing the autopilot flight director
coupling status (only the side that becomes the new flight director master will cancel the go-around
mode).
PITCH SYNCHRONIZATION
When flying the airplane manually and using the flight director, the command bars may be matched
to the existing pitch attitude, or if a vertical mode has been selected the mode reference may be
changed, by pressing the touch control steering (TCS) button. When the TCS button is released, the
command bars will synchronize to the airplane attitude existing at the moment of release. If a vertical
mode is selected (ALT, VS, FLC), the flight director/autopilot will hold the vertical reference existing
at the time of release.
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)
The electronic flight instrument system (EFIS) is an integral part of the Primus 1000 Control Display
System. The EFIS system consists of two DU-1080 electronic Primary Flight Displays (PFD), the
center instrument panel mounted DU-1080 Multi-function Display (MFD), a DC-550 Display
Controller for each pilot, dual MS-560 Mode Selectors, an MC-800 Multi-function Display Controller,
and an RI-553 Remote Instrument Controller. An AZ-950 micro air data computer in each system
also provides inputs which are used and displayed by the EFIS system; cross selection, or reversion,
(ADC1/ADC2 annunciation) of micro air data computers is possible, which provides system
redundancy. The heart of each pilot’s system is two IC-615 Integrated Avionics Computers. It
contains the flight director computer; the pilot’s IC-615 also contains the autopilot computer. The
symbol generator receives and processes airplane sensor inputs and transmits the data to the
electronic primary flight displays (PFD) or multi-function display (MFD) in its system. In case of
malfunction of a symbol generator, which is located in each IC-615, reversion is possible through a
selection on the three-position SG REV selector (SG1/NORM/SG2) located on the multi-function
display controller located on the center instrument panel.
Other parts of the system are discussed under different headings, since some of the sub-systems
must be covered individually, and components of the EFIS system also comprise parts of those
systems. The dual LCR-93 attitude and heading reference system (AHRS) for example, is also an
important part of the integrated system, however, it is discussed under its own heading.
The bottom third of the roll attitude pointer in the attitude director indicator (ADI) portion of the PFD
acts as slip-skid indicator. For zero lateral acceleration the bottom section of the triangular pointer
aligns with the top part and forms a complete triangle. When lateral acceleration is detected, to the
right for instance, the bottom part of the triangle moves to the left, as the ball in the conventional
inclinometer will move. For left lateral acceleration the bottom of the triangle will move right. Both
primary flight displays and the multi-function display can be dimmed manually by means of knobs on
the respective controllers and the relative brightness will then be maintained photoelectrically.
Cessna Citation XLS - Instrumentation & Avionics
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