Specifications

SECTION III
INSTRUMENTATION AND AVIONICS
MODEL 560
GO-AROUND MODE
A go-around mode (GA) is available through buttons on the left and right throttles. Depressing one of
the buttons will drop all other FD modes and disconnect the autopilot except, for the yaw damper. The FD
command bars will command a wings level and a ten-degree nose up climb attitude. GA will illuminate in
green on the EADI. 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 another pitch mode, pressing the TCS button, or engaging the autopilot.
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, SPD), the flight director/autopilot will hold the vertical reference existing at the time of release.
ELECTRONIC FLIGHT INSTRUMENT SYSTEM
The electronic flight instrument system (EFIS) is an integral part of the Primus 1000 Flight Guidance
System. The EFIS system consists of three DU-870 electronic flight displays (the pilot’s and copilot’s are
identical and interchangeable), and the center instrument panel mounted DU-870 Multifunction Display
(MFD), a DC -550 Display Controller for each pilot, an MC-800 Multifunction Display Controller, an MS-560
Mode Selector for each pilot, and an RI-553 Remote Instrument Controller. An AZ-850 micro air data
computer in each system also provides inputs which are used and displayed by the EFIS system; cross
selection (ADC1/ADC2 on the display controller) of micro air data computers is possible, which provides
system redundancy. The heart of each pilot’s system is an IC-600 Display Guidance Computer. It contains
the flight director computer; the pilot’s IC-600 also contains the autopilot controller. The symbol generator
receives and processes airplane sensor inputs and transmits the data to the electronic primary flight
displays (PFDs) in its system. In case of malfunction of a symbol generator, which is located in the
DU-870, reversion is possible through a selection (SG1/NORM/SG2) on the MC-800 Multifunction Display
Controller.
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 C-14D directional gyro and the VG-14A vertical gyro, for example, also are important parts of the
integrated system, however, they are discussed under separate headings.
A conventional slip/skid indicator is attached to the PFD of each pilot. Both primary flight displays and
the multifunction display can be dimmed manually by means of knobs on the respective controllers and the
relative brightness will then be maintained photoelectrically.
Selections for navigation sources and bearing needle presentations are controlled by means of buttons
and knobs on the display controller (DC). The selected sources are annunciated on the primary flight
displays. Each pilot may choose FULL or ARC mode (ARC mode also displays weather radar) for compass
display, single cue or cross pointer flight director display, a display of ground speed (GS) or time-to-go
(TTG), and elapsed time (ET); he may select either micro air data computer (ADC 1 or 2) as a source of
system air data information. NAV 1 or NAV 2, or FMS may be selected for navigation display and control of
the flight director These functions are explained under Display Controller below. Additional knobs which
select various navigation equipment for display (only) on the EFIS are also discussed below.
Operation of the EFIS is similar to a standard flight director system except for the presentation of
additional information on the small format of two electronic display units. More information is available in a
more compact arrangement and the format is variable as desired. Presentations that are not necessary or
desired at any one time can be removed and replaced with more appropriate data for the existing flight
conditions. The units of the system are discussed below.
The MC-800 multifunction display controller (MFD) is installed in the center pedestal. The MFD
controller provides for the selection and control of the MFD formats, modes, and waypoint designator. The
multifunction display controller is also discussed below in this section.
I 3-46 Configuration AA 56OMB-01