Specifications

SECTION III
INSTRUMENTATION AND AVIONICS
MODEL 560
EMERGENCY LOCATOR BEACON
The emergency locator beacon (ELT) system is an emergency transmitter designed to assist in
locating a downed airplane. The transmitter has a self-contained battery pack which must be changed
every three years or after a cumulative total of one hour of operation. The system is activated automatically
by an impact of 5.0 G,+2 or -0 G along the flight axis of the airplane. The ELT can also be activated
manually by a remote EMER switch on the instrument panel. When activated, a modulated omni-directional
signal is transmitted simultaneously on emergency frequencies 121.50 and 243.00 MHz. The modulated
signal is a downward swept tone signal starting at approximately 1600 to 1300 Hz and sweeping down every
two to four seconds continuously and automatically.
The transmitter itself has an integral ARM-ON-OFF switch which set to ARM upon final inspection and
release after installation. ON position is used by maintenance/inspection personnel, as required, to test the
system in compliance with FARs. Service center personnel may use the OFF position to disarm the ELT
during phase inspections. In which case, the integral switch must be returned to ARM upon release for
service.
A guarded EMER-NORM switch on the instrument panel provides manual activation of the system as
well as a means of testing the operation. In NORM position, the system is armed for activation by the
impact switch. In EMER position, the impact switch is bypassed and the emergency signal is transmitted.
EMER position can be used to test the system; however, prior approval from control tower and flight service
must be obtained. A RESET button is located next to the EMER-NORM switch on the instrument panel.
Pressing the RESET button resets the ELT transmitter if it has been energized by the impact switch. The
RESET button must be held depressed for a minimum of three seconds. A remote control, accessible from
outside the airplane, is located on the left side of the dorsal fin under a plug button. The ELT can be turned
ON, OFF, or RESET from that control. Two flush mounted antennas are located on either side of the dorsal
fin just forward of the vertical fin.
FLIGHT GUIDANCE
PRIMUS 1000 INTEGRATED AVIONICS SYSTEM
The Primus 1000 Integrated Avionics system is an autopilot/flight director and electronic flight
instrument system (EFIS) which are integrated into one complete automatic flight control system. The
primary component of the system is the IC-600 Display Guidance computer (DGC) which contains the
symbol generator, the flight director, and the autopilot computer. The entire system is comprised of the
flight director, automatic pilot, pilot's and copilot’s electronic attitude director indicators (EADIs) and
electronic horizontal situation indicators (EHSIs) located in one single primary flight display (PFD) for each
pilot, dual air data computers with associated outputs, autopilot controller, a vertical navigation (VNAV)
mode including altitude alert and altitude preselect, touch control steering, dual rate gyros, and the autopilot
servos. The air data system provides pressure altitude, indicated and true airspeed, altitude reporting,
altitude preselect, IAS hold, vertical speed hold, and it provides overspeed warning. A multifunction display
(MFD) provides a display for the weather radar returns and for flight management system (FMS) navigation
data, as well as for the electronic checklist presentation, it also serves as a backup PFD.
The system may be flown manually or automatically.
I 3-34 Configuration AA 56OMB-01