Specifications

SECTION III
INSTRUMENTATION AND AVIONICS
MODEL 560
Decision Height Rotation of the "DH" knob adjusts the decision height display on the EADI.
(Inner Concentric - Rotating the knob fully counterclockwise removes decision height information
“DH”) from the display.
Test Function (TEST) Pressing and holding the RA/TEST button causes the displays to enter the test
mode. Flags, cautions, and all flight director and mode annunciations are tested
and presented on the display. As the test button is held down an autopilot (left
display only) and flight director system checks will be accomplished. Satisfactory
or unsatisfactory test results will be annunciated on the display. The test will
also result in a self-test of the radio altimeter system; 50 feet will be indicated in
green at the bottom of the EADI display and the decision height (DH) horn will
sound. The TEST button is wired through a squat switch and is completely
active only when the airplane is on the ground. The Primus 1000 test is not
active in flight, but a self-test of the radio altimeter system may be made in flight
if the GS capture mode is not active. The EFIS system will also automatically
self-test when it is powered up. If the test is not satisfactory it will be so
annunciated.
BRG “
~ ” Knob This knob has three positions. The OFF position removes the bearing pointer
from the display. In NAV 2, NAV 2 bearing is displayed. In ADF 2 position (if
installed), ADF 2 bearing is displayed.
HEADING REVERSION SWITCH (HDG REV)
The heading reversion switch is an auxiliary push button switch on the pilot's and copilot’s instrument
panel which allows selection of the opposite side C-14D as an alternate (reversion) heading source for the
pilot's or copilot’s flight director. MAG 2 (MAG 1) or DG 2 (DG 1) will be annunciated in amber in the
center-left of the PFD. The annunciation of MAG or DG will be controlled by the position of the respective
GYRO MAN/AUTO switch on the pilot’s or copilot’s instrument panel. If there is no reversion selection and
both systems are selected to their own respective sources, there will be no annunciation. If there is a
cross-selection on both sides, the annunciation will be in white. If the same C-14D is selected as a heading
source on both sides, the heading source annunciation will be in amber, to apprise the pilots that both
indicators are selected to the same heading source.
ATTITUDE REVERSION SWITCH (ATT REV)
The attitude reversion switch is an auxiliary push button switch on the pilot's and copilot’s instrument
panel which allows selection of the opposite side VG-14A as an alternate (reversion) attitude source for the
pilot's or copilot’s attitude indicator. ATT 2 or ATT 1 will be annunciated in amber in the upper-left of the
PFD. If the same VG-14A is selected as an attitude source for the attitude indicators on both sides, the
attitude source annunciation will be in amber; if both systems are selected to their respective sources there
will be no annunciation. If there is a cross-selection on both sides the annunciation will be in white. In case
of a reversion selection, the annunciation is in amber to apprise the pilots that both indicators are selected
to the same heading source.
I 3-48 Configuration AA 56OMB-01