Several channels can be deleted at
between them. Scratchpadding 1 4
and depressing R2 will cause data in
channels 1 and 4 to be deleted.
Scratchpadding 1-4 and depressing
R2 will cause data in channels 1
through 4 to be deleted.
3-13. EMERGENCY LOCATOR TRANSMITTER (ELT
Description An automatic or manually activated
emergency locator transmitter (ELT, fig. 3-6), is located
in the left side of the aft fuselage. The associated
antenna is mounted on top of the aft fuselage. An
access hole with spring-loaded cover is located in the
fuselage skin adjacent to the transmitter, enabling a
downed pilot to manually initiate or terminate operation,
or reset the ELT to an armed mode. The transmitter
contains a G switch which automatically activates the
transmitter following a velocity change of 3.5 feet per
second. When activated, the ELT will radiate Omni-
directional radio frequency signals on the international
distress frequencies of 121.5 and 243.0 MHz. The
radiated signal is modulated with an audio swept tone.
Internal batteries provide transmitter operation for a
minimum of 50 hours at -200C.
Remote Switch and Functions. The remote
switch is accessible through a small (finger-size) spring
loaded door, located on the left side of the aft fuselage.
The remote switch is placarded ON ARMED/RESET.
transmissions for test or for emergency purposes.
ARMED/RESET. Used to ARM the ELT
or reset it after an accidental activation.
Emergency Operation. The ELT may be
manually activated by moving the remote switch to the
up (ON) position.
Resetting the ELT. If the ELT is activated
accidentally it will need to be reset. Do this by moving
the remote switch up to the ON position and holding it
there for one second, then immediately rocking it down
to the ARMED/RESET position, then releasing the
Section III. NAVIGATION
The navigation equipment group provides the pilot and
copilot with instrumentation required to establish and
maintain an accurate flight course and position, and to
make an approach on instruments under Instrument
Meteorological Conditions (IMC). The navigation
attitude, position, destination range and bearing, heading
reference, and grounds peed.
3-15. DIGITAL INTEGRATED FLIGHT CONTROL
The digital integrated flight control system (fig.
3-7), provides flight director guidance, autopilot, yaw
damper, and trim functions.
The digital integrated flight control system is an
integrated fail passive autopilot/flight director/air data
system which has a full complement of horizontal and
vertical flight guidance modes:
Radio guidance modes
Inertial navigation system tracking
Air data oriented vertical modes
The pilot can couple either the left or right
electronic flight instrument system (EFIS) to the single
automatic flight control system for control of the aircraft.
The flight control computer provides digital processing of
heading, navigation, and air data information to satisfy
the pilot's requirements. The data is presented to the
pilots on the altitude indicator and the electronic flight
instrument system (EFIS).
The flight control system displays heading,
course, radio bearing, pitch and roll attitude, barometric
altitude, selected alert altitude, radio altitude, short and
long range navigation, course deviation, glideslope
deviation, to-from indication, TACAN distance and
course indications, and VOR- DME distance information.
Display of weather radar and lightning sensor system
indicators (EHSI) is also provided.
Lighted annunciators denote selected flight
mode, altitude alert, decision height, and go-around
mode (on EADI's only) engagement. Pitch and roll
steering commands are displayed on the electronic
attitude director indicators (EADI).