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ADF operation is the same as COM and NAV tuning in that depressing
the line select key beside the ADF frequency will place the cursor over
the frequency to be changed. Rotating the small tuning knob slowly
will advance the frequency in 0.5 kHz steps. This change will increase
to 10 kHz steps when the large knob is used. The RMU has the capacity
to store one ADF frequency in memory. This is done by selecting the desired
frequency, then depressing the STO function key at the bottom of
the RMU. To retrieve the stored frequency from memory, the frequency
line select key must be depressed for two seconds. ADF modes are also
controlled within the ADF window. Repetitively depressing the line select
key adjacent to the ADF mode annunciator will step through the
available ADF modes of operation. This can also be accomplished by
placing the cursor over the mode annunciation, and using the tuning
knobs to step up or down through the available modes.
The ADF operating modes are as follows:
(1) ANT (Antenna) — ADF audio signal only.
(2) ADF — ADF receives signal and calculates the relative
bearing to the station.
(3) BFO (Beat Frequency Oscillator) — ADF adds a beat
frequency oscillator to detect continuous wave (CW)
signals.
(4) Voice — ADF has maximum audio clarity and fidelity,
but no bearing information.
Pilot’s Manual
5-56 PM-126A
TRANSPONDER/TCAS TUNING
Transponder operation is similar to COM and NAV operation in that
depressing a line select key beside the function desired will move the
cursor to that location. Those aircraft without TCAS installed will have
an ATC legend at the top of the transponder window, and those
equipped with TCAS will have ATC/TCAS labeled above the window.
Either transponder 1 or 2 can be selected for use and controlled by
either RMU. A number 1 or 2 will appear in front of the transponder
mode in the ATC window on both RMUs indicating which transponder
has been selected. Transponder side selection is toggled by depressing
the 1/2 key on either RMU with the cursor anywhere within the ATC
window.
The transponder is switched from standby to an operating mode by depressing
the line select key adjacent to the mode line. Once the cursor
has been selected, the mode line select key acts as a toggle to switch the
transponder between the standby mode and the active mode. Once the
transponder is in the ALT ON mode, the mode of operation is changed
using the tuning knobs. The active mode of operation can now be
changed by rotating the concentric tuning knobs. Depressing the ID
button of the RMU will initiate an approximate 18 second IDENT mode
on the transponder. This will also illuminate an ID annunciation along
the top edge of the transponder window. A reply annunciator is located
in the upper right corner of the ATC window.
TCAS (OPTIONAL)
The Traffic Alert and Collision Avoidance System (TCAS) provides the
crew with aural and visual indications of potentially dangerous flight
paths relative to other aircraft in the vicinity. The system uses the transponder
to interrogate other transponder-equipped aircraft and determine
their bearing, range, and altitude, if the intruder has an altitude
encoding transponder in operation. Advisories are issued to the crew
via the airplane Primary Flight Displays (PFDs), audio system and
Multi-Function Displays (MFDs) (traffic map). Two levels of TCAS are
in use today, TCAS I and TCAS II. TCAS II is the same as TCAS I with
the exception of providing Resolution Advisories (RAs) integrated
with the vertical speed indicator on the PFDs and additional aural commands
through the audio system. There is no RA display on TCAS I
equipped aircraft. The TCAS system consists of a processor, two bearing
antennas, and associated airplane wiring. System control is through
the radio management units. Power for the TCAS system operation is
28-vdc supplied through the 5-amp TCAS circuit breaker located on the
copilot’s circuit breaker panel (INSTRUMENT/INDICATIONS group).
Pilot’s Manual
PM-126A 5-57
TCAS OPERATION
The Learjet 45 may be equipped with either the optional TCAS I or
TCAS II system. The controls and displays are integrated with the Honeywell
Primus 1000 system. Controls are through the RMUs and
TCAS/annunciator displays are on the MFD and PFDs. On airplanes
equipped with TCAS II, the Resolution Advisories (RA) are integrated
with the vertical speed indicator display on the PFDs. The TCAS interrogates
other aircraft transponders and analyzes the replies to determine
range and bearing of the intruder. In addition, if the intruder’s
　
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