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by ship and/or ground-basedI- band radarsf or precision
vectoring. Pulsed (coded) I-band signals transmitted by
the surface radar station are received by the beacon and
decoded; if they match the mode (six available) selected
by the RIO, the beacon responds with a return pulse to
the radar site. The reply signal, considerably stronger
than a normal radare cho, enhancesth e radara cquisition
and tracking capability of the surface station.
17.2.4 ACLS Beacon Augmentor (R-1623). The
beacon augmentor is a crossband receiver that extends
the tracking capability of the ANISPN-42 shipboard radar
with the capability of operating with either or both
channels of the AN/SPN-42 without interference.
The beacon augmentor eliminates radar scintillation
by providing a large source of reply energy from one
point on the aircraft. The beacon augmentor receives
interrogationsf rom the AN/SPN42 carrier-basedra dar
in the Ka-banda t 33.0 to 33.4 GHz, processesth em, and
retransmits modulated I-band pulses at 8.8 to 9.5 GHx
to the AN/SPN-42, which has an I-band receiving system
mounted contiguous with the basic Ka-band radar
transmitting antenna. The unique feature of the augmentor
is that it uses the AN/APN- 154 beacon as its I-band
transmitter. This is accomplished by coupling the output
of the augmentor to the AN/APN-154 and triggering its
modulator and transmitter. During the landing phase, it
is necessaryto manually place the radarb eaconM ODE
switch to ACLS. In this mode, the AN/APN-154 receiver
is disabled to ensure that I-band signals in the area
will not trigger the AN/APN-154 transmitter during
landing.
ORIGINAL 17-2
NAVAIR 0%Pl4AAD-1
17.2.4.1 Beacon Controls. The RADAR BEACON
panel (Figure 17-1) is on the RIO right console.
POWER or STBY can be used for radar beacon warmup;
to precluder esponset o a prematureo r unintentional
interrogation, the STBY (ACLS not selected) position
should be used.
There are no cockpit displays for the beacon, although
the ACLS TEST button will be illuminated ifthe
beaconi s respondingd uring an ACLS approach.A selfcheck
of the beacon ACLS mode is accomplished by
depressingth e ACLS TEST or performing ano n-board
check. Either of these two use the receiver video processing
circuits of the augmentor in the same manner as
a Ka-band input from the ANKPN-42. If operation of
the receiver is normal, the ACLS TEST pushbutton light
on the RADAR BEACON panel will illuminate. A BAG
acronym will be displayed when performing an OBC
andintheeventofabeaconaugmentorfaihue. Theradar
beacon has a minimum warmup time of 5 minutes. During
this time, failure indications will be displayed and
self-test results should be regarded as inconclusive A
NO GO light during OBC should be verified by depressing
the ACLS TEST pushbutton. If the ACLS test light
illuminates, the system is functioning regardless of the
NO GO light indication.
[,,,,,,,I
If the aircraft is parked on the flight deck at?
of the island, the radar beacon should be in
either OFF or STBY with ACLS not selected.
With ACLS selected, stray energy
can trigger beacon response and may seriously
degrade performance or preclude lockon
of aircraft attempting ACLS approaches.
After shipboard arrestment and upon clearing
the landing area, the radar beacon power
switch should be turned to OFF to prevent
possible beacon signal interference with
other aircraft.
Note
Do not depress the ACLS TEST pushbutton
after coupling on a Mode I approach as it will
cause the ground station to break lock.
17.2.5 Approach Power Compensator Performance.
For successful Mode I and Mode IA
ACLS approachesi,t is essentialt hat the APC be functioning
satisfactorily. Sluggish APC performance or its
inability to maintain on-speeda ccuratelyd uring the approach
will result in degraded control on the glideslope
and unacceptable touchdown dispersion. A properly
functioning APC should hold the aircraft on-speedM .5
unit throughoutt he majority ofthe approach.A t tipover,
the aircraft may accelerateto as much as two units faster
but should correct to on-speed within 5 seconds. The
APC should be checked for satisfactory operation prior
to coupling. If the performance of the APC does not
meet the above criteria, the approach should be downgraded
to Mode II.
17.2.6 ACLWILS Displays (MFD and HUD). ACLS
and instrument landing system steering information can
be displayed on any MFD and the HUD (Figure 17-Z).
When the AWL pushbuttoni s depressedf,i nal determination
of the display submode is governed by the HUD
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F-14D 飞行手册 Flight Manual 2(143)
