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each quadrant. Faulty quadrants are displayed
with a flashing snowflake.
e. Listen for synthetic voice message at end
of self-test. A good self-test ends with the
message: APR-39 OPERATIONAL.
f. A bad self-test ends with the message:
APR-39 FAILURE.
g. After completing system self-test, verify
that the + symbol is shown at the center of
the RW display. The + symbol shall be displayed
anytime the system is ON.
4. Equipment off. PWR switch - OFF. Pull
PWR switch handle out to disengage lock.
Figure 4-25. Radar Warning OFP and EID
Display
Figure 4-26. Radar Warning Receiver Check
Display
Change 5 4-77
TM 1-1520-238-10
4.39 AN/AVR-2 (V)1 LASER DETECTING SET
4.39.1 AN/AWMA(V)1 Laser Detecting Set (LDS)
System Description. The AN/AVR-2A(V) Laser Detecting
Set (LDS) is a passive electronic warfare system
that detects, locates, and identifies hostile laser-aided
weapon threats fired from both airborne and groundbased
platforms. The LDS is a frequency extension of
the Radar Warning (RW) system and interfaces with
the RW receivers and processor to function as an integrated
Radar Laser Warning Receiver (RLWR). The
system detects optical radiation illuminating the helicopter,
processes this laser data into laser threat messages,
and sends these messages to the RW digital processor.
The digital processor processes these inputs to
provide for both visual and aural threat indications for
the system. The LDS can also be used with both the RW
and the Air-to-Ground Engagement Systems (AGES) to
provide an engagement simulation system, in the operational
training mode. The system is composed of five
components: four laser sensor units and an Interface
Unit Comparator (IFU). The four sensor units are strategically
located around the helicopter with two
mounted forward, facing forward and two mounted aft,
facing aft. Each sensor unit provides a 100° Field-Of-
View (FOV) and +/- 45° of coverage in elevation. This
configuration provides for 360° coverage in azimuth
and t/-45° in elevation about the helicopter with substantial
overlap. Each sensor unit contains four separate
laser detectors. They are located under a special
optical window and supply coverage of three different
spectral regions: Electra-Optical (EO) bands I, II, and
[II. Two detectors are employed in the band III region,
the band IILA and band IIIB detectors, to provide the
required band III detection coverage.
4.39.2 System Operation. The sensor units perform
the actual laser detection function for the system and
contain the necessary electronics to process detected laser
signals. If a valid laser signal is detected, a threat
message containing the laser type (band I, II, or III) is
sent to the IFU for processing. Each sensor unit contains
optical and electrical Built-In Test (BIT) electronics
to perform a self-test upon command from the IFU.
When a self-test command is received, the sensor unit
disables detection of all externally generated signals
and performs a self-test. When the self-test is completed,
the appropriate pass or fail message is sent to
the IFU for processing and normal operation is resumed.
The IFU is located in the LH aft avionics bay. It
is mounted just forward of the RW digital processor
with which it directly interfaces. The IFU provides the
control and timing necessary for the interface with the
sensor units. It also provides the interface with the RW
system. The LDS was designed to operate in conjunction
with the RW system, therefore, being an integral
part of the RW system. The IFU provides the majority
of the wiring interface between the RW system and the
associated helicopter systems. If the IFU is removed
from the helicopter, a jumper box must be installed in
the system or an alternate connector configuration
employed to permit the RW system to operate. The LDS
employs a removable User Data Module (UDM) which
is mounted in the face of the IFU. The UDM contains
the classified operational software required for tactical
operation of the system. This software gets downloaded
into volatile memory within the sensor units during
system power-up and initialization, and the sensor
units then become classified. When system power is removed,
the sensor units zeroize the classified software
and become unclassified components. The removal of
system power and the UDM for the IFU effectively declassifies
the system. The LDS has the capability to operate
in two modes, training and tactical. In the training
mode, the system operates with AGES in the
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