LIN:

R84943	(AN/ARS-6(V)1))
R85011	(AN/ARS-6(V)2))
R82903	(AN/PRC-112))
P04582	(KY-913))

GENERAL:

The AN/AYD-1 PLS is a system consisting of the AN/ARS-6(V) personnel locator, AN/PRC-112 radio set and KY-913/PRC-112 program loader. The AN/ARS-6(V) provides selected Army aircraft with the capability to perform the combat search and rescue mission for rescue of downed aircrew members without detection. It provides the rescue aircraft's pilot/co-pilot with the relative position (direction and range) of the grounded survivor equipped with an AN/PRC-112. The AN/ARS-6(V) radio can be used to navigate the rescue aircraft and to locate or retrieve Army personnel involved in special operations and other combat or peacetime situations. It also provides the capability to home to any continuous wave signal in its frequency range. The AN/PRC-112 provides the survivor the ability for two-way voice communications, a personal identification code and the means to utilize a continuous beacon. The difference between the (V)1 and (V)2 versions of the system is the "A" kit used to install the system in the aircraft.

PHYSICAL CHARACTERISTICS::

The AN/ARS-6(V) personnel locator operates in the half duplex mode, has amplitude modulated voice link and has the capability of selective interrogation of nine radios on the same or different frequencies. It has a range of 100 nautical miles (line of sight) with the AN/PRC-112 positioned over water or 75 nautical miles over land. It operates in a frequency of 225 - 300 megahertz (MHz) with 25 kilohertz channel spacing. The AN/PRC-112 radio has three pre-set channels that are one very high frequency at 121.5 MHz, and two ultra-high frequency (UHF) at 243.0 Mhz. The 121.5 and 243.0 MHz channels can transmit a continuous beacon and all three channels utilize two-way voice communications. There are also two additional channels, "A" and "B," which can be programmed with any UHF frequency between 225.0 - 300.0 MHz. These channels do not allow for a continuous beacon. The total system weight is 34.3 pounds.

AIRCRAFT APPLICABILITY:

UH-1H/V, CH-47D, UH-60A/L/Q, MH-47E, MH-60K

SPECIAL TEST EQUIPMENT:

TS-4360 Test Set

AN/ASN-128B DOPPLER GPS NAVIGATION SYSTEM

LIN: N/A

GENERAL:

The AN/ASN-128B is a Doppler Navigation System (DNS) with an embedded Global Positioning System (GPS) receiver card integrated into the CV-3888 Signal Data Converter (SDC). The GPS provides one per second updates to the DNS resulting in a very accurate navigation solution. Both the SDC and the Computer Display Unit (CDU) of the AN/ASN-128B are modified. The Doppler Receiver/Transmitter Antenna remains unmodified. A GPS antenna, data loader, zeroize switch and crypto interface are added to the aircraft. The system provides the complementary advantages of a GPS receiver and a Lightweight Doppler Navigation System. System installation and aircraft modifications have been minimized by embedding a one-card GPS receiver into the SDC. The system provides continuous velocities, navigation and guidance. Doppler improves GPS tracking in a jamming environment and minimizes GPS reacquisition time. When both Doppler and GPS are available, the GPS accurately initializes and automatically updates the Doppler present position. If the GPS is lost, the Doppler continues to provide GPS calibrated velocities for hover and navigation. If the Doppler is in memory, the GPS continues to provide present position to the Doppler and navigation continues. It provides for the insertion of vertical navigation and tactical landing data and displays Coordinated Universal Time.

PHYSICAL CHARACTERISTICS:

The standard AN/ASN-128 CDU module displays both Doppler and GPS data using a paging technique. It contains a new four-line display element designed to reduce pilot workload. The operator may select and display Doppler only, GPS only or combine Doppler/GPS data. The WGS-84 datum is added to the existing datums currently in the AN/ASN-128. The system has a HAVE QUICK timing interface and a High Resolution Present Position Latitude/Longitude Display.

AIRCRAFT APPLICABILITY:

CH-47D, UH-60A/L

SPECIAL TEST EQUIPMENT:

None

AN/ASN-149(V)1 NAVSTAR GLOBAL POSITIONING SYSTEM (GPS)

LIN: Z46320

GENERAL:

The NAVSTAR Global Positioning System is a space-based positioning, navigation and time-transfer system consisting of three segments: space, ground and user equipment. The primary purpose of the GPS is to provide a worldwide, real time navigation system capable of supporting users with highly accurate position, velocity, altitude and time information. Users equipped with special navigation radio receivers (user equipment) are capable of determining their position and time reference with a high degree of accuracy.

PHYSICAL CHARACTERISTICS:

The AN/ASN-149(V)1 set interfaces with the AN/ASN-128 doppler system or the carousel IV-E inertial navigation system. The AN/ASN-149(V)1 consists of an indicator control unit, a two- channel radio receiver, antenna amplifier unit and antenna. There are three different models of the radio receiver unit which are interchangeable and have the same functions (see the pictures on the opposite page). The system's internal memory is supported by a BA-3042 battery. The total system weight is 36.0 pounds.

AIRCRAFT APPLICABILITY:

CH-47D

SPECIAL TEST EQUIPMENT:

AN/GSM-336(V)2 Test Set (AVIM)

LIN: N/A

GENERAL:

The AN/APN-209(V) radar altimeter set provides a continuous indication of altitude of an aircraft 0 to 1500 feet above the surface of the earth by transmitting a radar signal to the ground, receiving the reflected signal in the receiver/transmitter (RT) unit and indicating the computed altitude of the aircraft on the remote indicator. It has various configurations for installation flexibility. It can operate accurately over ice and snow-covered surfaces and has an all weather operational capability. The altimeter is required if the aircraft is flying at night or over featureless terrain and is night vision goggle compatible.

PHYSICAL CHARACTERISTICS:

The AN/APN-209(V) radar altimeter set operates from an aircraft power supply having a nominal voltage of 28 volts direct current. In addition, the RT height indicator displays analog altitude and digital altitude warnings. The set has continuous resolution without step errors and has a solid state transmitter with power management. It is accurate during pitch and roll without slant range errors and is completely immune to doppler effect. Its operating frequency is 4.3 gigahertz and transmitted power is 5 watts peak at high altitude. The total weight of the system is 7.2 pounds.

AIRCRAFT APPLICABILITY:

AH-64D, OH-58D, UH-60A/L, CH-47D, MH-47E, MH-60K, EH-60A

SPECIAL TEST EQUIPMENT:

None

LIN: N/A

GENERAL:

The H-764G Embedded Global Positioning System (GPS)/Inertial Navigation System(INS) (EGI) integrates the two functions into one single line replaceable unit (LRU). The EGI is a hybrid system. The system is an all-attitude navigation system providing outputs of linear and angular acceleration, velocity, position attitude (roll, pitch and platform azimuth), magnetic and true heading, altitude, body angular rates, time tags and time. When installed in the host platforms in the appropriate configuration, the system provides the navigation functions of the equipment it replaces. The system uses the concept of an open system architecture which allows for the modularity of interface functions. It provides a MIL-STD-1553B digital interface, meets tri-service GPS/INS requirements and can interface with the U.S. Air Force satellite system.

PHYSICAL CHARACTERISTICS:

The EGI is a modular system consisting of a sub-nautical mile (nmi)/hour-class INS LRU with three expansion slots, one of which contains an embedded, tightly coupled GPS receiver. These three expansion slots allow the system to meet a wide variety of applications. The EGI major subsystems are the inertial sensor assembly, GPS receiver, system processor, synchro circuit card assembly and the direct current power supply. It uses a digital laser gyro vehicle electrical power (28 volts direct current), turn-on and mode commands, initialization and altitude data, as well as GPS satellite inputs for GPS or GPS/INS operation, and is able to track five space vehicles simultaneously. The system dimensions are 7 x 7 x 9.8 inches and it weighs less than 18 pounds.

THREAT COVERAGE:

The H-764G EGI includes a five channel L1/L2 P(Y) code; selective availability/anti-spoofing (SA/AS); dual port random access memory interface; anti-jam capabilities; quick reaction, stable reference oscillator; a precise-time-and-time interval interface; and a shielded enclosure for electromagnetic interference considerations.

AIRCRAFT APPLICABILITY:

AH-64A/D, OH-58D, MH-47D/E, MH-60A/L/K

SPECIAL TEST EQUIPMENT:

None

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