203 Avionics/electrical Sytem Eaws H-60S

Front 1

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 1

a. Communication systems control group: [ref. a, p. VII-16-1] A
1. Very High Frequency (VHF)/Ultra High Frequency (UHF) radio set A - Very High Frequency (VHF)/Ultra High Frequency (UHF) radio set - Two way LOS (Line of Sight) clear or secure V/UHF between the helicopter and other stations.
2. OTH/SATCOM A - OTH/SATCOM - Two-way clear or secure over-the-horizon (OTH) satellite communications between the helicopter and other stations.
3. Intercommunication System (ICS) A - To provide communication capabilities for the crew without transmitting over the radios

Front 2

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 2

b. Embedded GPS Inertial (EGI) navigation system [ref. a, p. VII-17-1] A B C - The Embedded GPS Inertial Navigation system is comprised of two EGI units to provide very reliable and accurate aircraft and navigational information. The EGI units are located in the nose electronics bay, and the GPS1 and GPS2/SATCOM antennae are located on top of the aircraft aft of the main rotor head above the ECS compartment. Each EGI consists of a five channel GPS receiver embedded in an all-attitude ring laser gyro inertial navigation unit. GPS and INS are both world-wide and passive systems. However, both systems alone have their own weaknesses. GPS relies on satellite signals for its information (which can be jammed or spoofed), and cannot provide aircraft heading or attitude inputs. INS is self-contained but will eventually exhibit geosituational errors due to inherent drift. Together as a complimentary system, INS assists GPS in tracking and locating satellites, while GPS provides time information, velocity, and position updates to the INS to prevent navigational errors. There are two basic navigation modes. They are GPS/INS (employing a hybrid solution as explained above) and INS Only (using only the INS portion of the EGI).

Front 3

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 3

c. Automatic Flight Control System (AFCS) [ref. a] A - The AFCS is an electrohydromechanical system, which provides inputs to the flight control system to assist the pilot in maneuvering and handling the helicopter. The AFCS is

composed of three major subsystems: the stability augmentation system (SAS), the stabilator system, and the digital automatic flight control system (DAFCS) which provide short term dampening (dynamic stability) and maintain desired altitude, speed, and heading (static stability). All engagement controls for the three subsystems are contained on the AFCS control and stabilator control panels. Each subsystem operates independently of the other two subsystems but as a total system, each subsystem complements the others.
1. Advanced Flight Control Computer (AFCC) [p. I-2-72] A B - Advanced Flight Control Computer (AFCC)- The central component of the AFCS is the digital computer. The computer commands the SAS actuators and trim actuators in all four-control channels. The computer also provides self-monitoring, fault isolation, and failure advisory. The AFCC employs two types of control, identified as inner-loop and outer-loop. The inner-loop (SAS) employs rate damping to improve dynamic helicopter stability. This system is fast in response, limited in authority, and operates without movement of the flight controls. The outer-loop (AUTOPILOT) provides long-term inputs by trimming the flight controls to the position required to maintain the selected flight regime. It is capable of driving the flight controls through their full range of travel, or 100% authority, at a limited rate of 10% per second. The inner-loop and outer-loop functions can be overridden by normal pilot flight control inputs. The AFCC is located in the nose electronics compartment.
2. AFCS control panel [p. I-2-71] A B - AFCS Control Panels - The AFCS is controlled by two panels: the AFCS Control panel and the Stabilator Control panel. The panels are located on the lower center console. All AFCS (except the Stabilator) controls are located on the AFCS Control panel. These include: SAS1, SAS2, Trim, AUTOPILOT, RADALT Hold, BARALT Hold, APPR/HVR, Crew HVR, Depart, SAS/Boost, Lateral and Longitudinal Velocities, and Computer Power/Reset. All detectable AFCS mode failures except for the stabilators, will cause the AFCS Degraded caution to appear with the appropriate mode failure capsule on the failure advisory section of the AFCS Control panel.

Front 4

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 4

Tactical systems [ref. a] A
1. Tactical navigation [p. VII-17-52] A - Tactical Navigation - The TACAN receiver-transmitter provides the navigation systems with bearing and distance information from a selected TACAN station. It provides station identity audio output to be distributed to the pilots stations, and bi-directional suppression capability (via the interference blanker) for use with the IFF transponder. The TACAN receiver-transmitter is located in the transition compartment and uses two antennas (the upper TACAN antenna on the nose e-bay door, and the lower VHF/UHF/TACAN antenna located under the tail-cone.)
2. Identification Friend or Foe (IFF) [p. VII-16-5] A - Identification Friend or Foe (IFF) - The identification, friend or foe (IFF) transponder responds to interrogation from other units. Contains encrypted circuitry for this purpose. Located in the nose electronics compartment.

3. Downed Aviator Locator System (DALS) [p. VII-17-9] A - Downed Aviator Locator System (DALS) - The downed aircrew locator system (DALS) radio set, AN/ARS-6, is an airborne electronic set designed to quickly and precisely locate downed aircrew survivors equipped with a survival radio AN/PRC-112. The AN/ARS-6 radio decodes the survivor's radio message and calculates range and steering information to the survivor. The AN/ARS-6 can also provide steering information to any source of continuous wave AM or FM UHF signals, such as the AN/PRC-90. The AN/ARS-6 operates in the UHF band between 225 and 300 MHz, and is tunable in 25KHz increments. To locate a survivor, the AN/ARS-6 transmits short coded messages. The survivor's radio receives the coded message and its internal transponder transmits a coded message back to the AN/ARS-6. The survivor's radio and the AN/ARS-6 will respond only to a coded message with the appropriate ID code. The radio set is capable of storing up to nine ID codes. The R/T is located in the transition section. The antennae are located under the forward fuselage.
4. LF/ADF [p. VII-17-6] A - LF/ADF- The set is made up of one receiver (located in the transition) and one antenna located on the bottom of the forward fuselage. The LF/ADF set is used for position fixing and maintaining course track. It receives low frequency signals from ground stations, which are used to determine relative bearing to the station.

Front 5

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 5

Flight displays: [ref. a] A B D - The Flight Displays (FD) provide turbine gas
temperature (TGT) indications, power turbine and rotor speed (Np/Nr)
indications, torque indications, and fuel management, navigation, and basic flight
instrument information. There are two FDs located in the cockpit, one for each
pilot. They are located on the instrument panel.
1. Attitude Indicator (AI) [p. I-2-5] A - Attitude Indicator (AI) - AI presentations are located on the pilots' FDs. These digital indications furnish a visual display of aircraft pitch and roll attitudes in respect to the artificial horizon. There is an analog AI provided on the center of the instrument panel as an emergency back up.
2. Radar altimeter [p. I-2-5] A - Radar altimeter - The radar altimeter is range-tracking radar that provides continuous measurement of height above land or water. It has a range of 0 feet to 5000 feet, with an accuracy of +3ft or +4%, whichever is greater. However, only a range of 0 to1050 feet is indicated on the FD presentation. Tracking from 1050 to 5000 feet will continue to be used by the operational navigation system and the AFCS.
3. Barometric altimeter [p. I-2-5] A - Barometric altimeter - There are two barometric altimeter indications on the FD, a tape scale and a digital readout window. Displays altitude above sea level based on outside air pressure. The analog AAU-32/a altimeter/encoder is provided on the center of the instrument panel as an emergency back up. Operates from - 1000ft to +50,000ft.
4. Vertical Speed Indicator (VSI) [p. I-2-5] A - Vertical Speed Indicator (VSI) - It is a digital presentation on the FD that displays aircraft vertical

speed, in feet-per-minute. One indicator on the center of the instrument panel provides the same information, and is used as an emergency back-up. The first 1000 feet is marked in 100-foot increments. The air pressure source to the indications is ambient cockpit air.
5. Airspeed indicator [p. I-2-5] A- Airspeed Indicator - Airspeed indications are provided on the FDs as a moving scale in 10 KIAS (knots indicated airspeed) increments with numbers displayed every 20 KIAS apart. A window under the scale displays the digital airspeed to the pilots. Installed on the center of the instrument panel is an analog Airspeed Indicator for emergency use. The indicator/indications are driven by differential pressure (measuring the difference between impact pressure and static pressure.)

Front 6

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 6

g. Position and anticollision lights [ref. b, WP 005 00 pars. 3, 5] A B - There are two anti-collision light assemblies. One is on the underside of the tail cone. The other is on top of the tail pylon. Each light contains two strobe lamps. Each lamp has a clear lens (day), and a red lens (night). Purpose: to prevent aircraft collisions

Front 7

what is the function
its location
modes of operation and control
supporting input signals that are required

Back 7

h. Electrical power system components: [ref. a, p. I-2-51]
1. ac generators A - The helicopter uses three sources of AC electrical power. These are primary AC power, auxiliary AC power, and external AC power. Each power source is 115/200 VAC, three-phase, 400 Hz. Primary AC power is provided by two independent generating systems. The primary system consists of two brush-less oil-cooled generators, two generator control units (GCU), two current transformers, and two generator-control switches.
Auxiliary ac power is provided by a single generator system. This system consists of a brush-less air-cooled generator, GCU, current transformer, and control switch. System operation is monitored by Caution/Advisory capsules. External AC power is supplied to the helicopter through an external power receptacle. This system consists of an external power receptacle, external power monitor panel and external power switch. Caution/Advisory capsules are used to monitor system operation.
2. Generator Control Unit (GCU) A - A GCU monitors and regulates each generator output. It provides over and under voltage protection feeder fault protection, and under-frequency protection. No. 1 and No. 2 generator under-frequency protection is disabled when the helicopter is airborne.