Fa-18 Eaws Avi&elec

Front 1

Barometric altimeter

Back 1

Pitot-static pressure to indicate altitude above sea level

Front 2

Radar altimeter

Back 2

Radio echoes to determine altitude above ground level

Front 3

Azimuth

Back 3

Angular position or bearing in a horizontal plane usually measured clockwise from true north.

Front 4

Bearing

Back 4

Angular position of an object with respect to a reference point.

Front 5

Range

Back 5

Distance of an object from an observer

Front 6

Heading

Back 6

Actual orientation of the aircrafts longitudinal axis at any instance.

Front 7

True heading

Back 7

Direction measured by true north.

Front 8

Magnetic Heading

Back 8

Uses Direction of earth's magnetic field at that location as the reference.

Front 9

Relative heading

Back 9

Uses the current direction that an object is facing at the 0/360 azimuth alignment.

Front 10

VHF

Back 10

Very high frequency. Communicate with aircraft, ground stations, shipping traffic, and coastal stations.

Front 11

UHF

Back 11

Ultra high frequency. Communicate with aircraft, ground stations, shipping traffic, and coastal stations.

Front 12

AJ

Back 12

Anti jam radio

Front 13

Intercommunication audio system. (IAS)

Back 13

Provide amplification and routing of audio signals cockpit, ground crew, and rear cockpit.

Front 14

(TACAN) Tactical Air Navigation

Back 14

Determines relative bearing and slant range distance to a TACAN ground station or TACAN equipped aircraft.

Front 15

Inertial navigation system. (INS)

Back 15

Self contained, fully automatic dead reckoning navigation system.

Front 16

Global positioning system. (GPS)

Back 16

Navigation system that receives reference information from a satellite source.

Front 17

Attitude Reference Indicator (ARI)

Back 17

Self contained pitch and roll attitude Reference system with an electrically driven gyro maintains vertical orientation through use of an electronic erections system.

Front 18

Instrument Landing System (ILS)

Back 18

All weather approach guidance system provides steering information during an aircraft approach.

Front 19

Pitot-static System

Back 19

Measures temperature, Pitot-static and static pressures surrounding the aircraft.

Front 20

Automatic Flight control system(AFCS)

Back 20

Autopilot and automatic throttle control. (ATC)

Front 21

Indicated Airspeed Indicator

Back 21

Displays airspeed as a function of Pitot and static pressure. Airspeed is indicated in 10 knot increments from 50 to 200 knots.

Front 22

Standby Pressure Altimeter

Back 22

3 display altitude. 1.) Pointer display from 0 to 1000 feet in 50 foot increments. 2. )Drum display with two moveable digits indicating 1000 foot increments to 99,000 ft. 3.) Four digit display indicating barometric pressure in inches of mercury.

Front 23

Vertical speed indicator

Back 23

Senses changes in air pressure and displays them in the firm of climb or dive rate from 0 to 6000 feet per minute; upper half of the display indicates rate of climb in 100 foot increments from 0 to 1000 feet.

Front 24

Air Data Pressure Transmitters

Back 24

Convert pneumatic static and total pressure inputs from the Pitot static/control temperature probes into digital signals.

Front 25

Angle of attack. (AOA)

Back 25

Shows approach angle of attack with lighted.

Front 26

Angle of Attack Transmitters (AOAT)

Back 26

Measures the difference between the longitudinal axis of the aircraft and the airstream.

Front 27

Air Data Computer. (ADC)

Back 27

Received inputs from various aircraft sensors. Any errors in these inputs are corrected in the ADC.

Front 28

Air Direction Sensing Units(ADSU)

Back 28

Provides angle of attack (AOA) information to the ADC.

Front 29

Total Temperature Probe (TTP)

Back 29

Measures total Temperature of the air outside the aircraft. Converts temperature into electrical signal.

Front 30

DATA LINK

Back 30

Is a two way UHF communications link

Front 31

Radio detection and Ranging. (RADAR)

Back 31

Provides air to air and air to ground modes for target detection, designation, tracking, and navugation.

Front 32

Mission computers. (MC)

Back 32

Communicate and provides data conversion with non-Mux avionic equipment through the control converter by way of the avionic mux channel. Provides the air to air and air to ground master modes of operstion.

Front 33

Heads-up display (HUD)

Back 33

Provides aircraft altitude, steering, navigation, A/A and A/G weapons, and navigation FLIRT Video display into the pilots forward field of view.

Front 34

DIGITAL DISPLAY INDICATORS (DDI)

Back 34

LDDI provides night vision image system. (NVIS) compatible; The RDDI may not be the same as in the LDDI except for the MENU.

Front 35

The up front control display (UFCD)

Back 35

Entry and display of aircraft data.

Front 36

The multipurpose color display. (MPCD)

Back 36

Used as a malfunction display.

Front 37

Tactical Aircraft Moving Map Capability. (TAMMAC)

Back 37

To provide enhanced navigational/tactical situational awareness to aircrew.

Front 38

COCKPIT VIDEO RECORDING SYSTEM

Back 38

Records critical events and displays as selected by the aircrew.

Front 39

SOLID STATE RECORDER (SSR)

Back 39

Has removable storage cartridge that records cockpit and sensor video. Removable memory module. (RMM)

Front 40

Advanced memory unit. (AMU)

Back 40

Two types of computer memory cards (PCMIA) are used with the memory unit to upload or download data.

Front 41

Deployable Flight Incident Recorder Set. (DFIRS)

Back 41

The retrieving and storage of flight data and the deployment of stored flight data before the aircraft crashes or upon aircraft impact. (Door 300) (Signals UHF guard frequency of 243hz) Detectable by satellite, aircraft guard receivers and directions finders. Battery operates beacon for 72 hrs.

Front 42

Flight Incident Recorder and monitoring System. (FIRAMS)

Back 42

Monitors engine and airframe operational status.

Front 43

Nose wheel well DDI.

Back 43

Used to receive and store maintenence codes

Front 44

Joint helmet Cueing System. (JHMCS)

Back 44

Improves situational awareness, increases aircraft survivability and increases the ability to acquire a Visual target. Works in conjunction with the AIM-9X missle.

Front 45

Position lights

Back 45

Used to determine relative position of the aircraft at night. Lights on the left side are red, right are green, and the tail light is white.

Front 46

Anti collision (strobe) lights.

Back 46

Provide coverage forward, aft, up, down, and outboard to guard against in flight collisions. Day ID strobe light assembly is located on the nose landing gear strut and is used to identify the aircraft.

Front 47

Landing/taxi light assembly

Back 47

Does not turn with nose wheel. During carrier approach, the AOA approach lights assembly displays the AOA to the landing signal officer. (LSO).

Front 48

Formation Lights

Back 48

Eight green LED lights. Two on each wing tip, one outside each vertical stab, One on each side of the forward fuselage just forward of the lex. Used during join up after takeoff, in flight refueling, and routine night formation flights, visible to the wingman and indicate changes of attitude and relative position of aircraft flying in formation.

Front 49

Electrical power supply system

Back 49

Consists of two generators, two transformer rectifiers (TR), ONE BATTERY with dedicated battery charger.

Front 50

Power distribution system.

Back 50

(BUS)

Front 51

PMG

Back 51

Permanent magnet generator

Front 52

Maintenance battery

Back 52

Supplies 28 vdc to the essential maintenance buses.

Front 53

Emergency battery. (E-BATT)

Back 53

Used for engine start when external power or aircraft generator power is not available.

Front 54

Two generators

Back 54

115/200 vac, 400Hz, three phase electrical power.