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Avionics Flashcards

Avionics

1
Q

Barometric Altimeter

A

uses pitot-static pressure to indicate altitude above sea level.

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2
Q

Radar Altimeter

A

uses radio echoes to determine altitude above ground level.

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3
Q

Azimuth

A

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

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4
Q

Bearing

A

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

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5
Q

Range

A

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

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6
Q

Heading

A

Actual orientation of the aircraft’s longitudinal axis at any instance.

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7
Q

True Heading

A

Direction measured by true north.

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8
Q

Magnetic Heading

A

Uses the direction of the earth’s magnetic field at that location as the reference.

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9
Q

Relative Heading

A

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

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10
Q

State the advantages of using Fiber Optic Cables in the EA-18G

A

Fiber optic cables provide the following advantages:
-Improved system performance
-Immunity to electrical noise
-Signal security
-Improved safety and electrical isolation
-Reduced size and weight
-Environmental protection
-Overall system economy.

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11
Q

Very-High Frequency/Ultra-High Frequency (VHF/UHF)

A

Provides for a way to communicate with other aircraft, ground stations, shipping traffic and coastal stations;

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12
Q

Intercommunication Audio System (IAS)

A

Provides amplification and routing of audio signals between cockpit, ground crew and rear cockpit; It also provides supplemental and backup communication, radio navigation, and identification (CNI) controls, combined aircraft threat warnings and advisories, weapon tones, and voice alerting.

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13
Q

Tactical Air Navigation (TACAN)

A

Used to determine the relative bearing and slant range distance to a TACAN ground station or a similar TACAN equipped aircraft; also used as a source to keep aircraft present position and update the aircraft present position being kept by another source (INS or ADC)

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14
Q

Inertial Navigation System (INS)

A

self-contained, fully automatic dead reckoning navigation system. On 164945 and up A/C the INS is closely coupled by the mission computer with the GPS to provide highly accurate aircraft present position and velocity data. The INS detects aircraft motion (acceleration and attitude) and provides acceleration, velocity, present position, pitch roll, and true heading to related systems.

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15
Q

Global Positioning System (GPS)

A

A navigation system that receives reference information from a satellite source; this information provides the pilot and other aircraft systems continuously updated present position, velocity and time information.

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16
Q

Attitude Reference Indicator (ARI)

A

A self-contained pitch and roll attitude reference system with an electrically driven gyro maintains vertical orientation through use of an electronic erection system; provides a minimum of 3 minutes of attitude information with total loss power; provide backup pitch and roll attitude for use by other systems.

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17
Q

Instrument Landing System (ILS)

A

All weather approach guidance system; provides steering information during an aircraft approach by decoding azimuth and elevation microwave signals received from surface transmitters; decoded signals are used for display on the HUD and the ARI; display depict the flight path the pilot must follow to line up accurately with the runway/carrier deck; by consecutively scanning through azimuth and elevation, the system provides continuous measurement of the lateral and vertical deviations from the optimum approach line for the aircraft.

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18
Q

Data Link

A

Is a two-way uhf communications link connecting the airborne data link system with a controlling shipboard, airborne, or land based combat direction system; has four selectable modes of operation: automatic carrier landing (ACL) mode, vector(VEC) mode, waypoint mode, and alignment (ALGN).

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19
Q

Radio Detection and Ranging (RADAR)

A

Provides Air-to-air (A/A) and Air-to-ground (A/G) modes for target detection, designation, tracking and navigation. Also provides terrain avoidance for low level navigation, a detection and tracking capability for moving surface targets, and precision velocity measurement for navigation update and improved weapon delivery accuracy.

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20
Q

Mission Computer (MC)

A

The mission computer system is made up of two identical digital data computers that control the displays sent to the multipurpose display group, navigation, air-to-air, and air-to-ground master mode operation, built-in test (BIT), and data conversion from non-mux avionic equipment.

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21
Q

Communication Countermeasures Set (CCS)

A

ALQ-227 detects, analyzes, reports, and produces waveforms for jamming communication emissions in the low frequency region of the EA-18G electronic spectrum; compatible with the ALQ-99 low band transmitter (LBT) pod, band 1, band 2 and band 2/3 pods, universal exciter upgrade (UEU), and provides growth provisions for a high power CCS transmitter.

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22
Q

ALQ-99

A

Provides Very Low, Low, Medium, and High Band radar and communication jamming capability of hostile radar and communications threats, in order to enable a safer penetration of enemy airspace.

23
Q

ALQ-165/214

A

Also known as the onboard jamming system; uses multiple techniques to defeat tracking and acquisition radar.

24
Q

ALQ-218

A

Detects, classifies, locates, and reports radar emitters and radar associated signals. The system receives these signals by way of antennas mounted around the aircraft on the forward and aft fuselage and on the wingtips. The system is made up of nine WRAs, twenty antenna units (AU), and six power dividers.

25
Q

Identify the location of the following major components of the AN/ALQ-99 (TJS) Pod

A

a. Turbo-generator housing (hardback)
b. Transmitters
c. Universal exciter
d. Ram air turbo-generator
e. Radome

26
Q

Heads-Up Display (HUD)

A

Provides aircraft altitude, steering,
navigation, A/A and A/G weapons, and navigation FLIR video display
into the pilot’s forward field of view. The total forward field of
view is 20 degrees, with optical center four degrees below aircraft
waterline.

27
Q

Left Digital Display Indicators (LDDI)

A

Night vision image system (NVIS) compatible;
During normal operation it provides any of the displays selectable
from the TAC or SUPT menu and on EA-18G, the AEA menu; normally
provides stores status, radar weapon video, cautions and advisories,
engine monitor, and BIT displays.

28
Q

Right Digital Display Indicator (RDDI)

A

Display may not be the same as on the RDDI
except for MENU, and the SPIN mode display which is displayed by both
at the same time, LDDI may also have a HUD display and display the
same display as the rear LDDI, rear MPCD or rear UFCD. On EA-18G the
AEA menu provides selection of airborne electronic attack (AEA) system
abilities.

29
Q

Up Front Control Display (UFCD

A

Provides for entry and
display of aircraft data; used for selection and control of
communication, radio navigation, and identification (CNI) functions;
provides for selection of aircrafts displays including tactical
displays to which the throttle designator control (TDC) is assigned,
and display of sensor video.

30
Q

Multipurpose Color Display (MPCD)

A

MPCD has mechanical pushbuttons for operator inputs and is used as a multifunction display; if two different map formats are selected on the MPCD and rear MPCD, only one displays the map video as background the other display format only provides symbology.

31
Q

Describe the function of the Digital Map Set (DMS)

A

The DMS is part of the Tactical Aircraft Moving Map Capability (TAMMAC) system. The DMS is made up of a Digital Map Computer (DMC) and a high speed interface cable. The purpose of the TAMMAC system is to provide enhanced navigational/tactical situational awareness to aircrew, using on-board stored moving map and image database.

32
Q

Describe the function of the Solid State Recorder

A

The SSR has a removable storage cartridge that records cockpit and sensor video, also stores off-board images received from the DCS and MIDS communication system in flight and allows access to images loaded on the Removable Memory Module (RMM) during mission planning.

33
Q

Position (Lights)

A

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

34
Q

Strobe (Lights)

A

The anti-collision strobe lights provide coverage forward, aft, up, down, and outboard to guard against in-flight collisions located on the vertical stab; the DAY ID Strobe light assembly is located on the nose landing gear strut and is used to identify the aircraft.

35
Q

Landing/Taxi (Lights)

A

The white landing/taxi light assembly faces forward (does not turn with nose wheel) and is used for landing and taxi operations at night.

36
Q

Approach (Lights)

A

The approach lights are located on the nose landing gear strut and are activated when all landing gear are down and locked and weight is off wheels. During carrier approach, the AOA approach lights assembly displays the AOA to the landing signal officer (LSO).

37
Q

Formation (Lights)

A

8 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 wingmen and indicate changes of attitude and relative position of aircraft flying in formation.

38
Q

State the purpose of the Deployable Flight Incident Recorder Set (DFIRS)

A

Have two functions; the retrieving and storage of flight data, the deployment of stored flight data before the aircraft crashes or upon aircraft impact. The DFIRS front mount, rear mount, impact initiator, severable door (door 300), thin layer explosive and shielded mild detonation cord provide deployment operations. Beacon transmits signals on military UHF guard frequency of 243 Hz detectable by search and rescue satellite, aircraft guard receivers and directions finders; battery can operate the beacon for 72 hours.

39
Q

Pitot Static System

A

Measures temperature, pitot and static pressures surrounding the aircraft.

40
Q

Indicated Airspeed Indicator

A

The cockpit airspeed indicator (green lighting for night vision goggle (NVG) compatibility) displays airspeed as a function of pitot and static pressure. Airspeed is indicated in 10 knot increments from 50 to 200 knots and is indicated in 50 knot increments from 200 to 850 knots

41
Q

Standby Pressure Altimeter

A

An instrument which displays altitude with three displays; Pointer display from 0 to 1000 feet in 50 foot increments, Drum display with two movable digits indicating 1000 foot increments to 99,000 ft and Four digit display indicating barometric pressure in inches of mercury

42
Q

Vertical Speed Indicator

A

Senses changes in air pressure and displays them in the form 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, and 500 foot increments from 1000 to 6000 feet; lower half except dive rate is indicted.

43
Q

Air Data Pressure Transmitters

A

Converts pneumatic static and total pressure inputs from the L-shaped pitot static/total temperature probes into digital signals which are proportional to the measured pressures. Air data is sent to the roll-pitch-yaw computers where it is evaluated using source error corrections to produce true air data. Air data and true air data are used by roll-pitch-yaw computer software for flight control law computations, pilot displays, and other avionics systems.

44
Q

Angle of Attack (AOA) Indexer

A

Operates with the landing gear down and weight off the gear; shows approach angle of attack with lighted symbols.

45
Q

Angle of Attack Transmitters (AOAT)

A

The AOAT measures the difference between the longitudinal axis of the aircraft and the airstream.

46
Q

Power Supply

A

The electrical power supply system consists of two generators, two transformer-rectifiers (TR), one battery with dedicated battery charger, and a power distribution (bus) system. Each generator provides a primary ac source and three isolated dc sources from a permanent magnet generator (PMG). During normal operation, the left generator powers only the left buses while the right generator powers only the right buses. If one generator fails, the other generator is capable of carrying the entire electrical load of the aircraft battery.

47
Q

Maintenance Battery

A

The maintenance battery supplies 28vdc power to the essential and maintenance buses. The battery supplies power to the essential buses if both power supplies and both AC generators are inoperative. The battery supplies power for engine start when external power is not applied.

48
Q

Generator

A

Each generator is a variable speed constant frequency power generator system supplying 115/200vdc, 400 Hz, three phase electrical power; also supplies 28vdc power. The presence of an under-speed, overvoltage, under-voltage, over-frequency, under-frequency, feeder fault, excessive waveform distortion or excessive dc voltage content causes the generator to de-energize the power contactor and the system output is disconnected from the main ac bus and must be reset.

49
Q

Describe the function of the Automatic Flight Control System (AFCS)

A

Provides autopilot and automatic throttle control (ATC)

50
Q

State the purpose of the nose wheel well Digital Display Indicator

A

Receives and stores maintenance codes from the recorder, and provides a visual display of stored maintenance codes on operator request. Provides for manual activation of MSDRS to perform fluids level test of consumable fluids.

51
Q

State the purpose of the Digital Memory Device (DMD)

A

Is a programmable computer which functions as a non-volatile solid state memory device; Two types of computer memory cards (PC cards) are used with the memory unit to upload or download data; mission data is stored on the mission PC card for uploading to the mission computer system/ Aircraft maintenance data is recorded on the maintenance/map PC card for downloading purposes/ Theater-level maps and updates to the digital map system are uploaded using the maintenance/map PC card. Each PC card has a unique part number/
Communicates with the mission computer system to provide recording of aircraft maintenance code history, fatigue strain gage, engine and tactical data

52
Q

State the purpose of the Flight Incident Recorder and Monitoring System (FIRAMS)

A

Monitors engine and airframe operational status for unit failures and caution/advisory conditions.

53
Q

Discuss the Joint Helmet Mounted Cueing System (JHMCS in relation to the EA-18G.

A

The JHMCS improves the situational awareness, increases aircraft survivability, and increases the ability to acquire a visual target.

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