Ea-18G Growler Specific Eaws

Front 1

SAFETY FUNDAMENTALS

Back 1

AIRCRAFT HANDLING FUNDAMENTALS

Front 2

Discuss the concept of ORM and it's process

Back 2

(IAMIS)
Identify
Assess
Make Risk Decisions
Implement
Supervise

Front 3

Respiratory Protection Program
Hearing Conservation Program
Sight Conservation Program
Personal Protective Equipment (PPE) Program

Back 3

Respiratory- identifies employee respirator requirement due to the nature of their work or job
Hearing- designed to prevent hearing loss and ensure auditory fitness
Sight- determines where eye protection is needed and what type
PPE- assesses all workplaces to determine if hazards are present that necessitate the use of PPE

Front 4

Identify the EA-18G danger areas.

Back 4

canopy, seat, DFIRS, external stores locations, engine, radar, antenna, exhaust, movable sufaces, flammable liquids and compressed gases

Front 5

Identify the minimum safe distances from aircraft intakes/exhaust at:
IDLE
MIL
MAX

Back 5

Intake Exhaust
IDLE: 9 115-155
MIL: 25 325-725
MAX: 25 850-925

Front 6

Purpose and Location of the aircraft STEP, NO STEP Areas

Back 6

To avoid damaging composite material.
LEFS, TEFS, horizontal stabs, ailerons, radome

Front 7

Safety precautions when applying and removing external power

Back 7

Ensure Circuitbreakers and switches are properly positioned
inspect power cable
ensure power is secured
mobile power unit is chocked and facing away from aircraft

Front 8

Identify the danger areas during Auxiliary Power Unit (APU) operations.

Back 8

The Exhaust velocity of the APU reaches 142 MPH
The Exhaust temperature reaches 328-350 degrees Fahrenheit

Front 9

Precautions/Restrictions that Apply to Ordnance Loaded Aircraft

Back 9

Major maintenance on aircraft is prohibited.
Minor maintenance and routine servicing may be conducted ONLY after all weapons have been safetied to the max degree.
Don't apply power when weapons are loaded or being loaded.
An aircraft requiring extensive troubleshooting shall be downloaded.

Front 10

WEAPONS LOADED placard/control stick cover indicates maintenance/servicing with electrical power is limited to:

Back 10

Refueling
Replacement and checkout of comm and nav equipment, and engine performance and flight instruments
Engine turnup for checkout
Flight control and hydraulic system checks

Front 11

Precautions when handling Graphite or Carbon/Epoxy Composite Materials.

Back 11

Wear respirator and close weave cotton gloves

Front 12

State the number of tie-down points on the EA-18G and identify their location.

Back 12

12 tie-down rings:
1&2- NLG
3- fwd, door 16
4- outboard left MLG
5- outboard right MLG
6&8- inboard left MLG
7&9- inboard right MLG
10&11- under wings in 107L/R
12- aft, door 164

Front 13

State the proper procedures for aircraft grounding

Back 13

Connect grounding cable to approved ground receptacle
then connect it to grounding point on the aircraft

Front 14

State the purpose of aircraft plugs and covers.

Back 14

Protect aircraft openings and protruding surfaces from FOD and physical and environmental damage

Front 15

Move Director

Back 15

Primarily responsible for move, delivers the move brief.
Assembles a qualified move team, secures towbar, checks clearance and determines when aircraft is ready to move
Sets the pace to a slow walking speed.

Front 16

Brake Rider

Back 16

Conducts a pre-movement inspection of aircraft Ensures aircraft pins are installed and aircraft is free from servicing equipment / external cords
Ensures aircraft has enough brake pressure
(Minimum 2900 PSI)
Does not leave the cockpit until aircraft is spotted

Front 17

Chock Walker

Back 17

Stays alert to director's signals
Pulls and installs chocks
Checks for clearance throught move.
Stay in a relatively safe position from aircraft wheels

Front 18

Safety Observer (Wing-Walker/Tail-Walker)

Back 18

Conduct's a pre-tow inspection of the aircraft
Ensures aircraft is free of chains, cable cords, & SE and watches for obstructions during move

Front 19

Tractor Driver

Back 19

Pre-OP's tractor
Tows aircraft at a slow walking speed
Follows instructions from the director
Avoid any and all obstructions

Front 20

Discuss towing preparations

Back 20

a. Minimum structural access doors must be installed
b. Radome must be closed and secured (if installed).
c. Doors 68 L/R (engine bay doors) closed or removed
d. Hydraulic break pressure of 2900-psi minimum.
e. Ensure aircraft is clear of all obstacles and support equipment.

Front 21

State the purpose of the landing gear aircraft ground safety pins

Back 21

Locks the nose and main landing gear in the down position, preventing gear retraction.

Front 22

Describe the hazard associated with canopy static buildup

Back 22

a high voltage static electrical charge of up to 100,000 volts may build up and be stored in the canopy during flight or when aircraft is exposed to prolonged high winds

Front 23

Discuss the canopy static discharge process

Back 23

Make sure a/c is properly grounded
Connect a preop'd static charge removal kit to the ground receptacle and lightly tap the windshield and canopy until static is discharged

Front 24

AIRFRAMES FUNDAMENTALS

Back 24

x

Front 25

State the purpose of Hydraulic Fluid Contamination Analysis

Back 25

Analyzes fluid contaminant level to ensure purity
Class 5 aircraft
Class 3 GSE

Front 26

State the purpose of a tactical paint scheme

Back 26

Lessen the probability of visual or photographic detection

Front 27

State the purpose of the following publications and their application:

-NAVAIR 01-1A-509
-IETM

Back 27

509- Provides information on material & procedures to prevent & repair of corrosion

IETM- Provides information to support the diagnostics, maintenance, and repair of aircraft systems

Front 28

3 modes of wheel brake operation

Back 28

Normal
Emergency
Parking

Front 29

Discuss the purpose of composite airframe materials

Back 29

limit weight, increase strength, and decrease effects of corrosion

Front 30

Describe the 3 types of repair

Back 30

Temporary Repair- simple and practical, allows aircraft to be flown until permanent repair can be made.

One-time flight- allows an aircraft to be flown to a repair station for permanent repairs

Permanent repair- equals or exceeds strength of original structure or component with no adverse affects

Front 31

Radome

Back 31

Covers radar and provides an electrically transparent window for transmission and reception of radar signals.

Front 32

Forward Fuselage

Back 32

Includes the windshield, canopy, cockpit, leading edge extension, and nose landing gear.

Front 33

Center Fuselage

Back 33

Includes main landing gear, intake ducts, external stores stations, fuselage fuel tanks and airframe mounted accessory drive.

Front 34

Aft Fuselage

Back 34

Includes the engines, speed brake, vertical stabilizers, horizontal stabilators, and arresting hook

Front 35

Wings

Back 35

Provides lift for the aircraft, stores fuel, houses LEF's, TEF's and Ailerons, outboard section folds for carrier operation, allows for attachment of non jettison pylons for weapons and stores.

Front 36

Leading Edge Extension (LEX)

Back 36

Provides added lift at high angles of attack. Mounted on either side of the Forward Fuselage they are an extension of the wing leading edge.

Front 37

Ailerons

Back 37

Deflect Asymmetrically to produce roll, Symmetrically to change lift.

Located outboard trailing edge of each wing.

Front 38

Leading Edge Flaps

Back 38

Deflect Symmetrically to change lift.
Asymmetrically to aid the ailerons in producing roll.

Located forward edge of wings.

Front 39

Trailing Edge Flaps

Back 39

Deflect Asymmetrically to aid the ailerons in producing roll.
Deflect Symmetrically to change lift.

Located aft edge of wings

Front 40

Stabilators

Back 40

Deflect Symmetrically to produce pitch.
Asymmetrically to produce roll.
Also provide pitch compensation during selection of the lex spoilers.

The stabilators are located on either side of the tail of the aircraft.

Front 41

Rudders

Back 41

Toe-in- increases lift and improves stability at AOA les than 8 degrees
Toe-out- improves stability at AOA greater than 8 degrees

In flight is commanded Symmetrically to produce yaw

Front 42

LEX Spoiler

Back 42

Provides speed brake when commanded by pilot at speeds less than MACH 1.5, provides a high nose down pitch movement when transitioning from a high AOA.

L/R of door 22L/R door 610 L/R

Front 43

Hydraulic System 1 (HS1)

Hydraulic System 2 (HS2)

Back 43

HS1- Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source.

System contains pump manifold, pump reservoir, filter unit, case drain filter, oil fuel heat exchange, and related indicator.

HS2- Same as HS 1. Provides hydraulic fluid pressure to the primary flight controls either as a primary or backup source. *The system also supplies pressure to all other non-flight control systems.

Front 44

Auxiliary Power Unit Accumulator

Back 44

Gas Charge cylinder provides required fluid pressure to the APU start motor and emergency hydraulic systems

Front 45

Switching Valves

Back 45

allow backup hydraulic pressure to replace the primary hydraulic pressure, should it fail. If primary hydraulic is restored, the switching valve shifts to normal operating position

Front 46

Nose Landing Gear

Back 46

Nose landing gear strut assembly provides landing, takeoff and taxi energy absorption, and tire/runway compliance.

Located on the underside of the Forward Fuselage.

Front 47

Main Landing Gear

Back 47

Absorbs the energy during landing and taxi operations. Also provides a stable platform for aircraft carrier and shore-based operations.

Located on the underside of the Center Fuselage.

Front 48

Wheel Brakes

Back 48

Provides modulated individual wheel-controlled braking combined with an anti-skid system to prevent wheel skid.

Front 49

Launch Bar

Back 49

Provides a means of steering the aircraft during carrier deck tracking and engages the catapult, applying catapult tow forces to the aircraft.

Located on the forward side of the nose landing gear shock strut.

Front 50

Arresting Hook

Back 50

Engages the arrestment cable on the carrier to stop the aircraft, also provides a means of stopping the aircraft where normal runway landings are unavailable

Located on the underside of the aft fuselage.

Front 51

Discuss basic operation of the Electronic Flight Control System

Back 51

The Electronic flight control system is made up of two flight control computers that combine inputs with air data and inertial inputs and provide electrical signals to servo actuators which move control surfaces. A built-in test provides failure warning and fault isolation.

Front 52

Discuss Emergency Extension of the Landing Gear

Back 52

Emergency extension is primarily free fall aided by stored energy in the MLG shock absorber and hydraulic system no. 2B pressure.

Front 53

POWER PLANTS

Back 53

xx

Front 54

State the 3 modes of operation for the APU

Back 54

Environmental Control Systems
Ground Maintenance Mode
Main Engine Start

Front 55

State the purpose and location of the IFR probe

Back 55

Right forward fuselage
Allows inflight refueling

Front 56

Purpose of Aircraft Fuel Storage System

Back 56

Manage and store fuel for delivery to aircraft engines
4 internal fuselage tanks
2 internal wing tanks
and up to 5 external tanks

Front 57

State the purpose of the foam-lined wing tanks.

Back 57

To self-seal holes or damage, decreasing fire and explosion hazards

Front 58

What are the secondary power systems?

Back 58

APU
AMAD
Secondary power compressed air

Front 59

Auxilary Power Unit (APU)

Back 59

A centrifugal flow gas turbine engine that supplies air for ECS operation and MES and GMM through AMADs.

Located in door 52.

Front 60

Airframe Mounted Accessory Drive (AMAD)

Back 60

Consists of two identical interchangeable gearboxes that are mechanically connected to the engine by a power transmission shaft (PTS). And is pneumatically connected to the APU through the air turbine starter (ATS). The AMAD transmits power to the engine for starts.

Power to drive the AMAD accessories is provided by the engine during normal operations or by the APU during ground maintenance operations.
Located inside door 53L/R.

Front 61

Secondary Power Compressed Air

Back 61

Provides pneumatic power for operating the air turbine starter or the environmental control system, provided by the APU or engine bleed air.

An air connection is located in the right well wheel and allows use of an external air source for system operation (huffer starts).

Front 62

State the model type and engine used in the EA-18G

Back 62

F414-GE-400 is a low by-pass axial flow turbo fan engine of modular construction with afterburner

Front 63

Ignition

Back 63

An automatic, intermittent duty, AC powered, capacitor discharge system.
Remains on until N2 rpm is 54% or more or throttle is below idle.

Front 64

Lubrication

Back 64

Provides lubrication and cooling to required bearings and gears.

Front 65

Main fuel

Back 65

Primarily supplies fuel for all main fuel combustion operations from IDLE to MIL power.

Also used for hydraulics and cooling.

Front 66

Afterburner fuel

Back 66

Governs the correct afterburner fuel flow controlling afterburner operation from start through MAX

Front 67

Variable Exhaust Nozzle (VEN)

Back 67

throat area for exhaust gasses from the turbine and afterburner.

Provides thrust and fuel efficiencies while maintaining exhaust gas temperature.

Front 68

Variable Geometry

Back 68

Consists of:
Fan Variable Geometry- which provides the best efficiency of the fan while preserving fan stall margin.
Compressor Variable Geometry- which provides the best efficiency of the compressor while preserving compressor stall margin.

Front 69

Anti-icing

Back 69

Manually activated system that provides anti-ice air flow to prevent ice buildup on air inlet hardware.

Front 70

Full Authority Digital Engine Control (FADEC)

Back 70

Receives aircraft and engine sensor information and determines the appropriate engine scheduling to operate the engine.

Front 71

Throttle

Back 71

Provides pilot control of engines.
L&R throttles independently control L&R engines respectively.

Movement is transmitted by an electrical interface that communicates with the FADEC.

Front 72

Fuel Systems

Back 72

x

Front 73

Fuel storage

Back 73

Fuel is stored in:
4 internal fuselage tanks
2 internal wing tanks
and up to 5 external tanks

Front 74

Refuel/Defuel System

Back 74

A manifold with a single point ground and an outlet in each tank.

Refuel/Defuel Can be done with or without electrical power or with engines operating and is monitored and controlled from door 8.

Front 75

Internal Fuel Transfer

Back 75

Keeps tanks 2 and 3 full and controls the sequence of tank-to-tank transfer.

1 & 2 transfer to 2 & 3
wing fuel tanks replenish 4

Front 76

Center of Gravity (CG) Control

Back 76

The SDC monitors the amount of fuel in tanks 1 and 4; so, if fuel in tank 4 becomes excessive the computer will close its valves to prevent an aft center of gravity problem

Front 77

Hot Fuel Recirculation

Back 77

Cools the fuel by circulating fuel up into the wings to be cooled by means of convection, which is used to dissipate heat from the AMAD and hydraulic system

Front 78

Fuel Pressurization and Vent

Back 78

Maintains positive pressure on the fuel in all tanks and vents fuel vapors overboard

Front 79

Fuel Quantity Gauging

Back 79

Fuel quantity is measured using capacitance gauging transmitters that send signals to the SDC

Front 80

State the components driven by the AMAD.

Back 80

fuel boost/motive flow pump
electrical generator
3000/5000 psi hydraulic pump

Front 81

How does the AMAD interface with the APU and engine?

Back 81

The AMAD is pneumatically connected to APU through the air turbine starter (ATS). The AMAD transmits power from the ATS to the engine for starting and motoring. Power to drive the AMAD accessories is provided by the engine during normal operation and by the APU in the ground maintenance mode of operation.

Front 82

What safety precautions must be observed during engine ground turn-up?

Back 82

During engine ground turn-up, danger can stem from exhaust velocity and temperature, air intakes, and noise.
Wear proper PPE.

Front 83

What special safety precautions apply to:

- Fueling

- Defueling

Back 83

Do NOT do within:
100ft of airborne radio or radar equipment
300ft of ground radar equipment.
Wear goggles, monitor guages, and man a fire bottle.

Same as fueling.

Front 84

AVIONICS/ELECTRICAL

Back 84

xx

Front 85

Barometric Altimeter

Radar Altimeter

Back 85

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

Radar- uses radio echoes to determine altitude above ground level

Front 86

1) Azimuth

2) Bearing

3) Range

Back 86

1) Angular position in a horizontal plane usually measured clockwise from true north.

2) Angular position of an object from a reference point

3) Distance of an object from an observer

Front 87

1) Heading

2) True Heading

3) Magnetic direction

4) Relative direction

Back 87

1) Actual orientation of aircrafts longitudinal axis
2) Direction measured by true north
3) Uses direction of earth's magnetic field at that location as reference
4) Uses the current direction that an object is facing as the 0/360-azimuth alignment

Front 88

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

Back 88

The provide improved system performance
Immunity to electrical noise
Signal security
Improved safety, environmental protection
Reduce size and weight

Front 89

State the purpose of the following communication systems

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

Back 89

provides air-to-air and air-to-ground communications in fixed frequency or anti-jam mode

Front 90

State the purpose of the following communication systems

Intercommunication and Audio System (IAS)

Back 90

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 tones, and voice alerting.

Front 91

Name the Navigation Systems

Back 91

TACAN
INS
GPS
ARI
ILS

Front 92

Tactical Air Navigation (TACAN)

Back 92

determine the relative bearing and distance to a TACAN ground station or TACAN equipped aircraft.

The TACAN is also used to update the aircraft present position being kept by another source (INS or ADC)

Front 93

Inertial Navigation System (INS)

Back 93

Fully automatic dead reckoning navigation system.

On 164945 and up A/C the INS is closely coupled by the MC with the GPS to provide position and velocity data. The INS detects aircraft motion and provides position information to related systems.

Front 94

Global Positioning System (GPS)

Back 94

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

Front 95

Attitude Reference Indicator (ARI)

Back 95

A self-contained attitude reference system that provides backup pitch and roll attitude for use by other systems. Provides 3 minutes of attitude information with loss of power.

Consists of an electrically driven gyro that maintains vertical orientation through use of electronic erection system.

Front 96

Instrument Landing System (ILS)

Back 96

An all weather approach guidance system. The ILS decodes transmitted azimuth and elevation signals during an aircraft approach and provides steering information to be displayed on the head-up display (HUD)

Front 97

Tactical Mission Systems

Back 97

Data Link
RADAR
MC

Front 98

Data Link

Back 98

A two-way uhf communication link between the aircraft and other ship, air, or ground systems.

Has 4 modes:
Automatic Carrier Landing (ACL)
Vector (VEC)
Waypoint
Alignment (ALGN)

Front 99

Radio Detection and Ranging (RADAR)

Back 99

Provides Air-to-air (A/A) and Air-to-ground (A/G) modes for target detection, designation, tracking and navigation

Front 100

Mission Computer (MC)

Back 100

MC System is made of 2 identical digital data computers that control the display sent to the multipurpose display group.

(Computes and produces missile launch and weapon release commands)

Front 101

Tactical Electronic Warfare Systems

Back 101

xx

Front 102

Communication Countermeasures Set (CCS)

ALQ-227

Back 102

Produces waveforms for jamming low frequency communication - and provides growth provisions for a high power CCS transmitter

Compatible with ALQ-99 low band transmitter

Front 103

ALQ-99

Back 103

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

Front 104

ALQ-165/214

Back 104

onboard jamming system; uses multiple techniques to defeat tracking and acquisition radar

Front 105

ALQ-218

Back 105

Detects, classifies, locates, and reports radar emitters and associated signals received by antennas mounted around the aircraft on the forward and aft fuselage and on the wingtips.

System is made up of:
9 WRAs
20 antenna
6 power dividers

Front 106

What are the major components of the AN/ALQ-99 Tactical Jamming System

Back 106

Turbo-generator housing (hardback)
Transmitters
Universal Exciter
Ram air turbo-generator
Radome

Front 107

Identify the location of the major components of the AN/ALQ-99 Tactical Jamming

Back 107

Front 108

What are the multipurpose display group (MDG) components?

Back 108

HUD
DDI (L/R)
UFCD
MPCD

Front 109

Heads-Up Display (HUD)

Back 109

Provides flight, navigational steering, and weapon delivery information to the pilot's forward field of view.

The total forward field of view is 20 degrees, with optical center 4 degrees below aircraft waterline

Front 110

Digital Display Indicators (DDI)

Back 110

LDDI-used primarily for stores management, caution, advisory, and BIT displays.
RDDI-used primarily for sensor displays. Information can be brought up on either DDI and both are interchangeable.

Front 111

Up Front Control Display (UPCD)

Back 111

Touch screen, provides for entry and display of aircraft data, used for selection and control of communication, navigation, and identification functions.

Front 112

Multipurpose Color Display (MPCD)-

Back 112

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

Front 113

Describe the function of the Digital Map Set (DMS)

Back 113

The DMS is made up of a Digital Map Computer (DMC) and a high speed interface cable. It's part of the Tactical Aircraft Moving Map Capability (TAMMAC) system which provides enhanced navigational/tactical situational awareness to aircrew, using a moving map and image database.

Front 114

Describe the function of the Solid State Recorder

Back 114

Records cockpit and sensor video, also stores off-board images and allows access to images loaded on the Removable Memory Module (RMM)

Front 115

State the location, purpose, and color of the following exterior lights

Back 115

xx

Front 116

Position

Back 116

Show position of A/C at night

left-red
right-green
tail-white

Front 117

Strobe

Back 117

Two red (anti-collision) lights, one on each outboard vertical stab.
Day ID strobe light (white) is located on the NLG strut and is used to identify the aircraft

Front 118

Landing/taxi

Back 118

White light on the nose gear strut. Used to illuminate the taxiway/runway

Front 119

Approach

Back 119

On NLG strut, activated when all landing gear are down and locked and weight off wheels. Displays the AOA to the LSO during carrier approach.

Front 120

Formation Lights

Back 120

8 green LED lights. Two on each wing tip, one outside of each vertical stab, and one on each side of the forward fuselage just forward of the lex. They indicate changes of attitude and relative position of aircraft flying in formation.

Front 121

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

Back 121

The purpose of DFIRS is to store flight data and to deploy it before a crash. In door 300; a thin layer explosive, impact initiator, and detonation cord provide deployment operations. A beacon will transmit signals to be detected by search and rescue sattelite for 72 hours.

Front 122

Flight Reference Equipment

Back 122

Pitot Static System
Indicated Airspeed Indicator
Standby Pressure Altimeter
Vertical Speed Indicator

Front 123

Pitot Static System

Back 123

Measures temperature, pitot and static pressures surrounding the aircraft.

Front 124

Indicated Airspeed Indicator

Back 124

Displays airspeed as a function of the pitot and static pressure. Airspeed is indicted in 10-knot increments from 50 to 200 and 50-knot increments from 200 to 850

Front 125

Standby Pressure Altimeter

Back 125

Displays altitude with 3 displays:
-A pointer display for alt to 1000ft in 50ft increments,
-A drum display for alt to 99,000ft with 1000ft increments
-A four digit display, indicating barometric pressure in inches of mercury

Front 126

Vertical Speed Indicator

Back 126

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 indicates rate of climb
Lower half indicates dive rate

Front 127

Air Data System Components

Back 127

Air Data Pressure Transmitters
AOA indexer
AOAT

Front 128

Air Data Pressure Transmitters

Back 128

Converts pneumatic static and total pressure inputs from pitot probes into digital signals. Air data is sent to the roll-pitch-yaw computers where it is evaluated to produce true air data. Air and true air data are used by roll-pitch-yaw computer software for flight control law computations, pilot displays, and other avionics systems.

Front 129

Angle of Attack (AOA) indexer

Back 129

Operates with landing gear down and weight off wheels, shows pilot approach AOA with lighted symbols

Front 130

Angle of Attack Transmitters (AOAT)

Back 130

measures the difference between the longitudinal axis of the aircraft and the airstream

Front 131

Describe the function of the following electrical power components:

Back 131

X

Front 132

Power Supply

Back 132

Consists of two generators, two transformer-rectifiers (TR), one battery with battery charger, and a power distribution (bus) system.
Each GEN provides a primary AC source and 3 isolated DC sources from a PMG.
Normal operation- L GEN powers L buses while R GEN powers R buses, if one fails, the other will carry the load of the battery.

Front 133

Maintenance Battery

Back 133

Supplies 28vdc to the essential and maintenance buses. It will supply power to the essential buses if both power supplies and generators are inoperative. It also supplies power for engine start when external power is not applied.

Front 134

Generator

Back 134

Each generator is a variable speed constant frequency power system supplying 115/200vdc, 400 Hz, three phase electrical power.
With the presence of underspeed, over/under voltage, over/under frequency, feeder fault, excessive waveform, or excessive DC voltage- the generator will de-energize and must be reset

Front 135

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

Back 135

Provides autopilot and automatic throttle control (ATC)

Front 136

State the purpose of the nose wheel well Digital Display Indicator (NDDI)

Back 136

Receives and stores maintenance codes and displays them upon operator request.
Provides for manual activation of MSDRS to perform fluids level test of consumable fluids.

Front 137

Digital Memory Device (DMD)

Back 137

Programmable solid state memory device. Records mission and maintenance data on two downloadable memory cards.

Communicates with the MC system to provide maintenance code history, fatigue strain gage, engine and tactical data.

Front 138

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

Back 138

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

Front 139

Discuss the Joint Helmet Mounted Cueing System (JHMCS)

Back 139

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

Front 140

State the objective of the Explosive Handling Qualification and Certification Program

Back 140

To certify and train all personnel in safely performing tasks involving explosive devices

Front 141

State the purpose of suspension/accessory equipment

Back 141

To suspend and release stores, bombs, and a variety of missiles

Front 142

State the purpose of an impulse cartridge (Cartridge Actuated Devices (CADS))

Back 142

To eject single stores and a variety of weapons from the aircraft

Front 143

Define the following acronyms:

AIM
AGM
CATM
HERO

Back 143

Air-Launched Intercept-Aerial Guided Missile. (Air Intercept Missile)
Air-Launched Surface-Attack Guided Missile. (Air to Ground Missile)
Captive Air Training Missile
Hazards of Electromagnetic Radiation to Ordnance

Front 144

Describe the application of the following types of bombs:

Retarded

Non-Retarded

Back 144

Retarded- Used during low-level bombing, fins open to slow down weapon, allowing jet time to clear the area

Non-Retarded- Used during high-level bombing, fins remain closed, allowing weapon to fall unimpeded to target

Front 145

Explain the significance of the following color-coding on weapons:

Yellow
Brown
Blue

Back 145

Yellow- High Explosive

Brown- Rocket Motor

Blue- Training

Front 146

Define the following types of weapon-guided systems:

Active
Semi-active
Passive

Back 146

Active- target illumination is supplied by component inside the missile
Semi-Active- Illumination is received from an outside source, such as aircraft
Passive- Illumination is received from target

Front 147

Describe the purpose of chaff and flares as countermeasure devices.

Chaff
Flares

Back 147

Chaff- Finely shredded metal strips that disperse into the atmosphere and jam radar

Flares- Used as decoy for heat seeking missiles

Front 148

Describe the hazards associated with forward firing ordnance.

Back 148

auto-ignition
toxic chemicals
inadvertent separation from aircraft
high heat
protruding surfaces
motor detonation

Front 149

Describe the type of bomb rack used on the EA-18G.

Back 149

BRU-32
Used to suspend and eject single stores and weapons with a 14 or 30 inch suspension.

Front 150

Describe the location and purpose of the ICM switch.

Back 150

On left forward fuselage.

Extended/safe position- all countermeasure dispensing is inhibited
Flush/arm position- dispensing is enabled

Front 151

State the purpose of the following components of the Stores Management System or (SMS)

1) Armament control processor set (aka SMS)
2) Command Launch Computer (CLC)

Back 151

1) Provides electrical interface between weapon stations and aircraft. Consists of the Armament Computer and up to nine Signal Data Converter Controls.

2) Controls and monitors the high-speed anti-radiation missile (HARM) ((Door 13R))

Front 152

State the purpose of the Countermeasures Dispensing system:

-AN/ALE-47

-AN/ALE-50

Back 152

47- The system provides protection for the aircraft against enemy radars and missiles by ejecting chaff, flares, or other jammer payloads.

50- A towed active RF decoy system which provides an effective off-board countermeasures capability

Front 153

State the basic armament configuration of the EA-18G aircraft.

Back 153

Fuselage LAU-116 missile launchers
Wingtip ALQ-218 pods
SUU-78 centerline pylon
SUU-79 in/mid board wing pylons
SUU-80 outboard pylons
BRU-32 bomb racks
ADU-733 launcher adapters

Front 154

Stations:
1) LAU-127
2) LAU-116
3) SUU-78
4) SUU-79
5) SUU-80
6) BRU-32

Back 154

1) LAU-127 - 2 or 10
2) LAU-116 - 5 & 7
3) SUU-78 - 6
4) SUU-79 - 3, 4, 8, 9
5) SUU-80 - 2, 10
6) BRU-32 - All pylons

Front 155

State the basic characteristics of the following air-to-air missiles:

AIM-7 series (Sparrow) guided missile

Back 155

Solid fuel rocket propelled air-to-air missile with a conventional warhead that uses SEMI-ACTIVE radar homing

Front 156

AIM-9 series (Sidewinder) guided missile

AIM-9M
AIM-9X

Back 156

9M- A supersonic, air-to-air weapon, with a PASSIVE infrared target detection, proportional-navigation guidance, and torque balance control system.

9X- A supersonic, air-to-air weapon with improved maneuverability. Incorporates a cryo-engine to eliminate the need for a cryo gas bottle.

Front 157

AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM)

Back 157

Is a supersonic, air-to-air weapon, with active radar target detection and on-board inertial navigation guidance.

Front 158

State the basic characteristics of the following air to ground missiles:

AGM-65 (Maverick) series missile

Back 158

A solid fuel rocket propelled AGM missile with a conventional warhead, uses imaging infared guidance.

Front 159

AGM-84 series missiles
-AGM-84D (Harpoon)
-AGM-84E Stand-off Land Attack Missile (SLAM)
-AGM-84H Stand-off Land Attack Missile Expanded Response (SLAM-ER)

Back 159

AGM-84 series: Liquid fuel jet engine propelled AGM missiles with conventional warhead, primarily used as anti-ship weapons.
D- Uses active radar seeker
E- Uses INS, GPS, and IR for guidance
H- Improved control, range, and target penetration

Front 160

AGM-88 High-speed Anti-Radiation Missile (HARM)

Back 160

A solid fuel rocket propelled AGM with conventional warhead, uses proportional guidance to home in on threat radar emissions.

Front 161

AVIATION LIFE SUPPORT/EGRESS

Back 161

X

Front 162

Identify the minimum requirements for aircrew Personnel Protective Equipment

Back 162

1) Flight suit
2) Aircrew fliers boots
3) Anti-g garment
4) Helmet
5) Survival radio/beacon
6) Gloves
7) Anti-exposure suit
8) ID tags
9) Knife
10) Personal survival kit
11) Signal device
12) Flashlight
13) Life preserver
14) Laser eye protection

Front 163

State the purpose of the Environmental Control System (ECS)

Back 163

Provides Avionics Cooling and Aircrew Comfort

Front 164

Environmental Control System (ECS) 12 subsystems:

Back 164

1) Bleed air control
2) Bleed air leak detection
3) Air cycle conditioning
4) Cabin cooling and defog
5) Avionics cooling
6) Cabin pressurization
7) Anti-g
8) On-board oxygen generating system (OBOGS)
9) Windshield anti-ice and rain removal
10) Radar Liquid cooling
11) Canopy seal
12) Wave guide pressurization

Front 165

State the purpose of the following personal flight equipment:

Oxygen Mask

Back 165

Provides breathing gas upon demand at a pressure schedule dependent on the altitude. Also provides facial protection from projectiles and fire as well as being qualified for depths of 16ft under water.

Front 166

The CRU-103/P Oxygen regulator

Back 166

A chest mounted, positive pressure, g-modulated regulator that provides on demand oxygen flow to the aircrew

Front 167

The LPU-36/P Life Preserver

Back 167

A Low Profile Floatation Collar equipped with the FLU-8B/P automatic/manual inflation assembly authorized for use only with aircraft equipped with ejection seats.

Front 168

Anti-G Suit

Back 168

Consist of a bladder system encased in fire-resistant cloth, As G-forces increase the bladders inflate automatically to apply pressure on the body to restrict downward bloodflow and lessen the effects of blackout.

Front 169

State the objective of the Egress Systems Checkout Certification Program.

Back 169

To familiarize and monitor personnel working in or around the cockpit with the ejection systems.

-Must qualify before working on or around aircraft -Every 6 months
-After 90 days TAD

Front 170

State the purpose of the ejection seats.

Back 170

Provides a place for the aircrew to sit and for emergency egress during flight

Front 171

Define the following conditions:

Hypoxia

Anoxia

Back 171

Hypoxia- Decrease in the amount of oxygen per unit volume of air which results in an insufficient amount of oxygen in the bloodstream causing the eyes, body and muscles to fail. (Blackout) ((Insufficient oxygen-causes blackout))

Anoxia- Death caused by complete lack of oxygen.

Front 172

Identify the two types of Aviator's Breathing Oxygen (ABO

Back 172

Type I: Gaseous oxygen - MIL-0-272710D

Type II: Liquid oxygen

Front 173

State the purpose of the Dry Bay Fire Suppression System (DBFSS)

Back 173

The Dry Bay Fire Suppression System suppresses fire events associated with ballistic damage to the aircraft before a significant fire occurs. Performs without pilot action and consists of 14 optical fire detectors, 6 dry bay extinguishers and a fire suppression control alarm.

Front 174

State the purpose of the Parachute Harness Sensing Release Unit (PHSRU)

Back 174

A sea water activated release system that provides a backup automatic mode of separating the parachute from the aircrew.

Front 175

Describe the A/A24A-56 Helmet Unit, Intergrated, Joint Helmet Mounted Cueing System (JHMCS)

Back 175

A display system used to cue, verify, and employ weapons and sensors in high off bore sight angles.

Provides the mounting platform for the HDU and protects the operator from high impact and wind during ejection.

Front 176

State the purpose of the Helmet Mounted Display Unit (HDU)

Back 176

HDU displays symbology onto the visor and is superimposed on the operators view.

Also records real-world view by routing the video to the cockpit video recording system (CVRS)

Front 177

Discuss the location and type of ejection seat used in the EA-18G.

Back 177

The ejection seat is a SJU-17B (V) 2/A (front) 9/B (back)
The seat is automatic, cartridge operated, and rocket assisted. Ejection is initiated by pulling the ejection control handle on the front of the seat bucket.

Front 178

Discuss the location and procedures for the operation of the canopy system.

Normal Operation
Emergency Operation

Back 178

Normal Operation- Electrically with internal or external switch. Manually as backup when electrical power fails.

Emergency Operation- Canopy Jettison

Front 179

Discuss the location and operation of the Aircraft Fire Detection and Fire Extinguishing Systems.

Back 179

The fire detection system monitors the AMAD, APU, and engine bays for fire or overheat conditions. Provides audible and visual warnings of these conditions.

The fire extinguishing system uses a single fire extinguisher tank with 3 distribution lines, one for APU, and one for each engine bay. A one shot, one bay system.

Front 180

Environmental Control Systems:

Bleed Air System

Back 180

Consists of various clamped, insulated metal ducts that connect system control valves and sensors.

The system supplies hot, high pressure engine bleed air for the ECS, OBOGS, and external fuel tank pressurization.

Front 181

Air Cycle Air Conditioning System

Back 181

Cools and conditions engine bleed air for use in ECS and other systems.

Front 182

Anti-Gravity System

Back 182

Made of tubing and a valve that automatically regulates air pressure to the pilot's anti-g suit to increase pilot tolerance to high acceleration levels.

Front 183

On-board Oxygen Generation System (OBOGS)

Back 183

Series of lines valves and a concentrator that regulate pressure, control flow and distribute oxygen to the crew station.

Contaminants are removed from engine bleed air leaving an oxygen rich breathing gas mixture. Gas is ducted to the cockpit to be monitored for the correct oxygen content before being supplied to the pilot. Waste gases are vented overboard.

Front 184

Ejection Seat System

Back 184

Operated by ballistic gas pressure. Each seat initiator contains 2 cartridges. Gases from the right cartridge start canopy jettison, activate the seat electronic sequencer and restraints, and fires the seat catapult after a delay inserted by the escape system. Gases from the left cartridge redundantly activate the seat electronic sequencer and also provides a backup source to fire the seat catapult.

Front 185

Canopy System

Back 185

Provides the capability to explosively jettison the canopy from the aircraft in case of emergency.

Jettison is automatic when seat ejection is initiated. A CANOPY JETT lever in the cockpit initiates canopy jettison without initiating seat ejection.

Front 186

Emergency Oxygen System

Back 186

Located in the seat pan and is manually operated by a green handle located on the left side of the seat platform.
Emergency oxygen is automatically activated during ejection by a lanyard connected to the cockpit floor.
An oxygen hose provides connections between the pilot and the aircraft survival kit system.

Front 187

Describe the safety precautions that apply to:

Ejection Seats
Canopy Jettison System
Canopy Operation

Back 187

Ejection Seats- Pins are installed and handle safe
Canopy Jettison System- Ensure canopy jettison pin is installed
Canopy Operation- Do not leave canopy in an intermediate position or open/close when in motion.
Don't use battery power to open below 0 degrees.
Insure clearance before operation.
Canopy ground safety pin installed.

Front 188

OPERATIONAL FUNDAMENTALS

Back 188

X

Front 189

Define the following acronyms:
AIRNAV
ACM
BFM
CAP
CAS
CSAR
FAC

Back 189

AIRNAV- Airborne Navigation
ACM- Air Combat Maneuvering
BFM- Basic Fighter Maneuvering
CAP- Combat Air Patrol Station
CAS- Close Air Support
CSAR- Combat Search and Rescue
FAC- Forward Air Combat

Front 190

Define the following acronyms:
FCLP
SEAD
WAS
EWSEX
HARMEX

Back 190

FCLP- Field Carrier Landing Practice
SEAD- Suppression Enemy Air Defences
WAS- War at Sea
EWSEX- Electronic Warfare System Exercise
HARMEX- Harm Missile Exercise

Front 191

Aviator Flight Rules:

VMC

IMC

Back 191

(Visual Meteorological Conditions)
Expressed in terms of visibility, cloud distance, and ceiling equal to or better than specified minimums of 1000 ft. ceiling and 3 mile visibility (1000/3).

(Instrument Meteorological Conditions)
Expressed in terms of visibility, distance from clouds and ceiling less than the minimum specified

(If the weather is less than 1000/3 then IMC exists.)

Front 192

Aviator Flight Rules:

VFR

IFR

Back 192

(Visual Flight Rules)
Rules that govern the procedures for conducting flights under visual conditions.

(Instrument Flight Rules)
Rules that govern the procedures for conducting instrument flight.

Front 193

Discuss the purpose of the Carrier Air Traffic Control Center (CATCC)

Back 193

Primary control of airborne aircraft operating from the carrier, responsible for the status and upkeep of all carrier air operations.

Front 194

Describe the following Landing Systems:
Describe the following:

Fresnel Lens Optical Landing System (FLOLS)

Manually Operated Visual Landing System (MOVLAS)

Back 194

The FLOLS or “meatball” is an optical system on board the carrier that aids pilots in landing aboard the ship.

MOVLAS is an emergency system that is supposed to be used when the primary optical landing system is rendered inoperative. (due to excessive pitching)

Front 195

Command's Mission Statement

Back 195

To indoctrinate, train, and qualify USN, USMC, and USAF aircrew in the EA-18G aircraft to fight and win in electronic combat. We enhance fleet combat readiness with direct support.

Front 196

Warfare Mission Areas:

Anti-Air Warfare (AAW)
Anti-Surface Ship Warfare (ASU)
Anti-Submarine Warefare (ASW)

Back 196

AAW- The detection, tracking, destruction or neutralization of enemy air platforms and weapons, whether launched by the enemy from air, surface, subsurface, or land platforms.
ASU- detection, tracking, destruction or neutralization of enemy ships
ASW- detection, tracking, destruction or neutralization of enemy submarines

Front 197

Warfare Mission Areas:

Command and Control Warfare (C2W)
Fleet Support Operations (FSO)
Intelligence (INT)

Back 197

C2W- The integrated use of psychological operations (PSYOP), military deception, operations security (OPSEC), electronic warfare (EW), and physical destruction; mutually supported by intelligence, to deny information to, influence, degrade, or destroy adversary.
FSO- consists of non-logistics replenishment to fleet units
INT- collection, processing, and evaluation of valuable information through reconnaissance and surveillance

Front 198

Warfare Mission Areas:

Mine Warfare (MIW)
Mobility (MOB)
Strike Warfare (STW)

Back 198

MIW- use of mines in sea control and mine countermeasure over, under, or on surface.
MOB- ability of naval forces to maneuver or maintain themselves over, under or upon surface.
STW- destruction or neutralization of enemy targets ashore through the use of conventional or nuclear weapons.