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218 Cards in this Set
- Front
- Back
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WHAT DO THE AIRCRAFT STRUCTURE AND SURFACES CONTAIN? |
GRAPHITE AND CARBON/EPOXY COMPOSITE MATERIALS
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NO STEP AREAS
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LEADING EDGE FLAPS, TRAILING EDGE FLAPS, HORIZONTAL STABILIZERS, AILERONS, AND RADOME SURFACES |
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HIGH VOLTAGE |
100,000 VOLTS
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HOW TO REMOVE STATIC ELECTRICITY CHARGE?
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STATIC CHARGE REMOVAL KIT (HAPPY HAND) |
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TOTAL TIEDOWN POINTS
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12
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TOTAL TIEDOWN POINTS WITH JACKS
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14 (13 AND 14 ON JACKING BEAM)
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LOCATIONS OF TIEDOWN POINTS
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1 & 2- NOSE LANDING GEAR 3- FORWARD FURELAGE IN DOOR 16 4, 6, 8- LEFT MAIN LANDING GEAR 5, 7, 9- RIGHT MAIN LANDING GEAR 10& 11- UNDER WINGS DOORS 107L/R 12- AFT FUSELAGE DOOR 164 |
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TYPES OF REPAIR (3)
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TEMPORARY PERMANENT ONE TIME FLIGHT |
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MAJOR SECTIONS OF AIRCRAFT
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RADOME FORWARD FUSELAGE CENTER FUSELAGE AFT FUSELAGE |
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RADOME
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COVERS THE RADAR
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FORWARD FUSELAGE |
END OF THE RADOME TO AFT OF PANEL 18 INCLUDES: WINDSHIELD, CAMOPY, COCKPIT, LEADING EDGE EXTENSION, NOSE LANDING GEAR |
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CENTER FUSELAGE
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FORWARD EDGE OF PANEL 26 TO AFT EDGE OF PANEL 55L/R INCLUDES: MAIN LANDING GEAR, INTAKE DUCTS, EXTERNAL STORES STATIONS, FUSELAGE FUEL TANKS, AMAD |
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AFT FUSELAGE
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PANEL 62 L/R TO EXHAUST NOZZLES INCLUDES: ENGINE, SPEED BRAKE, VERTICAL STABS, HORIZONTAL STABS, ARRESTING HOOK |
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LEADING EDGE EXTENSTION (LEX)
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PROVIDES ADDED LIFT AT HIGH ANGLES OF ATTACK MOUNTED ON EITHER SIDE OF THE FORWARD FUSELAGE |
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AILERONS
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IN FLIGHT, COMMANDED ASYMMETRICALLY TO PRODUCE ROLL TAKE OFF/LANDING, DEFLECT SYMMETRICALLY WITH THE TRAILING EDGE FLAPS UP TO 42 DEGREES LOCATION- OUTBOARD TRAILING EDGE OF WINGS |
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LEADING EDGE FLAPS
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TAKE OFF/LANDING, DEFLECT SYMMETRICALLY TO CHANGE LIFT IN FLIGHT, DEFLECT ASYMMETRICALLY TO AID AILERONS WITH ROLL LOCATION- INBOARD/OUTBOARD LEADING EDGE OF WINGS |
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TRAILING EDGE FLAPS
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TAKE OFF/LANDING, DEFLECT SYMMETRICALLY TO CHANGE LIFT IN FLIGHT, ASYMMETRICALLY TO AID AILERONS WITH ROLL LOCATION- TRAILING EDGE OF WINGS |
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STABILIZERS
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DEFLECT SYMMETRICALLY TO PRODUCE PITCH AND ASYMMETRICALLY TO PRODUCE ROLL LOCATION- EITHER SIDE OF THE TAIL OF THE AIRCRAFT |
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RUDDERS
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TAKE OFF/LANDING, AOA>8 DEGREES RUDDERS TOE IN TO INCREASE LIFT AOA<8 DEGREES, TOE OUT TO IMPROVE STABILITY IN FLIGHT, SYMMETRICALLY TO PRODUCE YAW LOCATION- REAR OF EACH VERTICAL STAB |
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SPEED BRAKE
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ONLY ON A-D EXTENDED TO CREATE DRAG LOCATION- TOP OF AFT FUSELAGE BETWEEN VERTICAL STABS |
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LEADING EDGE EXTENSION (LEX) SPOILER
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E-F ONLY PROVIDES SPEED BRAKE AT AIRSPEEDS>MACH 1.5 AND A NOSE DOWN PITCH MOVEMENT WHEN TRANSITIONING FROM A HIGH AOA W/AGGRESSIVE NOSE DOWN MANEUVER LOCATION- L/R SIDE OF AIRCRAFT |
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NOSE LANDING GEAR
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PROVIDES LANDING TAKE OFF, TAXI ENEGRY ABSORPTION, TIRE/RUNWAY COMPLIANCE LOCATION- UNDERSIDE OF FORWARD FUSELAGE |
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LAUNCH BAR
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PROVIDES A MEANS OF STEERING AIRCRAFT DURING DECK TRACKING AND ENGAGES THE CATAPULT LOCATION- FORWARD SIDE OF NOSE LANDING GEAR SHOCK STRUT |
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MAIN LANDING GEAR
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LEVER DESIGN W/SHOCK ABSORBER PROVIDES STABLE PLATFORM FOR AIRCRAFT CARRIER AND SHORE OPERATIONS LOCATION- UNDERSIDE CENTER FUSELAGE ON L/R SIDE OF AIRCRAFT WHEEL BRAKES ATTACHED TO MLG |
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WHEEL BRAKES
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PROVIDE PILOT WITH WHEEL CONTROLLED BRAKING ANTI SKID SYSTEM COMBINED WITH NORMAL SYSTEM TO PREVENT WHEEL SKID |
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ARRESTING HOOK
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HYDRAULICALLY HELD UP, PNEUMATICALLY HELD DOWN WHEN LOWERED FOR CARRIER LANDING, HOOK POINT ENGAGES AN ARRESTMENT CABLE PROVIDES A MEANS OF STOPPING WHERE NORMAL RUNWAYS AREN'T AVAILABLE |
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HYDRAULIC SYSTEM
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CONTAINS- ACCUMULATOR, HYDRAULIC RESERVOIR, LINES AND MULTIPLE VALVES
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HYDRAULIC SYSTEM 1
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PROVIDES HYD FLUID PRESSURE TO PRIMARY FLIGHT CONTROLS EITHER AS PRIMARY OR BACKUP SOURCE SMALLER OF THE TWO SYSTEMS |
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HYDRAULIC SYSTEM 2
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PROVIDES HYD FLUID PRESSURE TO PRIMARY FLIGHT CONTROLS EITHER AS PRIMARY OR BACKUP SOURCE ALSO SUPPLIES PRESSURE TO ALL OTHER NON FLIGHT CONTROL SYSTEMS |
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SWITCHING VALVES
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ALLOW BACKUP HYD PRESSURE TO REPLACE PRIMARY HYD PRESSURE WHEN PRIMARY FAILS
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SHARP
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SELECTOR VALVE HYDRAULIC LINES ACTUATING UNIT RESERVOIR PUMP |
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SAFE DISTANCES AT IDLE
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9 FT FROM INTAKES 115 FT FROM EXHAUST |
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SAFE DISTANCE AT MIL OR MAX
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25 FT FROM INTAKES 925 FT FROM EXHAUST |
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APU EXHAUST
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USE EXTREME CAUTION DURING START UP DUE TO HIGH TEMPERATURE
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JET FUEL
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COMBUSTIBLE AND CAN CAUSE CHEMICAL BURNS
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FUELING/DEFUELING
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100 FT AWAY FROM OPERATING AIRBORNE TYPE RADIO OR AIR RADAR EQUIPMENT 300 FT AWAY FROM GROUND RADAR EQUIPMENT |
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ARS POD
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MAKE SURE THE GUILLOTINE IS NOT ARMED OR LOADED WITH CADS
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ENGINE TYPE FOR F/A-18E/F
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F414-GE-400
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ENGINE TYPE FOR F/A-18A-D
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F404-GGE-400 OT F404-GE-402
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ENGINE
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LOW BYPASS, AXIAL FLOW, DUAL SPOOL TURBOFAN ENGINE OF MODULAR CONSTRUCTION WITH AFTERBURNER
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IGNITION SYSTEM
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MADE UP OF AN ALTERNATOR, FADEC OF ECA, ENGINE FUEL CONTROL, IGNITION EXCITER, MAIN IGNITER, AB IGNITER, AB FLAME SENSOR, TWO FAN SPEED TRANSMITTERS, THERMOCOUPLE HARNESSES
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LUBRICATION
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SELF CONTAINED RECIRCULATION, DRY SUMP PROVIDES LUBRICATION/COOLING TO THE REQUIRED BEARINGS AND GEARS |
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VARIABLE EXHAUST NOZZLE(VEN)
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CAM AND LINK POSITIONED HINGED FLAP, CONVERGENT-DIVERGENT NOZZLE "TURKEY FEATHERS" |
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VARIABLE GEOMETRY |
CONSISTS OF FAN VARIABLE GEOMTRY AND COMPRESSOR VARIABLE GEOMETRY |
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FAN VARIABLE GEOMETRY
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PROVIDE BEST EFFICIENCY OF THE FAN
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COMPRESSOR VARIABLE GEOMETRY |
PROVIDES BEST EFFICIENCY OF THE COMPRESSOR
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ANTI-ICING SYSTEM
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PROVIDES AIR FLOW TO ENGINE FRONT FRAME PREVENTS THE BUILD UP OF ICE ON AIR INLET HARDWARE |
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FULL AUTHORITY DIGITAL ENGINE CONTROL (FADEC)
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DETERMINES THE APPROPRIATE ENGINE SCHEDULING TO OPERATE THE ENGINE IN ALL AREAS OF THE FLIGHT ENVELOPE
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FUEL SYSTEM
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ALLOWS FOR FUEL DISTRIBUTION, CONTROL, AND STORAGE
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MAIN FUEL CONTROL
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GOVERN THE CORREXT MAIN FUEL FLOW
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AB FUEL CONTROL
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GOVERNS THE CORRECT AB FUEL FLOW |
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THROTTLE SYSTEM
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PROVIDES PILOT CONTROL OF THE AIRCRAFT ENGINES FLY BY WIRE SYSTEM |
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FUEL STORAGE
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FOUR INTERNAL FUSELAGE TANKS, TWO INTERNAL WING TANKS, UP TO FIVE EXTERNAL FUEL TNAKS
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WING TANKS
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FOAM SELF SEALING TO DECREASE FIRE AND EXPLOSION HAZARDS |
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REFUEL/DEFUEL SYSTEM
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MANIFOLD WITH SINGLE POINT GROUND CONTROLLED/MONITORED FROM DR 8 |
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IFR PROBE
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ALLOWS AIRCRAFT TO TAKE FUEL FROM A TNAKER AIRCRAFT IN FLIGHT LOCATION-RIGHT FORWARD FUSELAGE |
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INTERNAL FUEL TRANSFER
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REPLENISH THE FUEL IN #2 AND #3 FUAL TANKS WHILE MAINTAINING THE FUEL SYSTEM CG WITHIN ACCEPTABLE LIMITS |
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CENTER OF GRAVITY (CG)
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SIGNAL DATA COMPUTER MONITORS AMOUNT OF FUEL IN TANKS 1 AND 4 |
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HOT FUEL RECIRCULATION SYSTEM
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MAINTAINS AN OPTIMUM FUEL DELIVERY TEMPERATURE TO THE ENGINES, ANC COOLS THE ENGINES FADEC AND VARIOUS ENGINE COMPONENTS
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FLUE PRESSURIZATION AND VENT SYSTEM
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MAINTAINS PRESSURE ON THE FUEL IN ALL TANKS AND VENTS FUEL VAPORS OVERBOARD
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FUEL QUANTITY
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MEASURED USING CAPACIANCE GAUGING TRANSMITTERS
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SECONDARY POWER SYSTEM
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CONSISTS OF AN AUXILIARY POWER UNIT (APU) AND AIRFRAME MOUNTED ACESSORY DRIVE (AMAD)
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AUXILIARY POWER UNIT (APU)
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CENTRIFUGAL FLOW GAS TURBINE ENGINE SUPPLYING AIR FOR ENVIRONMENTAL CONTROL SYSTEMS, MAIN ENGINE START
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AIR CONNECTION
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LOCATED IN RIGHT WELL WHEEL AND ALLOWS USE OF AN EXTERNAL AIR SOURCE FOR SYSTEM OPERATION (HUFFER STARTS)
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AIRFRAME MOUNTED ACCESSORY DRIVE(AMAD)
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PNEUMATICALLY CONNECTED TO THE APU THROUGHT THE AIR TURBINE STARTER (ATS) TRANSMITS POWER TO THE ENGINE FOR STARTS |
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IDENTICAL INTERCHANGEABLE GEARBOXES
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CONNECTED TO AN ENGINE BY POWER TRANSMISSION SHAFT (PTS)
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COMPONENTS DRIVEN BY AMAD
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FUEL BOOST/MOTIVE FLOW PUMP, ELECTRICAL GENERATOR, AND 3000/5000 PSI HYDRUATLIC PUMMP
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AIR REFUELING STORE
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PROVIDE A BASIC AIRCRAFT WITH IN-FLIGHT REFUEALING TANKER CAPABILITIES HAS CAPABILITY OF TRANSFERRING FUEL INTO AND RECIEVING FUEL FROM THE TANKER AIRCRAFT |
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AIR REFUELING STORE CONSISTS OF:
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INTEGRATED STRUCTURAL, HYDRAULIC, PNEAMUMATIC, FUEL AND ELECTRICAL SYSTEMS WHICH PROVIDE THE CAPABILITY TO DELIVER FUEL TO A RECEIVER AIRCRAFT
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PNEUMATIC AND FUEL SYSTEMS
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PROVIDE FOR STORING 285 GAL
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FUEL SYSTEM MAINTAINS |
DELIVERY PRESSURE OF 35 TO 60 PSI AT THE REFUELING COUPLING AND IS CAPABLE OF OVER 220 GPM DELIVERY RATE
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CONTROL PANEL
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MOUNTED IN THE TANKER AIRCRAFT FLIGHT STATION AND CONTAINS SWITCHES AND INDICATORS USED TO CONTROL STORE OPERATION
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RAM AIR TURBINE A2 (RAT)
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FOUR BLADED POWER SOURCE WHICH DRIVES THE HYDRUALIC PUMP VIA A SPLINE SHAFT WHEN RAT REACHES GOVERNING SPEED OF 3600 TO 5000 RPM, CENTRIFUGAL FORCES REDUCE AIRSTREAM LOAD |
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HYDRAULIC PUMP
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SUPPLIES PRESSURIZED HYDRAULIC FLUID FOR THE OPERATION OF THE AIR REFUALING STORE |
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FUEL TRANSFER PUMP
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CONSISTS OF: FUEL PUMP AND A HYDRAULIC DRIVE MOTOR CENTRIFUGAL FORCE ACCELERATES AND PRESSURIZES THE FUEL BEFORE IT IS SENT OUT THE FUEL OUTLET PORT |
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GUILLOTINE
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INSTALLED ON THE SERVING GEAR ASSMEBLY AND CONTAINS A HOSE GUIDE AND ROLLERS TO ALLOW THE HOSE FREE TRAVEL DURING NORMAL OPERATION PROVIDES FOR EXPLOSIVE MEANS FOR SEVERING THE HOSE |
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HOSE REEL ASSEMBLY
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MOUNTED ON AFT BULKHEAD OF THE CENTER SECTION AND PROVIDES THE COMPONENTS NECESSARY TO EXTEND AND REFRACT THE REFUELING HOSE
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EXTERNAL POWER
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CIRCUIT BREAKERS AND SWITCHES MUST BE POSITIONED AS SPECIFIED IN MIMS
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PREVENT SHOCK AND DAMAGE TO AIRCRAFT
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INSPECT POWER CABLES AND CABLE ASSEMBLY PLUGS FOR PIN INTERNAL CORROSION AND DAMAGED OR MISSING INSULATOR WASHER OR SLEEVES
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MOBILE POWER UNIT
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ENSURE POWER UNIT IS CHOCKED AND FACING AWAY FROM AIRCRAFT
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BAROMETRIC ALTIMETER
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USES PITOT STATIC PRESSURE TO INDICATE ALTITUDE ABOVE SEA LEVEL
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RADAR ALTIMETER
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USES RADIO ECHOES TO DETERMINE ALTITUDE ABOVE GROUND LEVEL |
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AZIMUTH
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ANGULAR POSITION OR BEARING IN A HORIZONTAL PLANE MEASURED CLOCKWISE FROM TRUE NORTH |
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BEARING
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ANGULAR POSITION OF AN OBJECT WITH RESPECT TO REFENCE POINT OR LINE
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RANGE
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DISTANCE OF AN OBJECT FROM AN OBSERVER
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HEADING
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ACTUAL ORIENTATION OF THE AIRCRAFTS LONGITUDINAL AXIS AT ANY INSTANCE
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TRUE HEADING
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DIRECTION MEASURED BY TRUE NORTH
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MAGNETIC HEADING
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DIRECTION OF THE EARTHS MAGNETIC FIELD AT THAT LOCATION AS A REFERENCE
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RELATIVE HEADING
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CURRENT DIRECTION THAT AN OBJECT IS FACING THE 0/360 AZIMUTH ALIGNMENT
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FIBER OPTIC CABLES
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IMPROVED SYSTEM PERFORMANCE, IMMUNITY TO ELECTRICAL NOISE, SIGNAL SECURITY, IMPROVED SAFETY AND LECTRICAL ISOLATION, REDUCED SIZE AND WEIGHT, ENVIRONMENTAL PROTECTION
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VERY HIGH FREQUENCY
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30MHZ-300MHZ
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ULTR HIGH FREQUENCY
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300MHZ-36HZ
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INTERCOMMUNICATION AUDIO SYSTEM (IAS)
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PROVIDE AMPLICATION AND ROUTING OF AUDIO SIGNALS BETWEEN COCKPIT, GROUND CREW AND REAR COCKPIT
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TACTICAL AIR NAVIGATION (TACAN) |
DETERMINES THE RELATIVE BEARING AND SLANT RANGE DISTANCE TO A TACAN GROUND STATION
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INERTIAL NAVIGATION SYSTEM (INS)
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SELF CONTAINED, FULLY AUTOMATIC DEAD RECKONING NAVIGATION SYSTEM
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GLOBAL POSITIONING SYSTEM (GPS)
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RECEIVES REFERENCE INFORMATION FROM A SATELLITE SOURCE
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ATTITUDE REFERENCE INDICATOR (ARI)
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SELF CONTAINED PITCH AND ROLL ATTITUDE REFERENCE SYSTEM PROVIDES A INIMUM OF 3 MINUTES OF ATTITUDE INFO WITH TOTAL POWER LOSS |
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INSTRUMENT LANDING SYSTEM (ILS)
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ALL WEATHER APPROACH GUIDANCE SYSTEM PROVIDING STEERING INFORMATION DURING AIRCRAFT APPROACH DISPLAYED ON HUD AND ARI |
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AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)
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PROVIDES AUTOPILOT AND AUTOMATIC THROTTLE CONTROL (ATC)
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AIRSPEED
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INDICATED IN 10 KNOT INCREMENTS FROM 50 TO 200KNOTS
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STANDBY PRESSURE ALTIMETER
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DISPLAYS ALTITUDE WITH THREE DISPLAYS
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VERTICAL SPEED INDICATOR
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SENSES CHANGE IN AIR PRESSURE AND DISPLAYS THEM IN THE FORM OF CLIMB OR DIVE RATE FROM 0-6000 FEET PER MINUTE
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ANGLE OF ATTACK (AOA) INDEXER
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OPERATES WITH THE LANDING GEAR DOWN AND WEIGHT OFF THE GEAR; SHOWS APPROACH AOA WITH LIGHTED SYMBOLS
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ANGLE OF ATTACK TRANSMITTERS (AOAT)
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MEASURE THE DIFFERENCE BETWEEN THE LONGITUDINAL AXIS OF THE AIRCRAFT AND THE AIRSTREAM
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AIR DATA COMPUTER (ADC)
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RECEIVES THE INPUTS FROM VARIOUS AIRCRAFT SENSORS
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AIRSTREAM DIRECTION SENSING UNIT (ADSU)
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SAME AS AOAT, A-D ONLY |
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TOTAL TEMPERATURE PROBE (TTP)
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A-D ONLY MEASURES TOTAL TEMPERATURE OF THE AIR OUTSIDE AIRCRAFT |
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DATA LINK
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TWO WAY UHF COMMUNICATIONS LINK CONNECTING THE AIRBORNE DATA LINK SYSTEM WITH A CONTROLLING SHIPBBOARD, AIRBORNE, OR LAND BASED COMBAT DIRECTION SYSTEM
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RADIO DETECTION AND RANGING
(RADAR) |
PROVIDES AIR TO AIR, AIR TO GROUND MODES FOR TARGET DETECTION, DESIGNATION, TRACKING, AND NAVIGATION
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MISSION COMPUTERS (MC)
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COMMUNICATE AND PROVIDE DATA CONVERSION WITH NON MUX AVIONIC EQUIPMENT THROUGHT THE CONTROL CONVERTER
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HEADS UP DISPLAY ( HUD)
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PROVIDES AIRCRAFT ALTITUDE, STEERING, NAVIGATION, A/A AND A/G WEAPONS, AND NAVIGATION FLIR VIDEO DISPLAY
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DIGITAL DISPLAY INDICATOR (DDI)
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PRIVIDES NIGHT VISION IMAGE SYSTEM AND PROVIDES ANY OF THE DISPLAYS SELECTABLE FORMTHE TAC OR SUPT MENU |
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UP FRONT CONTROL DISPLAY (UFCD)
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PROVIDES FOR ENTRY AND DISPLAY OF AIRCRAFT DATA
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MULTIPURPOSE COLOR DISPLAY (MPCD)
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HAS MECHANICAL PUSHBUTTONS FOR OPERATOR INPUTS AND IS USED AS A MULTIFUNCTION DISPLAY
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DMS
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PART OF TACTICAL AIRCRAFT MOVING MAP CAPABILITY SYSTEM. CONTAINS: DIGITAL MAP COMPUTER AND A HIGH SPEED INTERFACE CABLE |
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COCKPIT VIDEO RECORDING SYSTEM (CVRS)
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RECORDS CRITICAL EVENTS AND DISPLAYS AS SELECTED BY AIRCREW. RECORDING DONE BY 8MM RECORDER OR SOLID STATE RECORDER |
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ADVANCED MEMORY UNIT (AMU)
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MSSION DATA IS STORED ON THE MISSION PC CARD FOR UPLOADING. AIRCRAFT MAINTENANCE DATA IS RECORDED ON THE MAINTENANCE PC CARD |
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DEPLOYABLE FLIGHT INCIDENT RECORDER SET (DFIRS)
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RETRIEVING AND STORAGE OF FLIGHT DATA AND THE DEPLOYMENT OF STORED FLIGHT DATA BEFORE AIRCRAFT CRASHES OR UPON IMPACT. LOCATION- DOOR 300 BATTERY CAN OPERATE UP TO 72 HOURS |
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FLIGHT INCIDENT RECORDER AND MONITORING SYSTEM (FIRAMS)
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MONITORS ENGINE AND AIRFRAME OPERATIONAL STATUS FOR UNIT FAILURES AND CAUTION/ADVISORY CONDITIONS
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NOSE WHEEL WELL DIGITAL DISPLAY INDICATOR
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USED TO RECEIVE AND STORE MAINTENANCE CODES FROM THE RECORDER
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POSITION LIGHTS
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USED TO DETERMINE THE RELATIVE POSITION OF THE AIRCRAFT AT NIGHT LEFT SIDE- RED RIGHT SIDE-GREEN TAIL LIGHT- WHITE |
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ANTI COLLISION STROBE LIGHT
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PROVIDE COVERAGE FORWARD, AFT, UP, DOWN, AND OUTBOARD TO GUARD AGAINST IN FLIGHT COLLISIONS LOCATED ON THE VERTICAL STAB |
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DAY ID STROBE LIGHT
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USED TO IDENTIFY THE AIRCRAFT LOCATION-NOSE LANDING GEAR STRUT |
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WHITE LANDING/TAXI LIGHT ASSEMBLY
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USED FOR LANDING AND TAXI OPERATIONS AT NIGHT |
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APPROACH LIGHTS
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ACTIVATED WHEN ALL LANDING GEAR ARE DOWN AND LOCKED AND WEIGHT IS OFF WHEELS CARRIER APPROACH, THE LIGHTS DISPLAYS THE AOA TO LANDING SIGNAL OFFICER LOCATION- NOSE LANDING GEAR STRUT |
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FORMATION LIGHTS
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8 GREEN LED LIGHTS 2 ON EACH WING TIP,1 OUTSIDE EACH VERTICAL STAB, ONE ON EACH SIDE OF THE FORWARD FUSELAGE INDICATE CHANGES OF ATTITUDE AND RELATIVE POSITION OF AIRCRAFT |
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ELECTRICAL POWER SUPPLY SYSTEM
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CONTAINS- 2 GENERATORS, 2 TRANSFORMER RECTIFIERS, 1 BATTERY WITH DEDICATED ABTTERY CHARGER AND POWER DISTRIBUTION SYSTEM
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MAINTENANCE BATTERY
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SUPPLIES 28 VDC TO ESSENTIAL AND MAINTENANCE BUSES
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EMERGENCY BATTERY (E-BATT)
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A-D ONLY USED FOR ENGINE START WHEN EXTERNAL POWER OR AIRCRAFT GENERATOR POWER IS NOT AVAILABLE |
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GENERATOR SYSTEM |
SUPPLIES 115/200 VDC, 400HZ, 3 PHASE ELECTRICAL POWER
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OBJECTIVE OF THE EXPLOSIVE HANDLING QUALIFICATION AND CERTIFICATION PROGRAM
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ENSURE THAT ALL PERSONNEL, AFTER HAVING RECEIVED TRAINING AND DEMONSTRATED THE ABILITY TO PROPERLY AND SAFELY PERFORM ALL FUNCTIONS AND TASK INVOLVING EXPLOSIVES
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HERO
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HAZARDS OF ELECTROMAGNETIC RADIATION TO ORDNANCE
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COLOR CODING/BANDING
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ALLOWS FOR INSTANT IDENTIFICATION OF ORDNANCE
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YELLOW BAND
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HIGH EXPLOSIVE
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BROWN BAND
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ROCKET MOTOR
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BLUE BAND
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TRAINING ROUND OR INERT WEAPON
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BOMB EJECTOR RACKS
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USED TO SUSPEND AND EJECT SINGLE STORES AND WAEPONS ON F/A-18 BRU-32, BRU-41, BRU-42, BRU-33 |
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LAU
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USED TO SUSPEND AND LAUNCH MISSILES LAU-7, LAU-127, LAU-116 |
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PYLONS
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MOUNTED ON THE AIRCRAFT SUU-62, SUU-63, SUU-78, SUU-79, SUU-80 |
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WEAPON STATIONS (9)
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STATIONS 1 & 9- LAU-7 STATIONS 4 & 6-LAU-116 STATIONS 2,3,7,8- SUU-63 PYLONS STATION 5- SUU-62 PYLON WITH BRU-32 AND M61A1 20-MM GUN |
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CADS
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SMALL EXPLOSIVE FILLED CARTRIDGES USED TO FIRE OTHER EXPLOSIVES OR RELEASE MECHANISMS MK.19, MK.125, MK.107 |
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MK.19
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AUXILIARY CAD THAT OPENS THE BRU-32 BOMB RACK HOOKS
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CLUSTER BOMB UNITS
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ANTI-TANK BOMB CLUSTERS AND IS AN AIR LAUNCHED CONVENTIONAL FREE FALL WEAPON MK.20, CBU-99, AND CBU-100 USED FOR ARMORED VEHICLES |
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FIRE BOMB
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THIN SKINNED CONTAINER OF FUEL GELL DESIGNED FOR USE AGAINST DUG-IN TROOP, SUPPLY INSTALLATIONS, WOODEN STRUCTURES, AND LAND CONVOYS
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GUIDED BOMB UNITS (GBU)
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GBU-12, GBU-16, GBU-10 DETECT A TARGET ILLUMINATED BY A LASER BEAM |
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RETARDED BOMB FINS
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LOW LEVEL BOMBING FINS OPEN TO SLOW DOWN WEAPON |
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NON RETARDED BOMB FINS
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HIGH LEVEL BOMBING, FINS REMAIN CLOSED
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CAPTIVE AIR TRAINING MISSILE (CATM)
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ALL OTHER TYPES OF MISSILES THAT AREN'T SERVICE OR TACTICAL
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MODES OF OPERATION
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ACTIVE, SEMI ACTIVE, PASSIVE
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ACTIVE OPERATION
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TARGET ILLUMINATION IS SUPPLIED BY COMPONENT CARRIED IN THE MISSILE
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SEMI ACTIVE OPERATION
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MISSILE GETS IT TARGET ILLUMINATION FROM EXTERNAL SOURCE
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PASSIVE OPERATION
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DIRECTING INTELLIGENCE IS RECEIVED FROM THE TARGET
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AIR TO AIR MISSILES
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AIM-7 SERIES (SPARROW)USES SEMI ACTIVE RADAR HOMING AIM-9 SERIES (SIDEWINDER) PASSIVE INFRARED TARGET DETECTION |
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AGM-84E STAND OFF LAND ATTACK MISSILE (SLAM) |
USES INS, GPS, AND IR FOR TERMINAL GUIDANCE
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AGM-84H STAND OFF LAND ATTACK MISSILE EXPANDED RESPONSE (SLAM-ER)
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UPDATED TO IMPROVE CONTROL, RANGE AND TARGET PENETRATION |
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M61A1 20-MM GUN
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AUTOMATIC GUNFIRE SYSTEM ENABLES SELECTING, ARMING, AND FIRING OF GUN
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GUN FIRE CONTROL SYSTEM
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AIR TO GROUND, AIR TO AIR, OR AIR COMBAT MANEUVER (ACM ENCOUNTER) MODE
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RATE OF FIRE
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HIGH, 6000 ROUNDS PER MINUTE LOW, 4000 ROUNDS PER MINUTE |
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STORES MANAGEMENT SYSTEM
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PROVIDES ELECTRICAL INTERFACE BETWEEN THE WEAPONS STATIONS, AIRCRAFT SWITCHING, AND RELATED AIRCRAFT SYSTEMS |
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STORES MANAGEMENT SYSTEM CONTAINS
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ARMAMENT CONTROL PROCESSOR (ACP) ALSO KNOWN AS THE STORES MANAGEMENT PROCESSOR (SMP), AND UP TO 9 SIGNAL DATA CONVERTER-CONTROLS (SDCC)
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COMMAND LAUNCH COMPUTER (CLC)
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USED TO CONTROL AND MONITOR THE IGH SPEED ANTI-RADIATION(HARM) MISSILE, LOCATED IN DR 13R
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COUNTERMEASURES DISPENSING SYSTEM
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AN/ALE-39 OR 47, PROVIDES AIRCRAFT PROTECTION IN SOPHISTICATED THREAT ENVIRONMENTS
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SEAT CHECK OUT
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EVERY 6 MONTHS, OR AFTER 90 DAYS TAD
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HYPOXIA
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DECREASE IN THE AMOUNT OF OXYGEN
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ANOXIA
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DEATH DUE TO COMPLETE LACK OF OXYGEN
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SAFETY PINS
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EJECTION SEAT AND CANOPY JETTISON |
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CANOPY OPERATION
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DO NOT USE BATTERY POWER TO OPEN THE CANOPY BELOW ZERO DEGREES FAHRENHEIT
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AVIATORS BREATHING OXYGEN (ABo0
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TYPE 1- GASEOUS OXYGEN TYPE 2- LIQUID OXYGEN |
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LIQUID OXYGEN (LOX)
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KEEP AWAY FROM GASOLINE, KEROSENE, OILS, GREASES, OTHER HYDROCARBONS DUE TO SPONTANEOUS IGNITION |
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OXYGEN
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LIQUID FORM TEMP OF -297 DEGREES FAHRENHEIT EXPANSION RATIO OF 862 TO 1 GENERATE UP TO 12,000 PSI WEAR CLOTHING ACCORDING TO NA 13-1-6.4 |
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SAFE DISTANCE
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50 FT FOR SMOKING, OPEN FLAMES, OR SPARKS |
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PERSONAL PROTECTIVE EQUIPMENT (PPE)
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FLIGHT SUIT, AVIATOR BOOTS, ANTI-G GARMENT, HELMET, SURVIVAL RADIO/BEACON, GLOVES, ANTI-EXPOSURE SUIT, ID TAGS, KNIFE, PERSONAL SURVIVAL KIT, SIGNAL DEVICE,FLASHLIGHT, LIFE PRESERVER, LASER EYE PROTECTION
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OXYGEN MASK
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USE WITH A REGULATOR AND PROVIDES BREATHING GAS UPON DEMAND WORKS UP TO 16 FT UNDER WATER |
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LPU-36/P LIFE PRESERVER
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LOW PROFILE FLOATATION COLLOR EQUIPPED WITH FLU-8B/P AUTOMATIC/MANUAL INFLATION ASSEMBLY
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ANTI-GRAVITY (ANTI-G) SUIT
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CONTAINS BALDDER SYSTEM ENCASES IN A FIRE RESISTANT CLOTH LESSENS EFFECTS OF BLACK OUT |
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PARACHUTE HARNESS SENSING RELEASE UNIT (PHSRU)
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SEA WATER ACTIVATED RELEASE SYSTEM
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HELMET MOUNTED DISPLAY UNIT ( HDU)
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PROVIDES A WAY OF RECORDING REAL WORLD VIEW BY ROUTING THE VIDEO TO COCKPIT VIDEO RECORDING SYSTEM (CVRS)
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EJECTION SEAT
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SJU-17A(V)2/A SERIES VARIANT OF NAVY COMMON EJECTION SEAT (NACES) AUTOMTIC, CARTIRIDGE OPERATED, AND ROCKET ASSISTED |
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EJECTION SEAT CONTROL HANDLE |
LOCATED ON THE FRONT OF THE SEAT BUCKET
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EJECTION SEAT SYSTEM
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OPERATED BY BALLSTIC GAS PRESSURE
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EMERGENCY OXYGEN SYSTEM
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OPERATED BY GREEN MANUAL OPERATING HANDLE MOUNTED ON THE LEFT SIDE PLATFORM
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CANOPY SYSTEM
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PYROTECHNICALLY OPERATED
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ENVIRONMENTAL CONTROL SYSTEM (ECS)
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PROVIDES AIR SUPPLY, THERMAL CONTROL, CABIN PRESSURIZATION
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SUBSYSTEMS OF ECS (12)
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BLEED AIR CONTROL, BLEED AIR LEAK DETECTION, AIR CYCLE CONDITIONING, CABIN COOLING AND DEFOG, AVIONICS COOLING, CABIN PRESSURIZATION, ANTI-G/VENT SUIT, OBOGS, WINDSHIELF ANTI ICE/RAIN REMOVAL, RADAR LIQUID COOLING, CANOPY SEAL, WAVE GUIDE PRESSURIZATION
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BLEED AIR SYSTEM
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CONTAINS: CLAMPED, INSULATED METAL DUCTS(TUBES) OF MANY SIZES AND SHAPES WHICH CONNECT SYSTEM CONTROL VALVES AND SENSORS
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AIR CYCLE AIR CONDITIONING SYSTEM
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COOLS AND CONDITIONS ENGINE BLEED AIR FOR USE IN ESC
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ANTI-GRAVITY (ANTI-G) SYSTEM
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TUBING AND A VALVE WHICH DELIVERS REGUALTED AIR PRESSURE TO PILOTS ANTI-G SUIT
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ON BOARD OXYGEN GENERATION SYSTEM (OBOGS)
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SERIES OF LINES, VALVES AND CONCENTRATOR THAT REGULATE PRESSURE, CONTROL FLOW AND DISTRIBUTE OXYGEN TO THE CREW STATION |
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FIRE DETECTION SYSTEM |
MONITORS THE AMAD, APU, AND ENGINE BAYS FOR FIRES OR OVERHEAT CONDITIONS PROVIDE AUDIBLE AND VISUAL WARNING |
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FIRE EXTINGUISHING SYSTEM
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USES A SINGLE FIRE EXTINGUISHER TANK WITH THREE DISTRIBUTION LINES 1 FOR APU, 1 FOR EACH OF THE ENGINE/AMAD BAYS ONE SHOT, ONE BAY |
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DRY BAY FIRE SUPPRESSION SYSTEM (DBFSS)
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E-F ONLY CONSIST OF 14 OPTICAL FIRE DETECTORS, 6 DRY BAY EXTINGUISHERS |
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SEAD
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SUPPRESSION OF ENEMY AIR DEFENSES
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SAM
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SURFACE TO AIR MISSILE
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WAS
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WAR AT SEA
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CAS
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CLOSE AIR SUPPORT |
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MAS
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MARITIME AIR SUPERIORITY
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ACM
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AIR COMBAT MANEUVERING
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CAP
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COMBAT AIR PATROL
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FCF
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FUNCTIONAL CHECK FLIGHT
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FCLP
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FIELD CARRIER LANDING PRACTICE
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FAC
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FORWARD AIR CONTROLLER
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TOT
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TIME ON TARGET
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VMC
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VISUAL METEOROLOGICAL CONDITIONS
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VFR
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VISUAL FLIGHT RULES
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IMC
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IMSTRUMENT METEOROLOGICAL CONDITIONS
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IFR
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INSTRUMENT FLIGHT RULES
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CATCC
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CARRIER AIR TRAFFIC CONTROL CENTER
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FLOLS
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FRENSEL LENS OPTICAL LANDING SYSTEM
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MOVLAS
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MANUALLY OPERATED VISUAL LANDING AID SYSTEM
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AAW
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ANTI AIR WARFARE
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AMW
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AMPHIBIOUS WARFARE
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FAC
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FORWARD AIR CONTROLLER (A-AIRBORNE) |
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CCC
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COMMAND, CONTROL, AND COMMUNICATIONS
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GCI
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GROUND CONTROL INTERCEPTS
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MIW
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MINE WARFARE
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MOB
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MOBILITY
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NCO
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NON COMBATANT OPERATIONS
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STW
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STRIKE WARFARE
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