Empennage
Fuselage aft section
Fuselage center section
Fuselage forward section
Empennage
Fuselage aft section
Fuselage center section
Fuselage forward section
Burning
Crushing
Shocking
Explosion
Chaff
Flare
Fuels
Liquid oxygen
Oils
Fuels
Hydraulic fluid
Liquid oxygen
Electrical (24)
Flight control (27)
Environmental control (21)
Pneudraulics/hydraulics (29)
Electrical (24)
Flight control (27)
Environmental control (21)
Pneudraulics/hydraulics (29)
Electrical (24)
Navigation (34)
Communication (23)
Electronic warfare (93)
Electrical (24)
Navigation (34)
Communication (23)
Electronic Warfare (93)
Control display unit (CDU)
Flight director computer (FDC)
Integrated flight and fire control computer (IFFCC)
Embedded global positioning/inertial navigation system (EGI)
Control display unit (CDU)
Flight director computer (FDC)
Integrated flight and fire control computer (IFFCC)
Embedded global positioning/inertial navigation system (EGI)
Control display unit (CDU)
Flight director computer (FDC)
Integrated flight and fire control computer (IFFCC)
Embedded global positioning/inertial navigation system (EGI)
Head-up display (HUD)
Central interface control unit (CICU)
Armament HUD control panel (AHCP)
Integrated flight and fire control computer (IFFCC)
1
2
3
4
Initiated
Periodic
Power-on
Continuous
Location and speed
Altitude and airspeed
Current date and time
Azimuth and elevation signals
LASTE control panel
Up-front controller (UFC)
Armament HUD control panel (AHCP)
Stability augmentation system (SAS) control panel
LASTE control panel
Avionics auxiliary panel
Stability augmentation system (SAS) control panel
Armament head-up display (HUD) control panel (AHCP)
LASTE control panel
Up-front controller (UFC)
Stability augmentation system (SAS) control panel
Armament head-up display (HUD) control panel (AHCP)
Stick grip
Left throttle grip
Right throttle grip
Armament head-up display (HUD) control panel (AHCP)
Embedded global positioning and inertial navigation system (EGI) mode
Heading attitude reference system (HARS) mode
Integrated flight and fire control computer (IFFCC) mode
Normal mode
Radar altitude must be on and operational
Low altitude autopilot (LAAP) must be engaged with no failures
Pitch and yaw stability augmentation system (SAS) must be engaged with no SAS failures
Heading attitude reference system (HARS) must be selected on the NAV mode select panel and its data valid
4 seconds
5 seconds
6 seconds
7 seconds
Control display unit (CDU)
Television (TV) monitor
Right and left multifunction color display (MFCD)
View through the head-up display (HUD)
1.5 hours
2.5 hours
3.5 hours
4.5 hours
OFF
REC
STBY
STOP
Eliminates high frequency spurious signals from the capacitors output
Eliminates high frequency spurious signals from the compensators output
Reduces pointer fluctuation by eliminating high frequency spurious signals
Reduces totalizer oscillations by eliminating high frequency spurious signals
INT
MAIN
EXT CTR
EXT WING
Resistor box
TEMS data unit.
Electronic processor unit
Fuel flow signal converter
-1,200 to 80,000 ft with an acceleration range for -3 to +9 Gs (gravity)
-1,500 to 50,000 ft with an acceleration range for -2 to +8 Gs
+1,200 to 80,000 ft with an acceleration range for +3 to +9 Gs
+1,500 to 50,000 ft with an acceleration range for +2 to +8 Gs
Level 1
Level 2
Level 3
Level 4
Level 1
Level 2
Level 3
Level 4
.25 amp
.5 amp
.75 amp
1.25 amp
Horizontal situation indicator (HSI) mode
Displacement gyroscope (DG) mode
Fast erect mode
Slave mode
Horizontal situation indicator (HSI)
Flight director computer (FDC)
Nav mode relay box (NMRB)
Nav mode select panel (NMSP)
Lateral (roll) stability
Directional (yaw) stability
Horizontal (vertical) stability
Longitudinal (pitch) stability
Ailerons
Rudders
Elevators
Speed brakes
Roll
Yaw
Trim
Pitch
220 KIAS
240 KIAS
260 KIAS
280 KIAS
20° elevator trailing edge up and 10° elevator trailing edge down
10° elevator trailing edge up and 10° elevator trailing edge down
20° elevator trailing edge up and 5° elevator trailing edge down
10° elevator trailing edge up and 5° elevator trailing edge down
2.5°
3.2°
.5°
.95°
Speedbrake deployment
Yaw SAS disengagement
Lowering the landing gear
Airspeed exceeding 255 knots indicated airspeed.
.5°
.95°
2.5°
3.2°
Density
Hysteresis
Mechanical
Compressibility
Increase in indicated altitude
Decrease in indicated altitude
Increase in indicated airspeed
Decrease in indicated airspeed
Pitot pressure
Static pressure
Impact pressure
Dynamic pressure
Fuel quantity imbalance
Impending stall conditions
Attitude hold autopilot failure
Left or right hydraulic failure
Stick shaker
Pitot-static system
Altitude/airspeed switch
Slat electrical safety switch
Improved data modem (IDM)
EPLRS receiver-transmitter (R/T)
Central interface control unit (CICU)
Integrated flight and fire control computer (IFFCC)
Weight on wheels
Weight off wheels
Flaps extended to 7°
Flaps extended to 20°
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