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F-16 > FLCS > Flashcards

FLCS Flashcards

1
Q

the FLCS uses a ____-redundant computer system which hydraulically positions the control surfaces by the ___

A

quad-redundant

ISA (integrated servoactuator)

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2
Q

the Flaperons include the ___ and ____

A

Ailerons and Trailing Edge Flaps (TEFs)

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3
Q

the Rudder has an ____ and a _____ at high AOA

A

Aileron-rudder-interconnect (ARI)

yaw rate limiter

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4
Q

Relaxed Static Stability means the ____ is forward of the ____ making the aircraft unstable in subsonic flight and requires the ___ to provide lift to help counteract

A

L(CL) is forward of the CG and needs Lift from the tail to counteract

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5
Q

Tansonic - the ___ shifts aft of the _____

A

L(CL) shifts aft of the CG

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6
Q

the FLCS wires are routed _____ to increase combat survivability

A

separately

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7
Q

the _______ allows you to communicate with the FLCS and provides consistent response at any airspeed and altitude

A

Command Augmentation system

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8
Q

the ____ provides feedback and automatic correction to make the F-16 smooth and stable

A

stability augmentation system

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9
Q

Gain-adjusted ____ commands help minimize roll-yaw coupling, enhance spin resistance, and improve turn coordination ; the 4 gain schedules are:_____ and are based on configuration and flight regime

A 
ARI (Aileron Rudder Interconnect)
4 schedules (STBY, Cruise, TO/LDG, and Ground)
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10
Q

Ground gains commands control surface deflection commanded in _____ and enables the flight control ground system check and requires

A

inches ; WOW

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11
Q

TO/LDG Gains requires ______ and is AOA biased above ____ AOA and limits roll rate to a max of _____

A

require Weight off wheels, LG down, ALT FLAPS extended, and/or AIR REFUEL switch open
AOA biased >10 degrees AOA
roll rate limit - 167/S (324/S gear up)

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12
Q

Cruise Gains require_____ and has two sub-gains categories (CATI and CATIII). CAT I makes it a __-command system that reduces G until only 1 g is available and 25* AOA when AOA >____

A

requires LG handle up, ALT FLAPS in NORM, AIR REFUEL switch in CLOSE
G-command system
CAT I biased when AOA>15*

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13
Q

Stby Gains when ______ and is based on ____ KCAS when LG handle is Up and ____ KCAS when LG handle is down

A

Dual air Data Failure
600 KCAS gear up
230 KAS gear down

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14
Q

Rudder moves ___ left and right

A

30 degrees

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15
Q

Secondary flight controls consist of the

A 
LEFs (controlled by combo of Mach, Altitude, and AOA) and optomizes airfoil aerodynamic optimization
TEFs (20* down until 240 kts gear down ; gear up - fully retracted at 370 kts)
speed brakes (system A hydraulics)
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16
Q

LEFs are ___-span control surfaces hinged to the wings and are controlled by the ____ that sends commands to the _______ that provides near-optimum wing camber

A

full-span
controlled by ADC (air data converter)
commands sent to LEF PDU (power drive unit)

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17
Q

LEFs fixed to 2* up when:

A

throttle in idle and MLG speed >60kts
WOW on both MLG
Supersonic

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18
Q

LEFs fixed at 0* when:

and 15* down when:

A

0*:LG handle up, ALT FLAPS in NORM

15*: LG handle down, ALT FLAPS EXTEND

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19
Q

LEF PDU (power drive unit) is located in ____ center fuselage and receives signals from the ____ then hydraulically drives the ______ through torque shafts then on to the LEF actuators

A

upper center fuselage
signals from the ADC
drives the Angle Gearbox

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20
Q

LEF asymmetry detected then the Asymmetry brakes stop the LEFs and commands the ____ to stop ; if a complete disconnect happens then the PDU should _______

A

PDU stops

PDU should limit asymmetry to <11*

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21
Q

Air data system includes the and their functions

A 
source components (collect raq data from Air pressure, temperature, and AOA)
ADC (converts data to signal for FLCC and control LEFs automatically)
CADC (central air data computer) converts data to signal for Aircraft avionics
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22
Q

the total temperature probe that provides a signal to the CADC for true airspeed and air density is located on the ________

A

right strake above the engine inlet nacelle

23
Q

there are ___ AOA Probes on each side of the _____

A

2 probes on either side of the radome

24
Q

two air data probes that supply static and total air pressure info are located ____ and _____

A

nose mounted probe (pitot boom) and fuselage mounted probe neat the AOA Probe (AOA and sideslip)

25
Q

air pressure electronic flow:

A

Pneumatic data –> PSA (pneumatic sensor assembly) –> electronic control assembly (ECA) –> FLCC –> LEFs

26
Q

primary function of the CADC

A

Central Air Data Computer: receives/processes electrical signals for flight instruments and avionics, detects internal failures

27
Q

3 packages of __ gyros sends __ redundant signals to the FLCC and provide the truest sense of Aircraft movement

A

4 gyros – 4 redundant signals

28
Q

8 torque balanced accelerometers provide quad-redundant signals to the FLCC for _____

A

G, pitch, and yaw axes

29
Q

the Flight Control Computer located in the _____ is the principal electronic assmbly in the FLCS and has 4 branches that each independently compute signals to the FLCS through the servo-amplifier to ISA based on:

A

equipment bay
based on: Flight contol panel, manual trim panel, MPO swithc, 4 force sensors, 4 rate sensors, 4 accelerometers, 2 AOA probes, ADC, sideslip diff press sensor

30
Q

___ of the 4 FLCS branches are compared in the selector, and ___ is held in stby unless needed because of a bad branch

A

3 are used, 1 is in stby

31
Q

there are ____ ISAs (integrated servoactuators) that integrate electronics and _______ and each contains 3 servovalves that accepts signals from the FLCC to position the FLCS

A

4 ISAs (one for each primary control surface) ; electronics and hydraulics

32
Q

System __ is the primary hydraulic source for ISA hydraulics for servos 1 and 2, System __ controls servovalve 3 and is heald in stby

A

B - primary

A - secondary

33
Q

the _______ is the “out-of-tolerance” hydraulic signals and helps isolate the bad hydraulic system

A

Hydro-Mechanical Comparator

34
Q

a second failure within the ISA is mechanically centered and hydraulically locked by a _______ and is a “fail safe”

A

Centering Spring

35
Q

stick force pressure pitch and roll

A

25 lbs nose up
16 lbs nose down
17 lbs roll cruise gains
12 lbs roll TO/LDG gains

36
Q

simultaneous illumination of PRY on the Flight Control panel indicates______

A

loss of power to one or more FLCS branches

37
Q

RESET switch to ELEC resets:

A

P,R,Y, ADC, LE FLAPS, CADC, FLT CONT SYS, and Master Caution lights

38
Q

A servo Light on the Flight Contol Panel indicates a _______ of hydraulics in the FLCS

A

first failure

39
Q

If servo light does not reset, then you should ______ the ISA to prevent a hardover control surface

A

Arm the ISA

40
Q

STORES CONFIG Switch CAT I and CAT III

A

CAT I: symmetrical missiles, centerline or wing tanks, empty pylon/TER combinations, more response, higher G, and roll limits for A-A

CAT III: used for most A-S, reduces max G and roll, protects against departures with destabilizing stores

41
Q

Manual Pitch Override switch in OVRD:

A

overrides AoA/G limiter if above 29*, gives you full horizontal stabilizer control, and bypasses negative G Limiter

42
Q

the PRobe Heat switch turns on automatically when :

A

weight off NLG

43
Q

DAUL FC Warning light if:

A

dual electronics failure in one axis
dual branch failure
dual AOA failure
second failure in an armed ISA

44
Q

TO/LDG CONFIG light:

A 
All gear not down and locked
altitude <10,000'
airspeed <190kts
Descent >250 fpm
TEFs failed to extend with gear
45
Q

HYD/OIL PRESS light:

A

either hydraulic system <1000 psi
loss of one system causes ISAs to operate nonredundant
total loss of both hydraulics - eject
illuminates all five servo lights on FLIGHT CONTROL panel

46
Q

FLCS CONT SYS light:

A

potential FLCS failure

47
Q

ADC Caution light

A

single/dual pressure sensing failure

or AOA failure

48
Q

LE FLAPS Caution lights

A

Dual air data failure
Dual AOA failure
Flap command servo valve failure
LE FLAPS switch in LOCK

49
Q

CADC light

A

malfunction in CADC

loss of Mach data to engine

50
Q

ACFT BATT TO FLCS

A

aircraft battery powering one or more FLCS branches with 25 volts or less

51
Q

FLCS BATT branch light:

A

respective FLCS battery is powering FLCS inverter with 22 volts or less

52
Q

prior to start FLCS TEST in NORM

A 
4 FLCS Power lights
FLCS PMG
MAIN GEN
STBY GEN
TO FLCS
53
Q

prior to start FLCS TEST in TEST

A 
4 FLCS power lights
4 FLCS Batt lights
MAIN GEN
STBY GEN
NO FLCS PMG (ensures FLCS batteries connected to FLCS)

F-16 (17 decks)

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