FLCS Flashcards
the FLCS uses a ____-redundant computer system which hydraulically positions the control surfaces by the ___
quad-redundant
ISA (integrated servoactuator)
the Flaperons include the ___ and ____
Ailerons and Trailing Edge Flaps (TEFs)
the Rudder has an ____ and a _____ at high AOA
Aileron-rudder-interconnect (ARI)
yaw rate limiter
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
L(CL) is forward of the CG and needs Lift from the tail to counteract
Tansonic - the ___ shifts aft of the _____
L(CL) shifts aft of the CG
the FLCS wires are routed _____ to increase combat survivability
separately
the _______ allows you to communicate with the FLCS and provides consistent response at any airspeed and altitude
Command Augmentation system
the ____ provides feedback and automatic correction to make the F-16 smooth and stable
stability augmentation system
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
ARI (Aileron Rudder Interconnect) 4 schedules (STBY, Cruise, TO/LDG, and Ground)
Ground gains commands control surface deflection commanded in _____ and enables the flight control ground system check and requires
inches ; WOW
TO/LDG Gains requires ______ and is AOA biased above ____ AOA and limits roll rate to a max of _____
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)
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 >____
requires LG handle up, ALT FLAPS in NORM, AIR REFUEL switch in CLOSE
G-command system
CAT I biased when AOA>15*
Stby Gains when ______ and is based on ____ KCAS when LG handle is Up and ____ KCAS when LG handle is down
Dual air Data Failure
600 KCAS gear up
230 KAS gear down
Rudder moves ___ left and right
30 degrees
Secondary flight controls consist of the
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)
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
full-span
controlled by ADC (air data converter)
commands sent to LEF PDU (power drive unit)
LEFs fixed to 2* up when:
throttle in idle and MLG speed >60kts
WOW on both MLG
Supersonic
LEFs fixed at 0* when:
and 15* down when:
0*:LG handle up, ALT FLAPS in NORM
15*: LG handle down, ALT FLAPS EXTEND
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
upper center fuselage
signals from the ADC
drives the Angle Gearbox
LEF asymmetry detected then the Asymmetry brakes stop the LEFs and commands the ____ to stop ; if a complete disconnect happens then the PDU should _______
PDU stops
PDU should limit asymmetry to <11*
Air data system includes the and their functions
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
the total temperature probe that provides a signal to the CADC for true airspeed and air density is located on the ________
right strake above the engine inlet nacelle
there are ___ AOA Probes on each side of the _____
2 probes on either side of the radome
two air data probes that supply static and total air pressure info are located ____ and _____
nose mounted probe (pitot boom) and fuselage mounted probe neat the AOA Probe (AOA and sideslip)
air pressure electronic flow:
Pneumatic data –> PSA (pneumatic sensor assembly) –> electronic control assembly (ECA) –> FLCC –> LEFs
primary function of the CADC
Central Air Data Computer: receives/processes electrical signals for flight instruments and avionics, detects internal failures
3 packages of __ gyros sends __ redundant signals to the FLCC and provide the truest sense of Aircraft movement
4 gyros – 4 redundant signals
8 torque balanced accelerometers provide quad-redundant signals to the FLCC for _____
G, pitch, and yaw axes
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:
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
___ of the 4 FLCS branches are compared in the selector, and ___ is held in stby unless needed because of a bad branch
3 are used, 1 is in stby
there are ____ ISAs (integrated servoactuators) that integrate electronics and _______ and each contains 3 servovalves that accepts signals from the FLCC to position the FLCS
4 ISAs (one for each primary control surface) ; electronics and hydraulics
System __ is the primary hydraulic source for ISA hydraulics for servos 1 and 2, System __ controls servovalve 3 and is heald in stby
B - primary
A - secondary
the _______ is the “out-of-tolerance” hydraulic signals and helps isolate the bad hydraulic system
Hydro-Mechanical Comparator
a second failure within the ISA is mechanically centered and hydraulically locked by a _______ and is a “fail safe”
Centering Spring
stick force pressure pitch and roll
25 lbs nose up
16 lbs nose down
17 lbs roll cruise gains
12 lbs roll TO/LDG gains
simultaneous illumination of PRY on the Flight Control panel indicates______
loss of power to one or more FLCS branches
RESET switch to ELEC resets:
P,R,Y, ADC, LE FLAPS, CADC, FLT CONT SYS, and Master Caution lights
A servo Light on the Flight Contol Panel indicates a _______ of hydraulics in the FLCS
first failure
If servo light does not reset, then you should ______ the ISA to prevent a hardover control surface
Arm the ISA
STORES CONFIG Switch CAT I and CAT III
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
Manual Pitch Override switch in OVRD:
overrides AoA/G limiter if above 29*, gives you full horizontal stabilizer control, and bypasses negative G Limiter
the PRobe Heat switch turns on automatically when :
weight off NLG
DAUL FC Warning light if:
dual electronics failure in one axis
dual branch failure
dual AOA failure
second failure in an armed ISA
TO/LDG CONFIG light:
All gear not down and locked altitude <10,000' airspeed <190kts Descent >250 fpm TEFs failed to extend with gear
HYD/OIL PRESS light:
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
FLCS CONT SYS light:
potential FLCS failure
ADC Caution light
single/dual pressure sensing failure
or AOA failure
LE FLAPS Caution lights
Dual air data failure
Dual AOA failure
Flap command servo valve failure
LE FLAPS switch in LOCK
CADC light
malfunction in CADC
loss of Mach data to engine
ACFT BATT TO FLCS
aircraft battery powering one or more FLCS branches with 25 volts or less
FLCS BATT branch light:
respective FLCS battery is powering FLCS inverter with 22 volts or less
prior to start FLCS TEST in NORM
4 FLCS Power lights FLCS PMG MAIN GEN STBY GEN TO FLCS
prior to start FLCS TEST in TEST
4 FLCS power lights 4 FLCS Batt lights MAIN GEN STBY GEN NO FLCS PMG (ensures FLCS batteries connected to FLCS)
