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100 Cards in this Set
- Front
- Back
What flight environmental pressure is sensed by small holes located on the sides of the pitot and air data probes?
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Static
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True angle-of-attack (AOA) is the angle between an aircraft’s wing cord line and its
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flight path.
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How many sources of pitot pressure (PT) and static pressure (PS) are routed by the pitot-static probe pneumatic system?
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2.
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The pitot-static probe pneumatic system supplies air data to the central air data computer (CADC), airspeed mach indicator (AMI), altimeter, and
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pneumatic sensor assembly (PSA).
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What component(s) receive air data inputs from the air data probe pneumatic system?
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Pneumatic sensor assembly (PSA).
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The angle of sideslip pneumatic system routed air data pressures to the
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differential pressure sensor (DPS).
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How are central air data computer (CADC) analog output signals transferred to their final destination?
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Via aircraft wiring
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The pitot-static probe pneumatic system supplies the airspeed mach indicator (AMI) with
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PT and static pressure (PS).
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One complete revolution of the altimeter’s altitude dial equals
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1,000 feet of altitude.
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What’s the display range of the altimeter’s altitude drum counter?
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-1,000 to 80,000 feet
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Why would a pilot adjust the altimeter to display pressure altitude?
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To standardize aircraft altitudes for high-altitude air traffic control.
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Which component develops the vertical velocity indicator’s (VVI) vertical velocity signal?
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Central air data computer (CADC).
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The angle-of-attack (AOA) indicator is considered a
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vertical tape indicator.
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What’s the function of the angle-of-attack (AOA) indexer’s lever control switch?
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Sector light intensity
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What’s the crash survivable flight data recorder (CSFDR) system’s prime component?
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Signal acquisition unit (SAU).
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What data is only stored in the crash survivable flight data recorder (CSFDR)?
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Type 1.
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How many dedicated sensors are utilized by the crash survivable flight data recorder (CSFDR) system?
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7.
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Which crash survivable flight data recorder (CSFDR) system component utilizes a pendulous device?
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Axial accelerometer transmitter.
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Which crash survivable flight data recorder (CSFDR) system control surface position transducer is not connected to an integrated servoactuator (ISA)?
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Rudder
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What’s crash survivable flight data recorder (CSFDR) type 1 data primarily used for?
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Mishap investigation.
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What predetermines the crash survivable flight data recorder (CSFDR) special event criteria?
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Signal acquisition unit operational flight program (SAU OFP).
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Which crash survivable flight data recorder (CSFDR) type data is dubbed as individual aircraft tracking data?
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2.
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Which crash survivable flight data recorder (CSFDR) type data is known as structural loads environmental data?
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3.
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Which crash survivable flight data recorder (CSFDR) type data is used for engine analysis?
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4.
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When does the seat data recorder (SDR) cease recording operations?
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Upon a weight-on-wheels (WOW) condition.
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What occurs if the maximum recording limit of the seat data recorder (SDR) is reached?
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Data overwrite.
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Which digital video recorder system component contains sync generator, Built-In Test (BIT), power supply, Automatic Gain Control (AGC), and automatic light control circuits?
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Cockpit television sensor electronics unit (CTVS E/U).
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Which digital video recorder system component controls the electrical power to the digital video recorder (DVR)?
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Airborne video tape recorder (AVTR) panel
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The digital video recorder system records morse code three-letter ground station identification signals from which system?
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Tactical air navigation (TACAN) system.
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Daniel Bernoulli developed a theory on the relationship of fluid speed,
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and pressure
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As fluid passes through a venturi, pressure is
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lowest where speed is highest.
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What force is created when pressure on the bottom of the airfoil is greater than on the top of the airfoil?
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Lift
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Angle-of-attack (AOA) is the angle between the aircraft’s
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wings and the flightpath.
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As angle-of-attack (AOA) increases, pressure on top of the airfoil
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decreases.
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At what degree do most airfoils enter a stall condition?
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20.
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An axis on an aircraft is an imaginary line that
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passes through the aircraft’s center of gravity
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The aircraft axis that runs from the nose to the tail is
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longitudinal.
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Aircraft movement around the vertical axis is called
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yaw.
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Aircraft pitch is referenced from
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the nose
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Connecting hydraulic actuators in line with the control stick and rudder pedals eliminated the need for pilots to use force to control surface movement. This feature is known as
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control augmentation
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Artificial feel was incorporated into the flight control system to
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keep the controls from being over controlled or accidentally jarred by the pilot
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The use of accelerometers and gyros to smooth out flight control inputs and to automatically adjust the flight control surfaces for turbulence is known as
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stability augmentation
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Command augmentation refers to
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control and stability augmentation.
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On the F–16, what is the principal component of the flight control system?
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Flight control computer (FLCC).
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The F–16 electronic component assembly (ECA) uses the angle of sideslip differential pressure sensor signal to compensate for
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AOA output by the pneumatic sensor assembly
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If the landing gear handle is up and standby gains are selected, the F–16 leading edge flaps drive to
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0 degrees
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On F–16s, to reset an integrated servoactuator (ISA) failure, you must select the SERVO position of the servo electric reset switch and simultaneously depress the
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flight control system (FLCS) CAUTION/RESET switch
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If there’s a second electronic failure in a given axis, what indication is there on the F–16 flight control panel (FLCP)?
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DUAL FC FAIL light illuminates
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If the F–16 flight control panel (FLCP) self-test control switch is in TEST, it can be switched off automatically
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whenever power is removed from the aircraft or when weight is off the main landing gear.
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The F–16 flight control system (FLCS) self-test can be performed
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only when weight is on wheels
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What is the range of motion for the F–16 side-stick?
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1/4 inch in any direction.
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The F–16 rate gyro assemblies contain pitch, roll, and yaw rate gyros that
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become unique only when connected to aircraft wiring
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How many force-balanced transducers are contained in the F–16 normal lateral accelerometer?
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8.
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When the F–16 manual trim panel TRIM/AP DISC switch is positioned to DISC, electrical power is
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removed from both trim motors and autopilot can’t be engaged.
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The F–16 manual trim panel crescent-shaped indicator(s) provide a visual indication of
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pitch and roll trim.
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From where does the F–16 angle of sideslip differential pressure sensor (DPS) receive its pneumatic pressure inputs?
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Flush-mounted static pressure ports
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How many pressure sensors does the F–16 pneumatic sensor assembly (PSA) contain?
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8.
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The F–16 digital flight control computer (DFLCC) performs the functions of what two analog flight control system (FLCS) components?
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FLCC and ECA.
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The F–16 digital flight control computer (DFLCC) has multiplex bus communication with the central air data computer (CADC) for
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pitch autopilot (altitude hold).
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The F–16 digital flight control panel’s RUN/FAIL lamp is only used
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during built-in test (BIT) operation
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On the F–16, which condition is not a requirement for the digital flight control panel’s builtin test (BIT) switch to electrically hold in the BIT position?
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Engine operating
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The F–16 digital flight control system angle-of-attack (AOA) transmitter probe’s travel rotation is
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100 degrees
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On the F–16, how many rotary variable differential tranducers does an F–16 digital flight control system (DFLCS) angle-of-attack (AOA) transmitter probe contain?
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1.
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The selected roll autopilot mode will only engage when either pitch attitude hold or
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pitch altitude hold is engaged
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Smooth flight control surface movements by modifying pilot commands as a function of air data scheduling is which feature of the F–16 flight control system (FLCS)?
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Command augmentation
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On F–16s, where are electrical command signals from the side-stick, manual trim panel, and rudder pedals compared and summed with inputs from the rate gyros, accelerometers, and air data system?
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Flight control computer (FLCC).
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The amount of control surface movement in relation to the amount of pressure applied to the side-stick or rudder pedals is called
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gain scheduling.
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On F–16s, what is the range of movement for the horizontal stabilizers?
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21 degrees up or down from streamline
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On F–16s, the flaperons will be extended 20 degrees down for increased lift when
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any of the actions identified above occur
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The F–16 rudder moves automatically during coordinated turns as a function of
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aileron rudder interconnect (ARI).
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The range of movement of the F–16 rudder is how many degrees left or right of streamline?
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30.
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On F–16s, the speed brake panels open symmetrically to a maximum of
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60 degrees each
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On F–16s, what are the three positions on the speed brake switch?
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Extend, retract, and hold
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The F–16 speed brakes receive hydraulic pressure from which hydraulic system?
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A.
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Pitch and roll attitude adjustments can be made on the F–16 while either autopilot attitude (ATT) mode is engaged. What feature enables this adjustment?
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Control stick steering
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If an F–16 experienced a “runaway trim” condition, which manual trim panel function would be used?
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TRIM/AP DISC switch
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When hydraulic power is required to drive the F–16 power drive unit (PDU), it is controlled by which component?
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Command servo
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If the F–16 digital flight control computer (DFLCC) commands provide near optimum wing camber by varying the leading edge flaps (LEF), what position is the LE FLAPS switch positioned to?
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AUTO
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If a single failure of the leading edge flap (LEF) command occurs with no adverse effect on LEF operation noticed, which of the below will be the result?
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Maintenance fault list (MFL) 007.
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How long will the F–16 standby attitude indicator continue to provide aircraft pitch and roll information when electrical power is lost and with what degree of accuracy?
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Minimum of nine minutes; ±6 degrees.
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The F–16 magnetic compass displays aircraft heading with respect to magnetic
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North.
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What does the F–16 magnetic compass use to balance north-south and east-west errors caused by magnetic influences generated by and within the aircraft?
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Adjustable magnets
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If there is a loss of aircraft power, the F–16 embedded global positioning system/inertial navigation system (EGI) will continue to operate using the EGI/inertial navigation unit (INU) battery for up to how many seconds?
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10.
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If the F–16 aircraft is going to fly at or below 80 degrees of latitude, what would be the primary alignment mode for the embedded global positioning system/inertial navigation system (EGI)?
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Normal.
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Which F–16 embedded global positioning system/inertial navigation (EGI) mode of operation is the primary flight mode and is entered from either a ground or in-flight alignment?
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Navigation
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If the F–16 embedded global positioning system/inertial navigation system (EGI) does not have any GPS almanac data, satellite acquisition can take up to how many minutes?
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90.
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On the F–16 embedded global positioning system/inertial navigation system (EGI), which navigation solution is the most accurate and preferred by the pilot?
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GPS/INS
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What is the indication range of the F–16 fan turbine inlet temperature (FTIT) indicator?
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200° to 1200° C.
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Which F–16 hydraulic pressure indicators display the indication for hydraulic system A and B?
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Left indicators display A and right indicators display B.
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How many internal fuel tanks does the F–16 have?
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Seven
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During operation, fuel is supplied directly to an F–16 aircraft engine from the
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forward and aft reservoirs simultaneously
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On an F–16 D-model, what tank is smaller than the one found on a C-model?
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F–1.
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What does the red portion of the fuel quantity indicator pointer disc indicate?
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A fuel imbalance between the forward and aft fuel systems.
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Which indication would you expect to see on the fuel quantity indicator when selecting the fuel quantity select switch TEST position?
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AL and FR pointers read 2,000 (100) pounds; total fuel reads 6,000 (100) pounds
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How many fuel probes are in each externally mounted fuel tank?
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One in the centerline; three in the wing tanks.
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What external tank component is used to cancel the capacitance signal to the control unit when the tank is empty?
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Negator circuit
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How are the positive and negative-going DC signals summed by the control unit?
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Positive for the discrete tank channel; negative for the total fuel channel.
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Where are the two low-level sensors and two air ejector control sensors found?
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On the fuel probes of the forward and aft reservoirs.
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For an F–16 block 40 aircraft, at approximately how many pounds of fuel does the ejector control sensor uncover?
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440 pounds.
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The F–16 fuel level sensing system uses 28-VDC from the right strake DC power panel for operation of the air ejector valves
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fuel level sensors, fuel level control unit, and the FWD and AFT FUEL LOW lights
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