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100 Cards in this Set

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