# Avionics 2a352g Volume 3

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Questions and Answers
• 1.

### WHAT FLIGHT ENVIRONMENTAL PRESSURE IS SENSED BY SMALL HOLES LOCATED ON THE SIDES OF THE PITOT AND AIR DATA PROBES?

• A.

PITOT

• B.

STATIC

• C.

IMPACT

• D.

DIFFERNTIAL

Correct Answer
B. STATIC
Explanation
Small holes located on the sides of the pitot and air data probes sense the static pressure of the flight environment. The static pressure is the atmospheric pressure exerted on the aircraft when it is not in motion. This pressure is used to measure altitude and airspeed. By comparing the static pressure with the total pressure measured by the pitot tube, the airspeed can be accurately determined. Therefore, the correct answer is STATIC.

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• 2.

### TRUE AOA IS THE ANGLE BETWEEN AN AIRCRAFTS WING CORD LINE AND ITS

• A.

ATTITUDE

• B.

ALTITUDE

• C.

FLIGHT PATH

• D.

GLIDE SLOPE

Correct Answer
C. FLIGHT PATH
Explanation
The true angle of attack (AOA) is the angle between an aircraft's wing cord line and its flight path. This angle is important for determining the lift and drag forces acting on the aircraft. It is crucial in maintaining the aircraft's stability and controlling its performance during flight. The AOA affects the aircraft's lift, stall speed, and maneuverability. Therefore, understanding and adjusting the AOA is essential for safe and efficient flight operations.

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• 3.

### HOW MANY SOURCES OF Pt AND Ps ARE ROUTED BY THE PITOT STATIC PROBE PNEUMATIC SYSTEM?

• A.

1

• B.

2

• C.

3

• D.

4

Correct Answer
B. 2
Explanation
The correct answer is 2 because the pitot static probe pneumatic system routes two sources of Pt (total pressure) and Ps (static pressure). The pitot tube measures the total pressure, which is the sum of the static pressure and dynamic pressure, while the static port measures the static pressure. Therefore, the pitot static probe pneumatic system uses two sources to measure both pressures.

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• 4.

### THE PITOT STATIC PRONE PNEUMATIC SYSTEM SUPPLIES AIR DATA TO THE CADC, AMI, ALTIMETER, AND

• A.

FLCC

• B.

PSA

• C.

ECA

• D.

DFLCC

Correct Answer
B. PSA
Explanation
The correct answer is PSA. The Pitot Static Prone Pneumatic System supplies air data to various aircraft systems, including the CADC (Central Air Data Computer), AMI (Airborne Meteorological Instrument), Altimeter, and PSA (Pressure Sensitive Area). This system is responsible for measuring air pressure, temperature, and density, which are crucial for accurate flight data calculations and instrument readings.

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• 5.

### THE CADC OUTPUTS ITS DATA USING THREE METHODS. THESE METHODS ARE SERIAL DIGITAL DATA WORDS, DISCRETES, AND

• A.

ANALOG

• B.

DISTINCT

• C.

ISOLATED

• D.

COMBINED

Correct Answer
A. ANALOG
Explanation
The correct answer is ANALOG. The question states that the CADC outputs its data using three methods, which are serial digital data words, discretes, and another method that is not mentioned. Since the options provided are analog, distinct, isolated, and combined, the most logical choice would be analog as it is a common method of data output in electronic devices.

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• 6.

### CADC SERIAL DIGITAL DATA WORDS ARE AVAILABLE ON THE

• A.

A MUX

• B.

B MUX

• C.

C MUX

• D.

D MUX

Correct Answer
A. A MUX
• 7.

### HOW ARE CADC ANALOG OUTPUT SIGNALS TRANSFERRED TO THEIR FINAL DESTINATION?

• A.

VIA THE A MUX

• B.

VIA THE D MUX

• C.

VIA AIRCRAFT WING

• D.

VIA FIBER OPTICS

Correct Answer
C. VIA AIRCRAFT WING
• 8.

### ONE COMPLETE REVOLUTION OF THE ALTIMETERS ALTITUDE DIAL EQUALS

• A.

100 FEET OF ALTITUDE

• B.

1000 FEET OF ALTITUDE

• C.

5000 FEET OF ALTITUDE

• D.

10000 FEET OF ALTITUDE

Correct Answer
B. 1000 FEET OF ALTITUDE
Explanation
One complete revolution of the altimeter's altitude dial equals 1000 feet of altitude. This means that for every full rotation of the dial, the altitude increases or decreases by 1000 feet.

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• 9.

### WHATS THE DISPLAY RANGE OF THE ALTIMETERS ALTITUDE DRUM COUNTER?

• A.

0 - 50000

• B.

0 - 80000

• C.

-1000 - 50000

• D.

-1000 - 80000

Correct Answer
D. -1000 - 80000
Explanation
The display range of the altimeter's altitude drum counter is from -1000 to 80000. This means that the altimeter can display altitudes ranging from -1000 feet to 80000 feet.

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• 10.

### WHY WOULD A PILOT ADJUST THE ALTIMETER TO DISPLAY PRESSURE ALTITUDE?

• A.

TO DISPLAY ALTITUDE ABOVE TERRAIN

• B.

TO DISPLAY ALTITUDE BELOW SEA LEVEL

• C.

TO STANDARDIZE AIRCRAFT ALTITUDES FOR LOW ALTITUDE AIR TRAFFIC CONTROL

• D.

TO STANDARDIZE AIRCRAFT ALTITUDES FOR HIGH ALTITUDE AIR TRAFFIC CONTROL

Correct Answer
D. TO STANDARDIZE AIRCRAFT ALTITUDES FOR HIGH ALTITUDE AIR TRAFFIC CONTROL
Explanation
A pilot would adjust the altimeter to display pressure altitude in order to standardize aircraft altitudes for high altitude air traffic control. This ensures that all aircraft are using the same reference point for altitude measurements, making it easier for air traffic controllers to manage and separate aircraft at high altitudes. Pressure altitude is calculated by setting the altimeter to a standard atmospheric pressure, which allows for accurate altitude readings regardless of changes in local atmospheric pressure.

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• 11.

### WHAT COMPONENT DEVELOPS THE VVIs VERTICAL VELOCITY SIGNAL?

• A.

VVI

• B.

FLCC

• C.

PSA

• D.

CADC

Correct Answer
D. CADC
Explanation
The Correct Answer is CADC. CADC stands for Central Air Data Computer, which is responsible for developing the VVI's (Vertical Velocity Indicator) vertical velocity signal. The CADC calculates the vertical velocity based on the rate of change of static pressure sensed by the aircraft's pitot-static system. It then sends this signal to the VVI, which displays the vertical speed of the aircraft to the pilot.

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• 12.

### THE AOA INDICATOR IS CONSIDERED A

• A.

BACK UP INDICATOR

• B.

VERTICAL TAPE INDICATOR

• C.

SELF CONTAINED INDICATOR

• D.

HORIZONTAL TAPE INDICATOR

Correct Answer
B. VERTICAL TAPE INDICATOR
Explanation
The AOA indicator is considered a vertical tape indicator because it provides a visual representation of the aircraft's angle of attack. The vertical tape on the indicator displays the angle of attack values, allowing the pilot to monitor and adjust the aircraft's pitch attitude for optimal performance and safety. This type of indicator is commonly used in aircraft to provide crucial information about the aircraft's angle of attack during flight.

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• 13.

### WHATS THE FUNCTION OF THE AOA INDEXERS LEVER CONTROL SWITCH?

• A.

ON/OFF SWITCH

• B.

SECTOR LIGHT INTENSITY

• C.

ENABLES AOA LOGIC CIRCUITS

• D.

ONLY USED DURING TAKEOFF AND LANDING CONFIGURES

Correct Answer
B. SECTOR LIGHT INTENSITY
Explanation
The function of the AOA indexers lever control switch is to control the intensity of the sector lights. The sector lights are used to provide visual cues to the pilot regarding the aircraft's angle of attack. By adjusting the sector light intensity, the pilot can customize the visibility of these cues based on their preference and the lighting conditions. This switch is not related to enabling AOA logic circuits or specific takeoff and landing configurations.

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• 14.

### HOW MANY DEDICATED SENSORS ARE UTILIZED BY THE CSFDR SYSTEM?

• A.

5

• B.

6

• C.

7

• D.

8

Correct Answer
C. 7
Explanation
The CSFDR system utilizes 7 dedicated sensors.

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• 15.

### WHATS CSFDR TYPE 1 DATA PRIMARILY USED FOR?

• A.

ENGINE ANALYSIS

• B.

MISHAP INVESTIGATION

• C.

INDIVIDUAL AIRCRAFT TRACKING

• D.

MAINTENANCE TROUBLESHOOTING

Correct Answer
B. MISHAP INVESTIGATION
Explanation
CSFDR Type 1 data is primarily used for mishap investigation. This means that when an aircraft is involved in an accident or incident, the CSFDR Type 1 data can be analyzed to determine the cause of the mishap. This data can provide valuable information about the aircraft's performance, systems, and any abnormalities that may have occurred leading up to the mishap. By analyzing this data, investigators can gain insights into what went wrong and take steps to prevent similar incidents in the future.

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• 16.

### WHAT PREDETERMINES CSFDR SPECIAL EVENT CRITERIA?

• A.

TYPE 1 DATA

• B.

BASELINE DATA

• C.

CMSU CONFIGURATION

• D.

SAU OFP

Correct Answer
D. SAU OFP
Explanation
The SAU OFP (System Authorization User Operational Flight Program) determines the CSFDR (Critical Safety Flight Data Recorder) special event criteria. The SAU OFP is responsible for setting the operational parameters and criteria for the CSFDR, which is used to record critical flight data for safety purposes. Therefore, the SAU OFP plays a crucial role in determining the criteria for special events to be recorded by the CSFDR.

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• 17.

### WHAT CSFDR TYPE DATA IS DUBBED AS INDIVIDUAL AIRCRAFT TRAKCING DATA?

• A.

1

• B.

2

• C.

3

• D.

4

Correct Answer
B. 2
• 18.

### WHAT DFLCC BRANCH COMMUNICATES WITH THE SDR?

• A.

A

• B.

B

• C.

C

• D.

D

Correct Answer
D. D
Explanation
The DFLCC branch communicates with the SDR.

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• 19.

### WHEN DOES THE SDR CEASE RECORDING OPERATIONS?

• A.

UPON FLCS SHUTDOWN

• B.

UPON A WOW CONDITION

• C.

DURING DIGITAL BACKUP OPERATIONS

• D.

UPON AUTOPILOT ENGAGEMENT

Correct Answer
B. UPON A WOW CONDITION
Explanation
The SDR (System Data Recorder) ceases recording operations upon a WOW (Weight on Wheels) condition. This means that when the aircraft is on the ground and the weight of the aircraft is supported by its wheels, the SDR stops recording data. This is a safety measure to ensure that only relevant data is recorded during flight operations and prevents unnecessary recording of data when the aircraft is not in use or on the ground.

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• 20.

### DANIEL BERNOULLI DEVELOPED A THEORY ON THE RELATIONSHIP OF FLUID SPEED,

• A.

AND PRESSURE

• B.

AIR, AND PRESSURE

• C.

TIME, AND PRESSURE

• D.

AIR PRESSURE, AND VENTURI

Correct Answer
A. AND PRESSURE
Explanation
Daniel Bernoulli developed a theory on the relationship of fluid speed and pressure. This theory, known as Bernoulli's principle, states that as the speed of a fluid increases, the pressure exerted by the fluid decreases. Conversely, as the speed of a fluid decreases, the pressure exerted by the fluid increases. This principle is applicable to various fluid systems, including air and water. Bernoulli's principle is widely used in various fields, such as aerodynamics, hydraulics, and fluid dynamics.

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• 21.

### AS FLUID PASSES THROUGH A VENTURI, PRESSURE IS

• A.

EQUAL THROUGHOUT THE VENTURI

• B.

LOWEST WHERE SPEED IS LOWEST

• C.

LOWEST WHERE SPEED IS HIGHEST

• D.

A PRODUCT OF FLUID SPEED, TIME, AND DISTANCE

Correct Answer
C. LOWEST WHERE SPEED IS HIGHEST
Explanation
According to the Venturi effect, as fluid passes through a constricted area of a pipe (such as a Venturi), the speed of the fluid increases while the pressure decreases. This is because the conservation of mass principle states that the mass flow rate of the fluid must remain constant. Therefore, when the fluid speeds up in the constricted area, the pressure decreases. Hence, the pressure is lowest where the speed is highest.

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• 22.

### AS AIR RUSHES PAST AN AIRFOIL, WHAT FORCE IS CREATED?

• A.

LIFT

• B.

DRAG

• C.

SPEED

• D.

THRUST

Correct Answer
A. LIFT
Explanation
As air rushes past an airfoil, the shape of the airfoil creates a pressure difference between the upper and lower surfaces. This pressure difference generates a lifting force called lift. This force acts perpendicular to the direction of the airflow and is responsible for keeping the aircraft in the air. Therefore, the correct answer is lift.

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• 23.

### A MORE STREAMLINED AIRFOIL HAS

• A.

LESS DRAG AND LESS LIFT

• B.

MORE DRAG AND LESS LIFT

• C.

LESS DRAG AND MORE LIFT

• D.

MORE DRAG AND MORE LIFT

Correct Answer
A. LESS DRAG AND LESS LIFT
Explanation
A more streamlined airfoil has less drag and less lift because a streamlined shape reduces the resistance of the air as it flows over the surface of the airfoil. This reduction in drag allows the airfoil to move through the air more efficiently, resulting in less resistance and drag. Additionally, the streamlined shape also reduces the amount of lift generated by the airfoil, as the streamlined shape minimizes the upward force created by the flow of air over the airfoil. Therefore, a more streamlined airfoil has both less drag and less lift.

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• 24.

### WHAT IS THE RELATIONSHIP BETWEEN LIFT AND THE AOA?

• A.

LIFT EQUALS AOA

• B.

LIFT INCREASES WITH AOA

• C.

LIFT DECREASES WITH AOA

• D.

THE TERMS ARE INTERCHANGEABLE

Correct Answer
B. LIFT INCREASES WITH AOA
Explanation
The correct answer is that lift increases with AOA (Angle of Attack). The angle of attack refers to the angle between the wing's chord line and the oncoming airflow. When the AOA increases, the lift generated by the wing also increases. This is because a higher AOA causes the airflow to be deflected more, resulting in a greater pressure difference between the upper and lower surfaces of the wing, thus generating more lift. Therefore, as the AOA increases, the lift force acting on the wing also increases.

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• 25.

### AT WHAT POINT DO MOST AIRFOILS ENTER A STALL CONDITION?

• A.

10

• B.

20

• C.

30

• D.

40

Correct Answer
B. 20
Explanation
Most airfoils enter a stall condition at a certain angle of attack. When the angle of attack exceeds a critical value, the airflow over the airfoil becomes separated, resulting in a loss of lift and an increase in drag. This is known as a stall condition. The correct answer of 20 suggests that most airfoils enter a stall condition at an angle of attack of 20 degrees.

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• 26.

### WHAT ARE THE FOUR AERODYNAMIC FORCES THAT AFFECT AN AICRAFT IN FLIGHT?

• A.

GRAVITY, LIFT, DRAG, AND THRUST

• B.

GRAVITY, LIFT, DRAG, AND AIRFOIL

• C.

GRAVITY, LIFT, FRICTION, AND POWER

• D.

GRAVITY, LIFT, FRICTION, AND AIRFOIL

Correct Answer
B. GRAVITY, LIFT, DRAG, AND AIRFOIL
Explanation
The four aerodynamic forces that affect an aircraft in flight are gravity, lift, drag, and airfoil. Gravity is the force that pulls the aircraft downwards, while lift is the force that opposes gravity and allows the aircraft to stay in the air. Drag is the force that opposes the forward motion of the aircraft, and airfoil refers to the shape of the wings that helps generate lift. These forces work together to keep the aircraft in balance and in controlled flight.

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• 27.

### WHAT IS THE PRIMARY FORCE AN AIRCRAFT MUST OVERCOME?

• A.

LIFT

• B.

DRAG

• C.

THRUST

• D.

GRAVITY

Correct Answer
D. GRAVITY
Explanation
An aircraft must overcome the force of gravity in order to stay in the air. Gravity is the force that pulls objects towards the center of the Earth, and it acts in the opposite direction of lift. In order for an aircraft to maintain altitude or climb, it must generate enough lift to counteract the force of gravity. If the force of gravity is greater than the lift produced by the aircraft, it will descend or fall. Therefore, gravity is the primary force that an aircraft must overcome.

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• 28.

### WHAT GENERATES THE FLOW OF AIR OVER AN AIRCRAFTS WINGS?

• A.

LIFT

• B.

THRUST

• C.

VENTURI

• D.

POWER PLANT

Correct Answer
B. THRUST
Explanation
Thrust is the force that propels an aircraft forward, and it is generated by the engines. As the engines produce thrust, the aircraft moves through the air, creating a flow of air over its wings. This flow of air is crucial for generating lift, which is the upward force that allows the aircraft to stay airborne. Therefore, thrust is what generates the flow of air over an aircraft's wings.

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• 29.

### WHAT FORCE OPPOSES THE MOVEMENT OF THE AIRCRAFT THROUGH THE AIR?

• A.

LIFT

• B.

DRAG

• C.

GRAVITY

• D.

PROPULSION

Correct Answer
B. DRAG
Explanation
Drag is the force that opposes the movement of an aircraft through the air. It is caused by the resistance of the air against the aircraft's forward motion. Drag can be influenced by factors such as the shape of the aircraft, its speed, and the air density. Increasing drag can make it more difficult for the aircraft to move through the air and can affect its performance and fuel efficiency.

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• 30.

### IN A STAIGHT AND LEVEL FLIGHT, LIFT EQUALS GRAVITY AND THRUST EQUALS

• A.

DRAG

• B.

SPEED

• C.

PROPULSION

• D.

TIME/DISTANCE RATIO

Correct Answer
A. DRAG
Explanation
In a straight and level flight, lift equals gravity to maintain the aircraft at a constant altitude. Similarly, thrust is equal to drag to maintain a constant speed. Drag is the resistance force that opposes the motion of the aircraft through the air. Therefore, the correct answer is drag.

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• 31.

### TO DECREASE ALTITUDE, YOU WOULD NEED TO

• A.

REDUCE DRAG

• B.

REDUCE THRUST

• C.

INCREASE DRAG

• D.

INCREASE GRAVITY

Correct Answer
B. REDUCE THRUST
Explanation
To decrease altitude, reducing thrust is necessary. Thrust is the force that propels an aircraft forward and upward. By reducing thrust, the aircraft's engines produce less power, resulting in a decrease in upward force. As a result, the aircraft will descend and decrease its altitude.

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• 32.

### AOA IS MOST IMPORTANT DURING TAKEOFF, LANDING, AND

• A.

STRAFING

• B.

LOW AIRSPEED

• C.

HIGH AIRSPEED

• D.

STEEP CLIMBS OR DIVES

Correct Answer
B. LOW AIRSPEED
Explanation
AOA (Angle of Attack) is most important during takeoff, landing, and low airspeed situations. During takeoff and landing, maintaining the correct AOA is crucial for safe and efficient operations. Low airspeed situations require careful management of AOA to prevent stalling or loss of control. AOA becomes increasingly important at lower speeds as the margin between the critical AOA (stall angle) and the current AOA decreases. Therefore, the correct answer is "LOW AIRSPEED" because it accurately identifies a critical phase of flight where AOA plays a significant role.

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• 33.

### ROLL IS ACHIEVED BY DEFLECTION OF THE

• A.

RUDDER

• B.

FLAPERONS ONLY

• C.

FLAPERONS AND RUDDER

• D.

FLAPERONS AND HORIZONTAL STABS

Correct Answer
D. FLAPERONS AND HORIZONTAL STABS
Explanation
The correct answer is FLAPERONS AND HORIZONTAL STABS. Roll is achieved by the deflection of both the flaperons and the horizontal stabs. Flaperons are control surfaces that combine the functions of both ailerons and flaps, and they are located on the wings. Horizontal stabs, also known as horizontal stabilizers, are fixed surfaces located at the tail of an aircraft. By deflecting both the flaperons and the horizontal stabs, the aircraft can generate a rolling motion around its longitudinal axis.

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• 34.

### WHICH AXIS ON AN AIRCRAFT EXTEDS CROSSWISE FROM WINGTIP TO WINGTIP?

• A.

LATERAL

• B.

VERTICAL

• C.

HORIZONTAL

• D.

LONGITUDINAL

Correct Answer
A. LATERAL
Explanation
The lateral axis on an aircraft extends crosswise from wingtip to wingtip. This axis is responsible for controlling the roll motion of the aircraft, allowing it to bank and turn. The other axes, such as the vertical axis, control the yaw motion (nose left or right) and the longitudinal axis controls the pitch motion (nose up or down). The term "lateral" is used to describe the side-to-side movement, which is why it is the correct answer in this context.

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• 35.

### YAW MOVEMENTS ARE ACHIEVED BY

• A.

DEFLECTION OF THE RUDDER

• B.

DEFLECTION OF THE FLAPERONS AND RUDDER

• C.

EQUAL DEFLECTION OF THE HORIZONTAL STABILIZERS

• D.

EQUAL DEFLECTION OF THE FLAPERONS AND HORIZONTAL STABS

Correct Answer
A. DEFLECTION OF THE RUDDER
Explanation
YAW MOVEMENTS ARE ACHIEVED BY DEFLECTION OF THE RUDDER. The rudder is responsible for controlling the yaw movement of an aircraft. By deflecting the rudder, the pilot can create a yawing motion, which is the side-to-side movement of the aircraft's nose. This movement helps in controlling the direction of the aircraft during flight. The deflection of the rudder creates a force that counteracts any unwanted yawing moments and helps maintain stability and control of the aircraft.

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• 36.

### AIRCRAFT ROLL IS REFERENCED FROM

• A.

THE NOSE

• B.

EITHER WINGTIP

• C.

THE LEFT WINGTIP

• D.

THE RIGHT WINGTIP

Correct Answer
B. EITHER WINGTIP
Explanation
Aircraft roll is referenced from either wingtip. This means that when an aircraft rolls, it rotates around its longitudinal axis, which is an imaginary line running from the nose to the tail of the aircraft. The roll can be measured or referenced from either the left wingtip or the right wingtip, depending on the specific aircraft and its design. This allows for accurate measurement and control of the aircraft's roll movement during flight.

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• 37.

### AIRCRAFT PITCH IS REFERENCED FROM

• A.

THE NOSE

• B.

EITHER WINGTIP

• C.

THE LEFT WINGTIP

• D.

THE RIGHT WINGTIP

Correct Answer
A. THE NOSE
Explanation
Aircraft pitch is referenced from the nose because the nose of an aircraft is the forwardmost part and acts as a reference point for measuring the pitch angle. Pitch refers to the up and down movement of the aircraft's nose in relation to the horizon. By referencing the pitch from the nose, pilots can accurately control the aircraft's attitude and maintain stability during flight.

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• 38.

### ARTIFICIAL FEEL WAS INCORPORATED INTO THE FLIGHT CONTROL SYSTEM TO

• A.

PROVIDE STABILITY AUGMENTATION

• B.

SMOOTH OUT AND CONTROL THE ANGLE OF SURFACE MOVEMENT ACCORDING TO AIRSPEED

• C.

ELIMINATE THE NEED FOR FORCE WHEN CONTROLLING FLIGHT CONTROL SURFACE MOVEMENT

• D.

KEEP THE CONTROLS FROM BEING OVER CONTROLLED OR ACCIDENTALLY JARRED BY THE PILOT

Correct Answer
D. KEEP THE CONTROLS FROM BEING OVER CONTROLLED OR ACCIDENTALLY JARRED BY THE PILOT
Explanation
The correct answer is to keep the controls from being over controlled or accidentally jarred by the pilot. Artificial feel was incorporated into the flight control system to provide a sense of resistance or feedback to the pilot, which helps them maintain control and prevents them from making sudden or excessive movements that could destabilize the aircraft. This feature ensures smoother and more controlled movement of the flight control surfaces, enhancing stability and safety during flight.

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• 39.

### THE USE OF ACCELEROMETERS AND GYROS TO SMOOTH OUT FLIGH CONTROL INPUTS AND TO AUTOMATICALLY ADJUST THE FLIGHT CONTROL SURFACES TO TURBULENCE IS KNOWN AS WHAT AUGMENTATION?

• A.

FLIGHT

• B.

DIRECT

• C.

CONTROL

• D.

STABILITY

Correct Answer
D. STABILITY
Explanation
The use of accelerometers and gyros to smooth out flight control inputs and automatically adjust the flight control surfaces to turbulence is known as stability augmentation.

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• 40.

### WHAT IS THE PRINCIPAL COMPONENT OF THE F-16 FLIGHT CONTROL SYSTEM?

• A.

ECA

• B.

FLCC

• C.

FCC

• D.

FLCP

Correct Answer
B. FLCC
Explanation
The principal component of the F-16 flight control system is the FLCC.

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• 41.

### WHAT TYPE OF MEMORY DOES THE F-16 FLCC CONTAIN?

• A.

VOLATILE

• B.

AUXILIARY

• C.

NONVOLATILE

• D.

THE FLCC HAS NO MEMORY, THE SDR RECORDS FLIGHT EVENT

Correct Answer
C. NONVOLATILE
Explanation
The F-16 FLCC contains nonvolatile memory. Nonvolatile memory is a type of computer memory that retains its stored data even when the power is turned off or lost. This is in contrast to volatile memory, which requires a continuous power supply to retain its data. Nonvolatile memory is commonly used in electronic devices such as computers, smartphones, and aircraft systems to store important data that needs to be retained even in the absence of power. Therefore, the F-16 FLCC's nonvolatile memory allows it to store and retain critical information even when the power is not available.

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• 42.

### THE F-16 ECA USES THE ANGLE OF SIDESLIP DIFFERENTIAL PRESSURE SENSOR SIGNAL TO COMPENSATE FOR

• A.

BOTH AOA TRANSMITTER PROBES

• B.

AOA OUTPUT BY THE PNEUMATIC SENSOR ASSEMBLY

• C.

THE RIGHT AOA TRANSMITTER PROBE

• D.

THE LEFT AOA TRANSMITTER PROBE

Correct Answer
B. AOA OUTPUT BY THE PNEUMATIC SENSOR ASSEMBLY
Explanation
The F-16 ECA uses the angle of sideslip differential pressure sensor signal to compensate for the AOA output by the pneumatic sensor assembly. This means that the sensor assembly may provide inaccurate or fluctuating AOA readings, and the angle of sideslip differential pressure sensor signal is used to correct and adjust the AOA output accordingly. This ensures that the aircraft receives accurate and reliable AOA information for proper operation and control.

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• 43.

### IN THE EVENT OF AN AIR DATA FAILURE, WHAT COMPONENT PROVIDES THE F-16 FLCC WITH STANDBY GAINS?

• A.

ANGLE OF SIDESLIP DPS

• B.

ECA

• C.

PSA

• D.

CADC

Correct Answer
B. ECA
Explanation
In the event of an air data failure, the F-16 FLCC (Flight Control Computer) relies on the ECA (Engine Control Amplifier) to provide standby gains. The ECA is responsible for amplifying and processing signals from various sensors, including those related to air data. Therefore, in the absence of accurate air data, the ECA steps in to provide the necessary backup gains to ensure proper control of the aircraft.

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• 44.

### LEADING EDGE FLAP COMMANDS ON THE F-16 ARE

• A.

NONREDUNDANT

• B.

DOUBLE REDUNDANT

• C.

TRIPLE REDUNDANT

• D.

QUADRUPLE REDUNDANT

Correct Answer
C. TRIPLE REDUNDANT
Explanation
The leading edge flap commands on the F-16 are triple redundant, meaning that there are three independent systems or components that can control the flaps. This redundancy is important for safety and reliability, as it ensures that even if one or two of the systems fail, there is still another functioning system that can control the flaps. Having triple redundancy increases the overall reliability and effectiveness of the leading edge flaps on the F-16 aircraft.

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• 45.

### IF THE LANDING GEAR HANDLE IS UP AND STANDBY GAINS ARE SELECTED, THE F-16 LEADING EDGE FLAPS DRIVE TO

• A.

-2 DEGREES

• B.

0 DEGREES

• C.

15 DEGREES

• D.

25 DEGREES

Correct Answer
B. 0 DEGREES
Explanation
When the landing gear handle is up and standby gains are selected, the F-16 leading edge flaps drive to 0 degrees. This means that the leading edge flaps are fully retracted and in their neutral position.

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• 46.

### WHEN A FLIGHT CONTROL PANEL'S SERVO ARM SWITCH IS PLACED TO ARM, A SUNSEQUENT FAILURE WILL SHUT DOWN THE F-16 ISA AND

• A.

LOCK THE SURFACE IN THE EXISTING POSITION

• B.

RETURN THE SURFACE TO THE STREAMLINED POSITION

• C.

RETURN THE SURFACE TO 2 DEGREES ABOVE STREAMLINE FOR LANDING

• D.

RETURN THE SURFACE TO 2 DEGREES BELOW STREAMLINE FOR LANDING

Correct Answer
B. RETURN THE SURFACE TO THE STREAMLINED POSITION
Explanation
When a flight control panel's servo arm switch is placed to arm, a subsequent failure will return the surface to the streamlined position.

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• 47.

### WHICH FLCP SWITCH RESETS THE F-16 FLCS FAULT LIGHT ALERTING FUNCTION?

• A.

SERVO/ELEC RESET

• B.

MASTER CAUTION

• C.

MASTER MODE RESET

• D.

FLCS CAUTION/RESET

Correct Answer
D. FLCS CAUTION/RESET
Explanation
The FLCS Caution/Reset switch resets the F-16 FLCS (Flight Control System) Fault Light Alerting Function. This switch is specifically designed to address any faults or issues detected in the FLCS, which is responsible for controlling the aircraft's flight surfaces. By resetting the FLCS Caution/Reset switch, any fault indications or alerts related to the FLCS can be cleared, allowing the pilot to continue operating the aircraft without the distraction or concern of a faulty FLCS.

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• 48.

### ON F-16s, TO RESET AN ISA FAILURE, YOU MUST SELECT THE SERVO POSITION OF THE SERVO ELECTRIC RESET SWITCH AND SIMULTANEOUSLY DEPRESS THE

• A.

MAL/IND SWITCH

• B.

MASTER CAUTION LIGHT

• C.

APPROPRIATE SERVO ARM SWITCH

• D.

FLCS CAUTION/RESET SWITCH

Correct Answer
D. FLCS CAUTION/RESET SWITCH
Explanation
To reset an ISA failure on F-16s, the appropriate action is to select the servo position of the FLCS (Flight Control System) caution/reset switch and simultaneously depress it. This action will reset the ISA (Inertial Sensor Assembly) failure. The FLCS caution/reset switch is specifically designed for this purpose and is the correct switch to use in this situation.

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• 49.

### WHAT DOES AN ILLUMINATED P, R, OR Y LIGHT ON THE F-16 FLCP INDICATE?

• A.

THE APPLICABLE CONTROL AXIS REQUIRES ADDITIONAL MANUAL TRIM

• B.

ANY MALFUNCTION IN THE ELECTRONIC CIRCUITS FOR THE APPLICABLE CONTROL AXIS

• C.

THE FIRST TIME MALFUNCTION IN THE ELECTRONIC CIRCUITS FOT THE APPLICABLE CONTROL AXIS

• D.

THE SECOND OR SUBSEQUENT MALFUNCTION IN THE ELECTRONIC CIRCUITS OF THE APPLICABLE CONTROL AXIS

Correct Answer
C. THE FIRST TIME MALFUNCTION IN THE ELECTRONIC CIRCUITS FOT THE APPLICABLE CONTROL AXIS
Explanation
An illuminated P, R, or Y light on the F-16 FLCP indicates the first time malfunction in the electronic circuits for the applicable control axis.

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• 50.

### WHAT INDIVATOIN IS THERE ON THE F-16 FLCP THAT THERE'S A SECOND ELECTRONIC FAILURE IN A GIVEN AXIS?

• A.

DUAL FC FAIL LIGHT ILLUMINATES

• B.

THE LIGHT FOR THE APPLICABLE AXIS WILL ILLUMINATE

• C.

THE LIGHT FOR THE APPLICABLE AXIS WILL ILLUMINATE ALONG WITH THE FLIGHT CONTROL SYSTEM CAUTION LIGHT

• D.

THE LIGHT FOR THE APPLICABLE AXIS WILL ILLUMINATE ALONG WITH THE MASTER CAUTION LIGHT

Correct Answer
A. DUAL FC FAIL LIGHT ILLUMINATES
Explanation
If there is a second electronic failure in a given axis on the F-16 FLCP, the Dual FC Fail light will illuminate. This indicates that there is a failure in both flight control channels for that axis.

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Quiz Review Timeline +

Our quizzes are rigorously reviewed, monitored and continuously updated by our expert board to maintain accuracy, relevance, and timeliness.

• Current Version
• Mar 21, 2023
Quiz Edited by
ProProfs Editorial Team
• Oct 20, 2011
Quiz Created by
Robdduarte1

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