FS3 Test 2

5602 - True airspeed is best described as calibrated airspeed corrected for: - installation or instrument error - non-standard temperature - altitude and non-standard temperature

- altitude and non-standard temperature

5214 (Refer to Figure 3) - How much altitude will this airplane lose in 3 miles of gliding at an angle of attack of 8 degrees? - 400 feet - 880 feet - 1,320 feet

- 1,320 feet

5016-4 - Newer airplanes have a design maneuvering speed that can generally be calculated as follows: - 1.2 V(SO) - 1.7 V(SO) - half the stall speed

- 1.7 V(SO)

5270 - If a standard rate turn is maintained, how long would it take to turn 360 degrees? - 1 minute - 2 minutes - 3 minutes

- 2 minutes

5114 - What altimeter setting is required when operating an aircraft at 18,000 feet MSL? - current reported altimeter setting of a station along the route - 29.92" Hg - altimeter setting at the departure or destination airport

- 29.92" Hg

5740 - To determine pressure altitude prior to takeoff, the altimeter should be set to: - the current altimeter setting - 29.92" Hg and the altimeter indication noted - the field elevation and the pressure reading in the altimeter setting window noted

- 29.92" Hg and the altimeter indication noted

5408 - An airplane is located at an airport with an elevation of 5,000 feet MSL and a temperature of 90 degrees F. The altimeter is set to airport elevation. Later that night the temperature plummets to 50 degrees F. Unless the altimeter setting is changed, it will read: - 4,800 feet - 5,000 feet - 5,200 feet

- 5,200 feet

5205 - In small airplanes, normal recovery from spins may become difficult if the: - CG is too far rearward and rotation is around the longitudinal axis - CG is too far rearward and rotation is around the CG -Spin is entered before the stall is fully developed

- CG is too far rearward and rotation is around the CG

5653 - Your aircraft has an exhaust manifold type heating system. The exhaust manifold should be periodically inspected to avoid: - Carbon monoxide poisoning - overheating in the cockpit - extremely cold temperatures in the cabin

- Carbon monoxide poisoning

5198-1 - An aircraft airfoil is designed to produce lift resulting from a difference in the: - Negative air pressure below and a vacuum above the airfoil's surface -Vacuum below the airfoil's surface and greater air pressure above the airfoil's surface - Higher air pressure below the airfoil's surface and lower air pressure above the airfoil's surface

- Higher air pressure below the airfoil's surface and lower air pressure above the airfoil's surface

5229 - What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased? - Increase the angle of attack to produce more lift than drag - Increase the angle of attack to compensate for the decreasing lift -Decrease the angle of attack to compensate for the increasing drag

- Increase the angle of attack to compensate for the decreasing lift

5601 - Calibrated airspeed is best described as indicated airspeed corrected for: - Installation and instrument error - Instrument error - Non-standard temperature

- Installation and instrument error

5189 - Which statement is true concerning the effect of the application of carburetor heat? - It enriches the fuel/air mixture - It leans the fuel/air mixture - It has no effect on the fuel/air mixture

- It enriches the fuel/air mixture

5198 - By changing the angle of attack of a wing, the pilot can control the airplanes: - Lift, airspeed, and drag -Lift, airspeed, and CG -Lift and airspeed, but not drag

- Lift, airspeed, and drag

5177-1 The ratio of an airplane's true airspeed to the speed of sound in the same atmospheric conditions is: - equivalent airspeed - transonic airflow - Mach number

- Mach number

5235 - Propeller efficiency is the: - ratio of thrust horsepower to brake horsepower - actual distance a propeller advances in one revolution - ratio of geometric pitch to effective pitch

- ratio of thrust horsepower to brake horsepower

5767 - Which is true regarding preheating an aircraft during cold weather operations? - The cabin area as well as the engine should be preheated - The cabin area should not be preheated with portable heaters - Hot air should be blown directly at the engine through the air intakes

- The cabin area as well as the engine should be preheated

5608 - What will occur if no leaning is made with the mixture control as the flight altitude increases? - The volume of air entering the carburetor decreases and the amount of fuel decreases - The density of air entering the carburetor decreases and the amount of fuel increases - The density of air entering the carburetor decreases and the amount of fuel remains the same

- The density of air entering the carburetor decreases and the amount of fuel remains the same

5232 (Refer to Figure 5) - The vertical line from point E to point F is represented on the airspeed indicator by the: - Upper limit of the yellow arc - Upper limit of the green arc - Blue radial line

- Upper limit of the yellow arc

5604-1 - Structural damage or failure is more likely to occur in smooth air at speeds above: - V(NO) - V(A) - V(NE)

- V(NE)

5014 - Which is the correct symbol for the stalling speed or the minimum steady flight speed at which the airplane is controllable? - V(S) - V(S1) - V(S0)

- V(S)

5013 - Which is the correct symbol for the stalling speed or the minimum steady flight speed in a specified configuration? - V(S) - V(S1) - V(S0)

- V(S1)

5173 - The most probable reason an engine continues to run after the ignition switch has been turned off is: - carbon deposits glowing on the spark plugs - a magneto ground wire is in contact with the engine casing - a broken magneto ground wire

- a broken magneto ground wire

5669 - A pilot is entering an area where significant clear air turbulence has been reported. Which action is appropriate upon encountering the first ripple? - maintain altitude and airspeed - adjust airspeed to that recommended for rough air - enter a shallow climb or descent at maneuvering speed

- adjust airspeed to that recommended for rough air

5177-2 - What could be one result of exceeding critical Mach number? - propeller stall - reduction in drag - aircraft control difficulties

- aircraft control difficulties

5505 - Which maximum range factor decreases as weight decreases? -altitude -airspeed -angle of attack

- airspeed

5236 - A fixed-pitch propeller is designed for best efficiency only at a given combination of: - altitude and RPM - airspeed and RPM - airspeed and altitude

- airspeed and RPM

5999-3 - You are flying an aircraft equipped with an electronic flight display and the air data computer fails. What instrument is affected? - ADS-B In capability - airspeed indicator - attitude indicator

- airspeed indicator

5212 - An airplane will stall at the same: - angle of attack regardless of the attitude with relation to the horizon -airspeed regardless of the attitude with relation to the horizon -angle of attack and attitude with relation to the horizon

- angle of attack regardless of the attitude with relation to the horizon

5174 - If the ground wire between the magneto and the ignition switch become disconnected, the engine: - will not operate on one magneto - cannot be started with the switch in the BOTH position - could accidentally start if the propeller is moved with fuel in the cylinder

- could accidentally start if the propeller is moved with fuel in the cylinder

5610 - The basic purpose of adjusting the fuel/air mixture control at altitude is to: - decrease the fuel flow to compensate for decreased air density - decrease the amount of fuel in the mixture to compensate for increased air density - increase the amount of fuel in the mixture to compensate for the decrease in pressure and density of the air

- decrease the fuel flow to compensate for decreased air density

5654 - To establish a climb after takeoff in an aircraft equipped with a constant-speed propeller, the output of the engine is reduced to climb power by decreasing manifold pressure and: - increasing RPM by decreasing propeller blade angle - decreasing RPM by decreasing propeller blade angle - decreasing RPM by increasing propeller blade angle

- decreasing RPM by increasing propeller blade angle

5015-1 - 14 CFR Part 1 defines V(F) as: - design flap speed - flap operating speed - maximum flap extended speed

- design flap speed

5604 - Why should flight speeds above V(NE) be avoided? - excessive induced drag will result in structural failure - design limit load factors may be exceeded, if gusts are encountered - control effectiveness is so impaired that the aircraft becomes uncontrollable

- design limit load factors may be exceeded, if gusts are encountered

5670 - If severe turbulence is encountered during flight, the pilot should reduce the airspeed to: - minimum control speed - design-maneuvering speed - maximum structural cruising speed

- design-maneuvering speed

5606 - Applying carburetor heat will: - not affect the mixture - lean the fuel/air mixture - enrich the fuel/air mixture

- enrich the fuel/air mixture

5202 - On a wing, the force of lift acts perpendicular to the relative wind and the force of drag acts parallel to the: - chord line -flightpath -longitudinal axis

- flightpath

5158 - Lift on a wing is most properly defined as the: - force acting perpendicular to the relative wind -differential pressure acting perpendicular to the chord of the wing -reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber

- force acting perpendicular to the relative wind

5611 - At high altitudes, an excessively rich mixture will cause the: - engine to overheat - fouling of the spark plugs - engine to operate smoother even though fuel consumption is increased

- fouling of the spark plugs

5172 - Fouling spark plugs is more apt to occur if the aircraft: - gains altitude with no mixture adjustment - descends from altitude with no mixture adjustment - throttle is advanced very abruptly

- gains altitude with no mixture adjustment

5166 (Refer to Figure 1) - At an airspeed represented by point B, in steady flight, the pilot can expect to obtain the airplane's maximum: -endurance -glide range -coefficient of lift

- glide range

5233 (Refer to Figure 5) - The vertical line from point D to point G is represented on the airspeed indicator by the maximum speed limit of the: - green arc - yellow arc - white arc

- green arc

5766 - During preflight in cold weather, crankcase breather lines should receive special attention because they are susceptible to being clogged by: - congealed oil from the crankcase - moisture from the outside air which has frozen - ice from crankcase vapors that have condensed and subsequently frozen

- ice from crankcase vapors that have condensed and subsequently frozen

5171 - A way to detect a broken magneto primary grounding lead is to: - idle the engine and momentarily turn the ignition off - add full power, while holding the brakes, and momentarily turn off the ignition - run on one magneto, lean the mixture, and look for a rise in manifold pressure

- idle the engine and momentarily turn the ignition off

5184 - In aircraft equipped with constant-speed propellers and normally-aspirated engines, which procedure should be used to avoid placing undue stress on the engine components? When power is being: - decreased, reduce the RPM before reducing the manifold pressure - increased, increase the RPM before increasing the manifold pressure - Increased or decreased, the RPM should be adjusted before the manifold pressure

- increased, increase the RPM before increasing the manifold pressure

5268 - What is an operational difference between the turn coordinator and the turn-slip indicator? The turn coordinator: - is always electric; the turn-and-slip indicator is always vacuum-driven - indicates bank angle only; the turn-and-slip indicator indicates rate of turn and coordination - indicates roll rate, rate of turn, and coordination; the turn-and-slip indicator indicates rate of turn and coordination

- indicates roll rate, rate of turn, and coordination; the turn-and-slip indicator indicates rate of turn and coordination

5269 - What is an advantage of an electric turn coordinator if the airplane has a vacuum system for other gyroscopic instruments? - it is a backup in case of vacuum system failure - it is more reliable than vacuum-driven indicators - it will not tumble as will vacuum-driven turn indicators

- it is a backup in case of vacuum system failure

5207 - If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its: -Vertical axis - lateral axis -longitudinal axis

- lateral axis

5016-1 - 14 CFR Part 1 defines V(LE) as: - maximum landing gear extended speed - maximum landing gear operating speed - maximum leading edge flaps extended speed

- maximum landing gear extended speed

5015-2 - 14 CFR Part 1 defines V(NO) as: - maximum structural cruising speed - never-exceed speed - maximum operating limit speed

- maximum structural cruising speed

5176 - The pilot controls the air/fuel ratio with the: - throttle - manifold pressure - mixture/control

- mixture/control

5016-2 14 CFR Part 1 defines V(NE) as: - maximum nose wheel extend speed - never-exceed speed - maximum landing gear extended speed

- never-exceed speed

5605 - Maximum structural cruising speed is the maximum speed at which an airplane can be operated during: - Abrupt maneuvers - normal operations - flight in smooth air

- normal operations

5237 - The reason for variations in geometric pitch (twisting) along a propeller blade is that it: - permits a relatively constant angle of incidence along its length when in cruising flight - prevents the portion of the blade near the hub from stalling during cruising flight - permits a relatively constant angle of attack along its length when in cruising flight

- permits a relatively constant angle of attack along its length when in cruising flight

5999-2 What is a consideration when using a hand-held GPS for VFR navigation? - position accuracy may degrade without notification - RAIM capability will be maintained for entire flight - waypoints will still be accurate even if database is not current

- position accuracy may degrade without notification

5186 - The uncontrolled firing of the fuel/air charge in advance of normal spark ignition is known as: - instantaneous combustion - detonation - pre-ignition

- pre-ignition

5188 - The mixture control can be adjusted, which: - prevents the fuel/air combination from becoming too rich at higher altitudes - regulates the amount of air flow through the carburetor's venturi - prevents the fuel/air combination from becoming lean as the airplane climbs

- prevents the fuel/air combination from becoming too rich at higher altitudes

5217 - What performance is a characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? - gain in altitude over a given distance - range and maximum distance glide - coefficient of lift and minimum coefficient of drag

- range and maximum distance glide

5271 - A detuning of engine crankshaft counterweights is a source of over-stress that may be caused by: - rapid opening and closing of the throttle - carburetor ice forming on the throttle valve - operating with an excessively rich fuel/air mixture

- rapid opening and closing of the throttle

5609 - Unless adjusted, the fuel/air mixture becomes richer with an increase in altitude because the amount of fuel: - decreases while the volume of air decreases - remains constant while the volume of air decreases - remains constant while the density of air decreases

- remains constant while the density of air decreases

5741 - Which is the best technique for minimizing the wing-load factor when flying in severe turbulence? - change power settings, as necessary, to maintain constant airspeed - control airspeed with power, maintain wings level, and accept variations of altitude - set power and trim to obtain speed, maintain wings level and accept variations of airspeed and altitude

- set power and trim to obtain speed, maintain wings level and accept variations of airspeed and altitude

5169 - Before shutdown, while at idle, the ignition key is momentarily turned OFF. The engine continues to run with no interruption; this: - is normal because the engine is usually stopped by moving the mixture to idle cut-off - should not normally happen. Indicates a magneto not grounding in OFF position - is an undesirable practice, but indicates that nothing is wrong

- should not normally happen. Indicates a magneto not grounding in OFF position

5667 - To develop maximum power and thrust, a constant-speed propeller should be set to a blade angle that will produce a: - large angle of attack and low RPM - small angle of attack and high RPM - large angle of attack and high RPM

- small angle of attack and high RPM

5668 - For takeoff, the blade angle of a controllable-pitch propeller should be set at a: - small angle of attack and high RPM - large angle of attack and low RPM - large angle of attack and high RPM

- small angle of attack and high RPM

5191 - Name the four fundamentals involved in maneuvering an aircraft: - power. pitch, bank, and trim - thrust, lift, turns, and glides - straight-and-level flight, turns, climbs, and descents

- straight-and-level flight, turns, climbs, and descents

5175 - For internal cooling, reciprocating aircraft engines are especially dependent on: - a properly functioning cowl flap augmenter - the circulation of lubricating oil - the proper freon/compressor output ratio

- the circulation of lubricating oil

5185-1 - Detonation may occur at high power settings when: - the fuel mixture ignites instantaneously instead of burning progressively and evenly - an excessively rich fuel mixture causes an explosive gain in power - the fuel mixture is ignited too early by hot carbon deposits in the cylinder

- the fuel mixture ignites instantaneously instead of burning progressively and evenly

5177 - Which airspeed would a pilot be unable to identify by the color coding of an airspeed indicator? - the never-exceed speed - the power-off stall speed - the maneuvering speed

- the maneuvering speed

5298 - The best power mixture is that fuel/air ratio at which: - cylinder head temperatures are the coolest - the most power can be obtained for any given throttle setting - a given power can be obtained with the highest manifold pressure or throttle setting

- the most power can be obtained for any given throttle setting

5607 - An abnormally high engine oil temperature indication may be caused by: - a defective bearing - the oil level being too low - operating with an excessively rich mixture

- the oil level being too low

5183 - Which statement best describes the operating principle of a constant-speed propeller? - as throttle setting is changed by the pilot, the prop governor causes pitch angle of the propeller blades to remain unchanged - a high blade angle, or increased pitch, reduces power for takeoffs - the propeller control regulates the engine RPM and in turn the propeller RPM

- the propeller control regulates the engine RPM and in turn the propeller RPM

5190 - Detonation occurs in a reciprocating aircraft engine when: - there is an explosive increase of fuel caused by too rich a fuel/air mixture - the spark plugs receive an electrical jolt caused by a short in the wiring - the unburned fuel/air charge in the cylinders is subjected to instantaneous combustion

- the unburned fuel/air charge in the cylinders is subjected to instantaneous combustion

5299 - Consider a reciprocating engine. Detonation can be caused by: - a "rich" mixture - low engine temperatures - using a lower grade fuel than recommended

- using a lower grade fuel than recommended

5178 - Which statement is true about magnetic deviation of a compass? Deviation: - varies over time as the agonic line shifts - varies for different headings of the same aircraft - is the same for all aircraft in the same locality

- varies for different headings of the same aircraft

5187 - Fuel/air mixture is the ratio between: - Volume of fuel and volume of air entering the cylinder - weight of fuel and weight of air entering the cylinder - weight of fuel and weight of air entering the carburetor

- weight of fuel and weight of air entering the cylinder

5170 - Leaving the carburetor heat on while taking off: - leans the mixture for more power on takeoff - will decrease the takeoff distance - will increase the ground roll

- will increase the ground roll

5215 (Refer to Figure 3) - The L/D ratio at a 2 degree angle of attack is approximately the same as the L/D ratio for a: - 9.75 degree angle of attack - 10.5 degree angle of attack -16.5 degree angle of attack

-16.5 degree angle of attack

5123 (Refer to Figure 3) - If an airplane glides at an angle of attack of 10 degrees, how much altitude will it lose in 1 mile? - 240 feet - 480 feet -960 feet

-480 feet

5223 - To generate the same amount of lift as altitude is increased, an airplane must be flown at: - The same true airspeed regardless of angle of attack -A lower true airspeed and a greater angle of attack -A higher true airspeed for any given angle of attack

-A higher true airspeed for any given angle of attack

5199 - The angle of attack of a wing directly controls the: - Angle of incidence of the wing -Amount of airflow above and below the wing -Distribution of pressures acting on the wing

-Distribution of pressures acting on the wing

5974 - A sweptwing airplane with weak static directional stability and increased dihedral causes an increase in: - Mach tuck tendency -Dutch roll tendency -Longitudinal stability

-Dutch roll tendency

5228 - Longitudinal stability involves the motion of the airplane controlled by its: -Rudder -Elevator -Ailerons

-Elevator

5161 - In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become: -Twice as great -Half as great -Four times greater

-Four times greater

5200 - In theory, if the angle of attack and other factors remain constant and the airspeed is doubled, the lift produced at the higher speed will be: -The same as at the lower speed -Two times greater than at the lower speed -Four times greater than at the lower speed

-Four times greater than at the lower speed

5162 - As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane: - decreases because of lower parasite drag -Increases because of increased induced drag -Increases because of increased parasite drag

-Increases because of increased induced drag

5226 - If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays: -Neutral longitudinal static stability -positive longitudinal static stability -neutral longitudinal dynamic stability

-Neutral longitudinal static stability

5231 (Refer to Figure 5) - The horizontal dashed line from point C to point E represents the: - Ultimate load factor -Positive limit load factor -Airspeed range for normal operations

-Positive limit load factor

5230 - If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays: -Positive dynamic stability -Positive static stability -neutral dynamic stability

-Positive static stability

5203 - Which statement is true, regarding the opposing forces acting on an airplane in steady-state level flight? -These forces are equal -Thrust is greater than drag and weight and lift are equal -Thrust is greater than drag and lift is greater than weight

-These forces are equal

5979 (Refer to Figure 5) - What does the intersection of the dashed line at point C represent? -Va -Negative limit load factor -Positive limit load factor

-Va

5167 - Which statement is true relative to changing angle of attack? - a decrease in angle of attack will increase pressure below the wing, and decrease drag -an increase in angle of attack will increase drag -an increase in angle of attack will decrease pressure below the wing, and increase drag

-an increase in angle of attack will increase drag

5220-1 - To hold an airplane in level flight at airspeeds from very slow to very fast, a pilot must coordinate thrust and: - angle of incidence -gross weight -angle of attack

-angle of attack

5220 - When transitioning from straight-and-level flight to a constant airspeed climb, the angle of attack and lift: - are increased and remain at a higher lift-to-weight ratio to maintain the climb -remain the same and maintain a steady state lift-to-weight ratio during the climb -are momentarily increased and lift returns to a steady state during the climb

-are momentarily increased and lift returns to a steady state during the climb

5218 - Which is true regarding the forces acting on an aircraft in a steady-state descent? The sum of all: - upward forces is less than the sum of all downward forces -rearward forces is greater than the sum of all forward forces -forward forces is equal to the sum of all rearward forces

-forward forces is equal to the sum of all rearward forces

5165 (Refer to Figure 1) - At the airspeed represented by point A, in steady flight, the airplane will: -have its maximum L/D ratio -have its minimum L/D ratio -be developing its maximum coefficient of lift

-have its maximum L/D ratio

5201 - An aircraft wing is designed to produce lift resulting from a difference in the: - negative air pressure below and a vacuum above the wing's surface -vacuum below the wing's surface and greater air pressure above the wing's surface -higher air pressure below the wing's surface and lower air pressure above the wing's surface

-higher air pressure below the wing's surface and lower air pressure above the wing's surface

5161-1 - In theory, if the airspeed of an aircraft in level flight is cut in half, parasite drag will become: - one-third as much -one-half as much -one-fourth as much

-one-fourth as much

5227 - Longitudinal dynamic instability in an airplane can be identified by: - bank oscillations becoming progressively steeper -pitch oscillations becoming progressively steeper -Trilatitudinal roll oscillations becoming progressively steeper

-pitch oscillations becoming progressively steeper

5016-3 - 14 CFR Part 1 defines V(Y) as: - speed for best rate of descent - speed for best angle of climb -speed for best rate of climb

-speed for best rate of climb

5219 - Which is true regarding the force of lift in steady, unaccelerated flight? - at lower airspeeds the angle of attack must be less to generate sufficient lift to maintain altitude -there is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude -an airfoil will always stall at the same indicated airspeed; therefore, an increase in weight will require an increase in speed to generate sufficient lift

-there is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude