1
Q
What is the Lift equation?
A
L=CL V2 P(1/2)S
Where
L = lift force
CL = lift coefficient
p = air density
V = velocity
A = lift surface area
2
Q
Name four ways to control lift.
A
Increasing airspeed
changing the angle of attack
changing shape of airfoil
using leading edge devises or flaps
2
Q
What type of thrust is a result of a engine failure in a light twin aircraft?
A
One of the problems of the conventional multi-engine layout is the asymmetrical thrust and drag resulting from an engine failure. In light twin, loss of power on either engine results in:
- Yaw. Asymmetric thrust results in yaw toward the failed engine.
- Roll. Loss of airflow causes a roll toward the failed engine.
3
Q
To generate the same amount of lift at a higher altitude, a airplane must do what?
A
Must be flown at either a higher angle of attack or a higher true airspeed.
3
Q
What is Centerline thrust?
A
An approach to correct for asymmetrical thrust, both engines are located along the centerline of the airplane so the failure of either engine causes no change in the direction of thrust.
4
Q
As the wing reaches a particular angle of attack, the airflow begins to decrease. you can usually feel airframe buffeting as the airflow begins to separate just before a stall. This angle is called what?
A
CLmax. (top of the curve at 19 degrees)
4
Q
This is the empty weight that consists of the airframe, engine(s), unusable fuel, and undrainable oil plus standard and optional equipment as specified in the equipment list. Some manufacturers used this term prior to GAMA standardization. What is it?
A
Licensed empty weight.
5
Q
What are the four common types of flaps and what do they do?
A
Flaps increase lift and reduce stall speed, allowing the wing tp produce the same lift at a lower airspeed. Conversely, raising the flaps increases stall speeds.
5
Q
What type of rating is a multi-engine and what are the requirements?
A
**Class rating** – multi-engine is a class of aircraft, so the requirements for adding a new class rating apply • Must have endorsement in logbook in the aeronautical knowledge area and operations. (FAR 61.63 c) • Pass the practical test
6
Q
The angle of attack directly controls what?
A
The distribution of pressures acting on a wing. By changing the angle of attack, you can control the airplane’s lift, airspeed, and drag.
6
Q
The small amount of fuel in the tanks that cannot be safely used in flight or drained on the ground. What is it?
A
Unusable fuel.
7
Q
When the angle of attack of a symmetrical airfoil is increased, what happens to the center of pressure?
A
The center of pressure remains unaffected.
7
Q
Flight simulators and flight training devices are used regularly in training for abnormal procedures, allowing you to rehearse actions to be taken when an engine or system fails. What is this called?
A
Abnormal procedures training (APT)
8
Q
What allows airflow to remain attaches over the outer portion of the wing after the roots have stalled?
A
Slots
8
Q
This is the weight of occupants, cargo, and baggage. Some POHs may refer to this as their total weight or gross weight. What is this called?
A
Payload
9
Q
What leading edge devise moves forward and down to create a path for air similar to a slot?
A
Slats
9
Q
Starting circuits for multi-engine airplanes installed on the drive-end of one or both magnetos on each engine. It performs two tasks to improve starting performance:
• Rotates the magneto at high speed to increase its spark intensity
• Delays ignition so it occurs at the optimum time
What are they?
A
Impulse coupling
10
Q
On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the what?
A
flightpath
10
Q
Standard empty weight plus the weight of optional and special equipment that have been installed is called what?
A
Basic empty weight
11
Q
The stalling speed of an airplane is most affected by
A
variations in airplane loading
11
Q
One or both magnetos on each engine have built-in starting components.This system generates a high-energy spark and delays ignition to improve starting performance. What is it??
A
Ignition vibrator system
12
Q
To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the
A
vertical component of lift
12
Q
The expendable fuel of the aircraft not including the fuel required to fill the lines or that which remains trapped in the tank sumps is called what?
A
Fuel load.
13
Q
In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become
A
four times greater
13
What are the lights that illuminate when the oil pressure becomes critically low?
Annunciator lights
14
Which is true regarding the use of flaps during level turns?
The raising of flaps increases the stall speed.
14
The weight of the pilot, copilot, passengers, baggage, fuel load, and drainable oil is called what?
Useful load
15
If the same angle of attack is maintained in ground effect as when out of ground effect, lift will
increase, and induced drag will decrease.
15
What happens when you **position the carburetor heat control to the ON position** if the induction system becomes obstructed due to ice or debris that are encountered in-flight on carbureted engines? This also works well if an air filter or inlet of a fuel-injected engine becomes obstructed.
An Alternate air source is created.
16
Airplane wing loading during a level coordinated turn in smooth air depends upon the
angle of bank.
16
What is the term used to describe a loaded airplane prior to engine start?
Ramp weight?
17
During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift
is momentarily increased.
17
What increases increases the amount of airflow through the cowlings of air-cooled engines?
Augmentor tubes or (cowl flaps)
18
Longitudinal dynamic instability in an airplane can be identified by
pitch oscillations becoming progressively steeper.
18
The aircraft weight that consists of the airframe, engines, and all items of operating equipment that have fixed locations and are permanently installed in the aircraft, including fixed ballast, hydraulic fluid, unusable fuel, and full engine oil is called what?
Standard empty weight
19
If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its
lateral axis.
19
What produces its own electrical power to drive the tachometers so that it will not be affected if the aircraft’s primary electrical system fails?
Tach-generator.
20
If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack
must be decreased or angle of bank increased.
20
What is the weight called after subtracting the fuel burned during engine start, runup, and taxi?
Takeoff weight
21
Longitudinal stability involves the motion of the airplane controlled by its
elevator.
21
What converts pressure and temperature measurements into electrical signals to power the respective instrument when normally it is read directly from either pressure or temperature lines that run from the engine to the instrument?
Transducers.
22
For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn
is constant and the stall speed increases.
22
Takeoff weight minus fuel burned is called what?
Landing weight.
23
As the angle of bank is increased, the vertical component of lift
decreases and the horizontal component of lift increases.
23
Control components that make up the electrical generating system and works with either the alternator or generator.
What ae Voltage regulators/circuit protection devices?
24
The angle of attack of a wing directly controls the
distribution of pressures acting on the wing.
24
This is the total weight of a loaded aircraft, and includes all fuel. It is greater than the takeoff weight due to the fuel that will be burned during the taxi and runup operations. This weight is also referred to as taxi weight. What is it called?
Maximum ramp weight
25
If an aircraft with a gross weight of 2,000 pounds was subjected to a 60° constant-altitude bank, the total load would be
4,000 pounds.
The load factor in a 60° bank is 2 Gs. Load Factor = G Load x Aircraft Weight. Therefore, 2,000 x 2 = 4,000 pounds.
25
Measures the amperage being produced by each alternator/indicates the percentage of load on the electrical system.
What are Ammeters/load meters?
26
In small airplanes, normal recovery from spins may become difficult if the
CG is too far rearward and rotation is around the CG.
26
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
?
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
27
To produce the same lift while in ground effect as when out of ground effect, the airplane requires
a lower angle of attack.
27
Powers the flight instruments and possibly some auxiliary systems such as wing de-ice boots and inflatable door seal. When either engine is operating, its vacuum pump automatically draws air through this system.
What is a Pneumatic pump?
28
In a rapid recovery from a dive, the effects of load factor would cause the stall speed to
increase.
28
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
?
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
29
A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the
wing root, with the stall progression toward the wing tip.
29
Supplies hydraulic pressure in most multi-engine aircrafts.
What are Engine driven hydraulic pumps?
30
What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?
Increase the angle of attack to compensate for the decreasing lift.
30
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
?
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
31
The angle of attack at which a wing stalls remains constant regardless of
weight, dynamic pressure, bank angle, or pitch attitude.
31
Maintains r.p.m on constant-speed propeller systems for multi-engines.
What are Governors?
32
An aircraft wing is designed to produce lift resulting from a difference in the
higher air pressure below the wing's surface and lower air pressure above the wing's surface.
32
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
?
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Landing weight
33
Which is true regarding the force of lift in steady, unaccelerated flight?
There is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude.
To maintain the lift and weight forces in balance, and to keep the airplane straight-and-level in a state of equilibrium, as velocity increases, angle of attack must be decreased. Conversely, as the airplane slows, the decreasing velocity requires the angle of attack be increased enough to create sufficient lift to maintain flight. Therefore, for every angle of attack, there is a corresponding indicated airspeed required to maintain altitude in steady, unaccelerated flight - all other factors being constant.
33
This applies force to the pitch-change piston to increase blade angles.
What are Counterweights and internal springs?
34
The need to slow an aircraft below V(A) is brought about by the following weather phenomenon:
Turbulence which causes an increase in stall speed.
34
BEW (basic empty weight)
+ ?
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Landing weight
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Landing weight
35
If the airspeed is increased from 90 knots to 135 knots during a level 60° banked turn, the load factor will
remain the same but the radius of turn will increase.
35
A force that tends to place the propeller in a low pitch position as the blade chordline tries to rotate parallel to the relative airflow created by the revolving propeller.
What is Aerodynamic twisting force?
36
During a takeoff made behind a departing large jet airplane, the pilot can minimize the hazard of wingtip vortices by
being airborne prior to reaching the jet's flightpath until able to turn clear of its wake.
Vortices begin to form when the jet rotates. Plan to be off the runway prior to reaching the jet's point of rotation, then fly above or turn away from the jet's flight path.
36
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- ?
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
?
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Landing weight
BEW (basic empty weight)
+ Payload
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Zero Fuel Weight
+ Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Ramp Weight
- Start/Taxi/Run-up
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Takeoff Weight
- Fuel
\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
Landing weight
37
While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will
decrease the rate of turn resulting in no change in load factor.
For any given angle of bank the rate of turn varies with the airspeed. In other words, if the angle of bank is held constant and the airspeed is increased, the rate of turn will decrease, or if the airspeed is decreased, the rate of turn will increase. Because of this, there is no change in centrifugal force for any given bank. Therefore, the load factor remains the same.
37
Limits the range of constant-speed operation for propellers.
What are Pitch-stops?
38
An airplane leaving ground effect will
experience an increase in induced drag and require more thrust.
As the wing encounters ground effect and is maintained at a constant lift coefficient, there is a reduction in the upwash, downwash, and wing-tip vortices. This causes a reduction in induced drag. While in ground effect, the airplane requires less thrust to maintain lift. It will also require a lower angle of attack. When an airplane leaves ground effect, there is an increase in drag which will require a higher angle of attack. Additional thrust will be required to compensate for the loss.
38
The maximum speed at which full, abrupt control movement can be used without overstressing the airframe is called what?
Maneuvering speed (VA)
39
What is the best indicator to the pilot of the load factor on the airplane?
How firmly the pilot is pressed into the seat during a maneuver.
Load factor can be detected by noting how firmly the pilot is pressed into the seat during a maneuver. If an aircraft is pulled up from a dive, subjecting the pilot to 3 Gs, he or she would be pressed down into the seat with a force equal to three times his or her weight.
39
A system that automatically adjust and syncs the propellers for you.
What are Synchronizers?
40
Which procedure should you follow to avoid wake turbulence if a large jet crosses your course from left to right approximately 1 mile ahead and at your altitude?
Make sure you are slightly above the path of the jet.
Fly above the jet's flight path whenever possible, because the vortices descend. Avoid flight below and behind a large aircraft's path.
40
A theoretical chord length that the CP moves along and from where the CP position is measured is called what?
Mean Aerodynamic Chord
41
To avoid possible wake turbulence from a large jet aircraft that has just landed prior to your takeoff, at which point on the runway should you plan to become airborne?
Past the point where the jet touched down.
Vortices cease to be generated when the aircraft lands. Plan to become airborne beyond this point.
41
Reduces cabin noise and vibration by shifting and maintaining the propeller’s rotational positions out of line with each other.
What is a Synchrophaser system?
42
To generate the same amount of lift as altitude is increased, an airplane must be flown at
a higher true airspeed for any given angle of attack.
In order to maintain its lift at a higher altitude, an airplane must fly at a greater true airspeed for any given angle of attack.
42
0% mean aerodynamic chord is called what?
Leading edge mean aerodynamic chord (LEMAC). It is defined by the manufacturer in terms of inches aft of the datum.
43
What performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? Maximum
range and maximum distance glide.
Maximum range condition would occur where the proportion between speed and power required is greatest. The maximum range condition (of propeller driven airplanes) is obtained at maximum lift-drag ratio (L/D(MAX)). The best angle of glide is one that allows the airplane to travel the greatest distance over the ground with the least loss of altitude. This is also the airplane's maximum L/D and is usually expressed as a ratio. This implies that the airplane should be flown at L/D(MAX) to obtain the greatest glide distance.
43
Helps reduce the strain on the starter motor and to increase the speed at which inflight restarts can be accomplished. These also causes the blades to unfeather without relying on engine oil pressure.
What are Unfeathering accumulators?
44
If an airplane category is listed as utility, it would mean that this airplane could be operated in which of the following maneuvers?
Limited acrobatics, including spins (if approved).
Utility category airplanes can do all normal category maneuvers plus limited acrobatics, including spins (if approved).
44
100% mean aerodynamic chord is called what?
Trailing edge mean aerodynamic chord (TEMAC). It is defined by the manufacturer in terms of inches aft of the datum.
45
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
four times greater than at the lower speed.
Lift is proportional to the square of the airplane's velocity. For example, an airplane traveling at 200 knots has four times the lift as the same airplane traveling at 100 knots, if the angle of attack and other factors remain constant.
45
Provides a means to connect multiple power generating sources. The individual aircraft electrical circuits are connected to these by way of fuses or circuit breakers, which are designed to deactivate the circuit in the event a short occurs.
What are Distribution buses?
46
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.
Neutral static stability is the initial tendency of the airplane to remain in the new condition after its equilibrium has been disturbed. When an airplane's attitude is momentarily displaced and it remains at the new attitude, it is displaying neutral longitudinal static stability. Longitudinal stability makes an airplane stable about its lateral axis (pitch).
46
This type of CG decreases stability and provides a slight increase in performance. It also increases the risks of stalls and may make recovery difficult, if not impossible. What is it?
An aft CG.
47
When landing behind a large aircraft, which procedure should be followed for vortex avoidance?
Stay above its final approach flightpath all the way to touchdown.
Stay at or above the large aircraft's final approach flight path. Note the touchdown point and land beyond it.
47
Allows the alternator output to reach the respective main bus. In this manner, the alternators carry the electrical loads and recharge the battery.
What are Alternator control units (ACU’s)?
48
By changing the angle of attack of a wing, the pilot can control the airplane's
lift, airspeed, and drag
48
This type of CG Increases stability because of the equilbrium between the forward CG and the forces produced by the tail. It also leads to higher stall speeds, higher takeoff speed and ground roll, reduced pitch authority, and in extreme cases, may not allow you to raise the nose on takeoff and landing flare. What is it?
A forward CG
49
To increase the rate of turn and at the same time decrease the radius, a pilot should
increase the bank and decrease airspeed
49
Reduces the parasite drag of a windmilling propeller and stops rotation of a damaged engine
What is Feathering?
50
Recovery from a stall in any airplane becomes more difficult when its
center of gravity moves aft.
50
This interconnect the two systems so an engine can be supplied with fuel from the opposite tanks.
What are cross-feed valves?
51
Which statement is true, regarding the opposing forces acting on an airplane in steady-state level flight?
These forces are equal.
51
Used to supply fuel pressure for starting or when the engine driven-pumps fail.
What are Auxiliary fuel pumps?
52
One of the main functions of flaps during the approach and landing is to
provide the same amount of lift at a slower airspeed.
52
Generally operated continuously to maintain fuel pressure to the engine-drive pumps and to supply fuel to the engine if the engine driven pump fails.
What are Boost pumps?
53
# Choose the correct statement regarding wake turbulence.
The primary hazard is loss of control because of induced roll.
53
May also be provided on some aircrafts to move fuel from one part of a fuel tank into another part in order to retain fuel near the tank’s outlet.
What are transfer pumps?
54
While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would
remain constant regardless of air density and the resultant lift vector.
54
Part of the electro-hydraulic landing gear system that houses a reservoir, pump, electric motor, and a series of check vales and regulators to control the system.
What is a hydraulic power-pack?
55
Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the
loss of the vertical component of lift.
55
This switch for each landing gear strut is ablo to shut the motor off when the gear reaches its travel limit and also activates the gear position indicator lights.
What is a limit switch?
56
The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flight is known as
load factor and directly affects stall speed.
56
This devise is installed to advise you of a potentially unsafe condition. In most cases, it also sounds if the selector switch is placed in the up position while the aircraft is on the ground. The main purpose of this devise, however, is to alert you to the fact that the gear is not in a safe position for landing.
What is landing gear warning horn?
57
Which is true regarding the forces acting on an aircraft in a steady-state descent? The sum of all
forward forces is equal to the sum of all rearward forces
57
This prevents the landing gear from retracting while the aircraft is on the ground. It is sometimes called the squat switch.
What is a landing gear safety switch?
58
A propeller rotating clockwise as seen from the rear, creates a spiraling slipstream. The spiraling slipstream, along with torque effect, tends to rotate the airplane to the
left around the vertical axis, and to the right around the longitudinal axis.
58
This system uses fuel from the aircraft system to support a flame within a combustion chamber. The combustion chamber is surrounded by a shroud that forms a cavity for ventilating air to pass through on its way to the cabin.
What is a combustion heater?
59
Which statement is true relative to changing angle of attack?
An increase in angle of attack will increase drag.
59
This system is used on most reciprocating-powered aircraft and can provide adequate oxygen up to an altitude of 25,000 feet. Above 17,000 feet, a tight mask seal must be maintained against your face.
What is a continuous-flow oxygen system ?
60
Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?
For a specific angle of bank and airspeed, the rate and radius of turn will not vary.
60
This system used on some turbo-prop and turbine-powered aircraft. This system increases the efficiency of basic continuous-flow equipment by conserving oxygen at lower altitudes and increasing the oxygen flow at higher altitudes. This system is required above 25,000 feet and incorporates a second regulator in the mask or hose assembly.
What is a diluter-demand oxygen system?
61
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 static stability
61
The cabin pressurization system found on many cabin-class twin-engine airplanes use \_\_\_\_\_\_\_from the compressor side of the turbine and directs it to the cabin.
Compressed turbocharger air.
62
A sweptwing airplane with weak static directional stability and increased dihedral causes an increase in
Dutch roll tendency
62
As the aircraft climbs through 8,000 feet, the pressurization system begins using this system to limit the amount of airflow that exists in the cabin. As this system begins to close, the cabin pressure increases to maintain an 8,000 feet cabin altitude as the aircraft climbs. At approximately 20,000 feet, the cabin pressure reaches the maximum differential pressure, and the cabin pressure altitude slowly begins to climb. The maximum differential pressure between the outside air and cabin air is normally in the 3.35 p.s.i to 4.5 p.s.i range.
What is an outflow valve?
63
As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane
increases because of increased induced drag.
63
This system advises you when the cabin altitude has exceeded a present level. Most systems are adjusted to actuate a warning light whenever the cabin altitude exceeds 12,500 feet.
What is a pressurization warning system?
64
Load factor is the lift generated by the wings of an aircraft at any given time
divided by the total weight of the aircraft.
64
What design feature of a fuel-injected engine prevents the engine from failing in the event the engine-driven fuel pump stops operating?
Fuel continues to flow to the engine by gravity
65
Stall speed is affected by
weight, load factor, and power.
65
While performing a magneto check on a multi-engine airplane equipped with toggle-type switches, the engine dies when you actuate the left magneto switch on the left engine. Which magneto is faulty?
The right magneto on the left engine
66
Which maximum range factor decreases as weight decreases?
Airspeed.
66
On a multi-engine airplane equipped with paddle-type ignition switches, the engine dies when you select the left position on the left engine ignition switch. Which magneto is faulty?
The left magneto on the left engine.
67
Lift on a wing is most properly defined as the
force acting perpendicular to the relative wind.
68
An airplane will stall at the same
angle of attack regardless of the attitude with relation to the horizon
69
What is the taper of the wing?
The ratio of the root chord to the tip chord
70
Dividing the wingspan by the average chord gives what?
The aspect ratio.
71
Parasite drag can be subdivided into what typs of drag?
Form drag, interference drag, and skin friction drag.
72
When airflow around one part of the airplane interacts with the airflow around an adjacent part is called what?
Interference drag.
73
What are the parts of this this Total drag chart?
74
What is L/DMAX?
The airspeed that gives the lowest total drag and provides the best power-off glide range,
75
What is the purpose of a spoiler?
It helps spoli the smooth airflow, reducing lift and increasing drag.
76
Load factor is defined as what?
The load the wings are supporting divided by the total weight of the airplane.
77
Name the areas of this V-G Diagram.
78
What are the three types of static stability?
**Positive static stability**—the initial tendency of the aircraft to return to the original state of equilibrium after being disturbed
**Neutral static stability**—the initial tendency of the aircraft to remain in a new condition after its equilibrium has been disturbed
**Negative static stability**—the initial tendency of the aircraft to continue away from the original state of equilibrium after being disturbed
79
initial tendency, or direction of movement, back to equilibrium when disturbed from a given AOA, slip, or bank is called what?
Static Stability
80
The aircraft response over time when disturbed from a given AOA, slip, or bank is called what?
Dynamic stability
81
What are the three types of Dynamic stability?
Positive dynamic stability—over time, the motion of the displaced object decreases in amplitude and, because it is positive, the object displaced returns toward the equilibrium state.
Neutral dynamic stability—once displaced, the displaced object neither decreases nor increases in amplitude. A worn automobile shock absorber exhibits this tendency.
Negative dynamic stability—over time, the motion of the displaced object increases and becomes more divergent
82
What is it called when the best rate of climb is zero and the airplane cannot climb any higher?
Absolute ceiling
83
The pressure altitude where the maximum rate of climb is 100 f.p.m is called what?
Service ceiling
84
The engine whose failure would result in the most adverse effects on the aircraft's handling and performance is called what?
Critical engine
85
A way to eliminate critical engine is to design airplanes with what?
Counterrotating propellers.
86
Below a certain airspeed, you cannot create enough force with the rudder to prevent the airplane from continuing its travel toward the inoperative engine. This airspeed is referred to as what?
Minimum control airspeed (VMC)
87
The ratio between the lift generated by the wings at any given time divided by the total weight of the airplane is called what?
Load Factor
88
Commercial Flight Theory
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