Performance & Limitations Flashcards

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1
Q

What are the four dynamic forces that act on an airplane during all maneuvers?

A

Lift: The upward acting force

Gravity: Or weight, the downward acting force

Thrust: The forward acting force

Drag: The backward acting force

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2
Q

What flight condition will result in the sum of the opposing forces being equal?

A

In steady-state, straight-and-level, unaccelerated flight, the sum of the opposing forces is equal to zero. There can be no unbalanced forces in stead, straight flight (Newton’s Third Law). This is true whether flying level or when climbing or descending. It does not mean the four forces are equal - it means the opposing forces are equal to, and thereby cancel the effects of each other.

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3
Q

What is an airfoil?

A

An airfoil is a device which gets a useful reaction from air moving over its surface, namely lift. Wings, horizontal tail surfaces, vertical tail surfaces, and propellers are examples of airfoils.

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4
Q

What is the angle of incidence?

A

The angle formed by the longitudinal axis of the airplane and the chord of the wing. It is measured by the angle at which the wing is attached to the fuselage. The angle of incidence is fixed and cannot be changed by the pilot.

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5
Q

What is a relative wind?

A

The direction of the airflow with respect to the wing. When a wing is moving forward and downward the relative wind moves backward and upward. The flight path and relative wind are always parallel, but travel in opposite directions.

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6
Q

What is the angle of attack?

A

The angle between the wing chord line and the direction of the relative wind. This can be changed by the pilot.

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7
Q

What is Bernoulli’s Principle?

A

The pressure of a fluid (liquid or gas) decreases at points where the speed of the fluid increases. In the case of airflow, high speed flow is associated with low pressure and low speed flow with high pressure. The airfoil of an aircraft is designed to increase the velocity of the airflow above its surface, thereby decreasing pressure above the airfoil. Simultaneously, the impact of the air on the lower surface of the airfoil increases the pressure below. This combination of pressure decrease above and increase below produces lift.

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8
Q

What are several factors that will affect both lift and drag?

A

Wing area: Lift and drag acting on a wing are roughly proportional to the wing area. A pilot can change wing area by using flaps.

Shape of the airfoil: As the upper curvature of an airfoil is increased (up to a certain point), the lift produced increases. Lowering an aileron or flap can accomplish this. Also, ice or frost on a wing can disturb normal airflow, changing its camber, and disrupting its lifting capability.

Angle of attack: As angle of attack is increased, both lift and drag are increased, up to a certain point.

Velocity of the air: An increase in velocity of air passing over the wing increases lift and drag.

Air density: Lift and drag vary directly with the density of the air. As air density increases, lift and drag increase. As air density decreases, lift and drag decrease. Air density is affected by these factors - pressure, temperature, and humidity.

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9
Q

What is torque effect?
(One of the left turning tendencies.)

A

Torque effect involves Newton’s Third Law of Physics - for every action, there is an equal and opposite reaction. Applied to the airplane, this means that as the internal engine parts and the propeller are revolving in one direction, an equal force is trying to rotate the airplane in the opposite direction. It is greatest when at low air speeds with high power settings and a high angle of attack.

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10
Q

What effect does torque reaction have on an airplane on the ground and in flight?

A

In flight: Torque reaction is acting around the longitudinal axis, tending to make the airplane roll. To compensate, some of the older airplanes are rigged in a manner to create more lift on the wing that is being forced downward. The more modern airplanes are designed with the engine offset to counteract this effect of torque.

On the ground: During takeoff roll, an additional turning moment around the vertical axis is induced by torque reaction. As the left side of the airplane is being forced down by torque reaction, more weight is being placed on the left main landing gear. This results in more ground friction, or drag, on the left tire than on the right, causing a further turning moment to the left.

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11
Q

What are the four turning tendencies?

A

Torque reaction to the engine and propeller: For every action there is an equal and opposite reaction. The rotation of the propeller (from the cockpit) to the right, tends to roll or bank the airplane to the left.

Gyroscopic effect of the propeller: Gyroscopic precession applies here - the resultant action or deflection of a spinning object when a force is applied to the outer rim of its rotational mass. If the axis of a propeller is tilted, the resulting force will be exerted 90 degrees ahead in the direction of rotation and in the same direction as the applied force. It is most noticeable on takeoffs in taildraggers when the tail is raised.

Spiraling slipstream: High-speed rotation of an airplane propeller results in a corkscrewing rotation to the slipstream as it moves rearward. At high propeller speeds and low forward speeds (takeoff), the slipstream strikes the vertical tail surface on the left side pushing the tail to the right and yawing the airplane to the left.

Asymmetrical loading of the propeller (P-factor): When an airplane is flying with a high angle of attack, the bite of the downward moving propeller blade is greater than the bite of the upward moving blade. This is due to the downward moving blade meeting the oncoming relative wind at a greater angle of attack than the upward moving blade. Consequently, there is greater thrust on the downward moving blade on the right side, and this forces the airplane to yaw to the left.

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12
Q

What is centrifugal force?

A

The equal and opposite reaction of the airplane to the change in direction, and it acts equal and opposite to the horizontal component of lift.

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13
Q

What is load factor?

A

The ratio of the total load supported by the airplane’s wing to the actual weight of the airplane and its contents. The actual load supported by the wings divided by the total weight of the airplane. It can also be expressed as the ration of a given load to the pull of gravity; i.e., to refer to a load factor of three as “3 Gs”. In this case the weight of the airplane is equal to 1G, and if a load of three times the actual weight of the airplane were imposed upon the wing due to curved flight, the load factor would be equal to 3 Gs.

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14
Q

For what two reasons is load factor important to pilots?

A

1) Because of the dangerous overload that it is possible for a pilot to impose on the aircraft structure.

2) Because an increased load factor increases the stalling speed and makes stalls possible at seemingly safe flight speeds.

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15
Q

What situations may result in load factors reaching the maximum or being exceeded?

A

Level turns: The load factor increases at a terrific rate after a bank has reached 45 or 50 degrees. The load factor in a 60 degree bank turn is 2 Gs. The load factor in a 80 degree bank turn is 5.76 Gs. The wing must produce lift equal to these load factors if altitude is to be maintained.

Turbulence: Severe vertical gusts cause a sudden increase in angle of attack, resulting in large loads which are resisted by the inertia of the airplane.

Speed: The amount of excess load that can be imposed upon the wing depends on how fast the airplane is flying. At speeds below maneuvering speed, the airplane will stall before the load factor can become excessive. At speeds above maneuvering speed, the limit load factor for which an airplane is stressed can be exceeded by abrupt or excessive application of the controls or by strong turbulence.

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16
Q

What are the different operational categories for aircraft and within which category does your aircraft fall?

A

The maximum safe load factors (limit load factors) specified for airplanes are as follows:

1) Normal - +3.8 to -1.52
2) Utility (mild aerobatics including spins) - +4.4 to -1.76
3) Aerobatic - +6.0 to -3.00

The 172 falls in the normal category

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17
Q

What effect does an increase in load factor have on stalling speed?

A

As load factor increases, stalling speed increases. Any airplane can be stalled at any airspeed within the limits of its structure and the strength of the pilot. At a given airspeed, the load factor increases as angle of attack increases, and the wing stalls because the angle of attack has been increased to a certain angle. Therefore, there is a direct relationship between the load factor imposed upon the wing and its stalling characteristics. A rule for determining the speed at which a wing will stall is that the stalling speed increases in proportion to the square root of the load factor.

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18
Q

Define the term maneuvering speed.

A

The maximum speed at which the limit load can be imposed (either by gusts or full deflection of the control surfaces) without causing structural damage.

The speed at which abrupt control changes can be made and the plane will stall before it breaks.

It is the speed below which you can, in smooth air, move a single flight control one time, to its full deflection, for one axis of airplane rotation only (pitch, roll, or yaw) without risk of damage to the airplane. Speeds up to, but not exceeding the maneuvering speed allow an aircraft to stall prior to experiencing an increase in load factor that would exceed the limit load of the aircraft.

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19
Q

Discuss the effect on maneuvering speed of an increase or decrease in weight.

A

Maneuvering speed increases with an increase in weight and decreases with a decrease in weight. An aircraft operating at a reduced weight is more vulnerable to rapid accelerations encountered during flight through turbulence or gusts. Design limit load factors could be exceeded if a reduction in maneuvering speed is not accomplished. An aircraft operating at or near gross weight in turbulent air is much less likely to exceed design limit load factors and may be operated at the published maneuvering speed for gross weight if necessary.

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20
Q

Define loss-of-control-inflight (LOC-I) and describe several situations that might increase the risk of an LOC-I accident occurring.

A

LOC-I is a significant deviation of an aircraft from the intended flight path and it often results from an airplane upset. Maneuvering is the most common phase of flight for LOC-I accidents to occur; however, LOC-I accidents occur in all phases of flight. Situations that increase the risk of this include uncoordinated flight, equipment malfunctions, pilot complacency, distraction, turbulence, and poor risk management such as attempting to fly in IMC when the pilot is not qualified or proficient in it.

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21
Q

What causes an airplane to stall?

A

Exceeding the critical angle of attack. Every airplane has a specific angle of attack where the airflow separates from the upper surface of the wing and the stall occurs. Each airplane has only one specific angle of attack where the stall occurs, regardless of airspeed, weight, load factor, or density altitude.

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22
Q

What is a spin?

A

A controlled (recoverable) or uncontrolled (possibly unrecoverable) maneuver in which the airplane descends in a helical path while flying at an angle of attack greater than the critical angle of attack. Spins result from aggravated stalls in either a slip or a skid. If a stall does not occur, a spin cannot occur.

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23
Q

What causes a spin?

A

The primary cause of an inadvertent spin is exceeding the critical angle of attack while applying excessive or insufficient rudder, and to a lesser extent, aileron.

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24
Q

When are spins most likely to occur?

A

A stall or spin can occur in any phase of flight, but is most likely to occur in the following situations:

1) Engine failure on takeoff during climbout: The pilot tries to stretch glide to landing area by increasing back pressure or makes an uncoordinated turn back to departure runway at a relatively low airspeed.

2) Crossed-control turn from base to final (slipping or skidding turn): The pilot overshoots final and makes uncoordinated turn at a low airspeed.

3) Engine failure on approach to landing: The pilot tries to stretch glide to runway by increasing back pressure.

4) Go-around with full nose-up trim: The pilot applies power with full flaps and nose-up trim combined with uncoordinated use of rudder.

5) Go-around with improper flap retraction: The pilot applies power and retracts flaps rapidly resulting in a rapid sink rate followed by an instinctive increase in back pressure.

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25
Q

What procedure should be used to recover from an inadvertent spin?

A

1) Close the throttle
2) Neutralize the ailerons
3) Apply full opposite rudder
4) Briskly move the elevator control forward to approximately the neutral position
5) Once the stall is broken the spinning will stop. Neutralize the rudder when the spinning stops.
6) When the rudder is neutralized, gradually apply enough aft elevator pressure to return to level flight.

Remember PARE
Power - reduce to idle
Ailerons - position to neutral
Rudder - apply full opposite against rotation
Elevator - apply positive, forward of neutral, movement to break stall

Once the spin rotation stops, neutralize the rudder and begin applying back pressure to return to level flight.

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26
Q

What causes adverse yaw?

A

When turning an airplane to the left (for example), the downward deflected aileron on the right produces more lift on the right wing. Since the downward deflected right aileron produces more lift, it also produces more drag, while the opposite left aileron has less lift and less drag. This added drag attempts to pull or veer the airplane’s nose in the direction of the raised wing; that is, it tries to turn the plane in the direction opposite to that desired. This undesired veering is referred to as adverse yaw.

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27
Q

What is ground effect?

A

A condition of improved performance the airplane experiences when it is operating near the ground. A change occurs in the three-dimensional flow pattern around the airplane because the airflow around the wing is restricted by the ground surface. This reduces the wing’s upwash, downwash, and wingtip vortices. In order for ground effect to be of a significant magnitude, the wing must be quite close to the ground.

When the plane is close to the ground (one wing length above or closer) wingtip vortices get cut off by the ground, so they can’t fully develop and instead dissipate against the ground. The reduction in vortices causes a reduction in downwash (when wind comes off the wing, it angles down to the ground). The reduction in vortices and downwash cause a reduction in induced drag, which causes improved performance.

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28
Q

What major problems can be caused by ground effect?

A

During landing: At a height of approximately one-tenth of a wing span above the surface, drag may be 40% less than when the airplane is operating out of ground effect. Therefore, any excess speed during the landing phase may result in a significant float distance. In this case, the pilot may run out of runway and options for landing.

During takeoff: Due to the reduced drag in ground effect, the aircraft may seem capable of takeoff well below the recommended speed. However, as the airplane rises out of ground effect with a deficiency of speed, the greater induced drag may result in very marginal climb performance, or the inability of the airplane to fly at all. In extreme conditions, such as high temperature, high gross weight, and high-density altitude, the airplane may become airborne initially with a deficiency of speed and then settle back to the runway.

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29
Q

Define empty weight.

A

The weight of the airframe, engines, all permanently installed equipment, and unusable fuel. Depending on the FARs under which the aircraft was certificated, either the undrainable oil or full reservoir of oil is included.

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30
Q

Define gross weight.

A

The maximum allowable weight of both the airplane and its contents.

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31
Q

Define useful load.

A

The weight of the pilot, copilot, passengers, baggage, usable fuel and drainable oil.

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32
Q

Define arm.

A

The horizontal distance, in inches, from the reference datum line to the center of gravity of the item.

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33
Q

Define moment.

A

The product of the weight of an item multiplied by its arm. Moments are expressed in pound-inches.

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34
Q

Define center of gravity.

A

The point about which an aircraft would balance if it were possible to suspend it at that point. Expressed in inches from datum.

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35
Q

Define datum.

A

An imaginary vertical plane or line from which all measurements of arm are taken. Established by the manufacturer.

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36
Q

What basic equation is used in all weight and balance problems to find the center of gravity location of an airplane and/or its components?

A

Weight x Arm = Moment

Weight = Moment/Arm

Arm (CG) = Total Moment/Total Weight

Remember WAM (Weight x Arm = Moment)

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37
Q

What performance characteristics will be adversely affected when an aircraft has been overloaded?

A

1) Higher takeoff speed
2) Longer takeoff run
3) Reduced rate and angle of climb
4) Lower maximum altitude
5) Shorter range
6) Reduced cruising speed
7) Reduced maneuverability
8) Higher stalling speed
9) Higher landing speed
10) Longer landing roll
11) Excessive weight on the nosewheel

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38
Q

What effect does a forward center of gravity have on an aircraft’s flight characteristics?

A

Higher stall speed - Stalling angle of attack is reached at a higher speed due to increased wing loading

Slower cruise speed - Increased drag; greater angle of attack is required to maintain altitude.

More stable - The center of gravity is farther forward from the center of pressure which increases longitudinal stability.

Greater back elevator pressure required - Longer takeoff roll; higher approach speeds, problems with landing flare, possible to land on nose wheel, possible to prop strike, possible to porpoise down the runway.

Higher induced drag.

Higher AOA.

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39
Q

What effect does a rearward center of gravity have on an aircraft’s flight characteristics?

A

Lower stall speed - Less wing loading.

Higher cruise speed - Reduced drag; smaller angle of attack is required to maintain altitude.

Less stable - Stall and spin recovery more difficult; the center of gravity is closer to the center of pressure, causing longitudinal instability.

Possible to balloon out of ground effect when landing. Landing on back wheels. Could float more when landing.

Easier rollout on takeoff.

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40
Q

What are the standard weights assumed for the following when calculating weight and balance?

Gas
Oil
Water

A

Gas - 6 pounds/gallon

Oil - 7.5 pounds/gallon

Water - 8.35 pounds/gallon

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41
Q

The rental aircraft you normally fly has just returned from the avionics shop with newer, lighter-weight avionics. When reviewing the aircraft weight and balance record, you don’t see an A&P entry reflecting this change. Is this normal? Why?

A

No. Changes of fixed equipment may have a major effect upon the weight of the aircraft. Many aircraft are overloaded by the installation of extra radios or instruments. Fortunately, the replacement of older, heavy electronic equipment with newer, lighter types results in a weight reduction. This weight change, however helpful, can cause the CG to shift, which must be computer and annotated in the weight and balance record. It’s the responsibility of the A&P mechanic or technician making any repair or alteration to know the weight and location of these changes, and to compute the CG and record the new empty weight and empty weight center of gravity in the aircraft weight and balance record.

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42
Q

What are some of the main elements of aircraft performance?

A

1) Takeoff and landing distance
2) Rate of climb
3) Ceiling
4) Payload
5) Range
6) Speed
7) Fuel economy
8) Maneuverability
9) Stability

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43
Q

What factors affect the performance of an aircraft during takeoffs and landings?

A

1) Air density (density altitude)
2) Surface wind
3) Runway surface
4) Upslope or downslope of runway
5) Weight

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44
Q

What effect does wind have on aircraft performance?

A

Takeoff - The effect of a headwind is to allow the aircraft to reach the lift-off speed at a lower ground speed, which will increase airplane performance by shortening the takeoff distance and increasing the angle of climb. The effect of a tailwind is the aircraft needs to achieve greater ground speed to get to lift-off speed. This decreases aircraft performance by increasing takeoff distance and reducing the angle of climb.

Landing - The effect of wind on landing distance is identical to its effect on takeoff distance. A headwind will lower ground speed and increase airplane performance by steepening the approach angle and reducing the landing distance. A tailwind will increase ground speed and decrease performance, by decreasing the approach angle and increasing the landing distance.

Cruise flight - Winds aloft have somewhat an opposite effect on airplane performance. A headwind will decrease performance by reducing ground speed, which in turn increases the fuel requirement for the flight. A tailwind will increase performance by increasing the ground speed, which in turn reduces the fuel requirement for the flight.

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45
Q

How does weight affect takeoff and landing performance?

A

Increased gross weight can have a significant effect on takeoff performance:

1) Higher liftoff speed
2) Greater mass to accelerate (slow acceleration)
3) Increased retarding force (drag and ground friction)
4) Longer takeoff distance

The effect of gross weight on landing distance is that the airplane will require a greater speed to support the airplane at the landing angle of attack and lift coefficient resulting in an increased landing distance.

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46
Q

What effect does an increase in density altitude have on takeoff and landing performance?

A

An increase in density altitude results in:

1) Increased takeoff distance (greater takeoff TAS required)
2) Reduced rate of climb (decreased thrust and reduced acceleration)
3) Increased true airspeed on approach and landing (same IAS)
4) Increased landing roll distance

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47
Q

Define density altitude.

A

Pressure altitude corrected for nonstandard temperature. Under standard atmospheric condition, air at each level in the atmosphere has a specific density, and under standard conditions, pressure altitude and density altitude identify the same level. Therefore, density altitude is the vertical distance above sea level in the standard atmosphere at which a given density is found.

The altitude that the plane thinks it’s at.

48
Q

How does air density affect aircraft performance?

A

Density of the air has a direct effect on:

1) Lift produced by the wings
2) Power output of the engine
3) Propeller efficiency
4) Drag forces

49
Q

What factors affect air density?

A

Altitude - The higher the altitude, the less dense the air.

Temperature - The warmer the air, the less dense it is.

Humidity - More humid air is less dense.

50
Q

How does temperature, altitude, and humidity affect density altitude?

A

1) Density altitude will increase (low air density) when one or more of the following occurs:
a) High air temperature
b) High altitude
c) High humidity

2) Density altitude will decrease (high air density) when one or more of the following occurs:
a) Low air temperature
b) Low altitude
c) Low humidity

51
Q

What is Vso? What is Vso for the airplane?

A

Stall speed in landing configuration; the calibrated power-off stalling speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration.

For 1UK, Vso is 49 kts

52
Q

What is Vsi? What is Vsi for the airplane?

A

Stall speed clean or in a specified configuration; the calibrated power-off stalling speed or the minimum steady flight speed at which the airplane is controllable in a specified configuration.

For 1UK, Vsi is 55 kts

53
Q

What is Vy? What is Vy in the airplane?

A

Best rate-of-climb speed; the calibrated airspeed at which the airplane will obtain the maximum increase in altitude per unit of time. This best rate-of-climb speed normally decreases slightly with altitude.

For the 172, Vy is 75 kts

54
Q

What is Vx? What is Vx for the airplane?

A

Best angle-of-climb speed; the calibrated airspeed at which the airplane will obtain the highest altitude in a given horizontal distance. This best angle-of-climb speed normally increases with altitude.

For the 172, Vx is 59 kts

55
Q

What is Vle?

A

Maximum landing gear extension speed; the maximum calibrated airspeed at which the airplane can be safely flown with the landing gear extended. This is a problem involving stability and controllability.

56
Q

What is Vlo? What is Vlo for the airplane?

A

Maximum landing gear operating speed; the maximum calibrated airspeed at which the landing gear can be safely extended or retracted. This is a problem involving the airloads imposed on the operating mechanism during extension or retraction of the gear.

Vlo does not apply to the 172 because the landing gear does not retract.

57
Q

What is Vfe? What is Vfe in the airplane?

A

Maximum flap extension speed; the highest calibrated airspeed permissible with the wing flaps in a prescribed extended position. This is a problem involving the airloads imposed on the structure of the flaps.

In the 172, Vfe is 85 kts

58
Q

What is Va? What is Va in the airplane?

A

Maneuvering speed; the calibrated design maneuvering airspeed. This is the maximum speed at which the limit load can be imposed (either by gusts or full deflection of the control surfaces) without causing structural damage.

In the 172, Va is:
2300 lbs - 97 kts
1950 lbs - 89 kts
1600 lbs - 80 kts

59
Q

What is Vno? What is Vno in the airplane?

A

Normal operating speed; the maximum calibrated airspeed for normal operation or the maximum structural cruise speed. This is the speed above which exceeding the limit load factor may cause permanent deformation of the airplane structure.

In 1UK, Vno is 125 kts

60
Q

What is Vne? What is Vne in the airplane?

A

Never exceed speed; the calibrated airspeed which should never be exceeded. If flight is attempted above this speed, structural damage or structural failure may result.

In 1UK, Vne is 154 kts

61
Q

How many miles can you glide in your aircraft per 1,000 feet of altitude lost?

A

1.5 NM per 1,000 feet of altitude lost above ground level.

62
Q

What information can you get from takeoff charts?

A

These allow you to compute the takeoff distance of the airplane with no flaps or with a specific flap configuration. You can also compute distances for a no flap takeoff over a 50-foot obstacle scenario as well as with flaps over a 50-foot obstacle. The takeoff distance chart provides for various airplane weights, altitudes, temperature, winds, and obstacle heights.

63
Q

What information can you get from a fuel, time, and distance-to-climb chart?

A

This chart will give the fuel amount used during the climb, the time it will take to accomplish the climb, and the ground distance that will be covered during the climb. To use this chart, obtain the information for the departing airport and for the cruise altitude.

64
Q

What information can you get from cruise and range performance charts?

A

This is designed to give true airspeed, fuel consumption, endurance in hours, and range in miles at specific cruise configurations.

65
Q

What information can you get from crosswind and headwind component charts?

A

This allows for figuring the headwind and crosswind component for any given wind direction and velocity.

66
Q

What information can you get from landing charts?

A

These provide normal landing distance as well as landing distance over a 50-foot obstacle.

67
Q

What information can you get from stall speed performance charts?

A

These are designed to give an understanding of the speed at which the airplane will stall in a given configuration. Will typically take into account the angle of bank, the position of the gear laps, and the throttle position.

68
Q

Define the term pressure altitude, and state why it’s important.

A

The altitude indicated when the altimeter setting window (barometric scale) is adjusted to 29.92. This is the altitude above the standard datum plane, a theoretical plane where air pressure (corrected to 15 degrees C) equals 29.92 in. Hg.

Pressure corrected from a standard day.

Pressure altitude is used to compute density altitude, true altitude, true airspeed, and other performance data.

69
Q

What engine-out glide speed will give the best maximum range in the 172?

A

65 knots

70
Q

What is the make and horsepower of the engine in 1UK?

A

Normally aspirated carbureted Lycoming O-360
Air cooled engine
Carburetor instead of fuel injected
360 cubic inches of displacement
Opposite opposed pistons
180 horsepower

71
Q

How many useable gallons of fuel can you carry in the 172?

A

38 gallons

72
Q

Where are the fuel tanks located, and what are their capacities, in the 172?

A

The fuel tanks are located in the wings of the plane and they can hold 42 gallons of fuel.

73
Q

Where are the fuel vents for the 172?

A
74
Q

What is the octane rating of the fuel used in the 172?

A

100LL

75
Q

Where are the fuel sumps located on the 172? When should you drain them?

A

The fuel sumps can be found under each wing (one per wing), above the pilot’s and passenger’s doors.

They should be drained…

76
Q

What are the minimum and maximum oil capacities for the 172?

A

Total - 8 qts

77
Q

What weight of oil is used in the 172?

A

Multi-viscosity with a range of SAE 10W30

78
Q

What is the maximum oil temperature and pressure in the 172?

A
79
Q

Is the landing gear in the 172 fixed, manual, hydraulic, or electric?

A

Fixed

80
Q

What are the nosewheel turning limitations for the 172?

A
81
Q

What is the maximum allowable/demonstrated crosswind component for 1UK?

A

17 kts

82
Q

How many people will this aircraft carry safely with a full fuel load?

A
83
Q

What is the maximum allowable weight the aircraft can carry with baggage in the baggage compartment?

A
84
Q

What takeoff distance is required if a takeoff were made from a sea-level pressure altitude?

A
85
Q

What is your maximum allowable useful load?

A
86
Q

Solve a weight and balance problem for the flight you plan to make with one passenger at 170 pounds.

a) Does your load fall within the weight and balance envelope?

b) What is the final gross weight?

c) How much fuel can be carried?

d) How much baggage can be carried with full fuel?

A
87
Q

What are the functions of the antennae on the 172?

A
88
Q

You have just landed on a 2,100-foot grass strip to pick up two passengers and you plan to depart in the early afternoon. The temperature will be warmer than expected, so you compute the density altitude and determine that the required takeoff distance over a 50-foot obstacle will be 2,000 feet. Your weight and balance calculation indicates you will be 100 pounds under gross weight. If you decide to takeoff, explain the potential hazards, the overall risk, and the actions you could take to mitigate that risk.

A
89
Q

Why are some aircraft not allowed to perform forward slips with flaps extended?

A
90
Q

While enroute, will the CG change as your aircraft uses fuel?

A
91
Q

What causes an airplane to pitch nosedown when power is reduced and controls are not adjusted?

A
92
Q

Will the indicated airspeed at which an aircraft stalls change as altitude is increased?

A
93
Q

How does an aircraft’s limitations (performance, fuel capacity, navigation capability) affect the total risk of a flight? What can a pilot do to mitigate that risk?

A
94
Q

What force causes an airplane to turn?

A
95
Q

The amount of excess load that can be imposed on the structure of an airplane is dependent on what factor?

A
96
Q

Define the terms ‘service ceiling’ and ‘absolute ceiling’. What are their values for the 172?

A
97
Q

The performance chart numbers for your aircraft are based on test flights conducted in a new aircraft. During preflight planning, how can a pilot minimize risk when using the charts to make performance calculations for takeoff, enroute cruise, and landing?

A
98
Q

You’re planning a VFR departure from Durango, Colorado (KDRO), which is at an elevation of 6,689 feet MSL, in a 172. Explain the potential hazards that exist when departing KDRO as compared to departing KLAX, which is at an elevation of 127 feet MSL. Is there anything you can do to mitigate the risk?

A
99
Q

What is Vapp?

A

Approach speed
65 kts
X1.3 Vso

100
Q

What is Vr?

A

Rotation speed
55 kts

101
Q

What kind of planes do pilots need type ratings to fly?

A

Planes that weigh over 12,500 pounds and planes that have turbo jets.

102
Q

What determines a plane’s crosswind limits?

A

The size of the rudder

103
Q

If you fly from a high pressure system to a low pressure system without changing the altimeter, what will the altimeter indicate?

A

The aircraft will be at a lower altitude than what is being indicated.

High to low, look out below.

104
Q

What happens when you fly from an area of low pressure to an area of high pressure without changing the altimeter?

A

The plane will be at a higher altitude than what is being indicated.

105
Q

When do we have our greatest lift?

A

Right before a stall

106
Q

How is a plane designed to stall?

A

From wing root to tip, so the aileron can still have some control over the plane

107
Q

What is parasite drag?

A

Drag caused by parts of the airplane (wings, antenna, etc.)

108
Q

What is induced drag?

A

The byproduct of lift

109
Q

Best glide speed is the point where parasite and induced drag are at their lowest. Best endurance speed is when power and speed are working best - no excess power is being used.

A
110
Q

Define the following airspeeds:
Indicated
Calibrated
True
Ground

A

Indicated airspeed - what you’re reading on the airspeed indicator

Calibrated airspeed - indicated airspeed corrected for installation and instrument error

True airspeed - calibrated airspeed corrected for temperature and pressure

Ground speed - corrected for wind

111
Q

What is a complex aircraft?

A

An airplane with a constant speed propeller, retractable gear, and flaps.

An endorsement is needed to fly.

112
Q

What is a high performance aircraft?

A

A plane with an engine over 200 horsepower

113
Q

What is a high altitude airplane?

A

An airplane that can fly over 25,000 feet altitude.

Need an endorsement to fly.

114
Q

When is supplemental oxygen needed while flying?

A

When at 12,500 - 14,000 for 30 minutes or more, required crew must have supplemental oxygen.

When at 14,000 - 14,999, required crew must wear supplemental oxygen regardless of duration of flight

When at 15,000+, passengers must be offered supplemental oxygen, but they’re not required to use it

115
Q

What type of flaps does 1UK have?

A

Plain flaps