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POF EXAM PREP CMPLT

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POF EXAM PREP CMPLT
tsampikos pompou
Quiz by tsampikos pompou, updated more than 1 year ago
tsampikos pompou
Created by tsampikos pompou over 8 years ago
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Resource summary

Question 1

Question
1 2On a standard atmosfaire the conditions at sea level are]
Answer
  • O 15 C, 1013,2 Mb
  • O 0 C, 29,92 Mb
  • O 15 C, 29,92 Mb
  • O 0 C, 1013,2 Mb

Question 2

Question
2 As the altitude increases the air density...
Answer
  • O decreases
  • O increases
  • O remains constant

Question 3

Question
3 As the altitude increases the air pressure...
Answer
  • O decreases
  • O increases
  • O remains constant
  • O depends on the day

Question 4

Question
4 Weel fairings on airgraft's landing gear decreases...
Answer
  • O interferance drag
  • O form drag
  • O induced drag

Question 5

Question
5 laminar flow boundary layer compared to turbulent boundary layer is...
Answer
  • O thinner]
  • O thikker
  • O having the same thickness

Question 6

Question
6 Figure POF01. Line a is called
Answer
  • O Chord Line
  • O Leading Edge
  • O Trailing Edge
  • O Mean Camber Line

Question 7

Question
7 Figure POF01. Line (c) is called
Answer
  • O Mean Camber Line
  • O Chord Line
  • O Leading Edge
  • O Trailing Edge

Question 8

Question
8 Figure POF02. Line (4) is called
Answer
  • O Maximum Airfoil Thickness
  • O Chord Line
  • O Leading Edge
  • O Trailing Edge

Question 9

Question
9 Figure POF01. Point (a) is called
Answer
  • O Leading Edge
  • O Mean Camber Line
  • O Chord Line
  • O Trailing Edge

Question 10

Question
10 Figure POF01. Point (e) is called
Answer
  • O Trailing Edge
  • O Leading Edge
  • O Mean Camber Line
  • O Chord Line

Question 11

Question
11 Figure POF03. Angle (a) is called
Answer
  • O sweepback
  • O angle of attack
  • O angle of incidence

Question 12

Question
12 When an aircraft is decelarating in a straight and level flight the induced drag...
Answer
  • O increases
  • O decreases
  • O remains the same

Question 13

Question
13 When an aircraft is decelarating in a straight and level flight the parasite drag...
Answer
  • O decreases
  • O increases
  • O remains the same

Question 14

Question
14 The lowest drag during straight and level flight is achieved...
Answer
  • O At a spesific angle of attack
  • O At a spesific speed
  • O At the stall speed
  • O At Vne

Question 15

Question
15 In a stable aircraft during straight and level flight the horizonta stabilizer produces lift...
Answer
  • O downwards
  • O upwards
  • O equal to zero

Question 16

Question
16 It is more possible for a pilot to have a tail strike during landing when landing with flaps up
Answer
  • O True
  • O False

Question 17

Question
17 An aircraft has a stalling speed of 55 kts, in straight and level flight with no power. With a higher weight the stalling speed will
Answer
  • O increase
  • O decrease
  • O reamain the same

Question 18

Question
18 An aircraft has a stalling speed of 55 kts, in straight and level flight with no power. With a higher engine output the stalling speed will
Answer
  • O decrease
  • O increase
  • O reamain the same

Question 19

Question
19 During an airplane's steady climb, lift is less than weight
Answer
  • O True
  • O False

Question 20

Question
20 We can decrease trim drag by...
Answer
  • O moving th CG as aft as permitable
  • O moving th CG as forward as permitable
  • O increasinvg the flight speed
  • O decreasing the flight speed

Question 21

Question
21 Figure POF04. The flaps type that coresponde with the letter (a) are called...
Answer
  • O Simple
  • O Split
  • O Slotted
  • O Fowler

Question 22

Question
22 Figure POF04. The flaps type that coresponde with the letter (b) are called...
Answer
  • O Split
  • O Simple
  • O Slotted
  • O Fowler

Question 23

Question
23 Figure POF04. The flaps type that coresponde with the letter (c) are called...
Answer
  • O Fowler
  • O Simple
  • O Split
  • O Slotted

Question 24

Question
24 Figure POF04. The flaps type that coresponde with the letter (d) are called...
Answer
  • O Slotted
  • O Simple
  • O Split
  • O Fowler

Question 25

Question
25 An airplane has a maximum maneuvering speed of 85 kts, in a given weight. With a higher weight the maximum maneuvering speed will
Answer
  • O increase
  • O decrease
  • O reamain the same

Question 26

Question
31 Dihedral angle contributes to the stability around the _____ axis
Answer
  • O longitutinal
  • O lateral
  • O vertical

Question 27

Question
32 Sweep angle contributes to the stability around the _____ axis
Answer
  • O vertical
  • O longitutinal
  • O lateral

Question 28

Question
33 The Horizontal stabilizer contributes to the stability around the _____ axis
Answer
  • O lateral
  • O vertical
  • O longitutinal

Question 29

Question
34 The vertical stabilizer contributes to the stability around the _____ axis
Answer
  • O vertical
  • O lateral
  • O longitutinal

Question 30

Question
35 It is a desirable wing characteristic to develop the stall from the tip toward the root]
Answer
  • O False
  • O True

Question 31

Question
36 During an airplane's steady descent, thrust is less than drag
Answer
  • O True
  • O False

Question 32

Question
37 In a constant speed, straight and level flight, as the airplane's weight is decreasing due to fuel consumption...
Answer
  • O the angle of attack decreases
  • O the angle of attack increases
  • O the angle of attack remains the same

Question 33

Question
38 When the angle of attack exceeds the critical angle of attack coefficient of lift inceases rapidly]
Answer
  • O False
  • O True

Question 34

Question
39 the drag coeficient (Cd) of an airplane
Answer
  • O No correct answer
  • O it is maximus on Vne
  • O it is maximus on Vso
  • O it is maximus on VsI

Question 35

Question
40 An airplane is approaching the stall having a right ball indication on the inclinometer. There is a danger that the airplane after the stall will enter a right spin
Answer
  • O False
  • O True

Question 36

Question
41 An airplane is approaching the stall having a right ball indication on the inclinometer. There is a danger that the airplane after the stall will enter a left spin
Answer
  • O True
  • O False

Question 37

Question
42 An airplane is approaching the stall having a left ball indication on the inclinometer. There is a danger that the airplane after the stall will enter a right spin
Answer
  • O True
  • O False

Question 38

Question
43 An airplane is approaching the stall having a left ball indication on the inclinometer. There is a danger that the airplane after the stall will enter a left spin
Answer
  • O False
  • O True

Question 39

Question
44 A single engine airplane with a clockwise rotating propeller is climbing with a very steep angle an the pilot is not countering the left turning tendency. If the airplane stalls under these conditions...
Answer
  • O a left spin is possible
  • O a right spin is possible
  • O a spin is impossible

Question 40

Question
45 The lift coefficient (Cl) is changing with a change of...
Answer
  • O the angle of attack
  • O the flight altitude
  • O the airspeed
  • O the lift

Question 41

Question
46 The drag coefficient (Cd) is changing with a change of...
Answer
  • O the angle of attack
  • O the flight altitude
  • O the airspeed
  • O the lift

Question 42

Question
47 in a straight and level flight when the airplane speed increases...
Answer
  • O the lift coefficient decreases.
  • O the lift coefficient increases.
  • O the lift coefficient remains unchanged

Question 43

Question
48 in a straight and level flight when the airplane speed decreases...
Answer
  • O the lift coefficient increases.
  • O the lift coefficient decreases.
  • O the lift coefficient remains unchanged

Question 44

Question
49 An airplane that exceeded a bank angle of 60°has the tendency...
Answer
  • O to increase its bank angle to 90°
  • O to gradualy decrease its bank angle
  • O to maintain its bank angle

Question 45

Question
50 An airplane that not exceeded a bank angle of 30°has the tendency...
Answer
  • O to gradualy decrease its bank angle
  • O to increase its bank angle to 90°
  • O to maintain its bank angle

Question 46

Question
51 The "T" tail system compare to the conventional system has the advandage of...
Answer
  • O less interference drag
  • O less induced drag
  • O less surface drag
  • O less weight

Question 47

Question
52 airfoil is]
Answer
  • O a cross section of the wing, parallel to the plan of symmetry of the aircraft] .
  • O a cross section of the wing at the joining point with the airframe] .
  • O a cross section of the wing at the middle of it.
  • O a cross section of the wing at the wing tip

Question 48

Question
53 angle of attack is]
Answer
  • O the angle between wing cord and the relative wind
  • O the angle between the wing cord and the longitudinal axis
  • O the angle between the wing cord and the lateral axis
  • O the dihedral angle

Question 49

Question
54 Sweep angle is]
Answer
  • O the angle between a line that connects the points on ? chord distance from the leading edge and a line perpendicular to the plane of symmetry of the aircraft
  • O the dihedral angle of the aircraft
  • O the angle between the leading edge and the longitudinal axis of a wing
  • O the angle between the leading edge and the lateral axis of the aircraft

Question 50

Question
55 center of prerssure is called]:
Answer
  • O the point where lift is applied on the wing
  • O the center of gravity of the aircraft
  • O the point wher the landing gear is attached to the wing
  • O the point where the weight of the wing is applied when the fuel tank is full

Question 51

Question
56 what is called Mean Aerodynamic Chord]
Answer
  • O is the chord of a hypothetical rectangular wing, that produces the same lift and at the same point as the real wing
  • O the mean value of the chord of a wing
  • O is the length of the wing chord at the middle of the wing
  • O is the length of the wing chord at the center of pressure of the wing

Question 52

Question
57 the coefficient of lift depends on]
Answer
  • O angle of attack
  • O air density
  • O the airspeed2

Question 53

Question
58 the higher part of the lift produced by an airfoil is applied]:
Answer
  • O on the upper surface as underpressure
  • O on the lower surface as overpressure
  • O on the frontal surface as drag

Question 54

Question
59 the thickness of the boundary layer around an airfoil…]
Answer
  • O increases when the altitude increases
  • O increases when the speed of the free airstream increases
  • O increases when the viscosity of the air increases

Question 55

Question
60 The critical angle of attack
Answer
  • O gives the coefficient of lift just before stall
  • O gives the minimum (negative) coefficient of lift
  • O gives coefficient of lift equal to zero
  • O gives the maximum coefficient of lift

Question 56

Question
61 Stall speed Vs is]
Answer
  • O it is not fixed and depends on the power output of the engine
  • O the speed when the aircraft flies straight and level at the critical angle of attack
  • O is the speed when flying at an angle of attack equal to zero
  • O is the speed when flying at a negative angle of attack

Question 57

Question
62 The stalling speed of an airplane Vs…
Answer
  • O depends on power output of the engine
  • O depends on altitude
  • O depends on ground speed
  • O no correct answer

Question 58

Question
63 the symbol of maneuvering speed is]..
Answer
  • O Va.
  • O VLO.
  • O VNE.
  • O no correct answer

Question 59

Question
64 the symbol of the maximum speed with the Flaps full down is
Answer
  • O VFE.
  • O VLOF
  • O VFC
  • O no correct answer

Question 60

Question
65 the symbol of the maximum speed with the Landing Gear full down is
Answer
  • O VLE.
  • O VLO.
  • O VFE.
  • O no correct answer

Question 61

Question
66 the speed range up to VNO is defined as]
Answer
  • O normal operating range
  • O never exceed speed
  • O maximum cruising speed
  • O no correct answer

Question 62

Question
67 VSO speed is called]
Answer
  • O stall speed in landing configuration
  • O stall speed in specified configuration
  • O stall speed or minimum safe take off speed
  • O no correct answer

Question 63

Question
68 the use of Flaps… ]
Answer
  • O increases drag, increases lift, decreases the critical angle of attack
  • O increases drag, increases lift, increase the critical angle of attack
  • O increases drag, decreases lift, decreases the critical angle of attack
  • O decreases drag, increases lift, increases the critical angle of attack

Question 64

Question
69 Usually we use maximum Flaps deflection ]
Answer
  • O only during landing
  • O during take off and landing
  • O only during take off and only on short runways
  • O only during take off, on pilot discretion

Question 65

Question
70 the purpose of aerodynamic trim of the controls is…]
Answer
  • O to reduce the force needed to move the controls
  • O the return of the controls to the neutral position when released
  • O to increase the rate of turn of the aircraft
  • O to coordinate the movement of all controls

Question 66

Question
71 Longitudinal dihedral is called]
Answer
  • O the difference of the angle of incidence of the wing and the tail plane relative to the longitudinal axis
  • O the difference of the angle of incidence of the left wing and the right wing relative to the longitudinal axis
  • O the difference of the angle of incidence of the left tail horizontal wing and the right tail horizontal wing relative to the longitudinal axis
  • O the difference of the angle of incidence of the wing and the horizontal stabilizer relative to the longitudinal axis

Question 67

Question
72 The use of Flaps during landing results in the…]:
Answer
  • O increase of the descend angle without an increase of the airspeed
  • O reduction of the descend angle without an increase of the airspeed
  • O landing with an increase IAS
  • O increase of angle of descent due to the reduction of lift

Question 68

Question
73 Refer to figure POF07. What is the speed range that is permitted to use the flaps .
Answer
  • O 60-100 Kts.
  • O 65-165 Kts.
  • O 60-208 Kts.
  • O 165-208 Kts

Question 69

Question
74 Refer to figure POF07. What is the maximum speed with the flaps down
Answer
  • O 100 Kts.
  • O 165 kts.
  • O 65 Kts.
  • O 60 Kts.

Question 70

Question
75 Refer to figure POF07. What color range symbolizes the range of speed that is permitted to use the flaps
Answer
  • O the white arc]
  • O from the lower speed of the white arc up to the upper level of the green arc
  • O the green arc
  • O the yellow arc

Question 71

Question
76 Refer to figure POF07. What color and which point on the instrument indicate the stalling speed with no thrust, landing gear and flaps in landing configuration].
Answer
  • O the low end of the white arc
  • O the high end of the green arc
  • O the high end of the white arc
  • O the low end of the green arc

Question 72

Question
77 Which aircraft's speed limit is not depicted on the color coding of the Airspeed indicator]
Answer
  • O Maximum maneuvering speed
  • O Never exceed speed
  • O Maximum cruising speed
  • O Maximum speed with the flaps down

Question 73

Question
78 The 4 forces acting on an aircraft in flight are]
Answer
  • O Engine thrust, lift, weight, drag
  • O Engine power, speed, gravity, drag
  • O Engine power, speed, weight, friction
  • O Engine thrust, lift, gravity, weight

Question 74

Question
79 In which case do the 4 forces acting on an aircraft equal to zero];
Answer
  • O During straight and level non accelerated flight
  • O With the aircraft still on the ground
  • O When the aircraft is accelerating
  • O When the aircraft is decelerating

Question 75

Question
80 What is the relationship between the forces of lift, drag, thrust and weight during straight and level non accelerated flight]
Answer
  • O lift and weight = thrust and drag
  • O lift = drag and thrust = weigh
  • O lift, drag and weight = thrust
  • O lift = weight and thrust = drag

Question 76

Question
81 What makes an aircraft turn
Answer
  • O the horizontal coefficient of lift
  • O The centrifugal force
  • O The coordinated effect of rudder and ailerons
  • O The ruder, ailerons and elevator

Question 77

Question
82 Refer to figure POF08, The angle A is called]
Answer
  • O angle of incidence
  • O dihedral angle
  • O angle of attack
  • O camber angle

Question 78

Question
83 The angle of attack is defined as]
Answer
  • O the angle between the wing chord and the relative wind
  • O the angle between the climb vector of the aircraft and the horizon
  • O the angle between the longitudinal axis and the chord of the aircraft
  • O the angle when the Lift to Drag ratio is the highest

Question 79

Question
84 Refer to figure POF09. If the aircraft's weight is 2.300 lb, what is the weight that his structure has to withstand during a level turn with an angle of 60 degrees relative to the horizon]
Answer
  • O 4.600 lb.
  • O 3.400 lb.
  • O 2.300 lb.
  • O 5.200 lb.

Question 80

Question
85 Refer to figure POF09. If the aircraft's weight is 3.300 lb, what is the weight that his structure has to withstand during a level turn with an angle of 30 degrees relative to the horizon]
Answer
  • O 3.960 lb.
  • O 3.100 lb.
  • O 1.200 lb.
  • O 7.220 lb.

Question 81

Question
86 Refer to figure POF09. If the aircraft's weight is 5.400 lb, what is the weight that his structure has to withstand during a level turn with an angle of 55 degrees relative to the horizon ]
Answer
  • O 9.180 lb.
  • O 5.400 lb.
  • O 6.720 lb.
  • O 10.800 lb.

Question 82

Question
87 Refer to figure POF09. If the aircraft's weight is 4.500 lb, what is the weight that his structure has to withstand during a level turn with an angle of 45 degrees relative to the horizon ]
Answer
  • O 6.750 lb.
  • O 4.500 lb.
  • O 7.200 lb.
  • O 12.000 lb.

Question 83

Question
88 Refer to figure POF09. The highest bank angle that the aircraft's wing can have without exceeding 4,4 G is]
Answer
  • O 77°
  • O 71°
  • O 73°
  • O 83°

Question 84

Question
89 One of the main reasons that we use flaps during landing is]
Answer
  • O to increase the angle of descend without increasing the aircraft's speed]
  • O to reduce the lift in order to have a steeper descend angle]
  • O to allow for greater speeds when the wheels contact the runway]
  • O to decrease the angle of descent, without increasing the aircraft's speed

Question 85

Question
90 the function of the vertical stabilizer is]
Answer
  • O to stabilize the aircraft around the vertical axis
  • O to control the tendency for left or right bank
  • O to reduce the slip or skid
  • O to maintain the turn after banking the aircraft

Question 86

Question
91 Flaps are needed to:
Answer
  • O allow the pilot to maintain high angle of descent during landing, without high speed
  • O allow the pilot to reduce speed
  • O increase the wing's lift by increasing its surface
  • O increase the drag, and as a result more thrust is required during landing

Question 87

Question
92 The number of G's applied on the airframe depend on]
Answer
  • O the bank of the aircraft during a level turn
  • O the position of the center of gravity
  • O The airspeed of the aircraft
  • O the stalling angle of attack

Question 88

Question
93 What will be the effect of load factor (G forces) on an aircraft approaching the stall]
Answer
  • O the aircraft will stall on a higher speed
  • O the aircraft will have a tendency to enter a spin
  • O the control of the aircraft will be more difficult
  • O the aircraft will have a tendency to rotate around the vertical and the longitudinal when approaching the stall speed

Question 89

Question
94 Which basic aircraft maneuver increases the load factor in relation to straight and level flight]
Answer
  • O turns
  • O climb
  • O stall
  • O slip

Question 90

Question
95 What is the basic advantage of a stable aircraft]
Answer
  • O is easily controlable
  • O it is impossible to spin
  • O it is difficult to stall
  • O it is not experiencing extreme bank angles during steep turns

Question 91

Question
96 Which factors affect aircraft stability along the longitudinal axis]
Answer
  • O the position of Center of Gravity relative to the Center of Pressure
  • O the effectivity of the elevator, the elevator trim and the rudder
  • O the relationship between thrust and lift to drag and weight
  • O the dihedral angle and sweep angle

Question 92

Question
97 What causes an aircraft to nose down when reducing engine power, without adjusting the elevator (T-tailed aircraft are exempted)]
Answer
  • O The downward force created from the air stream of the propeller hitting the horizontal stabilizer is reduced therefore the elevator is less effective
  • O The Center of Gravity moves forward when thrust and drag is reduced
  • O As the thrust becomes less than the weight, lift also decreases and the wings cannot support the weight of the aircraft
  • O the air pressure applied by the propeller on the wings decreases and also the angle of attack decreases

Question 93

Question
98 An aircraft is loaded with its center of gravity out of the aft center of gravity limit. The flight is dangerous because]
Answer
  • O the aircraft will not recover after a stall
  • O the aircraft will need more runway for take off
  • O the aircraft stalls at an unpredictable higher speed
  • O it is difficult to land the aircraft

Question 94

Question
99 How the flight characteristics of an aircraft are affected when the Center of Gravity is at its aft limit ]
Answer
  • O the aircraft will be less stable at all speeds
  • O the aircraft will be less stable at low speeds and more stable at high speeds
  • O the aircraft will be more stable at low speeds and less stable at high speeds
  • O the aircraft will be more stable at all speeds

Question 95

Question
100 when frost remains on the aircraft's wings before flight]
Answer
  • O take off may be difficult or impossible
  • O this can have as a result the take off with a lower angle of attack and at a lower indicated airspeed
  • O no problem exists since frost will be blown off by the pressure of the air during take off
  • O it will increase the camber of the wing and as a result more lift will becreated during take off

Question 96

Question
101 when is it possible for an aircraft to stall]
Answer
  • O at any speed and altitude
  • O only when the aircraft's nose is high and the speed low
  • O only when its speed falls below the published stall speed
  • O only when the aircraft's nose is high in relation to the horizon

Question 97

Question
102 during a left spin which wing(s) is (are) stalled]
Answer
  • O both wings are stalled
  • O neither wing is stalled
  • O only the left wing is stalled
  • O only the right wing is stalled

Question 98

Question
103 the stalling angle of attack
Answer
  • O remains the same irrespectively of the weight
  • O increases as the center of gravity moves forward
  • O is changing as the take off weight increases
  • O decreases as the center of gravity moves aft

Question 99

Question
104 At a given configuration, as the flight altitude increases, the stalling indicated airspeed
Answer
  • O remains the same as in lower altitudes
  • O decreases as the true airspeed decreases
  • O decreases as the true airspeed increases
  • O increase because the air density decreases

Question 100

Question
105 What is the required aircraft's condition in order for the aircraft to spin]
Answer
  • O to be stalled
  • O to be close to stall, one wing low and idle power
  • O to be in a steep dive and rotation at the same time
  • O to be in a steep climb with idle power

Question 101

Question
106 How can the ground effect affect an airplane]
Answer
  • O to take off before reaching the manufacturer speed for take off
  • O to sink back on the runway just after take off
  • O to be unable to take off even after passing the calculated take off speed
  • O high rate of descent and a hard landing during approach

Question 102

Question
107 Which unwanted effect may the pilot experience during take off due to the ground effect]
Answer
  • O to take off before reaching the manufacturer speed for take off
  • O to be unable to take off even after passing the calculated take off speed
  • O to sink back on the runway just after take off
  • O to experience difficulties during the first 20 feet of climb after take off

Question 103

Question
108 During landing the ground effect is more noticeable]
Answer
  • O When the height of the aircraft from the runway is less than half its wing span
  • O When the height of the aircraft from the runway is equal to twice its wing span
  • O when descending at a high angle of attack
  • O when descending at a speed close to the stall speed

Question 104

Question
109 At what altitude, can the ground effect affect an airplane]
Answer
  • O equal to the wing span
  • O between 100 and 200 feet above the runway in calm wind conditions
  • O at less than half the wing span
  • O 3 or 4 times the wing span

Question 105

Question
110 Wake turbulence are more intense when the aircraft creating them is
Answer
  • O heavy, clean and slow
  • O light and fast
  • O heavy and fast

Question 106

Question
111 wing tip vortices are created only when the aircraft...
Answer
  • O produces lift
  • O is flying at high speed
  • O is big
  • O no correct answer

Question 107

Question
112 Wing tip vortices have a tendency
Answer
  • O to sink behind the aircraft that creates them
  • O to climb and reach the traffic pattern altitude
  • O to climb and spread left and right
  • O to remain exactly behind and at the same altitude as the aircraft that created them

Question 108

Question
113 When a pilot is landing behind a big aircraft, he has to keep his path clear of wake turbulence by flying
Answer
  • O above the path of the big airplane and by landing after its the landing spot
  • O below the path of the big airplane and by landing before its the landing spot
  • O above the path of the big airplane and by landing before its the landing spot
  • O below the path of the big airplane by landing after its the landing spot

Question 109

Question
114 When a pilot is taking off behind a big aircraft, he has to keep his path clear of wake turbulence by flying
Answer
  • O higher and to the upwind side of the taking off aircraft
  • O lower and to the downwind side of the taking off aircraft
  • O lower and to the upwind side of the taking off aircraft
  • O higher and to the downwind side of the taking off aircraft

Question 110

Question
115 Aircraft's Empty weight includes...
Answer
  • O hydraulic fluid, oil and unuseable fuel
  • O only the airframe, the engine and the equipment installed by the manufacturer
  • O Fuel and Oil tanks full but without the weight of the crew and baggage
  • O unusable fuel and provisional equipment ex. potable water e.t.c.

Question 111

Question
116 The four forces acting on an airplane in flight are?
Answer
  • O lift, weight, thrust, and drug
  • O lift, weight, gravity, and thrust
  • O lift, gravity, power, and friction
  • O lift, power, thrust, and drug

Question 112

Question
117 What force makes an airplane turn:
Answer
  • O the horizontal component of lift
  • O the vertical component of lift
  • O centrifugal force
  • O Bernoulli's force

Question 113

Question
118 During an approach to a stall, an increased load factor will cause the airplane to :
Answer
  • O stall at a higher airspeed
  • O have a tendency to spin
  • O be more difficult to control
  • O turn left

Question 114

Question
119 The most important rule to remember in the event of a power failure after becoming airborne is to:
Answer
  • O immediately establish the proper gliding attitude and airspeed
  • O quickly check the fuel supply for possible fuel exhaustion
  • O determine the wind direction to plan for the forced landing
  • O determine the reasons for the power failure

Question 115

Question
120 The amount of excess load that can imposed on the wing of an airplane depends upon the:
Answer
  • O speed of the airplane
  • O position of the CG
  • O abruptness at which the load is applied
  • O wind direction

Question 116

Question
121 Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight?
Answer
  • O turns
  • O climbs
  • O stalls
  • O descents

Question 117

Question
122 When does the P- factor cause the airplane to yaw to the left:
Answer
  • O when at high angles of attack
  • O when at low angles of attack
  • O when at high airspeed
  • O when at low airspeed

Question 118

Question
126 In what flight condition is torque effect the greatest in a single-engine airplane?
Answer
  • O Low airspeed, high power, high angle of attack
  • O Low airspeed, low power, low angle of attack
  • O High airspeed, high power, high angle of attack
  • O High airspeed, high power, low angle of attack

Question 119

Question
127 During a spin to the left, which wing(s) s/are stalled?
Answer
  • O both wings are stalled
  • O neither wing is stalled
  • O only the left wing is stalled
  • O only the right wing is stalled

Question 120

Question
128 What is the purpose of the rudder on an airplane?
Answer
  • O to control yaw
  • O to control over banking tendency
  • O to control roll
  • O to control pitch

Question 121

Question
129 Loading an airplane to the most aft CG will cause the airplane to be:
Answer
  • O less stable at all speeds
  • O less stable at low speeds, but more stable at high speeds
  • O less stable at high speeds, but more stable at low speeds
  • O more stable at all speeds

Question 122

Question
130 In what flight condition must an aircraft be placed in order to spin?
Answer
  • O stalled
  • O in a steep diving spiral
  • O in a steep diving spiralL
  • O during a climb

Question 123

Question
131 An airplane said to be inherently stable will :
Answer
  • O require less effort to control
  • O be difficult to stall
  • O not spin
  • O be difficult to turn

Question 124

Question
132 What determines the longitudinal stability of an airplane?
Answer
  • O the location of the CG with respect to the center of lift
  • O the effectiveness of the horizontal stabilizer, and rudder
  • O the weight of the airplane
  • O the direction of the relative wind

Question 125

Question
133 Ground effect is most likely to result in which problem?
Answer
  • O becoming airborne before reaching recommended takeoff speed
  • O settling to the surface abruptly during landing
  • O inability to get airborne even though airspeed is sufficient for normal take off needs
  • O inability to land in short runways

Question 126

Question
134 Angle of attack is defined as the angle between the chord line of an airfoil and the:
Answer
  • O direction of the relative wind
  • O longitudinal axis f the airplane
  • O normal axis of the airplane
  • O lateral axis of the airplane

Question 127

Question
135 One of the main functions of flaps during approach and landing is to:
Answer
  • O increase the angle of descent without increasing the airspeed
  • O decrease the angle of descent without increasing the airspeed
  • O permit a touchdown at a higher airspeed
  • O decrease the angle of descent and increase the airspeed

Question 128

Question
136 What is one purpose of wing flaps?
Answer
  • O to enable the pilot to make steeper approaches to a landing without increasing the airspeed
  • O to relieve the pilot of maintaining continuous pressure on the controls
  • O to decrease wing area to vary lift
  • O to help in landing with increasing speed

Question 129

Question
137 The angle of attack at which an airplane wing stalls will:
Answer
  • O remain the same regardless of gross weight
  • O increase if the CG is moved forward
  • O change with an increase in gross weight
  • O decrease if the CG is moved forward

Question 130

Question
138 Floating caused by the phenomenon of ground effect will be most realized during an approach to land when:
Answer
  • O at less than the length of the wingspan above the surface
  • O at twice the length of the wingspan above the surface
  • O at a higher than normal angle of attack
  • O landing with tail wind

Question 131

Question
139 When are the four forces that act on an airplane in equilibrium?
Answer
  • O During unaccelerated flight
  • O When the aircraft is accelerating
  • O When the aircraft is at rest on the ground
  • O at MSL

Question 132

Question
140 What is the relationship of lift, drug, thrust, and weight when the airplane is in straight-and level flight?
Answer
  • O Lift equals weight and thrust equals drag
  • O Lift, drug and weight equal thrust
  • O Lift and weight equal thrust and drug
  • O Thrust, drug and weight equal lift

Question 133

Question
141 What is the effect of deploying trailing edge flaps?
Answer
  • O Increases CL and decreases Vs
  • O Increases CL and Vs
  • O Decreases CL and Vs
  • O Decreases CL and increases Vs

Question 134

Question
142 What is the effect of deploying leading edge slats?
Answer
  • O Energising boundary layer and decreasing Vs
  • O Energising boundary layer and increasing Vs
  • O De-energising boundary layer and decreasing Vs
  • O De-energising boundary layer and increasing Vs

Question 135

Question
143 What is the effect on wing pitching moment, of deploying trailing edge flaps prior to landing?
Answer
  • O Nose up pitching moment replaced by a nose down pitching moments.
  • O Increased nose down pitching moment.
  • O Decreased nose down pitching moment.
  • O Increased nose up pitching moment.

Question 136

Question
144 What effect does deployment of trailing edge flaps have on stalling angle of attack?
Answer
  • O Decreased stalling angle.
  • O No change.
  • O Increased stalling angle.
  • O Increased or decreased stalling angle depending on wing sweep angle.

Question 137

Question
145 What trailing edge flap angle will give the minimum stalling speed?
Answer
  • O Maximum deflection.
  • O Zero degrees.
  • O 20 degrees.
  • O 30 degrees.

Question 138

Question
146 What trailing edge flap angle will give best L : D ratio?
Answer
  • O Zero angle.
  • O Maximum angle.
  • O 20 degrees.
  • O 30 degrees.

Question 139

Question
147 What will be the effect of deploying triple slotted fowler flaps to maximum deflection?
Answer
  • O Wing area, camber and angle of incidence will increase but stalling angle, stalling speed and L/D ratio all decrease.
  • O L/D ratio, wing area, camber, stalling angle, stalling speed and angle of incidence will all increase.
  • O L/D ratio, wing area, camber, stalling angle, stalling speed and angle of incidence will all decrease.
  • O L/D ratio, wing area, camber and stalling angle will increase but stalling speed and angle of incidence will decrease.

Question 140

Question
148 Complete the following statement. As trailing edge flaps move from fully retracted to fully deployed, both lift and drag increase. Most of the additional drag is produced during the .............of deployment whilst most of the additional lift is produced during the..................The additional drag produced by the first half of the deployment is mainly.............................Whilst that produced during the second half is mainly................................. 1. First half 2. Induced 3. Profile 4. Second half
Answer
  • O 4, 1, 2, 3.
  • O 4, 2, 1, 3.
  • O 3, 1, 2, 4.
  • O 1, 4, 3, 2.

Question 141

Question
149 Deployment of trailing edge flaps in straight and level flight wil will……………………………………………………….induced drag?
Answer
  • O Increase.
  • O Not affect.
  • O Decrease.
  • O Increase or decrease depending on flap angle selected.

Question 142

Question
150 Which of the following will reduce L/D ratio most?
Answer
  • O 45° trailing edge flap.
  • O 15° trailing edge flap.
  • O 30° trailing edge flap.
  • O 15° slat.

Question 143

Question
151 A split flap is………………………………….compared to a plain flap?
Answer
  • O More efficient.
  • O Less efficient
  • O As efficient.
  • O More or less efficient depending on weight.

Question 144

Question
152 Deployment of flaps in turbulence will……………………………….?
Answer
  • O Decrease stalling speed and increase risk of exceeding limiting load factor.
  • O Increase stalling speed and risk of exceeding limiting load factor.,
  • O Decrease stalling speed and risk of exceeding limiting load factor.
  • O Increase stalling speed and decrease risk of exceeding limiting load factor.

Question 145

Question
153 Deployment of leading edge slats………………………………………...?
Answer
  • O Energises boundary layer and moves C of P forward.
  • O De-energises boundary layer and moves C of P aft.
  • O De-energises boundary layer and moves C of P forward,
  • O Energises boundary layer and moves C of P aft.

Question 146

Question
154 Deployment of flaps……………………………………………...CL?
Answer
  • O Increases.
  • O Decreases.
  • O Increases then decreases.
  • O Decreases then increases.

Question 147

Question
155 The first few degrees of flap deployment will………………………………………...L/D ratio?
Answer
  • O Increase.
  • O Decrease.
  • O Increase or decrease depending on speed.
  • O Not affect.

Question 148

Question
156 Deployment of trailing edge flaps………………………..stalling angle and…………………………………………..CLMAX?
Answer
  • O Decreases, Increases.
  • O Increases, Increase.
  • O Increases, Decreases.
  • O Decreases, Decreases.

Question 149

Question
157 Deployment of flaps in icing conditions might…………………..?
Answer
  • O Cause stalling.
  • O Increase stalling angle.
  • O Spin.
  • O Increase rate of climb.

Question 150

Question
158 Raising slats too soon after take-off might………………………..?
Answer
  • O Cause stalling.
  • O Increase stalling angle.
  • O Structural failure.
  • O Increase rate of climb.

Question 151

Question
159 Trailing edge flaps…………………….……………….landing attitude?
Answer
  • O Decrease.
  • O Increase.
  • O Do not affect,
  • O Increase or decrease depending on flap type.

Question 152

Question
160 Trailing edge flaps…………………………………….stalling angle?
Answer
  • O Decrease.
  • O Increase.
  • O Do not affect
  • O Increase or decrease depending on flap type.

Question 153

Question
161 The purpose of leading edge slats is to…………………………….?
Answer
  • O Increase stalling angle.
  • O Decreases stalling angle.
  • O Increase stalling speed,
  • O Create advanced turbulent boundary layer.

Question 154

Question
162 Leading edge slats……………………...stalling angle?
Answer
  • O increase.
  • O Decrease.
  • O Do not affect.
  • O Increase or decrease depending on weight.

Question 155

Question
163 Asymmetric flap deployment………………………………………...?
Answer
  • O Causes loss of control.
  • O Improves lift performance.
  • O Is used to prevent asymmetric yaw.
  • O Is not possible.

Question 156

Question
164 The diagram (Fig.1), includes?
Answer
  • O Split flap
  • O Double slotted plain flaps.
  • O Leading edge flaps
  • O Double slotted fowler flaps.

Question 157

Question
165 The diagram (Fig.2), includes?
Answer
  • O Slat and plain flap.
  • O Drooped leading edge and plain flap.
  • O Leading edge flap.
  • O Double slotted split flaps.

Question 158

Question
166 Flap asymmetry causes…………………………………………….?
Answer
  • O Roll and yaw.
  • O Roll.
  • O Roll, pitch and yaw.
  • O None of the above.

Question 159

Question
167 Trailing edge flap deployment………….……………………... pitch attitude required in take-off and landing?
Answer
  • O Decreases stalling speed and stalling angle of attack.
  • O Increases stalling speed and stalling angle of attack.
  • O Decreases stalling speed and angle of incidence.
  • O Improves stability.

Question 160

Question
168 Trailing edge flap deployment…………………………………………….. pitch attitude required in take-off and landing?
Answer
  • O Decreases,
  • O Increases.
  • O Does not affect.
  • O Increases or decreases depending on weight

Question 161

Question
169 Trailing edge flap deployment………………….power required?
Answer
  • O Increases.
  • O Decreases.
  • O Does not affect.
  • O Increases or decreases depending on C of G position.

Question 162

Question
170 Deployment of flaps………………………………………………….?
Answer
  • O Decreases lateral stability.
  • O Increases longitudinal stability.
  • O Decreases longitudinal stability.
  • O Increases lateral stability.

Question 163

Question
171 Trailing edge flap deployment...................................... ?
Answer
  • O Decreases stalling angle.
  • O Increases stalling angle.
  • O Does not affect stalling angle,
  • O Increases or decreases stalling angle depending on C of G position.

Question 164

Question
172 What effect does increasing load factor have on power required at any given aircraft eweight and TAS?
Answer
  • O Increases in direct proportion to load factor.
  • O .No effect.
  • O Decreases in direct proportion to load factor,
  • O Power required is inversely proportional to load factor.

Question 165

Question
173 What effect will increasing aircraft weight have on minimum drag speed (Vmd) and speed stability,
Answer
  • O Increase, Decrease.
  • O Increase, Increase.
  • O Decrease, Increase.
  • O Decrease, Decrease.

Question 166

Question
174 What effect will lowering the landing gear have on VMD and speed stability?
Answer
  • O Decrease, Increase,
  • O Increase, Increase.
  • O Increase, Decrease.
  • O Decrease, Decrease.

Question 167

Question
175 What is the relationship between Di and Dp at speeds below VMD?
Answer
  • O Di is greater than Dp.
  • O Di is less than Dp.
  • O Di = Dp.
  • O Di = DP =DTOTAL

Question 168

Question
176 Complete the following statement. As airspeed changes from VMD to CLMAX………………………………..increases and………………. decreases.
Answer
  • O DI, DP.
  • O DP, DI.
  • O DTOTAL DP.
  • O D TOTAL DI.

Question 169

Question
177 Which of the following definitions of Dp is the most accurate?
Answer
  • O It is made up of friction, form and interference drag,
  • O It is made up of form, friction and induced drag.
  • O It is made up of friction, induced and shock drag.
  • O It is made up of interference, shock and form drag.

Question 170

Question
178 What causes wing tip vortices?
Answer
  • O High pressure air leaking from below the wings.
  • O Pressure differences in front of and behind the wings.
  • O Spanwise flow from tip to root under the wings,
  • O Spanwise flow from root to tip above the wings.

Question 171

Question
179 Which of the following occur at Vmd?
Answer
  • O Minimum drag and greatest L/D ratio.
  • O Minimum power required and best L/D) ratio.
  • O Minimum angle of attack and best rate of climb.
  • O Minimum drag and greatest jet propeller aircraft range.

Question 172

Question
180 In what direction does the drag force act?
Answer
  • O Parallel but opposite to the direction of flight.
  • O Parallel to relative airflow.
  • O Parallel to lift,
  • O Parallel to weight.

Question 173

Question
181 In what direction does lift act?
Answer
  • O At right angles to the flight path.
  • O Straight up.
  • O At right angles to the relative airflow.
  • O At right angles to thrust.

Question 174

Question
182 The majority of lift is produced by?
Answer
  • O Low pressure above the wing.
  • O High pressure below the wing.
  • O Increased velocity below the wing.
  • O Increased density below the wing.

Question 175

Question
183 What proportion of total drag is made up of induced drag when flying at VMD?
Answer
  • O 50%
  • O 75%
  • O 25%
  • O 100%

Question 176

Question
184 All other factors being equal, minimum drag is……………………………………………...?
Answer
  • O Proportional to weight.
  • O Constant.
  • O A function of density altitude.
  • O A function of pressure altitud

Question 177

Question
185 If air density is reduced by a factor of 4, by what factor will drag alter?
Answer
  • O Decrease by a factor of 4.
  • O Decrease by a factor of 2.
  • O Increase by a factor of 4.
  • O Decrease by a factor of 16.

Question 178

Question
186 Which of the following, causes induced drag (Di) ?
Answer
  • O Downwash of airflow over the trailing edge caused by wing tip vortices.
  • O Shock waves above and below the wing.
  • O Friction due to the air passing over the wing.
  • O Upwash of airflow over the trailing edge caused by wingtip vortices.

Question 179

Question
187 Which of the following is responsible for the creation of induced drag?
Answer
  • O Angle of attack, camber, wing area and airspeed.
  • O Pitch angle, camber, wing area and airspeed.
  • O Pitch angle, camber, wing area and angle of attack.
  • O Airspeed, wing area and pitch angle.

Question 180

Question
188 Entering ground effect causes?
Answer
  • O Downwash is reduced.
  • O Low pressure below the wings reduces lift
  • O Downwash is increased.
  • O The aircraft slows down.

Question 181

Question
189 In what way does ground effect influence induced drag?
Answer
  • O Decreases it.
  • O Increases it.
  • O No effect.
  • O Angles it aft.

Question 182

Question
191 What will be the effect of raising the undercarriage of an aircraft?
Answer
  • O Decreased profile drag and lower speed stability.
  • O Increased induced drag due to more efficient lift production.
  • O Decreased induced drag due to less efficient lift production.
  • O Increased profile drag and greater speed stability.

Question 183

Question
192 How will power required vary when leaving ground effect?
Answer
  • O increase.
  • O No change.
  • O Decrease.
  • O Decrease or increase depending on airspeed.

Question 184

Question
193 In what ways are Di and Dp proportional to V?
Answer
  • O (1/V)2 (V)2
  • O (V)3 (1/V)3
  • O Inversely.
  • O (V)2 (1/V)2

Question 185

Question
194 How does total drag vary with air density?
Answer
  • O Directly.
  • O Constant.
  • O Inversely.
  • O Conversely.

Question 186

Question
195 How does retraction of flaps affect induced drag if IAS remains constant?
Answer
  • O Decreases.
  • O Increases.
  • O Constant.
  • O Increase or decrease depending on speed.

Question 187

Question
196 ……………………………………………………….causes induced drag?
Answer
  • O The generation of lift.
  • O Angle of attack.
  • O Aspect ratio.
  • O Boundary layer separation.

Question 188

Question
197 Entering ground effect……………………………..power required?
Answer
  • O Decreases,
  • O Increases.
  • O Does not affect,
  • O Increases or decreases depending on height.

Question 189

Question
198 Increasing air temperature will......................................?
Answer
  • O Decrease lift at any given CL and TAS.
  • O Increase the gradient of the lift slope
  • O Decrease CL max.
  • O Increase profile drag.

Question 190

Question
199 Increasing humidity will………………………………………………………...?
Answer
  • O Increase required CL,
  • O Increase CL max.
  • O Decrease stalling speed,
  • O Increase profile drag.

Question 191

Question
200 Which of the following statements are true? 1. Increasing aspect ratio reduces induced drag. 2. Increasing sweep back angle reduces induced drag. 3. Increasing EAS increases induced drag. 4. Increasing CL increases induced drag.
Answer
  • O 1 and 4.
  • O 1,2 and 3.
  • O 1,3 and 4.
  • O 2,3 and 4.

Question 192

Question
201 ……………………………………………………………………………..aircraft weight will………………………………………………………………………ground effect?
Answer
  • O Increasing, increase.
  • O Increasing, decrease.
  • O Decreasing, increase.
  • O Decrease, diminish.

Question 193

Question
202 ……………………………………………………………………….landing speed at constant weight will……………………………….ground effect?
Answer
  • O Increasing,………………………………………..decrease.
  • O Increasing,………………………………………increase.
  • O Decreasing,…………………………………….stabilize,
  • O Decreasing,……………………………………decrease

Question 194

Question
203 Increasing load factor will…………………………………..Dp,………………………VMD and………………………………..speed dtability.
Answer
  • O Not affect, Increase, Decrease,
  • O Increase, Increase, Increase.
  • O Decrease, Decrease, Decrease,
  • O Not affect, Decrease, Increase

Question 195

Question
204 Why might trim tabs be employed in power assisted flying controls?
Answer
  • O To reduce control forces to zero,
  • O To enable control to be maintained following hydraulic failure.
  • O To prevent overstressing of hydraulic actuators.
  • O To provide better sability.

Question 196

Question
205 How is control mass balance achieved?
Answer
  • O By fitting weights onto or in front and above the leading edge.
  • O By fitting weight aft of the hinge.
  • O By fitting weights into the tip cap.
  • O By fitting a extra weights to the aft of fuselage.

Question 197

Question
206 In a climbing turn the ................wing is likely to stall..... ……...causing the aircraft to.. .......and yaw .......... the turn?
Answer
  • O Outer first roll out of.
  • O Outer last pitch in to.
  • O Inner first roll in to.
  • O Inner last pitch out of.

Question 198

Question
207 In a descending turn the ......... wing is likely to stall...... causing the aircraft to…… ...and yaw ............'the turn?
Answer
  • O .Inner first roll in to.
  • O .Outer last pitch in to.
  • O Outer first roll out of.
  • O .Inner last pitch out of.

Question 199

Question
208 A swept............................wing is prone to..............................all due to separation of boundary layer air at the...............?
Answer
  • O Back tip tips
  • O Forward root roots
  • O Back tip roots,
  • O Forward root tips.

Question 200

Question
209 Straight wings are prone to pitch..................in low speed stall and pitch........................in high speed stall?
Answer
  • O Down up then down.
  • O Down up.
  • O Up up.
  • O d Up down then bank.
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