# 1_POF EXAM PREP1

Quiz by Osama Alkomy , updated 5 months ago More Less
 Created by tsampikos pompou over 3 years ago Copied by tsampikos pompou over 3 years ago Copied by Osama Alkomy 5 months ago
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POF EXAM PREP1

## Resource summary

### Question 1

Question
1 2On a standard atmosfaire the conditions at sea level are]
• 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...
• O decreases
• O increases
• O remains constant

### Question 3

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

### Question 4

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

### Question 5

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

### Question 6

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

### Question 7

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

### Question 8

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

### Question 9

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

### Question 10

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

### Question 11

Question
11 Figure POF03. Angle (a) is called
• 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...
• 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...
• O decreases
• O increases
• O remains the same

### Question 14

Question
14 The lowest drag during straight and level flight is achieved...
• 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...
• 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
• 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
• 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
• O decrease
• O increase
• O reamain the same

### Question 19

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

### Question 20

Question
20 We can decrease trim drag by...
• 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...
• 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...
• 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...
• 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...
• 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
• O increase
• O decrease
• O reamain the same

### Question 26

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

### Question 27

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

### Question 28

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

### Question 29

Question
34 The vertical stabilizer contributes to the stability around the _____ axis
• 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]
• O False
• O True

### Question 31

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

### Question 34

Question
39 the drag coeficient (Cd) of an airplane
• 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
• 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
• 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
• 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
• 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...
• 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...
• 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...
• 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...
• 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...
• 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...
• 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...
• 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...
• O less interference drag
• O less induced drag
• O less surface drag
• O less weight

### Question 47

Question
52 airfoil is]
• 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]
• 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]
• 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]:
• 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]
• 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]
• 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]:
• 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…]
• 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
• 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]
• 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…
• O depends on power output of the engine
• O depends on altitude
• O depends on ground speed

### Question 58

Question
63 the symbol of maneuvering speed is]..
• O Va.
• O VLO.
• O VNE.

### Question 59

Question
64 the symbol of the maximum speed with the Flaps full down is
• O VFE.
• O VLOF
• O VFC

### Question 60

Question
65 the symbol of the maximum speed with the Landing Gear full down is
• O VLE.
• O VLO.
• O VFE.

### Question 61

Question
66 the speed range up to VNO is defined as]
• O normal operating range
• O never exceed speed
• O maximum cruising speed

### Question 62

Question
67 VSO speed is called]
• O stall speed in landing configuration
• O stall speed in specified configuration
• O stall speed or minimum safe take off speed

### Question 63

Question
68 the use of Flaps… ]
• 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 ]
• 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…]
• 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]
• 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…]:
• 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 .
• 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
• 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
• 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].
• 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]
• 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]
• 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];
• 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]
• 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
• 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]
• 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]
• 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]
• 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]
• 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 ]
• 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 ]
• 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]
• O 77°
• O 71°
• O 73°
• O 83°

### Question 84

Question
89 One of the main reasons that we use flaps during landing is]
• 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]
• 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:
• 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]
• 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]
• 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]
• O turns
• O climb
• O stall
• O slip

### Question 90

Question
95 What is the basic advantage of a stable aircraft]
• 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]
• 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)]
• 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]
• 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 ]
• 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]
• 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]
• 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]
• 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
• 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
• 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]
• 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

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