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
2 As the altitude increases the air density...
O decreases
O increases
O remains constant
3 As the altitude increases the air pressure...
O depends on the day
4 Weel fairings on airgraft's landing gear decreases...
O interferance drag
O form drag
O induced drag
5 laminar flow boundary layer compared to turbulent boundary layer is...
O thinner]
O thikker
O having the same thickness
6 Figure POF01. Line a is called
O Chord Line
O Leading Edge
O Trailing Edge
O Mean Camber Line
7 Figure POF01. Line (c) is called
8 Figure POF02. Line (4) is called
O Maximum Airfoil Thickness
9 Figure POF01. Point (a) is called
10 Figure POF01. Point (e) is called
11 Figure POF03. Angle (a) is called
O sweepback
O angle of attack
O angle of incidence
12 When an aircraft is decelarating in a straight and level flight the induced drag...
O remains the same
13 When an aircraft is decelarating in a straight and level flight the parasite drag...
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
15 In a stable aircraft during straight and level flight the horizonta stabilizer produces lift...
O downwards
O upwards
O equal to zero
16 It is more possible for a pilot to have a tail strike during landing when landing with flaps up
O True
O False
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
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
19 During an airplane's steady climb, lift is less than weight
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
21 Figure POF04. The flaps type that coresponde with the letter (a) are called...
O Simple
O Split
O Slotted
O Fowler
22 Figure POF04. The flaps type that coresponde with the letter (b) are called...
23 Figure POF04. The flaps type that coresponde with the letter (c) are called...
24 Figure POF04. The flaps type that coresponde with the letter (d) are called...
25 An airplane has a maximum maneuvering speed of 85 kts, in a given weight. With a higher weight the maximum maneuvering speed will
31 Dihedral angle contributes to the stability around the _____ axis
O longitutinal
O lateral
O vertical
32 Sweep angle contributes to the stability around the _____ axis
33 The Horizontal stabilizer contributes to the stability around the _____ axis
34 The vertical stabilizer contributes to the stability around the _____ axis
35 It is a desirable wing characteristic to develop the stall from the tip toward the root]
36 During an airplane's steady descent, thrust is less than drag
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
38 When the angle of attack exceeds the critical angle of attack coefficient of lift inceases rapidly]
39 the drag coeficient (Cd) of an airplane
O No correct answer
O it is maximus on Vne
O it is maximus on Vso
O it is maximus on VsI
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
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
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
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
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
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
46 The drag coefficient (Cd) is changing with a change of...
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
48 in a straight and level flight when the airplane speed decreases...
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
50 An airplane that not exceeded a bank angle of 30°has the tendency...
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
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
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
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
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
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
57 the coefficient of lift depends on]
O air density
O the airspeed2
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
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
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
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
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
O no correct answer
63 the symbol of maneuvering speed is]..
O Va.
O VLO.
O VNE.
64 the symbol of the maximum speed with the Flaps full down is
O VFE.
O VLOF
O VFC
65 the symbol of the maximum speed with the Landing Gear full down is
O VLE.
66 the speed range up to VNO is defined as]
O normal operating range
O never exceed speed
O maximum cruising speed
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
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
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
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
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
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
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
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.
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
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
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
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
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
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
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
82 Refer to figure POF08, The angle A is called]
O dihedral angle
O camber angle
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
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.
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.
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.
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.
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°
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
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
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
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
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
94 Which basic aircraft maneuver increases the load factor in relation to straight and level flight]
O turns
O climb
O stall
O slip
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
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
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
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
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
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
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
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
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
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
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
