ECQB-PPL Principles of Flight Exam Questions PDF

ECQB-PPL Examination Questions PPL(A) Compliant to (EU) No. 1178/2011 and AMC FCL.115,.120,.210,.215 (Extract) 51 – Principles of Flight (Aeroplane) ECQB-PPL (AT) 51 Principles of Flight (Aeroplane)...

ECQB-PPL Examination Questions PPL(A) Compliant to (EU) No. 1178/2011 and AMC FCL.115,.120,.210,.215 (Extract) 51 – Principles of Flight (Aeroplane) ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) Publisher: AIRCADEMY LTD. LPLUS GmbH [email protected] [email protected] COPYRIGHT Remark: This document is protected by copyright. The commercial use of this work or extracts from the work is only allowed with prior approval by the publisher. For inquiries, please contact the Publisher. Please note that this extract contains about 75% of the questions of the entire examination question bank. Revision & Quality Management As part of the continuous revision and updating of the international question database for private pilots (ECQB-PPL), we are constantly looking for competent experts. If you are interested in participating, please contact via e-mail [email protected]. For any content related comments or suggestions for questions, please contact [email protected]. v2015.4 2 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 1 With regard to the forces acting, how can stationary gliding be described? (1,00 P.)  The sum of air forces compensates the gravity force  The sum of air forces acts along the direction of air flow  The lift force compensates the drag force  The sum the air forces acts along with the lift force 2 What is the result of extending flaps with increasing aerofoil camber? (1,00 P.)  Minimum speed descreases  Minimum speed increases  C.G. position moves forward  Maximum permissable speed increases 3 Following a single-wing stall and pitch-down moment, how can a spin be prevented? (1,00 P.)  Rudder opposite lower wing, releasing elevator to build up speed  Pulling the elevator to bring the plane back to normal attitude  Pushing the elevator to build up speed to re-attach airflow on wings  Deflect all rudders opposite to lower wing 4 Considering longitudinal stability, which C.G. position is most dangerous with a normal gliding plane? (1,00 P.)  Position beyond the rear C.G. limit  Position beyond the front C.G. limit  Position far back within permissable C.G. limits  Position too far aside permissable C.G. limits. 5 The static pressure of gases work... (1,00 P.)  in all directions.  only in flow direction.  only in the direction of the total pressure.  only vertical to the flow direction. 6 Which are the correct parameters of the International Standard Atmosphere (ISA)? (1,00 P.)  1013.25 hPa at MSL, 0° C at MSL, environmental lapse rate 2°/1000 ft  1000 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/100 m  1013.25 hPa at 36000 ft, -56,5° C at the tropopause, environmental lapse rate 2°/1000 ft  1013.25 hPa at MSL, +15° C at MSL, environmental lapse rate 2°/1000 ft v2015.4 3 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 7 Bernoulli's equation for frictionless, incompressible gases states that... (1,00 P.)  total pressure = dynamic pressure - static pressure.  static pressure = total pressure + dynamic pressure.  dynamic pressure = total pressure + static pressure.  total pressure = dynamic pressure + static pressure. 8 If surrounded by airflow (v>0), any arbitrarily shaped body produces... (1,00 P.)  drag.  constant drag at any speed.  drag and lift.  lift without drag. 9 All aerodynamic forces can be considered to act on a single point. This point is called... (1,00 P.)  center of gravity.  center of pressure.  lift point.  transition point. 10 The center of pressure is the theoretical point of origin of... (1,00 P.)  all aerodynamic forces of the profile.  gravity forces of the profile.  all forces of the profile.  only the resulting total drag. 11 Number 1 in the drawing corresponds to the... See figure (PFA-010) (1,00 P.)  chord.  chord line.  trailing edge.  camber line. v2015.4 4 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 12 Number 2 in the drawing corresponds to the... See figure (PFA-010) (1,00 P.)  angle of attack.  chord line.  chord.  profile thickness. 13 Number 3 in the drawing corresponds to the... See figure (PFA-010) (1,00 P.)  camber line.  chord line.  chord.  thickness. 14 Number 4 in the drawing corresponds to the... See figure (PFA-010) (1,00 P.)  camber.  thickness.  chord line.  trailing edge. v2015.4 5 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 15 The angle between the chord line and the direction of the oncoming airflow is called... (1,00 P.)  angle of stream.  angle of incidence.  angle of attack.  angle of lift. 16 Which type of boundary layer does the figure show? See figure (PFA-001) BL: Boundary layer SF: Surface (1,00 P.)  Laminar boundary layer  Turbulent boundary layer  Separated boundary layer  Interference layer 17 The angle of attack is the angle between... (1,00 P.)  the chord line and the oncoming airflow.  the chord line and the longitudinal axis of an aeroplane.  the undisturbed airflow and the longitudinal axis of an aeroplane.  the wing and the fuselage of an aeroplane. v2015.4 6 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 18 Which type of boundary layer does the figure show? See figure (PFA-002) BL: Boundary layer SF: Surface (1,00 P.)  Laminar boundary layer  Turbulent boundary layer  Separated boundary layer  Interference layer 19 The ratio of span and mean chord length is referred to as... (1,00 P.)  wing sweep.  trapezium shape.  tapering.  aspect ratio. 20 Which point on the aerofoil is represented by number 2? See figure (PFA-009) (1,00 P.)  Transition point  Separation point  Stagnation point  Center of pressure v2015.4 7 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 21 Which point on the aerofoil is represented by number 3? See figure (PFA-009) (1,00 P.)  Transition point  Separation point  Stagnation point  Center of pressure 22 Which point on the aerofoil is represented by number 4? See figure (PFA-009) (1,00 P.)  Transition point  Separation point  Stagnation point  Center of pressure 23 The start of vortex development is created during which phase of flight? (1,00 P.)  While setting take-off power during take-off run  While setting flaps to lower position  As soon as the aircraft starts moving  When lift is being generated during rotation 24 Which property is specific for a streamlined shape as compared to other shapes? (1,00 P.)  With other parameters remaining constant, it shows the lowest drag  Besides drag it always produces lift  With other parameters remaining constant, it shows the highest drag  Its drag is independent of the airflow speed v2015.4 8 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 25 Which point on the aerofoil is represented by number 1? See figure (PFA-009) (1,00 P.)  Transition point  Separation point  Stagnation point  Center of pressure 26 What pattern can be found at the stagnation point? (1,00 P.)  The laminar boundary layer changes into a turbulent boundary layer  Streamlines are divided into airflow above and below the profile  The boundary layer starts separating on the upper surface of the profile  All aerodynamic forces can be considered as attacking at this single point 27 Which of the following options describes the pressure pattern at a lift-generating wing profile passed by airflow? (1,00 P.)  Pressure below remains unchanged, lower pressure is created above the profile  High pressure is created above, lower pressure below the profile  Low pressure is created above, higher pressure below the profile  Pressure above remains unchanged, higher pressure is created below the profile 28 The position of the the center of pressure at a positively shaped profile... (1,00 P.)  moves to the trailing edge while the angle of attack becomes smaller.  does not move since it is independent of the angle of attack.  moves to the leading edge while the angle of attack becomes smaller.  is located at approximately 25% of the chord, measured from the leading edge. 29 The position of the the center of pressure at a positively shaped profile... (1,00 P.)  moves to the leading edge while the angle of attack becomes greater.  Does not move and it is independent of the angle of attack.  moves to the leading edge while the angle of attack becomes smaller.  is located at approximately 25% of the chord, measured from the leading edge. v2015.4 9 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 30 In which way does the position of the center of pressure move at a positively shaped profile with increasing angle of attack? (1,00 P.)  It moves forward first, then backward  It moves backward until reaching the critical angle of attack  It moves forward until reaching the critical angle of attack  It moves to the wing tips 31 During a regular flight, shortly before stalling the aircraft, what is approximately directly proportional to the lift of the wing? (1,00 P.)  Angle of attack  Angle of incidence  Aileron deflection  Elevator deflection 32 Which statement about lift and angle of attack is correct? (1,00 P.)  Increasing the angle of attack too far may result in a loss of lift and an airflow separation  Increasing the angle of attack results in less lift being generated by the aerofoil  Decreasing the angle of attack results in more lift being generated by the aerofoil  Too large angles of attack can lead to an exponential increase in lift 33 Which statement about the airflow around an aerofoil is correct if the angle of attack increases? (1,00 P.)  The stagnation point moves up  The stagnation point moves down  The center of pressure moves down  The center of pressure moves up 34 Which statement about the airflow around an aerofoil is correct if the angle of attack decreases? (1,00 P.)  The center of pressure moves forward  The stagnation point moves down  The stagnation point remains constant  The center of pressure moves aft v2015.4 10 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 35 The angle (alpha) shown in the figure is referred to as... See figure (PFA-003) DoF: direction of airflow (1,00 P.)  angle of incidence.  lift angle.  angle of inclination.  angle of attack. 36 With a constant angle of incidence, how is the change of the profile shape called? (1,00 P.)  Aspect ratio  Geometric washout  Wing span  Aerodynamic washout 37 In order to improve the stall characteristics of an aircraft, the wing is twisted outwards (the angle of incidence varies spanwise). This is known as... (1,00 P.)  geometric washout.  arrow shape.  aerodynamic washout.  V-form. 38 Which option states a benefit of aerodynamic washout? (1,00 P.)  At high angles of attack the effectiveness of the aileron is retained as long as possible  Structurally the wing is made more rigid against rotation  Greater hardness because the wing can withstand more torsion forces  With the washout the form drag reduces at high speeds v2015.4 11 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 39 Which statement concerning the angle of attack is correct? (1,00 P.)  Increasing the angle of attack results in decreasing lift  The angle of attack cannot be negative  The angle of attack is constant throughout the flight  A too large angle of attack may result in a loss of lift 40 If you double the airflow speed, how does the parasite drag coefficient change? (1,00 P.)  It is quadrupled  It is doubled  It does not change  It is octuplicated 41 The drag coefficient... (1,00 P.)  cannot be lower than a non-negative, minimal value.  may range from zero to an infinite positive value.  increases with increasing airspeed.  is proportional to the lift coefficient. 42 Pressure compensation on an aerofoil occurs at the... (1,00 P.)  leading edge.  wing tips.  trailing edge.  wing roots. 43 Which of the following options is likely to produce large induced drag? (1,00 P.)  Large aspect ratio  Tapered wings  Small aspect ratio  Low lift coefficients 44 Induced drag is generated... (1,00 P.)  at the outer part of the ailerons.  at the trailing edge of the wing.  at the front part of the aisle.  at the lower part of the gear. v2015.4 12 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 45 Where is interference drag generated? (1,00 P.)  At the ailerons  At the the gear  Near the wing tips  At the wing root 46 Which curve represents the total drag? See Appendix (PFA-011) (1,00 P.)  1  2  3  4 47 Which curve represents the induced drag? See Appendix (PFA-011) (1,00 P.)  1  2  3  4 v2015.4 13 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 48 Which curve represents the parasite drag? See Appendix (PFA-011) (1,00 P.)  1  2  3  4 49 Pressure drag, interference drag and friction drag belong to the group of the... (1,00 P.)  induced drag.  total drag.  parasite drag.  main resistance. 50 What kind of drag is NOT part of the parasite drag? (1,00 P.)  Skin-friction drag  Form drag  Interference drag  Induced drag 51 What statement about parasite drag is correct? (1,00 P.)  Parasite drag increases with increasing airspeed  Parasite drag decreases with increasing airspeed  Parasite drag has a minimum at a certain speed and increases at higher as well as lower speeds  Parasite drag has a maximum at a certain speed and decreases at higher as well as lower speeds v2015.4 14 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 52 How do induced drag and parasite drag change with increasing airspeed during a horizontal and stable cruise flight? (1,00 P.)  Induced drag decreases and parasite drag increases  Induced drag increases and parasite drag increases  Parasite drag decreases and induced drag increases  Parasite drag decreases and induced drag decreases 53 Which of the listed wing shapes has the lowest induced drag? (1,00 P.)  Elliptical shape  Trapezoidal shape  Rectangular shape  Double trapezoidal shape 54 Which type of drag is directly connected to lift-generation on an aerofoil? (1,00 P.)  Induced drag  Skin-friction dra  Parasite drag  Interference drag 55 Which effect does a decreasing airspeed have on the induced drag during a horizontal and stable cruise flight? (1,00 P.)  The induced drag will increase  The induced drag will slightly decrease  The induced drag will remain constant  The induced drag will collapse 56 Which statement about induced drag during the horizontal cruise flight is correct? (1,00 P.)  Induced drag increases with increasing airspeed  Induced drag decreases with increasing airspeed  Induced drag has a minimum at a certain speed and increases at higher as well as lower speeds  Induced drag has a maximum at a certain speed and decreases at higher as well as lower speeds 57 The total drag acts in the direction of... (1,00 P.)  the airflow.  the chord line.  the longitudinal axis of the airplane.  the horizon. v2015.4 15 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 58 The total drag consists of which parts of drag? (1,00 P.)  Induced drag and friction drag  Parasite drag and interference drag  Friction drag and interference drag  Parasite drag and induced drag 59 In which mentioned situation is the total drag at its minimum? (1,00 P.)  Parasite drag is equal to induced drag  Parasite drag is twice as much as induced drag  Induced drag is twice as much as parasite drag  Induced drag is smaller than parasite drag 60 Which statement about total drag is correct? (1,00 P.)  Total drag increases with increasing airspeed  Total drag decreases with increasing airspeed  Total drag has a minimum at a certain speed and increases at higher as well as lower speeds  Total drag has a maximum at a certain speed and decreases at higher as well as lower speeds 61 Which kinds of drag contribute to total drag? (1,00 P.)  Induced drag, form drag, skin-friction drag  Form drag, skin-friction drag, interference drag  Interference drag and parasite drag  Induced drag and parasite drag 62 What influence does the ground effect have on the landing distance? (1,00 P.)  The landing distance decreases in any case  The landing distance increases in case of tailwind  The landing distance increases in any case  The landing distance decreases in case of tailwind 63 How do lift and drag change when approaching a stall condition? (1,00 P.)  Lift and drag increase  Lift and drag decrease  Lift decreases and drag increases  Lift increases and drag decreases v2015.4 16 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 64 In case of a stall it is important to... (1,00 P.)  increase the angle of attack and reduce the speed.  increase the bank angle and reduce the speed.  decrease the angle of attack and increase the speed.  increase the angle of attack and increase the speed. 65 If the angle of attack increases, at which part of the wing will the stall begin? (1,00 P.)  Bottom side near the leading edge  Top side near the trailing edge  Bottom side near the trailing edge  Top side near the leading edge 66 During a stall, the lift... (1,00 P.)  increases and drag decreases.  increases and drag increases.  decreases and drag decreases.  decreases and drag increases. 67 The critical angle of attack... (1,00 P.)  is independent of the weight.  decreases with forward center of gravity position.  increases with backward center of gravity position.  changes with increasing weight. 68 What leads to a decreased stall speed Vs (IAS)? (1,00 P.)  Decreasing weight  Lower density  Lower altitude  Higher load factor 69 Stall speed... (1,00 P.)  increases with increasing weight.  decreases with increasing weight.  does not depend on the weight.  increases with increasing wing span. v2015.4 17 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 70 The stall warning will be activated just before reaching which speed? (1,00 P.)  VNE  VS  VR  VX 71 In motorplanes the stall warning is usually activated by a change of... (1,00 P.)  the center of pressure.  the center of gravity.  the stagnation point.  the transition point. 72 How should the pilot react to an engaged stall warning? (1,00 P.)  Raise the nose to decrease airspeed  Pull the elevator, increase power  Pull the elevator, decrease power  Push the elevator, increase power 73 Which statement regarding a spin is correct? (1,00 P.)  During recovery the ailerons should be kept neutral  During the spin the speed constantly increases  Only very old aeroplanes have a risk of spinning  During recovery the ailerons should be crossed 74 When extending the flaps for landing at constant angle of attack, in which way does the lift coefficient change far before reaching the maximum lift coefficient? (1,00 P.)  It increases  It decreases  It is not possible to define  It remains constant 75 Flap extention causes... (1,00 P.)  an increased glide angle and an increased minimum speed.  a decreased glide angle and an increased minimum speed.  a decreased glide angle and a decreased minimum speed.  an increased glide angle and decreased minimum speed. v2015.4 18 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 76 With regard to flaps, which of the following options provides a lift-increasing effect? (1,00 P.)  Decreasing the form drag  Increasing the aerofoil camber  Decreasing the angle of attack  Lowering the induced drag 77 Which factor can be changed by deploying flaps for landing? (1,00 P.)  The trim condition  The effectiveness of the ailerons  The position of the center of gravity  The twist effect of the engine 78 What is the principle of a Fowler flap? (1,00 P.)  The rear part of the wing is folded down  At high angles of attack a part of the leading edge lifts  A profile-like flap is extended from the trailing edge of the wing  A flap from the rear bottom side of the wing is folded down 79 What kind of landing aids may not be retracted suddenly near the ground? (1,00 P.)  Spoilers  Airbrakes  Flaps  Schempp-Hirth flaps 80 The increase in lift from a landing flap is based on... (1,00 P.)  an increase of the effective angle of attack.  a decrease of the form drag.  a decrease of the angle of attack.  a decrease of the induced drag. 81 Why are the flaps usually not fully extended at take-off? (1,00 P.)  Because the aeroplane would have a too heavy nose-down moment  Because the drag would be too high  Because the lift would be too high  Becasue the flaps could be overstressed v2015.4 19 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 82 A take-off with flaps in take-off position causes... (1,00 P.)  an increased rate of climb.  a decrease in drag.  an increased acceleration.  a shortening of the take-off run. 83 Provided that no other procedure is described in the Aircraft Operating Handbook, after increasing the engine power in a go-around, the flaps may... (1,00 P.)  be retracted to a middle position.  not be operated up to the minimum safe altitude.  be fully retracted without any delay.  remain fully extended until reaching the traffic pattern. 84 How do lift and drag change when setting flaps to a lower position? (1,00 P.)  Lift increases, drag increases  Lift increases, drag decreases  Lift decreases, drag increases  Lift decreases, drag decreases 85 What has to be considered when flaps are retracted? (1,00 P.)  Retraction of flaps is always possible without any loss of lift  Close to the ground, flaps may only be retracted stepwise at a safe height  When approaching too low, flaps should be retracted to provide a better gliding angle  When going around, flaps should be fully retracted immediately 86 The boundary layer turns from laminar to turbulent at the... (1,00 P.)  separation point.  transition point.  center of pressure.  stagnation point. 87 The laminar layer on the aerofoil is located between... (1,00 P.)  the transition point and the separation point.  the stagnation point and the transition point.  the stagnation point and the center of pressure.  the transition point and the center of pressure. v2015.4 20 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 88 What types of boundary layers can be found on an aerofoil? (1,00 P.)  Laminar boundary layer along the complete upper surface with non-separated airflow  Turbulent boundary layer along the complete upper surface with separated airflow  Turbulent layer at the leading wing areas, laminar boundary layer at the trailing areas  Laminar layer at the leading wing areas, turbulent boundary layer at the trailing areas 89 How does a laminar boundary layer differ from a turbulent boundary layer? (1,00 P.)  The turbulent boundary layer can follow the airfoil camber at higher angles of attack  The laminar boundary layer is thinner and provides more skin-friction drag  The turbulent boundary layer is thicker and provides less skin-friction drag  The laminar boundary layer produces lift, the turbulent boundary layer produces drag 90 In icing conditions, at which point will the most ice arise on an aeroplane? (1,00 P.)  On the upper and lower side of the control surfaces  On the pitot tube and the static pressure ports  On the upper und lower side of the wing's trailing edge  On all frontal areas of the airframe, the wings, and the tail 91 "Lateral stability" is referred to as stability around which axis? (1,00 P.)  Lateral axis  Vertical axis  Longitudinal axis  Rotational axis 92 What structural item provides lateral stability to an airplane? (1,00 P.)  Vertical tail  Elevator  Differential aileron deflection  Wing dihedral 93 Which statement describes a situation of static stability? (1,00 P.)  An aircraft distorted by external impact will maintain the deflected position  An aircraft distorted by external impact will return to the original position  An aircraft distorted by external impact will tend to an even more deflected position  An aircraft distorted by external impact can return to its original position by rudder input v2015.4 21 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 94 A statically unstable aeroplane... (1,00 P.)  is always dynamically stable.  becomes more stable with a rear centre of gravity.  can never be dynamically stable.  becomes more stable at higher speeds. 95 Which force does NOT act during straight and level flight? (1,00 P.)  Lift force  Centrifugal force  Gravitational force  Drag force 96 Which constructive feature is shown in the figure? See figure (PFA-006) L: Lift (1,00 P.)  Directional stability by lift generation  Lateral stability by wing dihedral  Differential aileron deflection  Longitudinal stability by wing dihedral 97 Which constructive feature provides longitudinal stability to an airplane in normal configuration (empennage at tail)? (1,00 P.)  Differential aileron deflection  Downforce at the elevator  Positive wing dihedral  Trim plate at the tailfin v2015.4 22 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 98 "Longitudinal stability" is referred to as stability around which axis? (1,00 P.)  Vertical axis  Longitudinal axis  Lateral axis  Propeller axis 99 Stability around which axis is strongly influenced by the center of gravity's position? (1,00 P.)  Longitudinal axis  Vertical axis  Gravity axis  Lateral axis 100 "Directional stability" is referred to as stability around which axis? (1,00 P.)  Vertical axis  Directional axis  Lateral axis  Longitudinal axis 101 What structural item provides directional stability to an airplane? (1,00 P.)  Wing dihedral  Large vertical tail  Large elevator  Differential aileron deflection 102 An aircraft can move around which axes? (1,00 P.)  Vertical axis, front axis, longitudinal axis  Central axis, vertical axis, longitudinal axis  Lateral axis, longitudinal axis, vertical axis  Longitudinal axis, vertical axis, front axis 103 Rotation around the vertical axis is called... (1,00 P.)  yawing.  slipping.  rolling.  pitching. v2015.4 23 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 104 Rotation around the lateral axis is called... (1,00 P.)  yawing.  pitching.  rolling.  stalling. 105 Rotation around the longitudinal axis is called... (1,00 P.)  pitching.  yawing.  yolling.  rotating. 106 The critical angle of attack... (1,00 P.)  decreases with a rear centre of gravity.  is not changed by different aircraft weights.  increases with a front centre of gravity.  is changed by different aircraft weights. 107 In straight and level flight with constant performance of the engine, the angle of attack at the wing is... (1,00 P.)  greater than in a climb.  smaller than in a climb.  greater than at take-off.  smaller than in a descent. 108 What is the function of the elevator (among other things)? (1,00 P.)  To stabilise the aeroplane around the longitudinal axis  To stabilise the aeroplane around the vertical axis  To stabilise the aeroplane around the lateral axis  To initiate a curve around the vertical axis 109 The elevator deflection for a specific maneuver... (1,00 P.)  is increased with a front centre of gravity.  is increased at high speeds.  is increased with a rear centre of gravity.  is independent of the speed. v2015.4 24 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 110 The elevator deflection during take-off rotation... (1,00 P.)  is increased for a front centre of gravity.  is increased at high speeds.  is increased for a rear centre of gravity.  is independent of the speed. 111 Rotation around the lateral axis is called... (1,00 P.)  pitch.  roll.  yaw.  slip. 112 The elevator moves an aeroplane around the... (1,00 P.)  vertical axis.  lateral axis.  longitudinal axis.  elevator axis. 113 Deflecting the elevator upwards results in... (1,00 P.)  lowering the aircraft's nose.  shifting the center of gravity ahead.  shifting the center of gravity backwards.  raising the aircraft's nose. 114 What has to be considered with regard to the center of gravity position? (1,00 P.)  Only correct loading can assure a correct and safe center of gravity position.  By moving the elevator trim tab, the center of gravity can be shifted into a correct position.  By moving the aileron trim tab, the center of gravity can be shifted into a correct position.  The center of gravity's position can only be determined during flight. 115 A rotation around the vertical axis is called... (1,00 P.)  pitch.  slip.  roll.  yaw. v2015.4 25 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 116 Rudder deflections result in a turn of the aeroplane around the... (1,00 P.)  vertical axis.  lateral axis.  longitudinal axis.  rudder axis. 117 Deflecting the rudder to the left causes... (1,00 P.)  yawing of the aircraft to the right.  yawing of the aircraft to the left.  pitching of the aircraft to the left.  pitching of the aircraft to the right. 118 Which deflection of the ailerons can be observed during a turn to the left? (1,00 P.)  Both ailerons upwards  Both ailerons downwards  Left aileron upwards, right aileron downwards  Left aileron downwards, right aileron upwards 119 Which deflection of differential ailerons can be observed during a turn to the right? (1,00 P.)  The right aileron moves down more than the left aileron moves up  The right aileron moves up more than the left aileron moves down  The right aileron moves up more than the left aileron  The right aileron moves down more than the left aileron 120 What is the advantage of differential aileron movement? (1,00 P.)  The adverse yaw is higher  The ratio of the drag coefficient to lift coefficient is increased  The drag of the downwards deflected aileron is lowered and the adverse yaw is smaller  The total lift remains constant during aileron deflection 121 Which design feature can compensate for adverse yaw? (1,00 P.)  Aileron trim  Differential aileron defletion  Wing dihedral  Full deflection of the aileron v2015.4 26 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 122 Differential aileron deflection is used to... (1,00 P.)  reduce wake turbulence.  avoid a stall at low angles of attack.  keep the adverse yaw low.  increase the rate of descent. 123 Which constructive feature reduces adverse yaw? (1,00 P.)  Differential aileron deflection  T-tail  Winglets  Wing dihedral 124 The right aileron deflects upwards, the left downwards. How does the aircraft react? (1,00 P.)  Rolling to the left, no yawing  Rolling to the left, yawing to the right  Rolling to the right, yawing to the right  Rolling to the right, yawing to the left 125 The aerodynamic rudder balance... (1,00 P.)  reduces the control surfaces.  reduces the control stick forces.  delays the stall.  improves the rudder effectiveness. 126 Which constructive feature provides less stick forces? (1,00 P.)  Differential aileron deflection  Aerodynamic rudder balance  Vortex generators  T-tail 127 What is the function of the static rudder balance? (1,00 P.)  To prevent control surface flutter  To limit the control stick forces  To increase the control stick forces  To trim the controls almost without any force v2015.4 27 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 128 How can flutter at the controls be prevented? (1,00 P.)  Static rudder balance  Aerodynamic rudder balance  Higher speed  Lower speed 129 During cruise flight with constant power setting, an aircraft shows a permanent tendency to raise the nose. How can this tendency be eliminated? (1,00 P.)  By shifting the center of gravity backwards  By elevator deflection upwards  By deflecting the elevator trim tab downwards  By deflecting the elevator trim tab upwards 130 What is a bendable trim tab? (1,00 P.)  A balance mass at a control surface  A term for a rudder balance  A trim device adjustable in flight  A fixed tab attached to the rudder or the aileron 131 What is the task of trim tabs? (1,00 P.)  Reduction of adverse yaw  Ensuring dynamic stability  Avoiding permanent stick forces  Adjusting bank angle to center of gravity position 132 The trim tab at the elevator is defelected upwards. In which position is the corresponding indicator? (1,00 P.)  Neutral position  Laterally trimmed  Nose-up position  Nose-down position 133 What describes "wing loading"? (1,00 P.)  Wing area per weight  Drag per wing area  Drag per weight  Weight per wing area v2015.4 28 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 134 What has to be considered regarding VNE? (1,00 P.)  It must not be exceeded in any case  It may be exceeded only in smooth air  It may be briefly exceeded in turbulent air  It depends on loading and turbulence whether it may be exceeded 135 Through which factor listed below does the load factor increase during cruise flight? (1,00 P.)  An upward gust  Higher aeroplane weight  A forward centre of gravity  Lower air density 136 Through which factor listed below does the load factor decrease during cruise flight? (1,00 P.)  A downward gust  An aft centre of gravity  Higher air density  Lower aeroplane weight 137 Which statement regarding the "constant-speed propeller" is correct? (1,00 P.)  The propeller keeps the airspeed constant  The pitch of the propeller rises with higher speeds  The RPM decreases with lower speeds  The set RPM is kept constant by the motor power (MAP) 138 What is the advantage of a "constant-speed propeller" compared to a "fixed-pitch propeller"? (1,00 P.)  It is more efficient over a greater speed range  It is less susceptible to interference by technical defects  It is designed to generate a higher thrust  It has a larger surface area and produces more thrust 139 The change in pitch at a propeller blade from the root to the tip ensures... (1,00 P.)  a nearly constant load by a constant effective angle of attack over the entire length of the blade.  the largest possible angle of attack at the blade tip.  that the most thrust is produced at the blade root.  that the most thrust is produced at the blade tip. v2015.4 29 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 140 After an engine failure, the windmilling propeller... (1,00 P.)  generates drag rather than thrust.  generates neither thrust nor drag.  improves the properties of the glide.  has a greater pitch in feathered position. 141 During a descent at idle power with constant speed, the propeller lever is moved backwards. How do the propeller pitch and sink rate change? (1,00 P.)  Propeller pitch is increased, sink rate is decreased  Propeller pitch is increased, sink rate is increased  Propeller pitch is decreased, sink rate is decreased  Propeller pitch is decreased, sink rate is increased 142 Point number 4 in the figure indicates which flight state? See figure (PFA-008) (1,00 P.)  Minimum drag  Best gliding angle  Inverted flight  Stall v2015.4 30 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 143 Point number 1 in the figure indicates which flight state? See figure (PFA-008) (1,00 P.)  Minimum drag  Best gliding angle  Inverted flight  Stall 144 Point number 3 in the figure indicates which flight state? See figure (PFA-008) (1,00 P.)  Minimum drag  Best gliding angle  Inverted flight  Stall v2015.4 31 ECQB-PPL (AT) 51 Principles of Flight (Aeroplane) PPL(A) 145 To keep speed and altitude constant during a turn, compared to horizontal flight, the pilot has to... (1,00 P.)  increase the angle of attack and increase the thrust.  keep the angle of attack constant and increase the thrust.  decrease the angle of attack and increase the thrust.  increase the angle of attack and keep the thrust constant. 146 The bank in a two-minute turn (rate one turn) depends on the... (1,00 P.)  TAS.  weight.  load factor.  wind. 147 In a co-ordinated turn, how is the relation between the load factor (n) and the stall speed (Vs)? (1,00 P.)  N is greater than 1, Vs is greater than in straight and level flight.  N is greater than 1, Vs is smaller than in straight and level flight.  N is smaller than 1, Vs is smaller than in straight and level flight.  N is smaller than 1, Vs is greater than in straight and level flight. 148 Which statement concerning a flight during a turn is correct? (1,00 P.)  More lift than in straight and level flight is needed  The same amount of lift as in straight and level flight is needed  Less lift than in straight and level flight is needed.  Less lift than in a descent is needed. 149 How is the balance of forces affected during a turn? (1,00 P.)  Lift force must be increased to compensate for the sum of centrifugal and gravitational force  A lower lift force compensates for a lower net force as compared to level flight  The horizontal component of the lift force during a turn is the centrifugal force  The net force results from superposition of gravity and centripetal forces v2015.4 32