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Exameneisen PPL Flight performance and planning (Mass and balance + Performance – aeroplanes) + Principles of flight – aeroplanes + Operational procedures – alleen PPLA en LAPLA

Algemene informatie

Opgesteld door: CBR divisie CCV

Categoriecode en exameninformatie:

LVPAFPP (PPLA, LAPLA), digitaal, 22 meerkeuzevragen, cesuur 75% (17 van de 22 vragen goed)

Bijzonderheden: Geen

Vastgesteld door:

Technische Commissie Flight Performance and Planning (Mass and balance + Performance – aeroplanes) en Principles of flight – aeroplanes en Operational procedures

Beoordeeld door:

Logistiek, Transport en Personenvervoer raad; kamer 3: Luchtvaart op 6 maart 2023

Goedgekeurd door:

Divisiemanager CCV op 8 maart 2023

Ingangsdatum:

1 juli 2023

Datum laatste aanpassing:

8 maart 2023

Toelichting gebruik toetstermen:

Eindtermen: Dit zijn de hoofdonderwerpen die in het examen voorkomen. Hierin staat 'ruim' omschreven wat er in het examen terug kan komen.
Toetstermen: Dit zijn onderdelen van een eindterm. Hierin staat meer uitgebreid omschreven wat er in het examen terug kan komen.
Tax: Dit is de taxonomiecode van Romiszowski. Deze code geeft aan op welk niveau de vragen over een toetsterm gesteld worden.

Toelichting taxonomiecode:

F = Feitelijke kennis. De kandidaat kan feiten reproduceren (herkennen of herinneren).
B = Begripsmatige kennis. De kandidaat kan begrippen of principes omschrijven.
R = Reproductieve vaardigheden. De kandidaat kan acties uitvoeren die volgens een vastgelegde procedure verlopen.
P = Productieve vaardigheden. De kandidaat kan acties uitvoeren waarbij hij zijn eigen creativiteit en inzicht nodig heeft.

Eindterm 031 01 00 00 Purpose of mass-and-balance considerations

031 01 01 00 Mass Limitations


01	Describe the relationship between aircraft mass and structural stress. Remark - see also 021 01 01 00.	Tax: B, PPLA
02	Describe that mass must be limited to ensure adequate margins of strength.	Tax: B, PPLA


01	Define commonly used Air Traffic Control abbreviations:Flight conditions; Airspace; Services; Time; Miscellaneous.	Tax: B, PPLA
02	Describe that aircraft mass must be limited to ensure adequate aircraft performance.	Tax: B, PPLA

031 01 02 00 Centre-of-gravity (CG) limitations


01	Describe the relationship between CG position and stability/controllability of the aircraft.	Tax: B, PPLA
02	Describe the consequences if CG is in front of the forward limit.	Tax: B, PPLA
03	Describe the consequences if CG is behind the aft limit.	Tax: B, PPLA


01	Describe the relationship between CG position and aircraft performance.	Tax: B, PPLA
02	Describe the effects of CG position on performance parameters (speeds, altitude, endurance and range).	Tax: B, PPLA

Eindterm 031 02 00 00 Loading

031 02 01 00 Terminology


01	Define the following mass terms:basic empty mass; take-off mass; landing mass; ramp/taxi mass; gross mass (the actual mass of an aircraft at a specified time); zero fuel mass.	Tax: F, PPLA


01	Define the following load terms: block fuel; taxi fuel; trip fuel; reserve fuel (contingency, alternate, final reserve fuel); extra fuel	Tax: F, PPLA
02	Explain the relationship between the various load-and-mass components listed in 031 02 01 01 and 031 02 01 02.	Tax: B, PPLA
03	Calculate the mass of particular components from other given components.	Tax: P, PPLA
04	Convert fuel mass, fuel volume and fuel density given in different units used in aviation.	Tax: R, PPLA

031 02 02 00 Mass limits


01	Define the maximum zero-fuel mass (the maximum permissible mass of an aircraft with no usable fuel).	Tax: F, PPLA
02	Define the maximum ramp/taxi mass	Tax: F, PPLA
03	Define maximum take-off mass.	Tax: F, PPLA
04	Define the maximum landing mass.	Tax: F, PPLA


p01	Describe the following performance and regulated mass limitations: performance-limited take-off mass; performance-limited landing mass; regulated take-off mass; regulated landing mass	Tax: B, PPLA


p01	Describe baggage compartment limitations.	Tax: B, PPLA

031 02 03 00 Mass calculations


03	Calculate the allowed mass for take-off.	Tax: P, PPLA
p01	Calculate the allowed mass for landing.	Tax: P, PPLA

Eindterm 031 04 00 00 Mass and balance details of aircraft

031 04 01 00 Contents of mass-and-balance documentation


01	State where the datum and moment-arms for aircraft can be found.	Tax: F, PPLA
02	Extract appropriate data from given documents.	Tax: R, PPLA
03	Define 'datum' (reference point), 'moment arm' and 'moment'.	Tax: F, PPLA


01	State where the CG position for an aircraft at basic empty mass can be found.	Tax: F, PPLA
02	State where the CG limits for an aircraft can be found.	Tax: F, PPLA
03	Describe the different forms in presenting CG position as distance from datum or other references.	Tax: B, PPLA
04	Explain the meaning of centre of gravity (CG).	Tax: B, PPLA

031 04 03 00 Extraction of basic empty mass (BEM) and CG data from aircraft documentation.


01	Extract values for BEM from given documents.	Tax: R, PPLA


01	Extract values for CG position and moment at BEM from given documents.	Tax: R, PPLA


01	Extract values from given documents for deviation from standard configuration as a result of varying crew, optional equipment, optional fuel tanks etc.	Tax: R, PPLA

Eindterm 031 05 00 00 Determination of cg position

031 05 01 00 Methods


01	Calculate the CG position of an aircraft by using the formula: CG position = sum of moments / total mass.	Tax: P, PPLA


01	Determine the CG position of an aircraft by using the loading graphs given in sample documents.	Tax: R, PPLA

031 05 02 00 Load and trim sheet


01	Explain the principle and the purpose of load sheets.	Tax: B, PPLA
02	Explain the principle and the purpose of trim sheets.	Tax: B, PPLA


01	Add loading data and calculate masses in a sample load sheet.	Tax: P, PPLA
02	Calculate moments and CG positions.	Tax: P, PPLA
03	Check CG position at zero fuel mass and take-off mass to be within CG envelope including last minute changes, if applicable.	Tax: R, PPLA

Eindterm 031 06 00 00 Cargo handling

031 06 03 00 Securement of load


01	Explain the reasons to restrain or secure cargo and baggage.	Tax: B, PPLA

Eindterm 032 01 00 00 Performance – Aeroplanes - General

032 01 02 00 General Performance Theory


p01	Describe the following stages of flight: Take off, Climbing flight, Level flight, Descending flight, Approach and landing	Tax: F, PPLA


02	Define the terms ‘flight path angle’ and ‘flight path gradient’.	Tax: F, PPLA
03	Define the terms ‘descent angle’ and ‘descent gradient’.	Tax: F, PPLA
04	Explain the difference between climb/descent angle (air-mass related) and flight path angle (ground related).	Tax: B, PPLA
05	Define ‘service ceiling’ and ‘absolute ceiling’ for single engine aircraft.	Tax: F, PPLA
06	Describe 'clearway' and 'stopway'.	Tax: B, PPLA
07	Describe: take-off run available (TORA); take-off distance available (TODA); accelerate stop distance available (ASDA); Landing Distance Available (LDA) and determine from given data and/or appropriate aerodrome charts.	Tax: B, PPLA
09	Define the terms ‘range’ and ‘endurance’,	Tax: F, PPLA


p01	Name and understand the following factors that affect aeroplane performance, particularly: pressure altitude and temperature; density altitude; wind; aeroplane weight; aeroplane configuration; aerodrome runway surface; aerodrome runway slope; aerodrome runway conditions	Tax: F, PPLA

032 01 03 00 Level flight, range and endurance


05	Describe situations in which a pilot may elect to fly for ‘maximum endurance’ or ‘maximum range’.	Tax: B, PPLA
p01	Explain the effects of power setting, wind, altitude and aircraft configuration on range and endurance.	Tax: B, PPLA

032 01 04 00 Climbing


01	Resolve the forces during a steady climb.	Tax: R, PPLA
02	Define and explain the following terms: speed for best angle of climb (Vx); speed for best rate of climb (Vy).	Tax: F, PPLA
06	Define the terms ‘climb angle’ and ‘climb gradient’.	Tax: F, PPLA
07	Explain the effect of weight on the climb angle and rate of climb, and on the speed for best angle and best rate of climb.	Tax: B, PPLA
08	Explain the effects of pressure altitude and temperature (angle and rate of climb).	Tax: B, PPLA
09	Explain the effect of configuration on climb performance (angle and rate of climb and Vx and Vy).	Tax: B, PPLA

032 01 05 00 Descending


01	Resolve the forces during steady descent and in the glide.	Tax: R, PPLA
p01	Explain the effect of mass, altitude, wind, speed and configuration on the glide distance.	Tax: B, PPLA

Eindterm 032 02 00 00 CS-23 performance class b (single-engine aeroplanes) – theory

032 02 01 00 Airworthiness requirements


01	Define the following speeds according to CS-23: Stall speeds Vs, Vs0 and Vs1; Rotation speed VR; Speed at 50 ft above the take-off surface level; Approach speed (1,3x Vs).	Tax: F, PPLA
02	Describe the limitations on VR and approach speed, and given the appropriate stall speed estimate the values based on these limitations for a single-engine aeroplane.	Tax: B, PPLA

032 02 03 00 Take-off and landing


01	Define the following distances: take-off distance; landing distance; ground-roll distance.	Tax: F, PPLA
02	Explain the effect of flap-setting on the take-off distance and landing ground-roll distance.	Tax: B, PPLA
03	Explain the effects of the following runway (RWY) variables on take-off distances: RWY slope; RWY surface conditions: dry, wet and contaminated; paved and grass; RWY elevation.	Tax: B, PPLA
06	Explain the effect of wind on take-off and landing distance and determine the actual head/tailwind component given runway direction, and wind speed and direction, by use of wind component graphs, mathematical calculations, and rule of thumb.	Tax: B, PPLA
07	Explain why an aeroplane has maximum crosswind limit(s) and determine the crosswind component given runway direction, and wind speed and direction, by use of wind component graphs, mathematical calculations, and rule of thumb.	Tax: B, PPLA
09	Explain the effect of runway conditions on the landing distance.	Tax: B, PPLA
10	Explain the effects of pressure altitude and temperature on the take-off distance, take-off climb, landing distance and approach.	Tax: B, PPLA
p01	Explain the use of a safety factor in take-off and landing calculations.	Tax: B, PPLA
p02	Describe the landing distance and ground roll distance and estimate the effect on the landing distance when the aeroplane is too fast/slow or too high/low.	Tax: B, PPLA

Eindterm 032 03 00 00 CS-23/EU-OPS performance class B – use of aeroplane performance data for single and multi-engine aeroplanes

032 03 03 00 Use of Aeroplane Performance data


p01	Determine the take-off distance and ground roll distance from given aircraft performance data (graphic or tabular data) and airfield data.	Tax: R, PPLA


p01	Determine the landing distance and ground roll distance from given aircraft performance data (graphic or tabular data) and airfield data.	Tax: R, PPLA

Eindterm 081 01 00 00 Principles of flight – Aeroplanes - Subsonic aerodynamics

081 01 01 00 Basic concepts, laws and definitions


01	List the international system of units of measurement (SI) for mass, weight, velocity, density, temperature, pressure, force, power and perform conversion calculations	Tax: F, PPLA
02	Define ‘mass’, ‘force’, and ‘weight’.	Tax: F, PPLA
03	State and interpret Newton’s first and second law of motion.	Tax: F, PPLA
04	Explain air density.	Tax: F, PPLA
05	List the atmospheric properties that effect air density.	Tax: B, PPLA
06	Explain how temperature and pressure changes affect air density.	Tax: F, PPLA
07	Define ‘static pressure’.	Tax: B, PPLA
08	Define ‘dynamic pressure’	Tax: F, PPLA
09	State the formula for ‘dynamic pressure’.	Tax: F, PPLA
11	State Bernoulli´s equation for incompressible flow.	Tax: F, PPLA
12	Define ‘total pressure’.	Tax: F, PPLA
13	Apply Bernoulli’s equation to flow through a venturi system tube for incompressible flow.	Tax: R, PPLA
14	Describe how the IAS is acquired from the pitot-static system.	Tax: B, PPLA
16	Explain the equation of continuity and its application to the flow through a stream tube for incompressible flow.	Tax: B, PPLA
17	Define ‘IAS’, ‘CAS’ and ‘TAS’.	Tax: F, PPLA


01	Describe steady and unsteady airflow.	Tax: B, PPLA
02	Explain the concept of a streamline.	Tax: B, PPLA
04	Explain the difference between two- and three-dimensional airflow.	Tax: B, PPLA


01	Describe the originating point and direction of the resultant force caused by the pressure distribution around an aerofoil.	Tax: B, PPLA
02	Resolve the resultant force into the components 'lift’ and ‘drag’.	Tax: R, PPLA
03	Describe the direction of lift and drag.	Tax: B, PPLA
08	Define ‘angle of attack’ (α) as the angle between the chord line and the undisturbed airflow.	Tax: F, PPLA


01	Describe the following parameter of an aerofoil section: leading edge.	Tax: B, PPLA
02	Describe the following parameter of an aerofoil section: trailing edge.	Tax: B, PPLA
03	Describe the following parameter of an aerofoil section: chord line.	Tax: B, PPLA
04	Describe the following parameter of an aerofoil section: chord ratio.	Tax: B, PPLA
06	Describe the following parameter of an aerofoil section: camber line.	Tax: B, PPLA
07	Describe the following parameter of an aerofoil section: camber.	Tax: B, PPLA
09	Describe a symmetrical and an asymmetrical aerofoil section.	Tax: B, PPLA


01	Describe the following parameters of a wing: span.	Tax: B, PPLA
02	Describe the following parameters of a wing: tip and root chord.	Tax: B, PPLA
04	Describe the following parameters of a wing: wing area.	Tax: B, PPLA
05	Describe the following parameters of a wing: wing planform (straight wing and tapered wing).	Tax: B, PPLA
08	Describe the following parameters of a wing: aspect ratio.	Tax: B, PPLA
09	Describe the following parameters of a wing: dihedral angle and anhedral.	Tax: B, PPLA
11	Describe the following parameters of a wing: geometric twist (wash out).	Tax: B, PPLA
12	Describe the following parameters of a wing: angle of incidence (the angle between the aeroplane longitudinal axis and the wing-root chord line).	Tax: B, PPLA

081 01 02 00 The two-dimensional airflow around an aerofoil


01	Describe the streamline pattern around an aerofoil.	Tax: B, PPLA
02	Describe converging and diverging streamlines, and their effect on static pressure and velocity.	Tax: B, PPLA
03	Describe upwash and downwash.	Tax: B, PPLA


01	Describe the stagnation point.	Tax: B, PPLA
02	Explain the movement of the stagnation point as the α changes.	Tax: B, PPLA


01	Describe pressure distribution and local speeds around an aerofoil including effects of camber and α.	Tax: B, PPLA
02	Describe where the minimum local static pressure is typically situated on an aerofoil.	Tax: B, PPLA


01	Define the centre of pressure.	Tax: F, PPLA


01	Describe the influence of α on lift.	Tax: B, PPLA


01	Describe the CL- α graph.	Tax: B, PPLA
02	Explain the significant points: point where the curve crosses the horizontal axis (zero lift); point where the curve crosses the vertical axis (α = 0); point where the curve reaches its maximum (CLMAX).	Tax: B, PPLA

081 01 03 00 The coefficients


01	Explain the lift formula and the factors that affect lift.	Tax: B, PPLA
02	Describe the effect of camber on the CL - α graph (symmetrical and positively cambered aerofoils).	Tax: B, PPLA
04	Define CLMAX (maximum lift coefficient) and αCRIT (stalling α) on the graph.	Tax: F, PPLA


01	Describe the two-dimensional drag formula and the CD- α curve.	Tax: B, PPLA
02	Discuss the effect of the shape of a body, cross-sectional area, and surface roughness on drag coefficient.	Tax: B, PPLA

081 01 04 00 Three-dimensional airflow around an aeroplane


01	Describe the general streamline pattern around the wing, tail section and fuselage.	Tax: B, PPLA
02	Explain and describe the causes of spanwise flow over top and bottom surfaces.	Tax: B, PPLA
03	Describe wing tip vortices and the contribution to downwash behind the wing.	Tax: B, PPLA
04	Explain why wing tip vortices vary with α.	Tax: B, PPLA
06	Describe the causes, distribution and duration of the wake turbulence behind an aeroplane.	Tax: B, PPLA


01	State that induced drag is caused by angle of attack.	Tax: B, PPLA
03	Describe the relationship between induced drag and total drag in straight and level flight with variable speed.	Tax: B, PPLA
04	Describe the effect of mass on induced drag at a given IAS.	Tax: B, PPLA
05	Describe the means to reduce induced drag:aspect ratio; winglets; tip tanks.	Tax: B, PPLA
08	Explain induced and effective local α.	Tax: B, PPLA
09	Explain the influence of the induced α on the direction of the lift vector.	Tax: B, PPLA
10	Explain the relationship between induced drag and: speed; aspect ratio.	Tax: B, PPLA

081 01 05 00 Total drag


01	State that total drag consists of parasite drag and induced drag	Tax: F, PPLA


01	Describe the types of drag that are included in parasite drag.	Tax: B, PPLA
02	Describe form (pressure) drag and the factors which affect its magnitude.	Tax: B, PPLA
03	Describe interference drag and the factors which affect its magnitude.	Tax: B, PPLA
04	Describe friction drag and the factors which affect its magnitude.	Tax: B, PPLA


01	Describe the relationship between parasite drag and speed.	Tax: B, PPLA


01	Explain the total drag – speed graph and the constituent drag components.	Tax: B, PPLA
02	Indicate the speed for minimum drag.	Tax: B, PPLA


01	Describe the effect of aeroplane gross mass on total drag.	Tax: B, PPLA
02	Describe the effect of pressure altitude on total drag.	Tax: B, PPLA
03	Describe speed stability from the graph.	Tax: B, PPLA
04	Describe non-stable, neutral and stable IAS regions.	Tax: B, PPLA
05	Explain what happens to the IAS and drag in the non-stable region if speed suddenly decreases and why this could occur.	Tax: B, PPLA

081 01 06 00 Ground effect


01	Explain the influence of ground effect on wing tip vortices and drag.	Tax: B, PPLA


01	Describe the influence of ground effect on take-off and landing characteristics and performance of an aeroplane.	Tax: B, PPLA

081 01 09 00 C_Lmax augmentation


01	Describe or identify the following types of trailing-edge flaps:split flaps; plain flaps; slotted flaps; Fowler flaps.	Tax: B, PPLA
02	Describe how the wing's effective camber increases the CL and CD, and the reasons why this can be beneficial.	Tax: B, PPLA
03	Describe their effect on: the location of CP; pitching moments (due to wing CP movement);stall speed.	Tax: B, PPLA
04	Compare their influence on the CL- α graph: indicate the variation in CL at any given α.; indicate their effect on CLMAX; indicate their effect on critical α.	Tax: R, PPLA
07	Describe flap asymmetry: explain the effect on aeroplane controllability.	Tax: B, PPLA
08	Describe trailing-edge flap effect on take-off and landing: explain the advantages of lower-nose attitudes; explain why take-off and landing speeds/distances are reduced.	Tax: B, PPLA
09	Explain the effects of flap-setting errors, such as mis-selection and premature/late extension or retraction of flaps, on:take-off and landing distance and speeds; climb and descent performance.	Tax: B, PPLA


01	Describe slats.	Tax: B, PPLA
02	Describe the function of the slot.	Tax: B, PPLA
04	Explain the effect of slats on the stall speed, also in comparison with trailing edge flaps.	Tax: B, PPLA
05	Compare their influence on the CL- α graph, compared with trailing-edge flaps and a clean wing: indicate the effect of leading-edge devices on CLMAX; explain how the CL curve differs from that of a clean wing; indicate the effect of leading-edge devices on αCRIT.	Tax: B, PPLA
07	Describe slat asymmetry: describe the effect on aeroplane controllability.	Tax: B, PPLA
08	Explain the reasons for using leading-edge high-lift devices on take-off and landing: explain the disadvantage of increased nose-up attitudes; explain why take-off and landing speeds/distances are reduced.	Tax: B, PPLA

081 01 12 00 Aerodynamic degradation


01	Describe the locations on an aeroplane where ice build-up will occur during flight.	Tax: B, PPLA
02	Explain the aerodynamic effects of ice and other contaminants on:lift (maximum CL; drag; stall speed; αCRIT; stability and controllability.	Tax: B, PPLA
03	Explain the aerodynamic effects of icing on high lift devices during take-off, landing and low speeds.	Tax: B, PPLA

Eindterm 081 03 00 00 Stall and upset prevention and recovery

081 03 01 00 The stall


01	Define the ‘boundary layer’.	Tax: F, PPLA
02	Describe the thickness of a typical laminar and turbulent boundary layer.	Tax: B, PPLA
03	Describe the properties, advantages and disadvantages of the laminar boundary layer.	Tax: B, PPLA
04	Describe the properties, advantages and disadvantages of the turbulent boundary layer.	Tax: B, PPLA
05	Define the ‘transition point’.	Tax: F, PPLA
06	Explain why the laminar boundary layer separates easier than the turbulent layer does.	Tax: F, PPLA
08	Define the ‘separation point’ and describe its location as a function of α.	Tax: F, PPLA
09	Define αCRIT.	Tax: F, PPLA
10	Describe in straight and level flight the influence of increasing the α on: the forward stagnation point; the pressure distribution; the CP location (straight wing); CL; CD and D (drag); pitching moments.	Tax: B, PPLA
11	Explain what causes the possible natural buffet on the controls and on the aeroplane in a pre-stall condition.	Tax: B, PPLA
12	Describe the effectiveness of the flight controls in a pre-stall condition.	Tax: B, PPLA
13	Describe and explain the normal post-stall behaviour of a straight-wing aeroplane.	Tax: B, PPLA
14	Describe the effect and dangers of using the controls close to the stall.	Tax: B, PPLA


01	Define the stall speed.	Tax: F, PPLA
02	Solve VS1G from the lift formula given varying CL.	Tax: R, PPLA
03	Describe and explain the influence of the following parameters on the stall speed: CG; thrust component; propeller slipstream; mass; wing contamination; altitude (neglecting compressibility effects); wing loading.	Tax: B, PPLA
04	Define the ‘load factor n’.	Tax: F, PPLA
05	Explain why the load factor increases in a turn.	Tax: B, PPLA
06	Explain why the load factor increases in a pull-up and decreases in a push-over manoeuvre.	Tax: B, PPLA
08	Describe and explain the influence of the load factor 'n’ on the stall speed.	Tax: B, PPLA
09	Explain the expression ‘accelerated stall’.	Tax: B, PPLA


01	Describe the initial stall sequence on a rectangular planform.	Tax: B, PPLA
02	Explain the purpose of washout.	Tax: B, PPLA
03	Discuss the use of ailerons on initial stall.	Tax: B, PPLA


01	Explain why stall warning is necessary.	Tax: B, PPLA
02	Describe aerodynamic and artificial stall warnings.	Tax: B, PPLA
03	Describe why CS-23 require a margin to stall speed for take-off and landing speeds.	Tax: B, PPLA
04	Describe: buffet; stall strip; flapper switch (leading edge stall warning vane).	Tax: B, PPLA
05	Describe the recovery after: stall warning; stall.	Tax: B, PPLA


02	Explain the difference between power-off and power-on stalls and recovery.	Tax: B, PPLA
03	Describe stall and recovery in a climbing and descending turn.	Tax: B, PPLA
04	Describe the effect on stall and recovery characteristics of a T-tailed aeroplane.	Tax: B, PPLA
07	Describe the factors that can lead to the absence of stall warning and explain the associated risks.	Tax: B, PPLA
12	Explain the effect of a contaminated wing (including ice) on the stall speed and αCRIT.	Tax: B, PPLA
p01	Describe the factors that may cause abnormal behaviour of the aircraft during stall.	Tax: B, PPLA


01	Explain how to avoid spins.	Tax: B, PPLA
02	List the factors that cause a spin to develop.	Tax: F, PPLA
03	Describe an ‘incipient’ and ‘developed’ spin, how to recognize a spin in terms of aircraft attitude and airspeed, and describe the general recovery technique.	Tax: B, PPLA

Eindterm 081 04 00 00 Stability

081 04 01 00 Static and dynamic stability


01	Define ‘static stability’: describe/identify a statically stable, neutral and unstable condition (positive, neutral and negative static stability).	Tax: F, PPLA
03	Explain why static stability is the opposite of manoeuvrability, and state that SEP aeroplanes are designed to be statically stable.	Tax: B, PPLA
04	Define ‘dynamic stability’: describe/identify a dynamically stable, neutral and unstable motion (positive, neutral and negative dynamic stability).	Tax: F, PPLA

081 04 03 00 Static and dynamic longitudinal stability


01	Explain the stabiliser, its control surfaces and the canard as the means to achieve balance about the lateral axis.	Tax: B, PPLA
p01	State the influence of ballast or weight trim on the longitudinal stability.	Tax: B, PPLA


01	Discuss the effect of the CG location on pitch manoeuvrability and longitudinal stability.	Tax: B, PPLA


02	Explain the CG forward and aft limits with respect to: longitudinal control forces; elevator effectiveness; stability; stability margin.	Tax: B, PPLA

081 04 04 00 Static directional stability


01	Define ‘static directional stability’.	Tax: F, PPLA
02	Explain the effects of static directional stability being too weak or too strong.	Tax: B, PPLA


01	Describe how the fin contributes to static directional stability.	Tax: B, PPLA

081 04 05 00 Static lateral stability


01	Define ‘static lateral stability’.	Tax: F, PPLA


01	Explain how without coordination, the bank angle (Ø) creates sideslip angle (ß).	Tax: B, PPLA


01	Explain the contribution to the static lateral stability of: dihedral, anhedral; high wing, low wing.	Tax: B, PPLA

081 04 06 00 Dynamic lateral/directional stability


03	Describe a spiral dive with respect to deviations in speed, bank angle, nose low-pitch attitude. and decreasing altitude.	Tax: B, PPLA
p01	Describe the differences between a spiral dive and a spin.	Tax: B, PPLA
p02	Describe the recovery procedure for a spiral dive.	Tax: B, PPLA

Eindterm 081 05 00 00 Control

081 05 01 00 General


01	Define: lateral axis; longitudinal axis; normal axis.	Tax: F, PPLA
03	Describe the motion about the three axes (pitch, roll and yaw).	Tax: B, PPLA
04	Name and describe the devices that control these motions.	Tax: F, PPLA


01	State that camber is changed by movement of a control surface and explain the effect.	Tax: F, PPLA


01	Explain the influence of local α change by movement of a control surface.	Tax: B, PPLA

081 05 02 00 Pitch (longitudinal) control


01	Explain the working principle of the elevator/all flying tails and describe its function.	Tax: B, PPLA
p01	Describe the characteristics of a T-tail.	Tax: B, PPLA


01	Explain the effect of downwash on the tailplane α.	Tax: B, PPLA


01	Explain the relationship between elevator deflection and CG location to produce a given aeroplane response.	Tax: B, PPLA
02	Explain the effect of forward CG limit on pitch control.	Tax: B, PPLA


01	Describe the effect of engine thrust on pitch.	Tax: B, PPLA

081 05 03 00 Yaw (directional) control


01	Explain the working principle of the rudder and describe its function.	Tax: B, PPLA

081 05 04 00 Roll (lateral) control


01	Explain the functioning of ailerons.	Tax: B, PPLA
05	Describe the use of aileron deflection in normal flight, flight with sideslip, crosswind landings and turns.	Tax: B, PPLA


01	Explain why the use of ailerons induces adverse yaw.	Tax: B, PPLA


01	Explain how the following reduce adverse yaw: Frise ailerons;differential ailerons deflection.	Tax: B, PPLA

081 05 05 00 Roll/yaw interaction


01	Explain the secondary effect of roll.	Tax: B, PPLA
02	Explain the secondary effect of yaw.	Tax: B, PPLA

081 05 06 00 Means to reduce control forces


01	Describe the purpose of aerodynamic balance.	Tax: B, PPLA
02	Describe the working principle of the horn balance.	Tax: B, PPLA
03	Describe the working principle of the internal balance. (mass balance)	Tax: B, PPLA
04	Describe the working principle and application of: balance tab; anti-balance tab; servo tab.	Tax: B, PPLA

081 05 08 00 Trimming


01	State the reasons for using trimming devices.	Tax: F, PPLA
02	Explain the difference between a trim tab and the various balance tabs.	Tax: B, PPLA


01	Describe the working principle of a trim tab including cockpit indications.	Tax: F, PPLA

Eindterm 081 06 00 00 Limitations

081 06 01 00 Operating limitations


01	Describe the phenomenon of flutter and how IAS and mass distribution affects the likelihood of flutter occurrence.	Tax: B, PPLA
02	Describe the use of control surface mass balance to alleviate the flutter problem by adjusting the mass distribution.	Tax: B, PPLA
03	State how to avoid flutter, and possible actions if flutter occurred.	Tax: F, PPLA


03	Define VFE and describe flap limiting speeds.	Tax: F, PPLA


01	Define VNO and VNE.	Tax: F, PPLA
03	Explain the hazards of flying at speeds close to VNE.	Tax: B, PPLA

081 06 02 00 Manoeuvring envelope


01	Describe the manoeuvring-load diagram.	Tax: B, PPLA
02	Define limit and ultimate load factor, and explain what can happen if these values are exceeded.	Tax: F, PPLA
03	Define VA.	Tax: F, PPLA
04	Identify and explain the varying features on the V-n diagram: load factor ‘n’; speed scale; CLMAX boundary; VA.	Tax: R, PPLA
06	State the positive manoeuvring load factor limit applicable to CS-23 aeroplanes in the normal category.	Tax: F, PPLA
08	Explain the significance of VA and the adverse consequences of applying full, abrupt nose-up elevator deflection when exceeding VA.	Tax: B, PPLA


01	State the relationship of mass to: load factor limits; VA and state that if a single value for VA is given, it will be at the aeroplane’s maximum structural take-off mass.	Tax: F, PPLA

081 06 03 00 Gust envelope


p01	State that VNO is the maximum operating airspeed in rough air for CS-23 aircraft.	Tax: F, PPLA


01	Describe the factors that contribute to gust load: altitude, wing loading, weight, wing area, indicated airspeed, aspect ratio and speed of vertical gust.	Tax: B, PPLA

Eindterm 081 07 00 00 Propellers

081 07 01 00 Conversion of engine torque to thrust


01	Explain resolution of aerodynamic force on a propeller blade element into lift and drag or thrust and torque. Remark: In de examens wordt voor 'torque' de term 'weerstand' of 'draaiweerstand' gebruikt.	Tax: B, PPLA
02	Describe how propeller thrust varies with IAS.	Tax: B, PPLA


01	Describe the geometry of a typical propeller blade element at the reference section: pitch or blade angle.	Tax: B, PPLA
02	Describe how the terms ‘fine pitch’ and ‘coarse pitch’ can be used to express blade angle.	Tax: B, PPLA


01	Define ‘blade twist’.	Tax: F, PPLA
02	Explain why blade twist is necessary.	Tax: B, PPLA


01	List the different types of propellers: fixed pitch; variable pitch (governing)/constant speed.	Tax: F, PPLA
02	Discuss advantages and disadvantages of fixed pitch and constant speed propellers.	Tax: B, PPLA
03	Discuss climb and cruise propellers.	Tax: B, PPLA
04	Explain the relationship between blade angle, blade angle of attack and airspeed for fixed and variable pitch propellers.	Tax: B, PPLA


01	Describe the effects and hazards of ice on a propeller.	Tax: B, PPLA

081 07 02 00 Engine failure


01	Describe the effects of an inoperative engine on the performance of an aeroplane: thrust loss/drag increase.	Tax: B, PPLA

081 07 04 00 Secondary effect of propellers


01	Describe the effects of engine/propeller torque.	Tax: B, PPLA


01	Describe the possible effects of the rotating propeller slipstream.	Tax: B, PPLA


01	Explain the asymmetric blade effect (also called P-factor).	Tax: B, PPLA


01	Describe, given direction of propeller rotation, the propeller effects during take-off run, rotation, initial climb and a go-around, and their consequence on controllability.	Tax: B, PPLA

Eindterm 081 08 00 00 Flight mechanics

081 08 01 00 Forces acting on an aeroplane. Remark: For theoretical knowledge examination purposes the term ‘climb angle’ or 'glide angle' is assumed to be air-mass-related; ‘flight-path angle’ is assumed to be ground-related.


01	Describe the forces that act on an aeroplane in straight, horizontal, and steady flight.	Tax: B, PPLA
02	List the four forces and state where they act on.	Tax: F, PPLA
03	Explain how the four forces are balanced including the function of the tailplane.	Tax: B, PPLA


01	Define 'flight path angle’ (ground related).	Tax: F, PPLA
02	Describe the relationship between pitch attitude, climb angle and angle of attack for zero bank conditions.	Tax: B, PPLA
03	Describe the forces that act on an aeroplane in a straight, steady climb.	Tax: B, PPLA
04	Name the forces parallel and perpendicular to the direction of flight.	Tax: F, PPLA
05	Explain why thrust is greater than drag.	Tax: B, PPLA
06	Explain why lift is less than weight.	Tax: B, PPLA


01	Describe the forces that act on an aeroplane in a straight steady descent.	Tax: B, PPLA
03	Explain why lift is less than weight.	Tax: B, PPLA
04	Explain why thrust is less than drag.	Tax: B, PPLA


01	Describe the forces acting on an aeroplane in a straight, steady glide.	Tax: B, PPLA
03	Describe the relationship between the glide angle and the lift-drag ratio.	Tax: B, PPLA
04	Explain the relationship between angle of attack, V<sub>md</sub> and the best lift-drag ratio.	Tax: B, PPLA


01	Describe the forces acting on an aeroplane in a steady, coordinated turn.	Tax: B, PPLA
03	Describe the difference between a coordinated and an uncoordinated turn and describe how to correct an uncoordinated turn using turn and slip indicator or turn coordinator.	Tax: B, PPLA
04	Explain that the turn radius only depends on TAS and bank angle.	Tax: B, PPLA
07	Explain the effects of bank angle (φ) on: load factor (LF = 1/cos φ); drag.	Tax: B, PPLA
09	Define ‘rate of turn’ and ‘rate-1 turn’.	Tax: F, PPLA

Eindterm 071 02 00 00 Special operational procedures and hazards (general aspects)

071 02 08 00 Wake turbulence


01	Define the term ”wake turbulence”.	Tax: F, PPLA
02	Describe tip vortices circulation.	Tax: B, PPLA
03	Explain when vortex generation begins and ends.	Tax: B, PPLA
04	Describe vortex circulation on the ground with and without crosswind.	Tax: B, PPLA


01	Define the term ”wake turbulence”.	Tax: F, PPLA
02	Describe tip vortices circulation.	Tax: B, PPLA


01	Describe the actions to be taken to avoid wake turbulence, specifically separations.	Tax: B, PPLA

Wijzigingen


031 01 02 02 01	Toegevoegd	Describe the relationship between CG position and aircraft performance.
031 01 02 02 02	Toegevoegd	Describe the effects of CG position on performance parameters (speeds, altitude, endurance and range).
031 02 02 01 02	Toegevoegd	Define the maximum ramp/taxi mass.
031 02 02 02 P01	Toegevoegd	Describe the following performance and regulated mass limitations: performance-limited take-off mass; performance-limited landing mass; regulated take-off mass; regulated landing mass
031 02 03 01 P01	Toegevoegd	Calculate the allowed mass for landing.
031 04 01 04 01	Verwijderd	Longitudinal CG limits. Extract the appropriate data from given sample documents.
031 04 01 05 01	Verwijderd	Lateral CG limits. Extract the appropriate data from given sample documents.
031 04 01 06 01	Verwijderd	Details of passenger and cargo compartments.Extract the appropriate data (e.g. seating schemes, compartment dimensions and limitations) from given sample documents.
031 04 01 07 01	Verwijderd	Details of fuel system relevant to mass-and-balance considerations. Extract the appropriate data (e.g. fuel-tank capacities and fuel-tank positions) from given sample documents.
031 05 02 01	Toegevoegd	General considerations
031 05 02 01 01	Toegevoegd	Explain the principle and the purpose of load sheets.
031 05 02 01 02	Toegevoegd	Explain the principle and the purpose of trim sheets.
032 01 02 03 01	Toegevoegd	aerodrome runway conditions
032 01 05 01 P01	Vervangen	Descent door distance.
032 02 03 01 P02	Vervangen	Describe the landing airborne distance and ground roll distance and estimate the effect on the landing distance when the aeroplane is too fast/slow or too high/low.
032 03 00 00	Toegevoegd	and multi
081 01 01 01 01	Toegevoegd	and perform conversion calculations
081 01 01 01 08	Toegevoegd	Define ‘dynamic pressure’
081 01 01 01 16	Toegevoegd	for incompressible flow
081 01 01 04 04	Toegevoegd	Describe the following parameter of an aerofoil section: chord ratio.
081 01 01 05 05	Toegevoegd	Describe the following parameters of a wing: wing planform (straight wing and tapered wing).
081 01 01 05 11	Toegevoegd	Describe the following parameters of a wing: geometric twist (wash out).
081 01 02 09	Toegevoegd	The lift coefficient (CL) – angle of attack () graph
081 01 02 09 01	Toegevoegd	Describe the CL–α graph
081 01 02 09 01	Toegevoegd	Explain the significant points: point where the curve crosses the horizontal axis (zero lift); point where the curve crosses the vertical axis (α = 0); point where the curve reaches its maximum (CLMAX).
081 01 03 03 P01	Verwijderd	Explain why the CL – CD ratio is important as a measure of performance.
081 01 04 03 01	Vervangen	Explain the factors that cause induced drag. door State that induced drag is caused by angle of attack
081 01 04 03 08	Toegevoegd	Explain induced and effective local α.
081 01 04 03 09	Toegevoegd	Explain the influence of the induced α on the direction of the lift vector.
081 01 05 01	Toegevoegd	Total drag in relation to parasite drag and induced drag
081 01 05 01 01	Toegevoegd	State that total drag consists of parasite drag and induced drag
081 01 09 02 05	Toegevoegd	Compare their influence on the CL– graph, compared with trailing-edge flaps and a clean wing: indicate the effect of leading-edge devices on CLMAX; explain how the CL curve differs from that of a clean wing; indicate the effect of leading-edge devices on CRIT.
081 01 12 01 01	Toegevoegd	Describe the locations on an aeroplane where ice build-up will occur during flight.
081 01 12 01	Toegevoegd	ice in stagnation point and ice on the surface (frost, snow and clear ice)
081 01 12 01 03	Toegevoegd	Explain the aerodynamic effects of icing on high lift devices during take-off, landing and low speeds.
081 03 01 01 06	Vervangen	State door Explain why
081 03 01 01 02	Toegevoegd	Describe the thickness of a typical laminar and turbulent boundary layer.
081 03 01 01 03	Toegevoegd	Describe the properties, advantages and disadvantages of the laminar boundary layer.
081 03 01 01 04	Toegevoegd	Describe the properties, advantages and disadvantages of the turbulent boundary layer.
081 03 01 01 05	Toegevoegd	Define the ‘transition point’.
081 03 01 02 02	Toegevoegd	Solve VS1G from the lift formula given varying CL.
081 03 01 02 03	Toegevoegd	Wing loading
081 03 01 03 P01	Toegevoegd	Discuss the use of ailerons on initial stall.
081 03 01 04 03	Toegevoegd	Describe why CS-23 require a margin to stall speed for take-off and landing speeds.
081 03 01 05 12	Toegevoegd	(including ice)
081 03 01 05 P01	Toegevoegd	Describe the factors that may cause abnormal behaviour of the aircraft during stall.
081 03 01 06 01	Toegevoegd	Explain how to avoid spins.
081 03 01 06 02	Toegevoegd	List the factors that cause a spin to develop.
081 03 01 06 03	Vervangen	Describe a spin (including the term ‘incipient’ spin), how to recognize a spin in terms of aircraft attitude and airspeed, and describe the general recovery technique door Describe an ‘incipient’ and ‘developed’ spin, how to recognize a spin in terms of aircraft attitude and airspeed, and describe the general recovery technique.
081 04 03 01 01	Toegevoegd	its control surfaces and the canard
081 04 03 01 P01	Toegevoegd	State the influence of ballast or weight trim on the longitudinal stability.
081 04 03 05 02	Toegevoegd	stability margin.
081 05 01 03	Toegevoegd	Angle-of-attack (α) change
081 05 01 03 01	Toegevoegd	Explain the influence of local α change by movement of a control surface.
081 05 02 04	Toegevoegd	Location of centre of gravity (CG)
081 05 02 04 01	Toegevoegd	Explain the relationship between elevator deflection and CG location to produce a given aeroplane response.
081 05 02 04 02	Toegevoegd	Explain the effect of forward CG limit on pitch control.
081 05 02 02	Toegevoegd	Downwash effects
081 05 02 02 01	Toegevoegd	Explain the effect of downwash on the tailplane α.
081 05 06 01 03	Toegevoegd	Describe the working principle of the internal balance. (mass balance)
081 05 06 01 04	Toegevoegd	servo tab
081 06 03 02	Toegevoegd	Factors affecting the gust–load diagram
081 06 03 02 01	Toegevoegd	Describe the factors that contribute to gust load: altitude, wing loading, weight, wing area, indicated airspeed, aspect ratio and speed of vertical gust.
081 07 04 03	Toegevoegd	Asymmetric