Question 100-1 : Unless otherwise specified in the afm for a performance class b aeroplane landing on a dry short grass runway what factor must be applied to the landing distance ? [ Exam pilot ]

Question 100-2 : Where on the power requiredpower available graph can you find the speed for best endurance for a propeller aircraft ?

At the lowest point on the power required curve.

Refer to figurespower required curve lowest point of curve – vmp=> for prop best endurance speed tangent – vmd best ld ratio=> for prop maximum range=> for jet vx = maximum endurance'by drawing a tangent from the origin of the graph up to the power required curve' incorrect this corresponds to the best endurance speed for a jet

Question 100-3 : Where on the power requiredpower available graph can you find the speed for best range ?

By drawing a tangent from the origin of the graph up to the power required curve.

Pistonpropeller aircraftmaximum best range vimd at the most efficient altitude for the power unitsjet aircraftmaximum best range vidmax at the highest practicable altitude

Question 100-4 : How are fuel flow and tas connected to each other in horizontal flight ?

An increase in tas will lead to a decrease in fuel flow up to the maximum endurance speed and increase thereafter.

If you take a close look at the power required curve bottom graph on the attached figure you may notice that up to the lowest point vmp as airspeed increases power required decreases thus fuel flow decreasesnow past vmp we can observe that an increase in airspeed will lead to an increased power required and consequently increased fuel flow

Question 100-5 : Assuming all other factors remain unchanged what statement is correct regarding the effect on the best glide angle ?

A higher mass allows for a higher speed while maintaining the same best glide angle.

Effect of weight on a glide descentsin = d t ÷ wfor the effect of weight on the descent we shall only consider the effect in a glide in other words with idle power sin = d ÷ wconsidering weight almost the same as lift sin = d ÷ l or sin = cd ÷ clbest glide angle occurs at maximum cl ÷ cd vmd also can be deducted that the best glide angle is unchanged by weight however a heavier aircraft will a have a higher vmd and the aircraft will fly at a higher airspeed through the same glide pathrate of descent fpm = gradient of descent x tas vmd maintaining the same gradient of descent with a higher airspeed rod also increases

Question 100-6 : With regard to a jet aeroplane specific range is the ?

Nautical air miles flown per unit mass of fuel.

Specific range there are two types of specific range specific air range sar and specific ground range sgr specific air range is the range through the air while sgr is the ground range the difference is due to wind strength and direction when wind is to be considered specific range is assumed to mean sgr specific range is the distance flown per unit of fuel using the aviation units nautical miles and kilograms specific range = nm kgdividing by timespecific range = tas fuel flow

Question 100-7 : Two identical aeroplanes at different masses are descending at zero wind and zero thrust at a given angle of attack which of the following statements correctly describes their descent characteristics ?

Both the vertical and the forward speed are greater for the heavier aeroplane.

Effect of weight on a glide descentsin = d t ÷ wfor the effect of weight on the descent we shall only consider the effect in a glide in other words with idle power sin = d ÷ wconsidering weight almost the same as lift sin = d ÷ l or sin = cd ÷ clbest glide angle occurs at maximum cl ÷ cd vmd also can be deducted that the best glide angle is unchanged by weight however a heavier aircraft will a have a higher vmd and the aircraft will fly at a higher airspeed through the same glide pathrate of descent fpm = gradient of descent x tas vmd maintaining the same gradient of descent with a higher airspeed rod also increases

Question 100-8 : Which of the following factors leads to the maximum flight time of a glide ?

Low mass.

The best glide angle occurs at vmd flying at this speed will give the best range in a glide glide angle and glide range itself is independent of aircraft mass provided the aircraft glides at vmd since it is the lift over drag ld ratio that determines the gliding range and it is unchanged with mass however a speed faster or slower than vmd will lead to steeper glide anglesglide angle = cd clgliding distancewind speed is an important practical influence on gliding distance over the surface with a tailwind the glide distance achieved will be increased as a result of the increased groundspeed whereas with a headwind it will be reduced because of the consequently slower groundspeedgliding timethe aircraft's mass varies the time the aircraft will glide for the heavier the aircraft is the higher the airspeed must be to obtain the same glide ratio higher vmd => glide duration will be decreased if two aircraft have the same ld ratio but different weights and start a glide from the same altitude the heavier aircraft gliding at a higher airspeed will arrive at the same touchdown point in a shorter time however both aircraft will cover the same distance but the lighter one will take a longer time to do sosummary glide distance varies with wind => tailwind increases glide distance=> headwind decreases glide distanceglide duration varies with mass => low mass increases glide duration=> high mass decreases glide duration

Question 100-9 : Vx and vy with take off flaps will be… ?

Lower than that for clean configuration.

Effect of flaps on climbwith a higher flap angle setting the profile of the wing is changed and the wing’s capability to provide lift at low speed increases the actual generated lift though remains the same considering the lower speed for the same amount of lift induced drags don’t change with the change of wing shape the parasite drag increases consequently total drag curve moves left and upwards this reduces vmd vx vy and the rate of climb achieved increasing roc vy vx prop vy vx jet altitude reduces same lower temperature reduces same lower mass reduces higher higher flap angle reduces lower lower

Question 100-10 : Assuming other factors remain constant and not limiting increasing the aerodrome pressure altitude ?

Will cause the maximum permitted take off mass to decrease.

Density is determined by pressure temperature and humidity density affects the power or thrust of the engine reduced density will reduce the thrust andor power that the engine can generate therefore acceleration will be less and the tom decreases the angle of the initial climb since there is less thrust andor power in low density the angle of climb will reduce therefore getting to the screen height will require a longer horizontal distance which could not be enough to be clear of obstacles

Question 100-11 : An aeroplane executes a steady glide at the speed for minimum glide angle if the forward speed is kept constant what is the effect of a lower mass rate of descent glide angle clcd ratio… ?

Increases increases decreases.

Refer to figureslower mass = less lift requirement = less induced drag = drag curves moves left = lower vmdbut if a higher vmd is maintained then drag increasesdescent angle is sin gamma = d twnormal descent is flown as a glide idle throttles thrust being zero in a glide the formula for glide angle becomes sin gamma = d weightlift can be taken equal to weight though it is actually slightly less the foumula becomes sin gamma = drag liftusing the co efficients of drag and liftsin gamma = cdclwith more drag cdcl increases = glide angle increases = rate of descent increasesclcd decreases for obvious reasons

Question 100-12 : Which of the following factors will lead to an increase of ground distance during a glide while maintaining the appropriate minimum glide angle speed ?

Tailwind.

The best glide angle occurs at vmd flying at this speed will give the best range in a glide glide angle and glide range itself is independent of aircraft mass provided the aircraft glides at vmd since it is the lift over drag ld ratio that determines the gliding range and it is unchanged with mass however a speed faster or slower than vmd will lead to steeper glide anglesglide angle = cd clgliding distancewind speed is an important practical influence on gliding distance over the surface with a tailwind the glide distance achieved will be increased as a result of the increased groundspeed whereas with a headwind it will be reduced because of the consequently slower groundspeedgliding timethe aircraft's mass varies the time the aircraft will glide for the heavier the aircraft is the higher the airspeed must be to obtain the same glide ratio higher vmd if two aircraft have the same ld ratio but different weights and start a glide from the same altitude the heavier aircraft gliding at a higher airspeed will arrive at the same touchdown point in a shorter time however both aircraft will cover the same distance but the lighter one will take a longer time to do sosummary glide distance varies with wind => tailwind increases glide distance=> headwind decreases glide distanceglide duration varies with mass => low mass increases glide duration=> high mass decreases glide duration

Question 100-13 : The maximum indicated air speed of a piston engine aeroplane without turbo charger in level flight is reached ?

At the lowest possible altitude.

The greatest power output from a piston engine is when the manifold pressure map is high mixture is rich rpm is at maximumin an un supercharged piston engine as the altitude or temperature increases then the map decreases and the power output decreases too for this reason the maximum ias is reached at the lowest possible altitudethe supercharged engines maintain their power output to a higher altitude but above the 'full throttle height' where the supercharger is no longer able to maintain the map then the power output decreases above that

Question 100-14 : The tangent from the origin to the power required against true airspeed curve for a jet aeroplane determines the speed for ?

Maximum endurance.

Refer to figurespower required curve•lowest point of curve – vmp=> for prop best endurance speed•tangent – vmd best ld ratio=> for prop maximum range speed=> for jet vx best endurance speed

Question 100-15 : What is the effect of increased mass on the performance of a gliding aeroplane ?

The speed for best angle of descent increases.

Increase of mass increases the weight of the aircraft that means more lift has to be provided to counteract itas lift increases there is an increase in lift induced dragif your airplane is heavy the speed for best glide distance will be higher than if it was lightvmd minimum drag speed increases for the increase in mass glide angle stays constant…

Question 100-16 : On the power versus tas graph for level flight the point at which a tangent from the origin touches the power required curve ?

Is the point where the lift to drag ratio is a maximum.

Refer to figurespower required curve lowest point of curve – vmp=> for prop best endurance speed tangent – vmd best ld ratio=> for prop maximum range=> for jet vx= best endurance

Question 100-17 : Which of the equations below defines specific range sr ?

Sr = true airspeed total fuel flow.

There is two important performance parameters in the cruise range and endurancefor an airliner range is more important than endurancewhere endurance is about the airborne time range is more concerned with distance coveredrange is not only about reduce the fuel flow but to maximize the speedmaximum range can be defined being the maximum distance an airplane can fly for a given quantity of fuelrange = distance nm ÷ fuel kg the formula above needs to be adjusted in order to practical and give us useful informationthe specific range can be determined with speed of the airplane and the fuel flowspecific range sr = tas ÷ fuel flow

Question 100-18 : When compared to still air conditions a constant headwind component ?

Increases the angle of flight path during climb.

A steady continuous head wind or tail wind will not affect your climb rate only your climb anglethe angle of climb flight path is the angle the plane is flying with respect to the ground when flying into a steady headwind the ground speed will be lower at the same airspeed but the climb rate will be the same therefore if you're climbing at the same rate but moving forward at a slower rate the angle will be steeper it means you will reach a specific altitude in the same time interval but your ground distance will be affected in the case of a headwind your ground distance will be reducednote a headwind will not affect the climb angle or rate of climb but it will affect the angle of climb relative to the ground => it will make the flight path angle steeper

Question 100-19 : An increase in atmospheric pressure has among other things the following consequences on landing performance ?

A reduced landing distance and improved go around performance.

Refer to figuresan increase in atmospheric pressure means distance between air molecules getting smaller that we have denser air to usedenser air used by engines so the performance will be better if we compare with use lesser dense airit effects pozitive for landing reduces distance more drag and go around improved performance more thrust more air mass flowing over your wings makes generate much lift and much oxygen mass in your cylinders makes burning much fuel meaning more powerincreasing air density increases performance

Question 100-20 : What does the abbreviation vle mean ?

Maximum landing gear extended speed.

Vle maximum landing gear extended speedva design maneuvering speedvb design speed for maximum gust intensityvc design cruising speedvd design diving speedvdfmdf demonstrated flight diving speedvf design flap speedvfcmfc maximum speed for stability characteristicsvfe maximum flaps extended speedvgo the slowest speed from which a takeoff can be safely continued after an engine failure for a given todatodrvh maximum speed in level flight with maximum continuous powervle maximum landing gear extended speedvlo maximum landing gear operating speedvlof lift off speedvmax maximum speedvmbe maximum brake energy speedvmc minimum control speedvmca mimimum control speed airbornevmcg minimum control speed groundvmin minimum speedvmo mmo maximum operating limit speedvmu minimum unstick speedvne never exceed speedvno maximum structural cruising speedvr rotation speedvref reference speedvs stalling speedvso stalling speed in the landing configurationvstop the highest speed from which a takeoff can be safely rejected for a given asdaasdrvs1 stalling speed in a specified configurationvtd touchdown indicated airspeedvtoss takeoff safety speed for category a rotocraftvx speed for best angle of climbvy speed for best rate of climbv1 takeoff decision speedv2 takeoff safety speedv2min minimum takeoff safety speed

Question 100-21 : The 'density altitude' is ?

The altitude in the standard atmosphere at which the prevailing density occurs.

Density altitude is pressure altitude corrected for non standard temperatureyou probably noticed that in hot days your airplane not well performingas temperature and altitude increase air density decreasesin a sense it's the altitude at which the airplane 'feels' its flyingthat's because with hot temperatures density altitude increases and your airplane 'feels' like it's flying at a higher altitude

Question 100-22 : What does the abbreviation 'oei' mean ?

One engine inoperative.

Icao doc 10085acronyms and abbreviationsaeo all engines operativeoei one engine inoperative

Question 100-23 : The abbreviation vy means ?

Speed for best rate of climb.

Speed of best rate of climb vy vy is the airspeed that will give the greatest height gain per unit of time it is the same speed for maximum excess of power all factors affecting the require power affects the vy

Question 100-24 : Which statement is correct for a descent without engine thrust at maximum lift to drag ratio speed ?

The higher the gross mass the greater is the speed for descent.

Considering aircraft's weight if it remains at vmd a heavier aeroplane has the same liftdrag ratio and same glide angle and rangethis is because the lift and drag have increased in the same proportionhowever the actual speed of vmd altersa heavier aeroplane has to glide at a faster speed to be at vmd because the drag curve has moved up and to the right

Question 100-25 : Having all other conditions the same taking off from an upward sloping runway compared to a zero slope runway will result in ?

An increased take off distance and a decreased stopping distance in case of an aborted take off.

Among others one of the factors affecting the take off distance required is the runway slope if the runway slopes downhill the aircraft will be easier to accelerate assisted by a component of the aircraft weight acting downhill and the distance to v1 and to rotate will be reduced while an uphill slope makes the aircraft more difficult to accelerate since the component of the aircraft weight is now added to the drag thus the distance to v1 and to rotate will be increased and as a result the take off distance increases tooalso if the runway slopes downhill it will be harder to stop while if the runway slopes uphill it will be easier therefore in case of an aborted take off the stopping distance decreasesnote the questions asks for the stopping distance and not the accelerate stop distance

Question 100-26 : All other criteria being equal what factor can reduce the landing distance ?

The use of spoilers.

In large commercial airliners once the main wheels have positive touch on the runway the lift spoilers or lift dumpers are deployed which disrupt the airflow over the wing destroying lift and increasing the parasite drag this will help the aircraft to stop and decrease the landing distance

Question 100-27 : Calculate the one engine failed climb gradient of a four engine aeroplane given the following information aeroplane mass 358 000 kg thrust per engine 245 000 n drag 455 000 n assume the acceleration due to gravity is 10 ms2 ?

78%.

t thrust = number of engines 4 1 inop x thrust per engine t = 3 x 245 000 n = 735 000 n w weight = aeroplane mass x 10 ms2 w = 358 000 kg x 10 ms2 = 3 580 000 n climb gradient = thrust drag weight x 100% climb gradient = 735000 455000 3 580 000 x 100% = 78%

Question 100-28 : What is the minimum width of a clearway ?

500 feet.

The clearway is described in eu ops as a defined rectangular area on the ground or water under the control of the appropriate authority selected or prepared as a suitable area over which an aeroplane may take a portion of its initial climb to a specified height the clearway may be load bearing or notthe clearway is expressed in terms of a clearway plane with a minimum width of 500 feet or 152 metres extending from the end of the runway with an upward slope not exceeding 125% above which no object or terrain protrudes however threshold lights may protrude above the plane if their height above the end of the runway is 066 metres or 26 inches or less and if they are located to each side of the runway also the clearway may not be greater than 50% of the tora and should extend at least 75 metres either side of the centre linethe tora take off run available plus the clearway make the toda take off distance available

Question 100-29 : The specific range sr is ?

The air distance that the aircraft would fly per kilogram of fuel.

Specific rangethere are two types of specific range specific air range sar and specific ground range sgr specific air range is the distance through the air covered per unit of fuel burnt while sgr is the ground distance per unit of fuel the difference is due to wind in the same way that groundspeed is just true airspeed plusminus windin the exam and throughout the notes consider specific range sr to be sar if not otherwise told there is a very similar question to this one that asks about sgr so watch out for that typically this is expressed in nautical miles per poundkg of fuelspecific air range = distance nm fuel burnt kg dividing both distance and fuel burnt by time specific air range nm = tasfuel flow

Question 100-30 : In a steady descending flight descent angle 3 equilibrium of forces acting on the aeroplane is given t = thrust d = drag w = weight ?

T+w sin 3 = d.

In a steady descent thrust is reduced as a result the aircraft slows down due to a reduced forward force thrust in comparison to the backward force drag in order for the aircraft to maintain speed and be in a steady descent the forward component of weight must be increased to balance the drag this is achieved by lowering the nose increasing descent angle y until this component of weight increases providing enough forward force to balance the dragat this point the backward and forward forces are balanced drag d is balanced by the thrust t and weight component w sin y 'y' being the angle of descent resulting on the following equation d = t + w sin yin this case descent angle = 3 therefore balance is represented d = t + w sin 3

Question 100-31 : For a jet transport aeroplane which of the following is the reason for the use of ‘maximum range speed’ ?

Minimum specific fuel consumption.

Range is the distance an airplane can travel with a given amount of fuel range will primarily depend on the amount of fuel carried on aboard and the specific fuel consumption sfc sfc is the fuel flow required by the engine to produce a unit of thrust or powerspecific range = tas ÷ sfc x drag therefore maximum range will be achieved at the minimum specific fuel consumptionendurance is the amount of time an aircraft can stay in the air with one load of fuel speed for maximum endurance is found where the thrust required to maintain level flight is minimum therefore maximum endurance is achieved at the minimum fuel flowminimum ff = speed for max endurance vmd for jets minimum sfc = speed for max range 132 vmd for jets

Question 100-32 : Given the following information what is the all engine climb gradient for a two engine aeroplane thrust per engine 118000 newtons mass 67000 kg lift to drag ratio 9 1 assume g = 10 ms ?

241%.

Climb gradient is the ratio of height gained to distance travelled => tangent to climb angle y sin y = t – d w sin y = tw – dw sin y = t m x g – d lcos y sin y = t m x g – d x cos y l for small angles => cos is nearly 1 so sin y = t m x g – dl climb gradient = t m x g – dl x 100 with regards to this question climb gradient = 236000 67000 x 10 – 19 x 100 = 241%

Question 100-33 : If the climb gradient in still air 32 percent the height achieved is 640 ft what is the distance travelled in the climb in still air ?

329 nm.

Still air gradient of climb % = rate of climb fpm ÷ tas kt x 6000 ÷ 6080 still air gradient of climb % = height gain distance travelled x 100distance travelled = 640 ÷ 32 x 100 = 20 000 ft = 329 nm

Question 100-34 : The best rate of climb at a constant gross mass ?

Decreases with increasing altitude since the thrust available decreases due to the lower air density.

Vy is the speed at which an aeroplane achieves its maximum rate of climbsince rate of climb depends on excess power vy is the speed at which the difference between power available and power required is greatestbecause power available is thrust available times tas power available again differs for turbojet and propeller aeroplanes and must be considered separatelythe above graph shows power available red line and power required green line for a propellerdriven aeroplanevy the speed where there is greatest excess power is close to vmd but will reduce with anincrease in altitude and decreased density thrust availablehowever vx for a propeller driven aeroplane is normally close to vmp and the stallfor a propeller driven aeroplane vy is slower than vmdvy is again faster than vx unless at the absolute ceiling

Question 100-35 : A jet aeroplane is flying at the speed for maximum range below the optimum altitude how does the specific range change when altitude increases the specific range… ?

First increases then decreases.

Optimum altitudeit is defined as being the pressure altitude which provides the greatest specific range or fuel mileage at a given weight and speed flying higher or lower than the optimum altitude will decrease the range of the airplaneit is important to understand that the optimum altitude is not fixed as the weight decreases through fuel burn the drag curve moves down and left therefore the best range speed 132vmd falls and the total drag decreases with decreasing weight the airplane needs to slow down to maintain the best range speed as it does so the mach number will also decrease meaning that the airplane is not limited by the high mach number and corresponding high drag this fact allows the airplane to climb a little as the airplane climbs the mach number will increase again to its previous limiting value and drag will increase back to its previous value but more importantly the higher altitude has decreased the specific fuel consumption this means that over time as the weight decreases with fuel burn the optimum altitude increasesspecific range sr = tas ÷ fuel flowreaching the optimum level the aircraft specific range increases as the aircraft mass decreases due to fuel consumption the optimum level will be higher if the aircraft does not climb to the new optimum altitude the specific range decreases

Question 100-36 : If the headwind increases by 10 kt the maximum endurance speed will ?

Remain unchanged.

Wind influence on range and endurancerangewind speed is an important practical influence on gliding distance over the surface with a tailwind the glide distance achieved will be increased as a result of the increased groundspeed whereas with a headwind it will be reduced because of the consequently slower groundspeedendurance the wind has no effect on endurance endurance is about time in the air not distance covered maximum endurance is concerned with minimizing fuel flow and wind does not affect the fuel flow into the engine as long as it has usable fuel in its tanks an aircraft will still remain airbornesummary range glide distance varies with wind => tailwind increases glide distance=> headwind decreases glide distanceendurance glide duration varies with mass => low mass increases glide duration=> high mass decreases glide duration

Question 100-37 : The stopway is an area designated to be used by an aircraft in order to… ?

Decelerate during an abortive take off.

Question 100-38 : During descent with idle power and assuming all other parameters remaining the same how will an increased mass change the minimum angle of descent and the corresponding speed the minimum angle of descent ?

Remains the same at an increased speed.

The effect of weight on dragif an aircraft is operated at a higher gross weight more lift will be required if more lift is generated induced drag will be higher total drag will be greater and vmd will occur at a higher iasangle of descent sin = d t wthe weight is increased but the angle of descent will remain constant cause drag is increased as well for the increased weight

Question 100-39 : When flying the 'backside of thrust curve' means… ?

A lower airspeed requires more thrust.

Region of reverse commandto maintain unaccelerated flight at an ias slower than vmd thrust available must be increased this is because at speeds below vmd thrust required drag increases the speed region slower than vmd has three alternative names the back side of the drag curve the speed unstable region the region of reverse command so called because to maintain unaccelerated flight at an ias slower than vmd thrust must be increased – the reverse of what is normally required

Question 100-40 : The length of any available clearway is included in the ?

Take off distance available.

icao annex 14 volume i declared distancesa take off run available tora the length of runway declared available and suitable for the ground run of an aeroplane taking off b take off distance available toda the length of the take off run available plus the length of the clearway if provided c accelerate stop distance available asda the length of the take off run available plus the length of the stopway if provided d landing distance available lda the length of runway which is declared available and suitable for the ground run of an aeroplane landing