Question 108-1 : The speed range between low speed buffet and high speed buffet ? [ Exam pilot ]

Question 108-2 : The danger associated with low speed andor high speed buffet ?

Limits the manoeuvring load factor at high altitudes.

At low speed buffet you are near the conventional stall it occurs at higher speeds with altitude in the other hand high speed buffet occurs at lower speeds with altitude so at some stage the buffets will merge the margin between them called 'coffin corner' is reduced by g force caused by turning and turbulence it means that you have to avoid any manoeuvres that can result in an increase of the load factor

Question 108-3 : Which of the jet engine ratings below is not a certified rating ?

Maximum cruise thrust.

Question 108-4 : At constant thrust and constant altitude the fuel flow of a jet engine ?

Increases slightly with increasing airspeed.

Because your mass decreases with time and the question states 'constant altitude' your airspeed will increase at constant thrust because you have to decrease your angle of attack to maintain constant altitude as more air is entering the engine ram effect is increased the compressor works harder which demands an increase of the fuel flow

Question 108-5 : The thrust of a jet engine at constant rpm ?

Increases in proportion to the airspeed.

Jomargra for a jet engine the net thrust is the difference between the gross thrust and the intake momentum drag increasing speed increases the intake momentum drag which reduces the thrust however at higher speeds the increased intake pressure due to ram effect is insufficient to counteract the loss of thrust due to intake momentum dragtherefore during the take off there will be a decrease of thrust from oxford book at constant rpm the ram effect increases the mass of air in the intake and at a higher pressure thrust starts to increase

Question 108-6 : A higher altitude at constant mass and mach number requires ?

A higher angle of attack.

Lift = cl x 12 rho v² x scl = lift coefficientrho = densityv = tas in ms s = surfaceat higher altitude 'rho' and 'tas' are reduced you can only act on lift coefficient you must to increase your angle of attack to maintain lift constant

Question 108-7 : The long range cruise speed is selected because ?

The higher speed achieves 99% of the maximum still air range.

Question 108-8 : The optimum altitude ?

Increases as mass decreases and is the altitude at which the specific range reaches its maximum.

Question 108-9 : The engine failure take off run is ?

The horizontal distance along the take off path from the start of the take off to a point equidistant between the point at which vlof is reached and the point at which the aeroplane is 35 ft above the take off surface.

Question 108-10 : Reduced take off thrust ?

Has the benefit of improving engine life.

Question 108-11 : A 'balanced field length' is said to exist where ?

The accelerate stop distance is equal to the take off distance available.

Question 108-12 : The optimum cruise altitude increases ?

If the aeroplane mass is decreased.

Question 108-13 : Below the optimum cruise altitude ?

The mach number for long range cruise decreases continuously with decreasing altitude.

Long range cruise is derived from the drageas curve lrc is slightly faster 137vmd than maximum range speed 132vmd vmd means velocity minimum drag lrc is 4% faster than maximum range speed for 99% of the range lrc is flown as a mach number and since it is a point on the drageas curve it will be constant eas on the ertm graph thus lrc decreases with decreasing altitudethe ertm diagram ertm for e as r as rectified air speed or cas t as m ach 1960eas is vertical mach number decreases with altitude and increases with increasing altitude

Question 108-14 : If after experiencing an engine failure when cruising above the one engine inoperative ceiling an aeroplane is unable to maintain its cruising altitude the procedure that should be adopted is ?

Drift down procedure.

In a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdownthis would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s then achieving a computed driftdown airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining 2519the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport

Question 108-15 : Drift down is the procedure to be applied ?

After engine failure if the aeroplane is above the one engine out maximum altitude.

In a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdownthis would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s then achieving a computed driftdown airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining 2519the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport

Question 108-16 : If the level off altitude is below the obstacle clearance altitude during a drift down procedure ?

Fuel jettisoning should be started at the beginning of drift down.

In a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdownthis would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s then achieving a computed driftdown airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining 2519the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down

Question 108-17 : The landing field length required for turbojet aeroplanes at the destination wet condition is the demonstrated landing distance plus ?

92%.

For jet aeroplanes the landing field length required at destination and at alternate must be factored by 166 to make it 60% of distance availablelanding distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 115166 x 115 = 192 92% the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92%

Question 108-18 : The landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus ?

92%.

For jet aeroplanes the landing field length required at destination and at alternate must be factored by 166 to make it 60% of distance availablelanding distance required must be increased by 15% if the runway is wet not to exceed 60% of the landing distance available multiply the dry result by 115166 x 115 = 192 92% the landing field length required for jet aeroplanes at the alternate wet condition is the demonstrated landing distance plus 92%

Question 108-19 : The speed vsr is defined as ?

As reference stall speed and may not be less than 1 g stall speed.

Question 108-20 : The speed v2 is defined for jet aeroplane as ?

Take off climb speed or speed at 35 ft.

Question 108-21 : The aerodynamic ceiling ?

Is the altitude at which the speeds for low speed buffet and for high speed buffet are the same.

If there is no reserve of power available to permit any climb you are at the absolute ceiling if you have lots of power you can climb until mmo and minimum control speed coincide you are at your aerodynamic ceiling the aerodynamic ceiling is that altitude at which the low speed buffet and the high speed buffet are equal

Question 108-22 : 'stepped climbs' are used on long distance flights ?

To fly a profile as close as possible to the optimum altitude as the aeroplane mass reduces.

Question 108-23 : The climb gradientafter take off in a standard atmosphere and still air at 0 ft pressure altitude is 6%use the following corrections to determine the climb gradient after take off on a aerodrome 1000 ft aerodrome pressure altitude oat +17°c 101325 hpa wing and engine anti ice systems onaerodrome ?

39 %.

6% minus 02% for aerodrome elevation = 58%58% minus 04% for temperature deviation = 54%54% minus 1% for wing anti ice on = 44%44% minus 05% for engine anti ice on = 39%

Question 108-24 : The drift down procedure specifies requirements concerning the ?

Obstacle clearance after engine failure.

In a multi engine aircraft losing power from one or more engines may require a descent due to aircraft weight and atmospheric conditions if a descent is required the most fuel efficient method is a driftdownthis would be done by first setting the engines to a prescribed power setting usually set to max continuous thrust mct on the remaining engine s then achieving a computed driftdown airspeed begin a descent to the best altitude for the aircraft on the engines that are remaining 2519the goal is to stay the longest time at high altitude to remain clear of obstacles and to burn the less fuel as possible for having the maximum chances to reach a suitable airport fuel jettisoning should be started at the beginning of drift down

Question 108-25 : Given a jet aircraft which order of increasing speeds in the performance diagram is correct ?

Vs vx maximum range speed.

This is the order of speeds from slowest to fastestobviously vs is slowest then vxvs is stall speed very slow vx is the speed for best angle of climb climbing at vx allows pilots to maximize the altitude gain per unit ground distance vx is faster than vs maximum endurance speed gives you the most lift for the least drag for the most economy and the most distance for altitude lost maximum endurance speed is found at best liftdrag speed which is faster than vxmaximum range speed is higher than endurance range speed and is used as the standard speed for cruise it is 4% faster than best range speed for 99% of the range 1100note vmp is vx

Question 108-26 : When determining the maximum landing mass of an turbojet powered aeroplane during the planning phase what factor must be used on the landing distance available dry runway ?

060.

Eu ops 1515 landing dry runways a an operator shall ensure that the landing mass of the aeroplane determined in accordance with eu ops 1475 a for the estimated time of landing at the destination aerodrome and at any alternate aerodrome allows a full stop landing from 50 ft above the threshold 1 for turbo jet powered aeroplanes within 60% of the landing distance available or 2 for turbo propeller powered aeroplanes within 70% of the landing distance available example an aircraft needs 1200 m to stop landing distance required with maximum braking manufacturers data factored for slope and wind effectsfor a dry runway this 1200 m must not represent more than 60% percent of landing distance available lda so the minimum landing distance available is indeed 1200 x 167 = 2004 mnow if you start from 2004 m the landing distance available we use a 060 factor 2004 x 06 = 1200 m

Question 108-27 : On a segment of the take off flight path an obstacle requires a minimum gradient of climb of 26% in order to provide an adequate margin of safe clearance at a mass of 110000 kg the gradient of climb is 28%for the same power and assuming that the sine of the angle of climb varies inversely with mass ?

118455 kg.

28 26 x 110000 = 118461 kgas we decrease our climb gradient for the same power our mass can be increased

Question 108-28 : Which statement with respect to the step climb is correct ?

Performing a step climb based on economy can be limited by the 13g buffet onset requirements.

In order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 13 this value is an operating limitation but not a regulatory one the corresponding altitude is called the 13g buffet limited altitude or buffet ceiling

Question 108-29 : In accordance to cs 25 which of the following listed speeds are used for determination of v2min ?

Vsr vmca.

Question 108-30 : Reduced take off thrust should normally not be used when ?

Anti skid is not usable.

A reduced take off thrust is not permitted with icy or slippery runways contamined runways contamination can have a large and uncertain drag on the take off runfor safety reasons it is preferable to reduce the running distance to reach v1 even if you can accomplish a safety rejected take off on the allowed asda thus you shouldn't use reduced take off thrust when anti skid is not usable

Question 108-31 : Maximum tyre speed can limit the lift off speed which kind of speed can be directly used to determine this limitation ?

Groundspeed.

Question 108-32 : According to cs 25 the landing reference speed vref may not be less than ?

123 vsr0 and must be maintained down to 50 ft height.

Cs 25125 landing a the horizontal distance necessary to land and to come to a complete stop from a point 15 m 50 ft above the landing surface for standard temperatures at each weight altitude and wind within the operational limits established by the applicant for the aeroplane with a landing reference speed vref not be less than 123 vsr0vsr0 reference stall speed in the landing configuration

Question 108-33 : Which statement with respect to the step climb is correct ?

Executing a desired step climb at high altitude can be limited by buffet onset at g loads greater than 1.

In order to maintain a minimum margin against buffeting and ensure good aircraft maneuverability it is necessary to determine an acceptable load factor limit below which buffeting shall never occur this load factor limit is generally fixed to 13 this value is an operating limitation but not a regulatory one the corresponding altitude is called the '13g buffet limited altitude' or 'buffet ceiling'

Question 108-34 : Select from the following list of conditions those that must prevail in the second segment of the take off net flight path for a class a aeroplane are 1 undercarriage retracted2 undercarriage extended3 flaps up4 flaps in take off position5 all engines at take off thrust6 operative engine s at take ?

1 4 6 9.

Question 108-35 : V1 for a balanced field is calculated when ?

The accelerationstop distance available is equal to the take off distance available.

Question 108-36 : With regard to the drift down performance of the twin jet aeroplane why does the curve representing 35 000 kg gross mass in the chart for drift down net profiles start at approximately 4 minutes at fl370 2128 ?

Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

2519you will stay at the original cruising level until you reach the optimum speed for descent

Question 108-37 : The requirements of the take off net flight path for a class a aeroplane assume ?

The failure of the critical engine of a multi engined aeroplane at vef.

Question 108-38 : The angle of attack required to attain the maximum still air range for a turbo jet aeroplane is ?

Less than that for the maximum lift to drag ratio.

com encom032 334jpgfor a jet aeroplane maximum ld ratio is maximum endurance which is vmd where the gap between power required and power available is greatest at this speed for a conventional aerofoil the angle of attack is about 4°the speed for maximum range maximum still air range occurs at 132 times the speed of minimum drag vmd in level flight as speed goes up the angle of attack goes down angle of attack is less than 4° typically at around 25°

Question 108-39 : Compared with balanced field calculations for an aerodrome with no stopway or clearway the use of a clearway in the take off calculations will ?

Increase the field length limited take off mass.

A field length is balanced when take off distance available equals accelerate stop distance availablethe take off distance available is the length of the take off run available plus the length of the clearway availablea clearway is an area beyond the paved runway free of obstacles 771the use of any additional clearway in take off performance calculations may allow a greater field limited take off mass but the v1 will be lower because the extra take off mass means that more distance will be required to stop in the event of an aborted takeoff

Question 108-40 : The relationship of the reference landing speed vref to the reference stalling speed in the landing configuration vsro is that vref may not be below ?

123 vsro.