Question 99-1 : Which of the following statements concerning tires is the major consideration when establishing the tyre speed limit ? [ Diploma registration ]

Question 99-2 : What will increase the 'landing field length limited landing mass' when operating with the anti skid inoperative ?

A headwind.

Ecqb04 october 2017if you have a weight limitation at landing due to the length of the runway a headwind will help you to have a reduced approach and landing speed therefore you may land at a higher massother statements will are wrong since theay lead to an increase in the required landing distance and therefore a decrease in the 'landing field length limited landing mass'

Question 99-3 : When calculating approach speeds the minimum approach speed in the initial approach phase is usually ?

14 to 15 times vs1.

Question 99-4 : You are approaching a wet runway in gusty conditions you should ?

Increase approach speed.

Ecqb04 october 2017you should in order to avoid windshear increase slightly your approach speed but you must land at your calculated landing speed not less not more

Question 99-5 : Compared with a level runway the use of a runway with a 2% downslope will ?

Reduce vmbe.

Ecqb04 october 2017vmbe maximum brake energy speed is the speed from which the aeroplane may be brought to a stop without exceeding the maximum energy absorption capability of the brakes for a downhill slope you will reach vmbe at a lower speed compared to a level runway more kinetic energy needs to be absorb due to the down hill component of the runway also a downhill slope means that you need a longer distance to stop in case of failure before v1 and you will reach v1 at an earlier point in the take off run than on a 'flat' runway v1 has to be reducedvmbe and v1 will be reduced

Question 99-6 : If the anti skid system is inoperative may auto brake system can be used ?

No never.

Anti skid system protection is provided during auto brake operation therefore if anti skid is inoperative you can not use the auto brake system

Question 99-7 : You climb with a climb speed schedule 30078 what do you expect in the crossover altitude 29200 ft oat = isa ?

The rate of climb increases since the constant ias climb is replaced by the constant mach climb.

Question 99-8 : The effect of an aft cg on take off performance are ?

Take off distance decreases climb gradient increases.

Ecqb04 october 2017

Question 99-9 : At maximum landing mass the structure of the aircraft is designed for a rate of descent of ?

600 ftmin.

Question 99-10 : The approach climb requirement is normally met by ?

Reducing flap setting for approach with one engine inoperative.

Question 99-11 : A change of runway in use from a runway slope of 1% downhill to a runway slope of 1% uphill will ?

Increase take off run increase take off distance.

Question 99-12 : An uphill slope runway will ?

Question 99-13 : Runway 30 is in use and the threshold elevation is 2139 feet threshold elevation of runway 12 is 2289 feettake off run available is 1720 metres and clearway is 280 metreswhat is the slope of the runway in use ?

265% uphill.

2289 ft 2139 ft = 150 ft150 ft x 03048 = 4572mrunway lenght is 1720m slope in % is 4572m 1720m x 100 = 265%

Question 99-14 : In the event of an engine failure during cruise it is necessary to reduce speed and descend to lower altitude at speed ?

For maximum liftdrag ratio and if necessary start fuel jettisoning.

Ecqb04 october 2017

Question 99-15 : On a long distance flight the optimum cruise altitude is continuously increased during the flight ?

As a consequence of the fuel consumption.

Ecqb04 october 2017

Question 99-16 : The take off and landing distances on a grass runway are in relation to that for a paved runway ?

Take off distance and landing distance increase.

Ecqb04 october 2017take off distance on a dry short grass runway compared to a paved dry runway distance increases by 20%landing distance on a dry short grass runway compared to a paved dry runway distance increases by 15%

Question 99-17 : Which take off condition is most likely resulting in the poorest climb performance ?

5000 ft field elevation isa +20° take off flaps 30°.

Question 99-18 : During take off the time between critical engine failure and v1 recognition time is assumed to be approximately ?

2 seconds.

Following an engine failure at v1 and allowing for a reaction time of 2 seconds a correctly loaded aircraft must be capable of decelerating to a halt within the accelerate stop distance available

Question 99-19 : The lift off speed vlof and take off safety speed v2 when flap position is changed from 10° to 5° will ?

Increase increase.

Question 99-20 : An aircraft has this following flap position up 5° 10° 20° if the flap setting is 'up' instead of 10° it will ?

Increase take off distance.

Ecqb04 october 2017

Question 99-21 : Changing flaps selection from 10° to flaps 0° while establish in climb after take off will have the following effects ?

Climb gradient and vy increase.

Ecqb04 october 2017vy is the indicated airspeed for best rate of climb climbing at vy allows pilots to maximize the altitude gain per unit timeclimb gradient is defined as the ratio of the increase of altitude to horizontal air distance expressed as a percentageyou will generate less drag with a less flaps selection the gap between the thrust available and thrust required increases

Question 99-22 : During a descent a headwind will have the following effects ?

Descent angle remains constant flight path angle increases.

Ecqb04 october 2017during a descent a headwind will increases the flight path angle com encom080 642jpgthe descent distance over ground is decreased the rate of descent and the angle of descent remain unchangedangle of descent descent angle is the angle you maintain on your attitude indicator artificial horizon pfd note for theoretical knowledge examination purposes 'flight path angle' is assumed to be ground relatedthe flight path angle is the actual vector flown in relation to the ground it will increase during descent with a headwind

Question 99-23 : During a descent a tailwind will have the following effects ?

Descent angle remains constant flight path angle decreases.

Ecqb04 october 2017during a descent a tailwind will decreases the flight path angle com encom032 351jpgthe descent distance over ground is increased the rate of descent and the angle of descent remain unchangedangle of descent descent angle is the angle you maintain on your attitude indicator artificial horizon pfd note for theoretical knowledge examination purposes 'flight path angle' is assumed to be ground relatedthe flight path angle is the actual vector flown in relation to the ground it will decrease during descent with a tailwind

Question 99-24 : The 'flight path angle' is the angle ?

Between the horizontal plane and the flight path.

Ecqb04 october 2017 682note for theoretical knowledge examination purposes 'flight path angle' is assumed to be ground relatedthe flight path angle is the actual vector flown in relation to the ground it will decrease during descent with a tailwindangle of descent descent angle is the angle you maintain on your attitude indicator artificial horizon pfd

Question 99-25 : The vertical 'flight path angle' is assumed to be ?

Ground related.

Ecqb04 october 2017 682note for theoretical knowledge examination purposes 'flight path angle' is assumed to be ground relatedthe flight path angle is the actual vector flown in relation to the ground it will decrease during descent with a tailwind and will increase with a headwindangle of descent descent angle is the angle you maintain on your attitude indicator artificial horizon pfd

Question 99-26 : Specific fuel consumption sfc is ?

Mass of fuel required to produce unit power for unit time.

Ecqb04 october 2017specific fuel consumption is the amount of fuel burnt per unit of thrust for jets it reduces with altitude up to the tropopause

Question 99-27 : The specific range sr is ?

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

Specific range sr is the enroute tas divided by the current fuel flowsr = true airspeedtotal fuel flowthe units of sr are nautical miles per gallon or nautical miles per pound of fuel

Question 99-28 : How does the asdr accelerate stop distance required will be affected by the addition of a stopway into the runway strip length the asdr ?

Remains the same.

Ecqb04 november 2017a stopway is a defined rectangular area on the ground at the end of the take off run available prepared as a suitable area in which an aircraft can be stopped in the case of an abandoned take offasdr accelerate stop distance required is calculated with the actual values of the flight mass wind up or down slope oat pressure altitude etc it's a fixed value for the projected take offthe declared distances 'asda' acceleration stop distance available is the length of the take off run available plus the length of stopway with a stopway provided the 'runway strip' is increase

Question 99-29 : What is the effect of using engine bleed air on the take off distance ?

Reduces available thrust and increases the take off distance.

Question 99-30 : Which of the following will decrease landing distance ?

The spoilers.

Ecqb04 november 2017

Question 99-31 : If cabin altitude cannot be controlled eg rapid decompression while in cruise at fl370 a rapid descent is needed if structural integrity is not in doubt you should adopt at first the following speed and configuration ?

Target speed mmo speedbrake deployed no flaps.

Ecqb04 november 2017

Question 99-32 : The climb gradient is ?

Always larger than the angle of climb.

Ecqb04 november 2017the 'climb gradient' is defined as the ratio expressed as a percentage of the change in geometric height divided by the horizontal distance travelledclimb gradient = change in height distance travelledthe value of the climb gradient is given as percent the value of the angle of climb is given in degreefor example 5% = 3°we can say that the climb gradient is always larger than the angle of climb

Question 99-33 : Induced drag is caused by ?

Movement of the aerofoil through the air.

Ecqb04 feedback november 2017

Question 99-34 : How does an increase in aircraft mass affect the gliding range ?

Has no effect on gliding range.

Question 99-35 : Under what condition does pressure altitude has the same value as density altitude ?

At standard temperature.

Ecqb04 revised november 2017

Question 99-36 : What is true about a clearway ?

A clearway can be water or land and must be under the control of the aerodrome authority.

Ecqb04 november 2017

Question 99-37 : The effect an increase of weight has on the value of stalling speed las is that vs ?

Increases.

Stall speed of an aircraft changes in proportion to the square root of the change in massfor example if an aeroplane has a stall speed of 78 kt at its mass of 5000 kg the stall speed when the mass is 6850 kg will be change in mass ratio = new mass old mass = 68505000 = 137square root of 137 = 117original stall speed = 78 ktstall speed for a weight of 6850 kg ==> 78 x 117 = 91 ktvs increases for an increase of weight stall will occur earlier

Question 99-38 : An aircraft has a stall speed of 83 kt on short final its speed will be ?

108 kt.

On short final you are supposed to be at 13 x vs

Question 99-39 : In twin engine aeroplanes with propellers turning clockwise as seen from behind ?

The left engine is the critical engine.

Clockwise rotation as viewed from the pilot's seat the critical engine will be the left engine com encom080 341jpgmulti engine aeroplanes are subject to p factor just as single engine aeroplanes are the descending propeller blade of each engine will produce greater thrust than the ascending blade when the aeroplane is operated under power and at positive angles of attack the descending propeller blade of the right engine is also a greater distance from the center of gravity and therefore has a longer moment arm than the descending propeller blade of the left engine as a result failure of the left engine will result in the most asymmetrical thrust adverse yaw as the right engine will be providing the remaining thrust

Question 99-40 : The parameters taken into account for take off performance calculations are ?

Outside temperature pressure altitude wind mass.