Which of the following statements concerning tires is the major consideration when establishing the tyre speed limit ?
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What will increase the 'Landing Field Length Limited landing mass' when operating with the anti skid inoperative ?
When calculating approach speeds the minimum approach speed in the initial approach phase is usually ?
You are approaching a wet runway in gusty conditions you should Increase approach speed, adopt a steeper approach path, decrease approach speed, increase landing speed. Ecqb04, october 2017 you should, in order to avoid windshear, increase slightly your approach speed... but you must land at your calculated landing speed, not less, not more... 
Compared with a level runway use of a runway with a 2% downslope will Reduce vmbe, increase vmbe v , not affect value of v , increase vmbe decreased v. Ecqb04, october 2017 vmbe (maximum brake energy speed) the speed from which aeroplane may be brought to a stop without exceeding maximum energy absorption capability of 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 down hill component of runway). also, a downhill slope means that you need a longer distance to stop in case of failure before v1, you will reach v1 at an earlier point in take off run than on a 'flat' runway. v1 has to be reduced. vmbe v1 will be reduced. 
If anti skid system inoperative may auto brake system can be used No, never, yes, without any limitation, yes, if selected to minimum, only if full reverse thrust used. anti skid system protection provided during auto brake operation, therefore, if anti skid inoperative you can not use auto brake system. 
You climb with a climb speed schedule 300/ 78 what do you expect in crossover altitude 29200 ft oat = isa The rate of climb increases since constant ias climb replaced the constant mach climb, during acceleration to mach number.78 rate of climb approximately zero, rate of climb decreases since climb performance at a constant mach number grossly reduced as compared to constant ias, no noticeable effect since true airspeed at 3 kts ias.78 mach are same (at isa temperature tas = 46kt). Question CS-23 Performance Class B - theory 78 Answer 8
The effect of an aft cg on take off performance are Take off distance decreases, climb gradient increases, take off distance decreases, climb gradient remains constant, take off distance climb gradient increase, take off distance climb gradient decrease. Ecqb04, october 2017. Question CS-23 Performance Class B - theory 78 Answer 9
At maximum landing mass structure of aircraft designed a rate of descent of 6 ft/min, 2 ft/min, 25ft/min, 22ft/min. Question CS-23 Performance Class B - theory 78 Answer 10
The approach climb requirement normally met Reducing flap setting approach with one engine inoperative, selecting a runway with no obstacles in go around area, a threshold speed of 2 times stall speed, reducing final approach speed. Question CS-23 Performance Class B - theory 78 Answer 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, increase take off run, decrease take off distance, decrease take off run, decrease take off distance, decrease take off run, increase take off distance. Question CS-23 Performance Class B - theory 78 Answer 12
An uphill slope runway will Increase asdr, decrease asdr, increase asdr only if tom increases, decrease asdr only if tom decreases. Ecqb04, october 2017 a uphill slope increases accelerate stop distance required (asdr). taking off on a uphill slope does decrease braking distance in case of a rejected take off, but it increases distance taken to accelerate to v1 due to addition of uphill component of weight of aircraft decreasing rate of acceleration. Question CS-23 Performance Class B - theory 78 Answer 13
Runway 30 in use and threshold elevation 2139 feet threshold elevation of runway 12 2289 feet take off r available 1720 metres and clearway 280 metres what the slope of runway in use 2.65% uphill,.49% uphill, 2.53% per minute,.86% downhill. 2289 ft 2139 ft = 150 ft. 150 ft x 0.3048 = 45,72m. runway lenght 1720m, slope in % is (45,72m /1720m) x 100 = 2.65%. Question CS-23 Performance Class B - theory 78 Answer 14
In event of an engine failure during cruise it necessary to reduce speed and descend to lower altitude at speed For maximum lift/drag ratio and, if necessary, start fuel jettisoning, close to stall speed and, if necessary, starting fuel jettisoning, best rate of climb with full flaps, minimum drag speed (vmd) with full flaps. Question CS-23 Performance Class B - theory 78 Answer 15
On a long distance flight optimum cruise altitude continuously increased during flight As a consequence of fuel consumption, to take in account passenger movements all along flight, due do decreasing outside air temperature, because of movements of centre of gravity. Question CS-23 Performance Class B - theory 78 Answer 16
The take off and landing distances on a grass runway are in relation to that a paved runway Take off distance landing distance increase, take off distance landing distance decrease, take off distance decreases landing distance increases, take off distance increases landing distance decreases. Ecqb04, october 2017 take off distance on a dry short grass runway compared to a paved dry runway distance increases 20%. landing distance on a dry short grass runway compared to a paved dry runway distance increases 15%. Question CS-23 Performance Class B - theory 78 Answer 17
Which take off condition most likely resulting in poorest climb performance 5ft field elevation, isa +2 °, take off flaps 3 °, sea level field elevation, isa2 °, take off flaps °, sea level field elevation, isa +5°, take off flaps °, 5ft field elevation, isa5°, take off flaps °. Question CS-23 Performance Class B - theory 78 Answer 18
During take off time between critical engine failure and v1 recognition time assumed to be approximately 2 seconds, 5 seconds, 6 seconds, seconds. following an engine failure at v1 allowing a reaction time of 2 seconds a correctly loaded aircraft must be capable of decelerating to a halt within accelerate stop distance available. Question CS-23 Performance Class B - theory 78 Answer 19
The lift off speed vlof and take off safety speed v2 when flap position changed from 10° to 5° will Increase / increase, decrease / increase, increase / decrease, decrease / decrease. Question CS-23 Performance Class B - theory 78 Answer 20
An aircraft has this following flap position up 5° 10° 20° if flap setting 'up' instead of 10° it will Increase take off distance, decrease landing distance, decrease ground roll distance, decrease take off distance. Question CS-23 Performance Class B - theory 78 Answer 21
Changing flaps selection from 10° to flaps 0° while establish in climb after take off will have following effects Climb gradient vy increase, climb gradient vy decrease, climb gradient remains unchanged vy decreases, climb gradient increases vy decreases. Ecqb04, october 2017 vy the indicated airspeed best rate of climb. climbing at vy allows pilots to maximize altitude gain per unit time. climb gradient defined as ratio of increase of altitude to horizontal air distance expressed as a percentage. you will generate less drag with a less flaps selection, gap between thrust available thrust required increases. Question CS-23 Performance Class B - theory 78 Answer 22
During a descent a headwind will have following effects Descent angle remains constant, flight path angle increases, descent angle decreases, flight path angle increases, descent angle flight path angle increases, descent angle remains constant, flight path angle decreases. Ecqb04, october 2017 during a descent a headwind will increases flight path angle img /com_en/com080 642.jpg the descent distance over ground decreased, rate of descent the angle of descent remain unchanged. angle of descent (descent angle) the angle you maintain on your attitude indicator (artificial horizon / pfd). note for theoretical knowledge examination purposes, 'flight path angle' assumed to be ground related. the flight path angle the actual vector flown in relation to ground, it will increase during descent with a headwind. Question CS-23 Performance Class B - theory 78 Answer 23
During a descent a tailwind will have following effects Descent angle remains constant, flight path angle decreases, descent angle remains constant, flight path angle increases, descent angle flight path angle increases, descent angle increases, flight path angle decreases. Ecqb04, october 2017 during a descent a tailwind will decreases flight path angle img /com_en/com032 351.jpg the descent distance over ground increased, rate of descent the angle of descent remain unchanged. angle of descent (descent angle) the angle you maintain on your attitude indicator (artificial horizon / pfd). note for theoretical knowledge examination purposes, 'flight path angle' assumed to be ground related. the flight path angle the actual vector flown in relation to ground, it will decrease during descent with a tailwind. Question CS-23 Performance Class B - theory 78 Answer 24
The 'flight path angle' the angle Between horizontal plane the flight path, between relative airflow the horizontal plane, between longitudinal axis the horizontal plane, displayed on attitude indicator (artificial horizon). Ecqb04, october 2017 note for theoretical knowledge examination purposes, 'flight path angle' assumed to be ground related. the flight path angle the actual vector flown in relation to ground, it will decrease during descent with a tailwind. angle of descent (descent angle) the angle you maintain on your attitude indicator (artificial horizon / pfd). Question CS-23 Performance Class B - theory 78 Answer 25
The vertical 'flight path angle' assumed to be Ground related, same as pitch angle, relative to longitudinal axis, angle of attack. Ecqb04, october 2017 note for theoretical knowledge examination purposes, 'flight path angle' assumed to be ground related. the flight path angle the actual vector flown in relation to ground, it will decrease during descent with a tailwind, will increase with a headwind. angle of descent (descent angle) the angle you maintain on your attitude indicator (artificial horizon / pfd). Question CS-23 Performance Class B - theory 78 Answer 26
Specific fuel consumption sfc Mass of fuel required to produce unit power unit time, designed fuel consumption a given rpm, quantity of fuel required to run engine one minute at maximum operating conditions, maximum fuel consumption of aircraft. Ecqb04, october 2017 specific fuel consumption the amount of fuel burnt per unit of thrust. for jets, it reduces with altitude up to tropopause. Question CS-23 Performance Class B - theory 78 Answer 27
The specific range sr The air distance that aircraft would fly per kilogram of fuel, ground distance that aircraft would fly per kilogram of fuel, ground distance divided air distance, air distance that aircraft would fly per unit of thrust. specific range (sr) the enroute tas divided the current fuel flow. sr = true airspeed/total fuel flow. the units of sr are nautical miles per gallon, or nautical miles per pound of fuel. Question CS-23 Performance Class B - theory 78 Answer 28
How does asdr accelerate stop distance required will be affected the addition of a stopway into runway strip length the asdr Remains same, increases, decreases, decreases only a downhill stopway. Ecqb04, november 2017 a stopway a defined rectangular area on ground at end of take off run available, prepared as a suitable area in which an aircraft can be stopped in case of an abandoned take off. asdr (accelerate stop distance required) calculated with actual values of flight (mass, wind, up or down slope, oat, pressure altitude, etc...), it's a fixed value the projected take off. the declared distances 'asda' (acceleration stop distance available) the length of take off run available plus length of stopway. with a stopway provided, 'runway strip' increase. Question CS-23 Performance Class B - theory 78 Answer 29
What the effect of using engine bleed air on take off distance Reduces available thrust increases take off distance, reduces available thrust take off distance, bleed air has no effect on take off distance, increases available thrust take off distance. Question CS-23 Performance Class B - theory 78 Answer 30
Which of following will decrease landing distance The spoilers, a wet runway, a tailwind, a high altitude airfield. Ecqb04, november 2017. Question CS-23 Performance Class B - theory 78 Answer 31
If cabin altitude cannot be controlled eg rapid decompression while in cruise at fl370 a rapid descent needed if structural integrity not in doubt you should adopt at first following speed and configuration Target speed mmo, speedbrake deployed, no flaps, target speed vmo, speedbrake deployed, no flaps, target speed mmo, speedbrake up, flaps °, target speed mmo, speedbrake deployed, full flaps. Ecqb04, november 2017. Question CS-23 Performance Class B - theory 78 Answer 32
The climb gradient Always larger than angle of climb, always smaller than angle of climb, same as angle of climb, represents angle of variation. Ecqb04, november 2017. the 'climb gradient' defined as ratio, expressed as a percentage, of change in geometric height divided the horizontal distance travelled. climb gradient = change in height / distance travelled the value of climb gradient given as percent, value of angle of climb given in degree. for example, 5% = 3°. we can say that climb gradient always larger than angle of climb. Question CS-23 Performance Class B - theory 78 Answer 33
Induced drag caused Movement of aerofoil through air, boundary layer effects, shape of aerofoil, increased zero lift drag. Ecqb04 (feedback), november 2017. Question CS-23 Performance Class B - theory 78 Answer 34
How does an increase in aircraft mass affect gliding range Has no effect on gliding range, increases gliding range, decreases gliding range, none of above. Question CS-23 Performance Class B - theory 78 Answer 35
Under what condition does pressure altitude has same value as density altitude At standard temperature, at sea level when temperature°c, when altimeter setting3.25 hpa, when altimeter has no position error. Ecqb04 (revised), november 2017. Question CS-23 Performance Class B - theory 78 Answer 36
What true about a clearway A clearway can be water or land must be under control of aerodrome authority, a clearway has a virtual gradient of.5%, a clearway can be used to bring aircraft to a full stop after an engine failure, a clearway has a minimum width of 9 m. Ecqb04, november 2017. Question CS-23 Performance Class B - theory 78 Answer 37
The effect an increase of weight has on value of stalling speed las that vs Increases, decreases, remains constant, increases or decreases, depending on amount of weight increase. stall speed of an aircraft changes in proportion to square root of change in mass. for example, if an aeroplane has a stall speed of 78 kt at its mass of 5000 kg. the stall speed when mass 6850 kg will be change in mass ratio = new mass / old mass = 6850/5000 = 1.37 square root of 1.37 = 1.17 original stall speed = 78 kt stall speed a weight of 6850 kg ==> 78 x 1.17 = 91 kt. vs increases an increase of weight. stall will occur earlier. Question CS-23 Performance Class B - theory 78 Answer 38
An aircraft has a stall speed of 83 kt on short final its speed will be on (short) final you are supposed to be at 1.3 x vs. Question CS-23 Performance Class B - theory 78 Answer 39
The parameters taken into account take off performance calculations are Outside temperature, pressure altitude, wind, mass, standard temperature, pressure altitude, wind, mass, standard temperature, standard pressure, wind, mass, outside temperature, standard pressure, wind, mass. Question CS-23 Performance Class B - theory 78 Answer 40
For a piston engine aeroplane speed maximum range That which gives maximum lift to drag ratio, that which gives minimum value of induced drag, that which gives maximum value of lift,.4 times stall speed in clean configuration. if you want to stay in flight longest time possible (maximum endurance), you need to fly at minimum power required speed (vmp velocity minimum power)). if you want to travel maximum distance possible (maximum range), you need to fly at speed that wich gives maximum lift to drag ratio (vmd velocity minimum drag).
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