Which of these statements about computer architecture are correct or incorrect 1 multiprocessing configuration is a hardware solution2 multitasking ?
Control > visibility
The software used to run the ATSU application ATC and AOC ?
Which document deals with considerations of software use in on board aircraft computers ?
Which of these statements about computer architecture are correct or incorrect 1 the software part does not include programmes that make up operating system os 2 the hardware part does not include physical components of computer incorrect 2 incorrect. the operating system (os) a software that acts as intermediary between applications computer hardware hardware part includes physical components of computer (cpu hard drive memory ) at exam this question also appears with statements the software part includes programmes that make up operating system (os) the hardware part includes physical components of computer which in this case correct/correct. 
In computer architecture software defined as A collection of computer programs. the operating system (os) a software that acts as intermediary between applications computer hardware hardware part includes physical components of computer (cpu hard drive memory ) at exam this question also appears with statements the software part includes programmes that make up operating system (os) the hardware part includes physical components of computer which in this case correct/correct. 
In computer architecture hardware defined as The physical components of a computer system. hardware part includes physical components of computer (cpu hard drive memory ). 
In computer architecture a bus a system that Transfers data between computer components. hardware part includes physical components of computer (cpu hard drive memory ). Question 64-8
In a basic computer input and output devices are typically 1 a printer2 a keyboard3 a display4 an optical diskthe combination that regroups all of correct statements Transfers data between computer components. hardware part includes physical components of computer (cpu hard drive memory ). Question 64-9
A basic computer 'von neumann architecture' type uses A processing unit a single storage structure to hold both instructions data. hardware part includes physical components of computer (cpu hard drive memory ). Question 64-10
A machine manipulating data according to a list of instructions A processing unit a single storage structure to hold both instructions data. hardware part includes physical components of computer (cpu hard drive memory ). Question 64-11
In computer architecture a system that transfers data between computer components A processing unit a single storage structure to hold both instructions data. hardware part includes physical components of computer (cpu hard drive memory ). Question 64-12
On an aeroplane without central fuel tank maximum zero fuel mass related to The bending moment at wing root. The maximum zero fuel mass a regulatory limitation (cs23 cs25) it a design limitation to prevent wing bending it defined on assumption that fuel consumed from centre wing tank first without central fuel tank maximum zero fuel mass remains related to bending moment at wing root. Question 64-13
Considering only structural limitations on long distance flights at aeroplane's maximum range traffic load normally limited The maximum take off mass. Maximum zero fuel mass dry operating mass + traffic load maximum take off mass dry operating mass + traffic load + fuel on long distance flight you need lots of fuel fuel does not count as part of traffic load thus traffic load normally limited the maximum take off mass if you need more fuel to perform flight you will normally need to reduce traffic load because maximum take off mass will be reached. Question 64-14
Loads must be adequately secured in order to Avoid unplanned cg movement aircraft damage. Cg will move during flight this change of cg can be planned loads must be adequately secured in order to avoid unplanned cg movement tragic example on august 7 1997 fine air flight 101 a cargo dc 8 61f registration n27ua en route from miami to santo domingo in dominican republic suffered sudden movement of cargo materials in aft cargo hold while on take off the aircraft's nose rose steeply due to sudden uneven weight distribution caused shifting boxes of denim material that had not been securely fastened the pilots departing out of runway 27r attempted to recover but aircraft stalled crashed onto a field adjacent miami city rail yard less than a mile from airport the only deaths were those of three aircrew members a company security guard on flight a man in a parking. Question 64-15
What determines longitudinal stability of an aeroplane The location of centre of gravity with respect to neutral point. Neutral point (easa definition) the aft position of aircraft centre of gravity where aircraft on point of becoming unstable it point where longitudinal stability becomes neutral. Question 64-16
The zero fuel mass of an aeroplane always equal to The take off mass minus mass of fuel while setting take off thrust. Neutral point (easa definition) the aft position of aircraft centre of gravity where aircraft on point of becoming unstable it point where longitudinal stability becomes neutral. Question 64-17
If centre of gravity near forward limit aeroplane will Require elevator trim which will result in an increase in fuel consumption. Neutral point (easa definition) the aft position of aircraft centre of gravity where aircraft on point of becoming unstable it point where longitudinal stability becomes neutral. Question 64-18
The maximum taxi ramp mass governed Structural considerations. The maximum taxi or ramp mass the maximum weight authorised manoeuvring (taxiing or towing) an aircraft on ground as limited aircraft strength airworthiness requirements it governed structural considerations. Question 64-19
When considering effects of increased mass on an aeroplane which of following true Stalling speeds will be higher. The maximum taxi or ramp mass the maximum weight authorised manoeuvring (taxiing or towing) an aircraft on ground as limited aircraft strength airworthiness requirements it governed structural considerations. Question 64-20
If an aeroplane at a higher mass than anticipated a given airspeed angle of attack will Be greater drag will increase endurance will decrease. Since you have to generate more lift a same speed drag increases to counteract this drag fuel consumption will increase endurance decreases. Question 64-21
Which of following most likely to affect range of centre of gravity positions on an aeroplane Elevator tailplane (horizontal stabiliser) effectiveness in all flight conditions. Every aircraft has a maximum forward rearward cg position at which aircraft designed to operate operating an aircraft with cg outside these limits affects handling characteristics of aircraft. Question 64-22
During a violent avoidance manoeuvre a light twin aircraft certified to easa cs 23 requirements was subjected to an instantaneous load factor of 4 2 the flight manual specifies that aircraft certified in normal category a load factor of 1 9 +3 8 considering certification requirements and taking into account that manufacturer of twin did not include during its conception a supplementary margin in flight envelope it might be possible to observe A permanent deformation of structure. The easa cs 23 requirements state that safety margin 1 5 3 8 x 1 5 = 5 7g at 4 2g we remain below ultimate load (rupture) but it might be possible to observe a permanent deformation of structure. Question 64-23
For a given configuration stall speed of an aeroplane will be highest when loaded To maximum allowable mass with most forward cg. A heavier aircraft needs to push more air downward to generate enough lift to maintain level flight to generate more lift you need to increase airspeed or angle of attack at same airspeed a heavier airplane will need a higher angle of attack to maintain level flight at same angle of attack a heavier airplane will need a higher airspeed to maintain level flight thus stall speed higher a heavier airplane the most forward cg is more down force tail needs to generate to compensate keep airplane from pitching down this increased down force must be counteracted increased lift from wing that of course means an increase in angle of attack or airspeed = stall speed increases. Question 64-24
Comparing a forward cg position with an aft one forward cg position will cause a To maximum allowable mass with most forward cg. A aft cg will have folowing effect decreased stability decreased down tail force required leading to less drag less fuel consumption the forward cg position will cause an increasing down tail force required leading to more drag leading to more fuel consumption resulting in a decreasing range. Question 64-25
In cruise flight an aft centre of gravity location will Decrease longitudinal static stability. Positive longitudinal static stability the initial response in pitch in level flight to return to equilibrium around a trim point after displacement a gust or the temporary movement of elevator control static stability decreases as centre of gravity moves aft toward neutral point when a gust or a pilot input increases or decreases angle of attack it will produce a more important destabilizing moment. Question 64-26
Overloading has following effects on performance Increased take off landing distance reduced rate of climb increased fuel consumption. Positive longitudinal static stability the initial response in pitch in level flight to return to equilibrium around a trim point after displacement a gust or the temporary movement of elevator control static stability decreases as centre of gravity moves aft toward neutral point when a gust or a pilot input increases or decreases angle of attack it will produce a more important destabilizing moment. Question 64-27
Which of following statements correct The maximum landing mass of an aeroplane restricted structural limitations performance limitations the strength of runway. The maximum landing mass the maximum aircraft mass due to design or operational limitations at which an aircraft permitted to land performance limitations are due to length of runway or presence of obstacle in 'go aroun path (you will have to maintain a minimum climb gradient in case of go around). Question 64-28
Which of following statements correct A tail heavy aeroplane less stable stalls at a lower speed than a nose heavy aeroplane. The question talking about centre of gravity being towards rear of envelope compared to near front as opposed to out of envelope on either side within envelope further forward (nose heavy) greater stability (good thing) but price paid in greater wing loading induced tail down elevator to balance forward centre of gravity this leads to higher stalling speed (bad thing) if tail heavy contrast stability reduced (bad thing) but stall speed lower (good thing) as there less need the wing load inducing tail down elevator. Question 64-29
An aeroplane which scheduled to fly an oceanic sector due to depart from a high altitude airport in tropics at 1400 local time the airport has an exceptionally long runway which of following most likely to be limiting factor s in determining take off mass Altitude temperature of departure airfield. Altitude temperature affect your performances (engine thrust lift) even if an exceptionally long runway will permit to take off regulations state that you must also be able meet a minimum value of climb performance thus limiting factors are altitude temperature of departure airfield. Question 64-30
At maximum certificated take off mass an aeroplane departs from an airfield which not limiting either take off or landing masses during initial climb number one engine suffers a contained disintegration an emergency declared and aeroplane returns to departure airfield an immediate landing the most likely result of this action will be A high threshold speed possible undercarriage or other structural failure. As actual landing mass will be much higher than normal landing we need a higher approach speed (stall speed increased approach speed equal to velocity stall x 1 3) and as we are heavier than normal landing there may be undercarriage or other structural failure an overweight landing generally recommended under following conditions a malfunction that seriously affects airworthiness of aircraft a condition where an expeditious landing would reduce exposure to a degrading level of safety one engine inoperative (although a one engine out condition affects aircraft performance handling characteristics a landing must be considered in order to reduce exposure toadditional problems with remaining engine a serious illness on board requiring immediate medical attention after an overweight landing company maintenance staff must be advised appropriate maintenance checks carried out before further flight. Question 64-31
The effect of centre of gravity cg being close to forward limit A reduced rate of climb capability. The forward cg limit defined as most nose heavy loading condition that will allow aircraft to be rotated on takeoff flared upon landing with a centre of gravity close to forward limit you need a large up deflection on tail horizontal stabiliser to maintain at least horizontal flight if you need to climb you will quickly reach maximum up deflection your rate of climb capability reduced. Question 64-32
The maximum zero fuel mass a mass limitation the Strength of wing root. Maximum zero fuel mass the maximum permissible mass of an aeroplane with no usable fuel the mzfm a structural limit based on bending moments of wing root. Question 64-33
In order to provide an adequate stall margin in level flight a speed of 1 3vs used at a mass of 120000 kg this a cas of 180 kt if mass of aeroplane increased to 135000 kg value of 1 3vs will be Increased to 9 kt drag will increase air distance per kg of fuel will decrease. 135000/120000 = 1 125 180 x square root of 1 125 = 191 kt if speed increases drag increases thus a same unit of fuel air distance will be lesser. Question 64-34
What are effects of a cg in front of forward limit range And absolute ceiling decrease. A forward cg means that pitch down moment high the elevator must provide a moment opposing this pitch down moment adding a high downward force to weight of aircraft which then increased therefore climb performance ceiling will be decreased the increased drag of elevator will cause a higher fuel consumption a given airspeed thus decreasing range endurance. Question 64-35
The centre of gravity of an aircraft Can be allowed to move between defined limits. Centre of gravity (cg) that point through which force of gravity said to act on a mass always acts parallel to gravity vector. Question 64-36
Which statement regarding relationship between traffic load and range correct The traffic load can be limited the desired range. Traffic load might be exchanged fuel to extend range. Question 64-37
The term 'useful loa as applied to an aircraft includes Traffic load usable fuel only. Traffic load might be exchanged fuel to extend range. Question 64-38
If other factors are unchanged fuel mileage nautical miles per kg Lower with a forward centre of gravity position. With a forward cg aircraft 'nose heavy' it has a nose down moment thus downforce on tail on a steady flight must be increased the total aircraft weight increases therefore more weight = more drag = more power the fuel mileage (nautical miles per kg) lower with a forward centre of gravity position example with a aft cg fuel mileage = 10 nm 100 kg with a forward cg fuel mileage = only 8 nm 100 kg. Question 64-39
The stalling speed of an aeroplane will be highest when it loaded with a High gross mass forward centre of gravity. A forward cg requires more lift generates more drag stalling speed will be greater than with an aft cg also a higher gross mass it mandatory to generates more lift which generates more induced drag stalling speed increases. Question 64-40
With centre of gravity on forward limit which of following to be expected High gross mass forward centre of gravity. The most forward cg is more down force tail needs to generate to compensate keep airplane from pitching down this increased down force must be counteracted increased lift from wing that of course means an increase in angle of attack or airspeed = stall speed increases = consumption increases = range decreases.
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