In computer architecture the software is defined as ? [ Students VFR ]

Question 65-1 : A collection of computer programs the physical components of a computer system the storage structure inside the central processing unit cpu the volatile memory ram random access memory

exemple 165 A collection of computer programs. — A collection of computer programs.

In computer architecture the hardware is defined as ?

Question 65-2 : The physical components of a computer system the programmes which make up the operating system os the non volatile memory rom read only memory the non volatile memory ram random access memory

exemple 169 The physical components of a computer system. — Admin .hardware part includes the physical components of the computer cpu hard drive memory The physical components of a computer system.

In computer architecture a bus is a system that ?

Question 65-3 : Transfers data between computer components ensures sequencing and co ordination of operations performs basic arithmetic operations performs basic logic operations

exemple 173 Transfers data between computer components. — Transfers data between computer components.

In a basic computer the input and output devices are typically .1 a printer.2 ?

Question 65-4 : 1 2 3 4 2 3 4 2 4 1 2 3

A basic computer 'von neumann architecture' type uses ?

Question 65-5 : A processing unit and a single storage structure to hold both instructions and data a control unit and two storage structures one for instructions another for data a control unit which is a user/computer interface an arithmetic and logic unit alu to store the instructions

A machine for manipulating data according to a list of instructions is ?

Question 65-6 : A computer a control unit a central processing unit cpu an optical disk

In computer architecture the a system that transfers data between computer ?

Question 65-7 : A bus a control unit the volatile memory the arithmetic logic unit alu

On an aeroplane without central fuel tank the maximum zero fuel mass is related ?

Question 65-8 : The bending moment at the wing root variable equipment for the flight maximum structural take off mass wing loaded trip fuel

exemple 193 The bending moment at the wing root. — The maximum zero fuel mass is a regulatory limitation cs23 and cs25 it is a design limitation to prevent wing bending and it is defined on the assumption that fuel is consumed from the centre wing tank first .without central fuel tank the maximum zero fuel mass remains related to the bending moment at the wing root The bending moment at the wing root.

Considering only structural limitations on long distance flights at the ?

Question 65-9 : The maximum take off mass the maximum zero fuel mass the maximum zero fuel mass plus the take off mass the maximum landing mass

exemple 197 The maximum take-off mass. — Maximum zero fuel mass is dry operating mass + traffic load .maximum take off mass is dry operating mass + traffic load + fuel .on long distance flight you need lots of fuel and fuel does not count as part of the traffic load thus the traffic load is normally limited by the maximum take off mass if you need more fuel to perform the flight you will normally need to reduce the traffic load because the maximum take off mass will be reached The maximum take-off mass.

Loads must be adequately secured in order to ?

Question 65-10 : Avoid unplanned cg movement and aircraft damage avoid any cg movement during flight prevent excessive 'g' loading during the landing flare allow steep turns

exemple 201 Avoid unplanned cg movement and aircraft damage. — Cg will move during the 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 the dominican republic suffered sudden movement of cargo materials in the aft cargo hold while on take off the aircraft's nose rose steeply due to the sudden uneven weight distribution caused by shifting boxes of denim material that had not been securely fastened .the pilots departing out of the runway 27r attempted to recover but the aircraft stalled and crashed onto a field adjacent the miami city rail yard less than a mile from the airport .the only deaths were those of the three aircrew members a company security guard on the flight and a man in a parking Avoid unplanned cg movement and aircraft damage.

What determines the longitudinal stability of an aeroplane ?

Question 65-11 : The location of the centre of gravity with respect to the neutral point the effectiveness of the horizontal stabilizer rudder and rudder trim tab the relationship of thrust and lift to weight and drag the dihedral angle of sweepback and the keel effect

exemple 205 The location of the centre of gravity with respect to the neutral point. — Neutral point easa definition .the aft position of the aircraft centre of gravity where the aircraft is on the point of becoming unstable it is point where longitudinal stability becomes neutral The location of the centre of gravity with respect to the neutral point.

The zero fuel mass of an aeroplane is always equal to ?

Question 65-12 : The take off mass minus the mass of fuel while setting take off thrust the take off mass minus the wing fuel mass the maximum take off mass minus the mass of fuel while setting take off thrust the take off mass minus the fuselage fuel mass

exemple 209 The take-off mass minus the mass of fuel while setting take-off thrust. — The take-off mass minus the mass of fuel while setting take-off thrust.

If the centre of gravity is near the forward limit the aeroplane will ?

Question 65-13 : Require elevator trim which will result in an increase in fuel consumption benefit from reduced drag due to the decrease in angle of attack require less power for a given airspeed tend to over rotate during take off

exemple 213 Require elevator trim which will result in an increase in fuel consumption. — Require elevator trim which will result in an increase in fuel consumption.

The maximum taxi ramp mass is governed by ?

Question 65-14 : Structural considerations tyre speed and temperature limitations bearing strength of the taxiway pavement taxi distance to take off point

exemple 217 Structural considerations. — The maximum taxi or ramp mass is the maximum weight authorised for manoeuvring taxiing or towing an aircraft on the ground as limited by aircraft strength and airworthiness requirements it is governed by structural considerations Structural considerations.

When considering the effects of increased mass on an aeroplane which of the ?

Question 65-15 : Stalling speeds will be higher stalling speeds will be lower gradient of climb for a given power setting will be higher flight endurance will be increased

exemple 221 Stalling speeds will be higher. — Stalling speeds will be higher.

If an aeroplane is at a higher mass than anticipated for a given airspeed the ?

Question 65-16 : Be greater drag will increase and endurance will decrease be decreased drag will decrease and endurance will increase remain constant drag will decrease and endurance will decrease remain constant drag will increase and endurance will increase

exemple 225 Be greater, drag will increase and endurance will decrease. — Since you have to generate more lift for a same speed drag increases to counteract this drag fuel consumption will increase endurance decreases Be greater, drag will increase and endurance will decrease.

Which of the following is most likely to affect the range of centre of gravity ?

Question 65-17 : Elevator and tailplane horizontal stabiliser effectiveness in all flight conditions location of the undercarriage the need to maintain a low value of stalling speed the need to minimise drag forces and so improve efficiency

exemple 229 Elevator and tailplane (horizontal stabiliser) effectiveness in all flight conditions. — Every aircraft has a maximum forward and rearward cg position at which the aircraft is designed to operate operating an aircraft with the cg outside these limits affects the handling characteristics of the aircraft Elevator and tailplane (horizontal stabiliser) effectiveness in all flight conditions.

During a violent avoidance manoeuvre a light twin aircraft certified to easa cs ?

Question 65-18 : A permanent deformation of the structure a elastic deformation whilst the load was applied but no permanent distortion no distortion permanent or temporary of the structure rupture of one or more structural components

exemple 233 A permanent deformation of the structure. — The easa cs 23 requirements state that safety margin is 1 5 .3 8 x 1 5 = 5 7g.at 4 2g we remain below the ultimate load rupture but it might be possible to observe a permanent deformation of the structure A permanent deformation of the structure.

For a given configuration the stall speed of an aeroplane will be highest when ?

Question 65-19 : To the maximum allowable mass with the most forward cg to a low total mass with the most forward cg to a low total mass with the most aft cg to the maximum allowable mass with the most aft cg

exemple 237 To the maximum allowable mass with the 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 the same airspeed a heavier airplane will need a higher angle of attack to maintain level flight at the same angle of attack a heavier airplane will need a higher airspeed to maintain level flight thus stall speed is higher for a heavier airplane .the most forward the cg is the more down force the tail needs to generate to compensate and keep the airplane from pitching down this increased down force must be counteracted by increased lift from the wing that of course means an increase in angle of attack or airspeed = the stall speed increases To the maximum allowable mass with the most forward cg.

Comparing a forward cg position with an aft one the forward cg position will ?

Question 65-20 : Decrease in range decrease in the landing speed decrease of the stalling speed tendency to yaw to the right on take off

A aft cg will have the folowing effect . decreased stability . decreased down tail force required leading to less drag and less fuel consumption .the forward cg position will cause an increasing down tail force required leading to more drag and leading to more fuel consumption resulting in a decreasing range

In cruise flight an aft centre of gravity location will ?

Question 65-21 : Decrease longitudinal static stability increase longitudinal static stability have no effect on longitudinal static stability not change the manoeuvrability

exemple 245 Decrease longitudinal static stability. — Positive longitudinal static stability is the initial response in pitch in level flight to return to equilibrium around a trim point after displacement by a gust or by the temporary movement of the elevator control .static stability decreases as the centre of gravity moves aft toward the neutral point .when a gust or a pilot input increases or decreases angle of attack it will produce a more important destabilizing moment Decrease longitudinal static stability.

Overloading has the following effects on performance ?

Question 65-22 : Increased take off and landing distance reduced rate of climb and increased fuel consumption increased take off and landing distance increased rate of climb and increased fuel consumption reduced take off and landing distance increased vne and increased fuel consumption reduced take off and landing distance increased vne and reduced rate of climb

Which of the following statements is correct ?

Question 65-23 : The maximum landing mass of an aeroplane is restricted by structural limitations performance limitations and the strength of the runway the maximum zero fuel mass ensures that the centre of gravity remains within limits after the uplift of fuel the maximum take off mass is equal to the maximum mass when leaving the ramp the basic empty mass is equal to the mass of the aeroplane excluding traffic load and useable fuel but including the crew

exemple 253 The maximum landing mass of an aeroplane is restricted by structural limitations, performance limitations and the strength of the runway. — The maximum landing mass is the maximum aircraft mass due to design or operational limitations at which an aircraft is permitted to land .performance limitations are due to the length of the runway or presence of obstacle in the 'go around' path you will have to maintain a minimum climb gradient in case of go around The maximum landing mass of an aeroplane is restricted by structural limitations, performance limitations and the strength of the runway.

Which of the following statements is correct ?

Question 65-24 : A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane if the actual centre of gravity is located behind the aft limit of centre of gravity it is possible that the aeroplane will be unstable making it necessary to increase elevator forces if the actual centre of gravity is close to the forward limit of the centre of gravity the aeroplane may be unstable making it necessary to increase elevator forces the lowest stalling speed is obtained if the actual centre of gravity is located in the middle between the aft and forward limit of centre of gravity

exemple 257 A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane. — The question is talking about the centre of gravity being towards the rear of the envelope compared to near the front as opposed to out of the envelope on either side within the envelope the further forward nose heavy the greater the stability good thing but the price is paid in greater wing loading induced by tail down elevator to balance the forward centre of gravity .this leads to higher stalling speed bad thing .if tail heavy by contrast stability is reduced bad thing but stall speed is lower good thing as there is less need for the wing load inducing tail down elevator A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane.

An aeroplane which is scheduled to fly an oceanic sector is due to depart from ?

Question 65-25 : Altitude and temperature of the departure airfield maximum zero fuel mass maximum certificated take off mass en route obstacle clearance requirements

exemple 261 Altitude and temperature of the departure airfield. — Altitude and temperature affect your performances engine thrust and 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 the limiting factors are altitude and temperature of the departure airfield Altitude and temperature of the departure airfield.

At maximum certificated take off mass an aeroplane departs from an airfield ?

Question 65-26 : A high threshold speed and possible undercarriage or other structural failure a high threshold speed and a shorter stop distance a landing further along the runway than normal a landing short resultant from the increased angle of approach due to the very high aeroplane mass

exemple 265 A high threshold speed and possible undercarriage or other structural failure. — As the actual landing mass will be much higher than normal for landing we need a higher approach speed stall speed is increased and approach speed is equal to velocity stall x 1 3 .and as we are heavier than normal for landing there may be undercarriage or other structural failure .an overweight landing is generally recommended under the following conditions . a malfunction that seriously affects the airworthiness of the aircraft . a condition where an expeditious landing would reduce the exposure to a degrading level of safety . one engine inoperative although a one engine out condition affects the aircraft performance and handling characteristics a landing must be considered in order to reduce the exposure toadditional problems with the remaining engine . a serious illness on board requiring immediate medical attention .after an overweight landing company maintenance staff must be advised and appropriate maintenance checks carried out before further flight A high threshold speed and possible undercarriage or other structural failure.

The effect of the centre of gravity cg being close to the forward limit is ?

Question 65-27 : A reduced rate of climb capability an improved rate of climb capability reduced specific fuel consumption decreased induced drag

exemple 269 A reduced rate of climb capability. — The forward cg limit is defined as the most nose heavy loading condition that will allow the aircraft to be rotated on takeoff and flared upon landing .with a centre of gravity close to the 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 the maximum up deflection your rate of climb capability is reduced A reduced rate of climb capability.

The maximum zero fuel mass is a mass limitation for the ?

Question 65-28 : Strength of the wing root strength of the fuselage allowable load exerted upon the wing considering a margin for fuel tanking total load of the fuel imposed upon the wing

exemple 273 Strength of the wing root. — Maximum zero fuel mass is the maximum permissible mass of an aeroplane with no usable fuel the mzfm is a structural limit based on the bending moments of the wing root Strength of the wing root.

In order to provide an adequate stall margin in level flight a speed of 1 3vs ?

Question 65-29 : Increased to 191 kt drag will increase and air distance per kg of fuel will decrease unaffected as vs always occurs at the same angle of attack increased to 191 kt drag will decrease and air distance per kg of fuel will increase increased to 202 kt but since the same angle of attack is used drag and range will remain the same

exemple 277 Increased to 191 kt, drag will increase and 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 for a same unit of fuel the air distance will be lesser Increased to 191 kt, drag will increase and air distance per kg of fuel will decrease.

What are the effects of a cg in front of the forward limit .range ?

Question 65-30 : And absolute ceiling decrease and absolute ceiling increase increases and absolute ceiling decreases decreases and absolute ceiling increases

exemple 281 And absolute ceiling decrease. — A forward cg means that the pitch down moment is high the elevator must provide a moment opposing this pitch down moment adding a high downward force to the weight of the aircraft which is then increased therefore the climb performance and ceiling will be decreased the increased drag of the elevator will cause a higher fuel consumption for a given airspeed thus decreasing range and endurance And absolute ceiling decrease.

The centre of gravity of an aircraft ?

Question 65-31 : Can be allowed to move between defined limits is in a fixed position and is unaffected by aircraft loading must be maintained in a fixed position by careful distribution of the load may only be moved if permitted by the regulating authority and endorsed in the aircraft's certificate of airworthiness

exemple 285 Can be allowed to move between defined limits. — Centre of gravity cg is that point through which the force of gravity is said to act on a mass and always acts parallel to the gravity vector Can be allowed to move between defined limits.

Which statement regarding the relationship between traffic load and range is ?

Question 65-32 : The traffic load can be limited by the desired range the maximum traffic load is not limited by the reserve fuel quantity the maximum landing mass is basically equal to the maximum zero fuel mass the maximum zero fuel mass limits the maximum quantity of fuel

exemple 289 The traffic load can be limited by the desired range. — Traffic load might be exchanged for fuel to extend range The traffic load can be limited by the desired range.

The term 'useful load' as applied to an aircraft includes ?

Question 65-33 : Traffic load and usable fuel only pilot operating items passengers baggage cargo and usable fuel the revenue earning portion of load plus usable fuel the revenue earning portion of load only

exemple 293 Traffic load and usable fuel only. — Traffic load and usable fuel only.

If other factors are unchanged the fuel mileage nautical miles per kg is ?

Question 65-34 : Lower with a forward centre of gravity position independent from the centre of gravity position higher with a forward centre of gravity position lower with an aft centre of gravity position

exemple 297 Lower with a forward centre of gravity position. — With a forward cg the aircraft is 'nose heavy' it has a nose down moment thus the downforce on the tail on a steady flight must be increased .the total aircraft weight increases and therefore more weight = more drag = more power .the fuel mileage nautical miles per kg is lower with a forward centre of gravity position .example . with a aft cg fuel mileage = 10 nm for 100 kg . with a forward cg fuel mileage = only 8 nm for 100 kg Lower with a forward centre of gravity position.

The stalling speed of an aeroplane will be highest when it is loaded with a ?

Question 65-35 : High gross mass and forward centre of gravity low gross mass and forward centre of gravity high gross mass and aft centre of gravity low gross mass and aft centre of gravity

exemple 301 High gross mass and forward centre of gravity. — A forward cg requires more lift and generates more drag the stalling speed will be greater than with an aft cg .also for a higher gross mass it is mandatory to generates more lift which generates more induced drag the stalling speed increases High gross mass and forward centre of gravity.

With the centre of gravity on the forward limit which of the following is to be ?

Question 65-36 : A decrease in range a decrease in the landing speed a decrease of the stalling speed a tendency to pitch up on take off

exemple 305 A decrease in range. — The most forward the cg is the more down force the tail needs to generate to compensate and keep the airplane from pitching down this increased down force must be counteracted by increased lift from the wing that of course means an increase in angle of attack or airspeed = the stall speed increases = consumption increases = range decreases A decrease in range.

If the centre of gravity of an aeroplane moves forward during flight the ?

Question 65-37 : Heavier making the aeroplane more difficult to manoeuvre in pitch lighter making the aeroplane more difficult to manoeuvre in pitch heavier making the aeroplane more easy to manoeuvre in pitch lighter making the aeroplane more easy to manoeuvre in pitch

exemple 309 Heavier making the aeroplane more difficult to manoeuvre in pitch. — When the centre of gravity moves forward during flight the aeroplane will be more stable but requires more forces to change pitch elevator control will become heavier Heavier making the aeroplane more difficult to manoeuvre in pitch.

The determination of the centre of gravity in relation to the mean aerodynamic ?

Question 65-38 : Length of the mean aerodynamic chord and the leading edge length of the mean aerodynamic chord and the trailing edge position of the aerodynamic convergence point position of the aerodynamic centre of pressure

exemple 313 Length of the mean aerodynamic chord and the leading edge. — Longitudinal cg location is normally expressed as a percentage of the mean aerodynamic chord mac from its leading edge Length of the mean aerodynamic chord and the leading edge.

The maximum zero fuel mass ?

Question 65-39 : Is calculated for a maximum load factor of +2 5 g is calculated for a maximum load factor of +3 5 g can be increased by stiffening the wing imposes fuel dumping from the outer wings tank first

exemple 317 Is calculated for a maximum load factor of +2.5 g. — Is calculated for a maximum load factor of +2.5 g.

When has the centre of gravity to be computed ?

Question 65-40 : Prior to every flight at least every four years during every yearly inspection after every 400 hours inspection

exemple 321 Prior to every flight. — Prior to every flight.

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