Quiz
Mass and Balance ATPL
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Fragen in diesem Quiz (50)
1The higher the Takeoff Mass:
1) Manoeuvrability is reduced.
2) Range will decrease but endurance will increase.
3) Gliding range will reduce.
4) Stalling speed will increase.- A1,2,3,4
- B3
- C1,4
- D4
2A flight benefits from a strong tailwind which was not forecast.
On arrival at destination a straight in approach and immediate
landing clearance is given. The Landing Mass will be
higher than planned and:- Athe approach path will be steeper.
- Bthe landing distance will be unaffected.
- Cthe landing distance required will be longer.
- Dthe approach path will be steeper and threshold speed
higher.
3When considering the effects of increased mass on an aeroplane,
which of the following is true?- AFlight endurance will be increased.
- BStalling speeds will be lower.
- CGradient of climb for a given power setting will be higher.
- DStalling speeds will be higher.
4If an aeroplane is at a higher mass than anticipated, for a given
airspeed the angle of attack will:- Aremain constant, drag will decrease and endurance will decrease.
- Bbe decreased, drag will decrease and endurance will increase.
- Cbe greater, drag will increase and endurance will decrease.
- Dremain constant, drag will increase and endurance will increase.
5Fuel loaded onto an aeroplane is 15.400 kg but is erroneously
entered into the load and trim sheet as 14.500 kg. This error
is not detected by the flight crew but they will notice that:- AV, will be reached sooner than expected.
- Bspeed at un-stick will be higher than expected.
- CV, will be increased.
- Dthe aeroplane will rotate much earlier than expected.
6In order to provide an adequate buffet boundary at the commencement
of the cruise a speed of 1,3 Vs is used. At a mass
of 120.000 kg this is a CAS of 180 kts. If the mass of the aeroplane
is increased to 135.000 kg the value of 1,3 V 5 will be:- Aincreased to 202 kts but, since the same angle of attack
is used, drag and range will remain the same. - Bunaffected as Vs always occurs at the same angle of attack.
- Cincreased to 191 kts, drag will decrease and air distance
per kg of fuel will increase. - Dincreased to 191 kts, drag will increase and air distance per kg
of fuel will decrease.
- Aincreased to 202 kts but, since the same angle of attack
7An additional baggage container is loaded into the aft cargo
compartment but is not entered into the load and trim sheet.
The aeroplane will be heavier than expected and calculated
takeoff safety speeds:- Aare unaffected but V, will be increased.
- Bwill not be achieved.
- Cwill be greater than required.
- Dwill give reduced safety margins.
8Prior to departure an aeroplane is loaded with 16.500 lit res
of fuel at a fuel density of 780 kg/m3. This is entered into
the load sheet as 16.500 kg and calculations are carried out accordingly.
As a result of this error, the aeroplane is:- Aheavier than anticipated and the calculated safety speeds
will be too high. - Blighter than anticipated and the calculated safety speeds will
be too low. - Clighter than anticipated and the calculated safety speeds will
be too high. - Dheavier than anticipated and the calculated safety speeds
will be too low.
- Aheavier than anticipated and the calculated safety speeds
9At maximum certificated Takeoff Mass, an aeroplane departs
from an airfield which is not limiting for either takeoff or Landing
Masses. During initial climb the number one engine suffers
a contained disintegration. An emergency is declared
and the aeroplane returns to departure airfield for an immediate
landing. The most likely result of this action will be:- Aa landing short resultant from the increased angle of approach
due to the very high aeroplane mass. - Ba high threshold speed and possible undercarriage or other
structural failure. - Ca high threshold speed and a shorter stop distance.
- Da landing further along the runway than normal.
- Aa landing short resultant from the increased angle of approach
10During a violent avoidance manoeuvre, a light twin aircraft
certified to EASA requirements, was subjected to an instantaneous
load factor of 4,2. The Flight Manual specifies that
the aircraft is certified in the normal category for a load factor
of -1,9 to +3,8. Considering the certification requirements
and taking into account that the manufacturer of the twin
did not include, during its conception, a supplementary margin
in the flight envelope, it might be possible to observe:- Arupture of one or more structural components.
- Ba permanent deformation of the structure.
- Can elastic deformation whilst the load was applied,
but no permanent distortion. - Dno distortion, permanent or temporary, of the structure.
11If an extra load is loaded into an aircraft, the stall speed
is likely to:- Astay the same.
- Bdecrease.
- Cincrease.
- Dchange depending on whether the load was placed FWD
or AFT ofthe eG.
12Overloading has the following effects on performance:
- Aincreased takeoff and landing distance, reduced rate of climb
and increased fuel consumption. - Bincreased takeoff and landing distance, increased rate
of climb and increased fuel consumption. - Creduced takeoff and landing distance, increased VNE
and increased fuel consumption. - Dreduced takeoff and landing distance, increased VNE
and reduced rate of climb.
- Aincreased takeoff and landing distance, reduced rate of climb
13Over-loading would result in:
- Aa decrease in stalling speed.
- Ba decrease in fuel consumption.
- Can increase in range.
- Da reduction of aircraft performance.
14Is it possible to fly a certified aircraft at a regulated Takeoff
Mass with both full Traffic Load and a full fuel load?- AAll aircraft at all times.
- BNo, it is not possible.
- COnly if the performance limited Takeoff Mass is less than
the structural limited Takeoff Mass. - DSome aircraft in some cases
15For a conventional, nose wheel aircraft configuration,
the higher the Takeoff Mass:
1) Range will decrease but endurance will increase.
2) Gliding range will reduce.
3) Stalling speed will increase.
4) Stick forces at rotation will increase.
Select the combination of correct statements:- A1, 3
- B1,3,4
- C2, 4
- D3, 4
16Which of the following statements is correct?
- AThe station (STA) is always the location of the centre of gravity
in relation to a reference pOint, normally the leading edge
of the wing at MAC. - BA tail heavy aeroplane is less stable and stalls at a lower speed
than a nose heavy aeroplane. - CThe centre of gravity is given in percent of MAC calculated
from the leading edge of the wing, where MAC always =
the wing chord halfway between the centre line of the fuselage
and the wing tip. - DIf the actual centre of gravity is located behind the aft limit
the aeroplane longitudinal stability increases.
- AThe station (STA) is always the location of the centre of gravity
17During takeoff you notice that, for a given elevator input, the
aeroplane rotates much more rapidly than expected. This isan
indication that:- Athe aeroplane is overloaded.
- Bthe centre of gravity may be towards the aft limit.
- Cthe centre of gravity is too far forward.
- Dthe centre of pressure is aft of the centre of gravity.
18If the aeroplane is neutrally stable, this would suggest that:
- Athe CG is forward.
- Bthe CG is in mid range.
- Cthe CG is on the rear limit.
- Dthe CG is behind the rear limit.
19An aeroplane is loaded with its centre of gravity towards
the rear limit. This will result in:- Aan increase in longitudinal stability.
- Ba reduction in power required for a given speed.
- Can increased fuel consumption as a result of increased drag.
- Dan increased risk of stalling due to a decrease in tailplane moment.
20If the centre of gravity of an aeroplane moves forward during
flight the elevator control will:- Abecome heavier making the aeroplane more difficult to manoeuvre
in pitch. - Bbecome lighter making the aeroplane more difficult to manoeuvre
in pitch. - Cbecome heavier making the aeroplane more easy to manoeuvre
in pitch. - Dbecome lighter making the aeroplane more easy to manoeuvre
in pitch.
- Abecome heavier making the aeroplane more difficult to manoeuvre
21An aeroplane is said to be neutrally stable. This is likely to:
- Abe caused by a centre of gravity, which is towards the forward
limit. - Bbe caused by a centre of gravity, which is towards the rearward
limit. - Cbe totally unrelated to the position of the centre of gravity.
- Dcause the centre of gravity to move forwards.
- Abe caused by a centre of gravity, which is towards the forward
22The mass displacement caused by landing gear extension:
- Adoes not create a longitudinal moment.
- Bcreates a pitch-up longitudinal moment.
- Ccreates a longitudinal moment in the direction (pitch-up
or pitch-down) determined by the type of landing gear. - Dcreates a pitch-down longitudinal moment.
23What determines the longitudinal stability of an aeroplane?
- AThe dihedral, angle of sweepback and the keel effect.
- BThe effectiveness of the horizontal stabilizer, rudder and rudder
trim tab. - CThe relationship of thrust and lift to weight and drag.
- DThe location of the centre of gravity with respect to the neutral
point.
24The stalling speed of an aeroplane will be highest when it is
loaded with a:- Ahigh gross mass and aft centre of gravity.
- Blow gross mass and forward centre of gravity.
- Clow gross mass and aft centre of gravity.
- Dhigh gross mass and forward centre of gravity.
25If the centre of gravity is near the forward limit, the aeroplane
will:- Abenefit from reduced drag due to the decrease in angle
of attack. - Brequire elevator trim, which will result in an increase in fuel
consumption. - Crequire less power for a given airspeed.
- Dtend to over rotate during takeoff.
- Abenefit from reduced drag due to the decrease in angle
26Which of the following statements is correct?
- AIf 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. - BIf 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. - CA tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane
- DThe 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.
- AIf the actual centre of gravity is close to the forward limit
27Which ofthe following is most likely to affect the range of centre
of gravity positions on an aeroplane?- AThe need to minimize drag forces and so improve efficiency.
- BLocation of the undercarriage.
- CThe need to maintain a low value of stalling speed.
- DElevator and tailplane (horizontal stabilizer) effectiveness
in all flight conditions.
28When the centre of gravity is at the forward limit, an aeroplane
will be:- Aextremely stable and will require excessive elevator control
to change pitch. - Bextremely stable and require small elevator control to change
pitch. - Cextremely unstable and require excessive elevator control
to change pitch. - Dextremely unstable and require small elevator control
to change pitch.
- Aextremely stable and will require excessive elevator control
29Assuming gross mass, altitude and airspeed remain unchanged,
movement of the centre of gravity from the forward
to the aft limit will cause:- Aincreased cruise range.
- Bhigher stall speed.
- Clower optimum cruising speed.
- Dreduced maximum cruise range.
30With the centre of gravity on the forward limit which
of the following is to be expected?- AA decrease of the stalling speed.
- BA decrease in the landing speed.
- CA decrease in range.
- DA tendency to yaw to the right on takeoff.
31If nose wheel moves aft during gear retraction, how will
this movement affect the location of the ce"ntre of gravity (CG)
on the aircraft?- AIt will not affect the CG location.
- BIt will cause the CG to move aft.
- CIt will cause the CG to move forward.
- DThe CG location will change, but the direction cannot be told
from the information given.
32In cruise flight, an aft centre of gravity location will:
- Adecrease longitudinal static stability.
- Bincrease longitudinal static stability.
- Cdoes not influence longitudinal static stability.
- Dnot change the static curve of stability into longitudinal.
33A forward CG would result in:
- Aa reduced rate of climb.
- Ba decrease in cruise range.
- Ca decrease in both rate of climb and cruise range.
- Dan increase in both rate of climb and cruise range.
34Who establishes the limits of CG?
- AThe CAA.
- BThe JAA.
- CThe manufacturer.
- DThe insurers.
35What effect does the CG on the aft limit have on the fuel consumption
of an aeroplane?- AIncrease
- BDecrease
- CNo effect
- DMarginal increase
36Which combination of weight and CG position will produce
the highest stalling speed?- AHeavy weight and aft CG.
- BHeavy weight and forward CG.
- CLow weight and aft CG.
- DLow weight and forward CG.
37If the CG is aft of the neutral point it results in:
- Aincreased stability with increased elevator trim.
- Bdecreased stability with decreased elevator trim.
- Cneutral stability.
- Dlongitudinal instability.
38An aeroplane is said to be neutrally stable. This is likely to:
- Abe caused by the CG towards the forward limit.
- Bbe caused by the CG at the aerodynamic centre ofthe aircraft.
- Cbe totally unrelated to the position of the CG.
- Dcause the CG to move forwards.
39The undercarriage of an aircraft moves rearward when it is being
retracted. Does this affect the CG?- ANo, the position of the CG would remain the same.
- BYes, but the CG movement could not be calculated.
- CYes, the CG would move aft.
- DYes, the CG would move forward.
40The effect of operating an aeroplane with a CG too far forward
is to experience:- Ainability or difficulty in trimming when flaps are retracted.
- Blower stick forces per G loading.
- Cinability or difficulty in flaring on touchdown, resulting
in nose-wheel landing first. - Dlower stalling speed.
41The handling and performance problems encountered with
a CG too far aft include:- Aimprovement in nose wheel steering.
- Bhigher stick forces per G loading with no risk of over-stressing
the airframe in maneuvers. - Cdifficulty or inability to recover from a spin.
- Dno likelihood of a nose up overbalance (on a tricycle gear aircraft)
on the ground resulting in tail damage.
42For a large aircraft where the main and nose landing gears retract
forward, the effect on the CG on lowering the gear is:- Ato move aft.
- Bto move forward.
- Cto remain static.
- Dto move forward then aft.
43Select the correct statement for the CG safe range:
- AThe safe range falls between the front and rear CG limits
but does not include them. - BThe safe range falls between the front and rear CG limits
but only includes the fwd limit. - CThe safe range falls between the front and rear CG limits
but only includes the aft limit. - DThe safe range falls between the front and rear CG limits
and includes both limits.
- AThe safe range falls between the front and rear CG limits
44In cruise, an extreme aft longitudinal centre of gravity:
- Amoves away the cyclic stick from its forward stop and increases
the stress in the rotor head. - Bbrings the cyclic stick closer to its forward stop and decreases
the stress in the rotor head. - Cmoves away the cyclic stick from its forward stop and decreases
the stresses in the head rotors. - Dbrings the cyclic stick closer to its forward stop and increases
the stress in the rotor head.
- Amoves away the cyclic stick from its forward stop and increases
45For a given configuration, the stall speed of an aeroplane will
be highest when loaded:- Ato a low Total Mass with the most forward CG.
- Bto a low Total Mass with the most aft CG.
- Cto the maximum allowable mass with the most aft CG.
- Dto the maximum allowable mass with the most forward CG.
46What effect has a centre of gravity close to the most forward
limit?- AA reduction in the specific fuel consumption.
- BA decreased induced drag.
- CA better rate of climb capability.
- DA reduced rate of climb capability.
47When must the centre of gravity be computed?
- AAfter every 400 hrs inspection.
- BPrior to every flight.
- CAt least every four years.
- DDuring every yearly inspection.
48The effect of an aircraft being tail heavy would be a:
- Adecrease in range.
- Btendency to pitch down during final stage of landing.
- Cdecreased stalling speed.
- Dtendency to roll right during takeoff.
49One effect on an aircraft that is nose-heavy is:
- Aa tendency for the nose to pitch-up.
- Ban increase in range.
- Ca decrease in stability.
- Dan increase in drag, due to excessive elevator trim.
50With the centre of gravity outside the forward limit:
- Alongitudinal stability would be reduced and stick forces
in pitch increased. - Blongitudinal stability would be reduced and stick forces
in pitch reduced. - Clongitudinal stability would be increased and stick force
in pitch reduced. - Dlongitudinal stability would be increased and stick forces
in pitch increased.
- Alongitudinal stability would be reduced and stick forces
Informationen
- Beschreibung
- Quiz am Mass and Balance ATPL, erstellt von Jesús Nieto Domínguez am 20/11/2017.
- Sprache
- Español
- Aufrufe
- 761
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