Jesús Nieto Domínguez
Quiz by , created more than 1 year ago

Quiz on Mass and Balance ATPL, created by Jesús Nieto Domínguez on 20/11/2017.

671
1
0
No tags specified
Jesús Nieto Domínguez
Created by Jesús Nieto Domínguez about 7 years ago
Close

Mass and Balance ATPL

Mass and Balance ATPL

Question 1 of 50

1

The 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.

Select one of the following:

  • 1,2,3,4

  • 3

  • 1,4

  • 4

Explanation

Question 2 of 50

1

A 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:

Select one of the following:

  • the approach path will be steeper.

  • the landing distance will be unaffected.

  • the landing distance required will be longer.

  • the approach path will be steeper and threshold speed
    higher.

Explanation

Question 3 of 50

1

When considering the effects of increased mass on an aeroplane,
which of the following is true?

Select one of the following:

  • Flight endurance will be increased.

  • Stalling speeds will be lower.

  • Gradient of climb for a given power setting will be higher.

  • Stalling speeds will be higher.

Explanation

Question 4 of 50

1

If an aeroplane is at a higher mass than anticipated, for a given
airspeed the angle of attack will:

Select one of the following:

  • remain constant, drag will decrease and endurance will decrease.

  • be decreased, drag will decrease and endurance will increase.

  • be greater, drag will increase and endurance will decrease.

  • remain constant, drag will increase and endurance will increase.

Explanation

Question 5 of 50

1

Fuel 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:

Select one of the following:

  • V, will be reached sooner than expected.

  • speed at un-stick will be higher than expected.

  • V, will be increased.

  • the aeroplane will rotate much earlier than expected.

Explanation

Question 6 of 50

1

In 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:

Select one of the following:

  • increased to 202 kts but, since the same angle of attack
    is used, drag and range will remain the same.

  • unaffected as Vs always occurs at the same angle of attack.

  • increased to 191 kts, drag will decrease and air distance
    per kg of fuel will increase.

  • increased to 191 kts, drag will increase and air distance per kg
    of fuel will decrease.

Explanation

Question 7 of 50

1

An 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:

Select one of the following:

  • are unaffected but V, will be increased.

  • will not be achieved.

  • will be greater than required.

  • will give reduced safety margins.

Explanation

Question 8 of 50

1

Prior 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:

Select one of the following:

  • heavier than anticipated and the calculated safety speeds
    will be too high.

  • lighter than anticipated and the calculated safety speeds will
    be too low.

  • lighter than anticipated and the calculated safety speeds will
    be too high.

  • heavier than anticipated and the calculated safety speeds
    will be too low.

Explanation

Question 9 of 50

1

At 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:

Select one of the following:

  • a landing short resultant from the increased angle of approach
    due to the very high aeroplane mass.

  • 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.

Explanation

Question 10 of 50

1

During 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:

Select one of the following:

  • rupture of one or more structural components.

  • a permanent deformation of the structure.

  • an elastic deformation whilst the load was applied,
    but no permanent distortion.

  • no distortion, permanent or temporary, of the structure.

Explanation

Question 11 of 50

1

If an extra load is loaded into an aircraft, the stall speed
is likely to:

Select one of the following:

  • stay the same.

  • decrease.

  • increase.

  • change depending on whether the load was placed FWD
    or AFT ofthe eG.

Explanation

Question 12 of 50

1

Overloading has the following effects on performance:

Select one of the following:

  • increased takeoff and landing distance, reduced rate of climb
    and increased fuel consumption.

  • increased takeoff and landing distance, increased rate
    of climb and increased fuel consumption.

  • reduced takeoff and landing distance, increased VNE
    and increased fuel consumption.

  • reduced takeoff and landing distance, increased VNE
    and reduced rate of climb.

Explanation

Question 13 of 50

1

Over-loading would result in:

Select one of the following:

  • a decrease in stalling speed.

  • a decrease in fuel consumption.

  • an increase in range.

  • a reduction of aircraft performance.

Explanation

Question 14 of 50

1

Is it possible to fly a certified aircraft at a regulated Takeoff
Mass with both full Traffic Load and a full fuel load?

Select one of the following:

  • All aircraft at all times.

  • No, it is not possible.

  • Only if the performance limited Takeoff Mass is less than
    the structural limited Takeoff Mass.

  • Some aircraft in some cases

Explanation

Question 15 of 50

1

For 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:

Select one of the following:

  • 1, 3

  • 1,3,4

  • 2, 4

  • 3, 4

Explanation

Question 16 of 50

1

Which of the following statements is correct?

Select one of the following:

  • The 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.

  • A tail heavy aeroplane is less stable and stalls at a lower speed
    than a nose heavy aeroplane.

  • The 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.

  • If the actual centre of gravity is located behind the aft limit
    the aeroplane longitudinal stability increases.

Explanation

Question 17 of 50

1

During takeoff you notice that, for a given elevator input, the
aeroplane rotates much more rapidly than expected. This isan
indication that:

Select one of the following:

  • the aeroplane is overloaded.

  • the centre of gravity may be towards the aft limit.

  • the centre of gravity is too far forward.

  • the centre of pressure is aft of the centre of gravity.

Explanation

Question 18 of 50

1

If the aeroplane is neutrally stable, this would suggest that:

Select one of the following:

  • the CG is forward.

  • the CG is in mid range.

  • the CG is on the rear limit.

  • the CG is behind the rear limit.

Explanation

Question 19 of 50

1

An aeroplane is loaded with its centre of gravity towards
the rear limit. This will result in:

Select one of the following:

  • an increase in longitudinal stability.

  • a reduction in power required for a given speed.

  • an increased fuel consumption as a result of increased drag.

  • an increased risk of stalling due to a decrease in tailplane moment.

Explanation

Question 20 of 50

1

If the centre of gravity of an aeroplane moves forward during
flight the elevator control will:

Select one of the following:

  • become heavier making the aeroplane more difficult to manoeuvre
    in pitch.

  • become lighter making the aeroplane more difficult to manoeuvre
    in pitch.

  • become heavier making the aeroplane more easy to manoeuvre
    in pitch.

  • become lighter making the aeroplane more easy to manoeuvre
    in pitch.

Explanation

Question 21 of 50

1

An aeroplane is said to be neutrally stable. This is likely to:

Select one of the following:

  • be caused by a centre of gravity, which is towards the forward
    limit.

  • be caused by a centre of gravity, which is towards the rearward
    limit.

  • be totally unrelated to the position of the centre of gravity.

  • cause the centre of gravity to move forwards.

Explanation

Question 22 of 50

1

The mass displacement caused by landing gear extension:

Select one of the following:

  • does not create a longitudinal moment.

  • creates a pitch-up longitudinal moment.

  • creates a longitudinal moment in the direction (pitch-up
    or pitch-down) determined by the type of landing gear.

  • creates a pitch-down longitudinal moment.

Explanation

Question 23 of 50

1

What determines the longitudinal stability of an aeroplane?

Select one of the following:

  • The dihedral, angle of sweepback and the keel effect.

  • The effectiveness of the horizontal stabilizer, rudder and rudder
    trim tab.

  • The relationship of thrust and lift to weight and drag.

  • The location of the centre of gravity with respect to the neutral
    point.

Explanation

Question 24 of 50

1

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

Select one of the following:

  • high gross mass and aft centre of gravity.

  • low gross mass and forward centre of gravity.

  • low gross mass and aft centre of gravity.

  • high gross mass and forward centre of gravity.

Explanation

Question 25 of 50

1

If the centre of gravity is near the forward limit, the aeroplane
will:

Select one of the following:

  • benefit from reduced drag due to the decrease in angle
    of attack.

  • require elevator trim, which will result in an increase in fuel
    consumption.

  • require less power for a given airspeed.

  • tend to over rotate during takeoff.

Explanation

Question 26 of 50

1

Which of the following statements is correct?

Select one of the following:

  • 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.

  • 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.

  • A tail heavy aeroplane is less stable and stalls at a lower speed than a nose heavy aeroplane

  • 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.

Explanation

Question 27 of 50

1

Which ofthe following is most likely to affect the range of centre
of gravity positions on an aeroplane?

Select one of the following:

  • The need to minimize drag forces and so improve efficiency.

  • Location of the undercarriage.

  • The need to maintain a low value of stalling speed.

  • Elevator and tailplane (horizontal stabilizer) effectiveness
    in all flight conditions.

Explanation

Question 28 of 50

1

When the centre of gravity is at the forward limit, an aeroplane
will be:

Select one of the following:

  • extremely stable and will require excessive elevator control
    to change pitch.

  • extremely stable and require small elevator control to change
    pitch.

  • extremely unstable and require excessive elevator control
    to change pitch.

  • extremely unstable and require small elevator control
    to change pitch.

Explanation

Question 29 of 50

1

Assuming gross mass, altitude and airspeed remain unchanged,
movement of the centre of gravity from the forward
to the aft limit will cause:

Select one of the following:

  • increased cruise range.

  • higher stall speed.

  • lower optimum cruising speed.

  • reduced maximum cruise range.

Explanation

Question 30 of 50

1

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

Select one of the following:

  • A decrease of the stalling speed.

  • A decrease in the landing speed.

  • A decrease in range.

  • A tendency to yaw to the right on takeoff.

Explanation

Question 31 of 50

1

If nose wheel moves aft during gear retraction, how will
this movement affect the location of the ce"ntre of gravity (CG)
on the aircraft?

Select one of the following:

  • It will not affect the CG location.

  • It will cause the CG to move aft.

  • It will cause the CG to move forward.

  • The CG location will change, but the direction cannot be told
    from the information given.

Explanation

Question 32 of 50

1

In cruise flight, an aft centre of gravity location will:

Select one of the following:

  • decrease longitudinal static stability.

  • increase longitudinal static stability.

  • does not influence longitudinal static stability.

  • not change the static curve of stability into longitudinal.

Explanation

Question 33 of 50

1

A forward CG would result in:

Select one of the following:

  • a reduced rate of climb.

  • a decrease in cruise range.

  • a decrease in both rate of climb and cruise range.

  • an increase in both rate of climb and cruise range.

Explanation

Question 34 of 50

1

Who establishes the limits of CG?

Select one of the following:

  • The CAA.

  • The JAA.

  • The manufacturer.

  • The insurers.

Explanation

Question 35 of 50

1

What effect does the CG on the aft limit have on the fuel consumption
of an aeroplane?

Select one of the following:

  • Increase

  • Decrease

  • No effect

  • Marginal increase

Explanation

Question 36 of 50

1

Which combination of weight and CG position will produce
the highest stalling speed?

Select one of the following:

  • Heavy weight and aft CG.

  • Heavy weight and forward CG.

  • Low weight and aft CG.

  • Low weight and forward CG.

Explanation

Question 37 of 50

1

If the CG is aft of the neutral point it results in:

Select one of the following:

  • increased stability with increased elevator trim.

  • decreased stability with decreased elevator trim.

  • neutral stability.

  • longitudinal instability.

Explanation

Question 38 of 50

1

An aeroplane is said to be neutrally stable. This is likely to:

Select one of the following:

  • be caused by the CG towards the forward limit.

  • be caused by the CG at the aerodynamic centre ofthe aircraft.

  • be totally unrelated to the position of the CG.

  • cause the CG to move forwards.

Explanation

Question 39 of 50

1

The undercarriage of an aircraft moves rearward when it is being
retracted. Does this affect the CG?

Select one of the following:

  • No, the position of the CG would remain the same.

  • Yes, but the CG movement could not be calculated.

  • Yes, the CG would move aft.

  • Yes, the CG would move forward.

Explanation

Question 40 of 50

1

The effect of operating an aeroplane with a CG too far forward
is to experience:

Select one of the following:

  • inability or difficulty in trimming when flaps are retracted.

  • lower stick forces per G loading.

  • inability or difficulty in flaring on touchdown, resulting
    in nose-wheel landing first.

  • lower stalling speed.

Explanation

Question 41 of 50

1

The handling and performance problems encountered with
a CG too far aft include:

Select one of the following:

  • improvement in nose wheel steering.

  • higher stick forces per G loading with no risk of over-stressing
    the airframe in maneuvers.

  • difficulty or inability to recover from a spin.

  • no likelihood of a nose up overbalance (on a tricycle gear aircraft)
    on the ground resulting in tail damage.

Explanation

Question 42 of 50

1

For a large aircraft where the main and nose landing gears retract
forward, the effect on the CG on lowering the gear is:

Select one of the following:

  • to move aft.

  • to move forward.

  • to remain static.

  • to move forward then aft.

Explanation

Question 43 of 50

1

Select the correct statement for the CG safe range:

Select one of the following:

  • The safe range falls between the front and rear CG limits
    but does not include them.

  • The safe range falls between the front and rear CG limits
    but only includes the fwd limit.

  • The safe range falls between the front and rear CG limits
    but only includes the aft limit.

  • The safe range falls between the front and rear CG limits
    and includes both limits.

Explanation

Question 44 of 50

1

In cruise, an extreme aft longitudinal centre of gravity:

Select one of the following:

  • moves away the cyclic stick from its forward stop and increases
    the stress in the rotor head.

  • brings the cyclic stick closer to its forward stop and decreases
    the stress in the rotor head.

  • moves away the cyclic stick from its forward stop and decreases
    the stresses in the head rotors.

  • brings the cyclic stick closer to its forward stop and increases
    the stress in the rotor head.

Explanation

Question 45 of 50

1

For a given configuration, the stall speed of an aeroplane will
be highest when loaded:

Select one of the following:

  • 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.

  • to the maximum allowable mass with the most forward CG.

Explanation

Question 46 of 50

1

What effect has a centre of gravity close to the most forward
limit?

Select one of the following:

  • A reduction in the specific fuel consumption.

  • A decreased induced drag.

  • A better rate of climb capability.

  • A reduced rate of climb capability.

Explanation

Question 47 of 50

1

When must the centre of gravity be computed?

Select one of the following:

  • After every 400 hrs inspection.

  • Prior to every flight.

  • At least every four years.

  • During every yearly inspection.

Explanation

Question 48 of 50

1

The effect of an aircraft being tail heavy would be a:

Select one of the following:

  • decrease in range.

  • tendency to pitch down during final stage of landing.

  • decreased stalling speed.

  • tendency to roll right during takeoff.

Explanation

Question 49 of 50

1

One effect on an aircraft that is nose-heavy is:

Select one of the following:

  • a tendency for the nose to pitch-up.

  • an increase in range.

  • a decrease in stability.

  • an increase in drag, due to excessive elevator trim.

Explanation

Question 50 of 50

1

With the centre of gravity outside the forward limit:

Select one of the following:

  • longitudinal stability would be reduced and stick forces
    in pitch increased.

  • longitudinal stability would be reduced and stick forces
    in pitch reduced.

  • longitudinal stability would be increased and stick force
    in pitch reduced.

  • longitudinal stability would be increased and stick forces
    in pitch increased.

Explanation

Previous
Next