Mass and Balance ATPL

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.

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:

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

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

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:

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:

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:

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:

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:

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:

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

Overloading has the following effects on performance:

Over-loading would result in:

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

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:

Which of the following statements is correct?

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

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

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

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

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

The mass displacement caused by landing gear extension:

What determines the longitudinal stability of an aeroplane?

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

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

Which of the following statements is correct?

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

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

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

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

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?

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

A forward CG would result in:

Who establishes the limits of CG?

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

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

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

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

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

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

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

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

Select the correct statement for the CG safe range:

In cruise, an extreme aft longitudinal centre of gravity:

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

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

When must the centre of gravity be computed?

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

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

With the centre of gravity outside the forward limit: