GsPilot

1/30

Question ID: 101394

Due to a mistake in the load sheet the aeroplane is 1000 kg heavier than you believe it to be As a consequence?

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A

V1 will be higher

B

VR will be higher

C

VMU will be higher

D

V1, VMU and VR will all occur earlier

2/30

Question ID: 101197

A loaded aircraft has its Centre of Gravity (CG) 48 inches forward of the datum, and its mass is 2966 lb

If a last-minute load of 128 lb is added 28 inches aft of the datum.

What is the new position of the CG?

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A

46.01 inches aft of the datum

B

46.84 inches aft of the datum

C

44.86 inches forward of the datum

D

44.72 inches forward of the datum

3/30

Question ID: 101419

The Basic Empty Mass (BEM) is 4 800 kg, the Dry Operating Mass (DOM) is 5 050 kg and the Zero Fuel Mass (ZFM) is 6 210 kg. If the Take-off Mass (TOM) is 8 010 kg the Useful Load (UL) is?

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A

3210 kg

B

2960 kg

C

1800 kg

D

1160 kg

4/30

Question ID: 101190

The moment for an item is?

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A

The square of the distance the item is from the datum divided by its mass

B

The mass of the item divided by its distance from the datum

C

The mass of the item multiplied by its distance from the datum

D

The distance the item is from the datum divided by its mass

5/30

Question ID: 101448

An aeroplane has a Landing Mass of 56 000 kg The range of safe CG positions, as determined from the appropriate graph in the Loading Manual, is?

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A

Forward limit 8.7% MAC, aft limit 26.8% MAC

B

Forward limit 7.3% MAC, aft limit 26.8% MAC

C

Forward limit 7.8% MAC, aft limit 27.0% MAC.

D

Forward limit 8.2% MAC, aft limit 27.0% MAC

6/30

Question ID: 101444

At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position 625.6 inches aft of the datum and the MAC is given as 134.5 inches determine the position of the CG in relation to the datum

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A

228.34 inches aft of datum

B

645.78 inches aft of datum

C

605.43 inches aft of datum

D

20.18 inches aft of datum

7/30

Question ID: 101438

The datum used for balance calculations is?

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A

Chosen on the longitudinal axis of the aircraft, and always at the firewall level

B

Chosen on the longitudinal axis of the aircraft and necessarily situated between the leading edge and trailing edge of the wing

C

Chosen on the longitudinal axis of the aeroplane, but not necessarily between the nose and the tail of the aircraft

D

Chosen on the longitudinal axis of the aeroplane, and necessarily situated between the nose and the tail of the aircraft

8/30

Question ID: 101141

A pilot is taking-off from an airport with a light aircraft which has a maximum structural take-off mass of 3 250 lb and 25 lb of taxi fuel can be added. It is a hot summer day and the maximum all up mass (MAUM) is 3 100 lb. What is the maximum ramp mass in these conditions?

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A

3100 lb

B

3125 lb

C

3250 lb

D

3275 lb

9/30

Question ID: 101274

Considering only structural limitations, on long distance flights (at the aeroplane maximum range), the Traffic Load is normally limited by?

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A

The Maximum Landing Mass

B

The Maximum Take-off Mass

C

The Maximum Zero Fuel Mass plus the Take-off Mass

D

The Maximum Zero Fuel Mass

10/30

Question ID: 101160

The fuel index?

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A

Is a standard value given by EASA and can be used for different types of aircraft

B

Is the difference between the zero-fuel mass index and the DOI

C

Is only used for aeroplanes with wing tip tanks

D

Is used to calculate the correct position of the CG due to different locations of the fuel tanks

11/30

Question ID: 101550

Given Basic Empty Mass 44800 kg Special operational equipment 1240 kg Crew 1060 kg Maximum Zero Fuel Mass 65500 kg The maximum traffic load which could be carried is

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A

20700 kg

B

23000 kg

C

19460 kg

D

18400 kg

12/30

Question ID: 101496

Given Dry Operating Mass (DOM) 33500 kg Load 7600 kg Maximum Allowable Take-off Mass 66200 kg Standard taxi fuel 200 kg Tank capacity 16100 kg The maximum possible take-off fuel is?

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A

25300 kg

B

15900 kg

C

17300 kg

D

16300 kg

13/30

Question ID: 101270

The Maximum Structural Take-off Mass is?

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A

A take-off limiting mass which is governed by the gradient of climb after reaching VY

B

A limit which may not be exceeded for any take-off

C

Limited by the take-off distance available. It is tabulated in the flight manual

D

A take-off limiting mass which is affected by the aerodrome altitude and temperature

14/30

Question ID: 101325

For the medium range transport aeroplane, from the loading manual, determine the maximum total volume of fuel which can be loaded into the main wing tanks (conversion 1 US-GALLON = 3.785 LITRES)

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A

11347 liters

B

9084 liters

C

20102 liters

D

5673 liters

15/30

Question ID: 101375

An aeroplane weighing schedule indicates that the Basic Empty Mass is 57320 kg.

The Dry Operating Mass is 60120 kg.

The Maximum Zero Fuel Mass is given as 72100 kg.

The Take-off fuel is 18600 kg.

What is the maximum Traffic Load?

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A

30580 kg

B

21400 kg

C

11980 kg

D

14780 kg

16/30

Question ID: 101342

The Maximum Zero Fuel Mass is?

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A

Tabulated in the Flight Manual against arguments of airfield elevation and temperature

B

A structural limit listed in the Flight Manual as a fixed value

C

Governed by the traffic load to be carried

D

Governed by the CG limits

17/30

Question ID: 100296

The CG position of an aeroplane is 12.40 m aft of the datum. Determine the CG position as % MAC, given:

Leading edge of the wing root: 11.83 m aft of the datum

Leading edge of MAC: 12.12 m aft of the datum

Leadiing edge of the wing tip: 12.81 m aft of the datum

Length of the wing root chord: 1.55 m

Length of MAC: 1.34 m

Length of the wing tip chord: 0.61 m

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A

86.94 % MAC

B

36.77 % MAC

C

20.90 % MAC

D

90.65 % MAC

18/30

Question ID: 101491

The Total Mass of an aeroplane is 145,000 kg and the center of gravity limits are between 4.7 m and 6.9 m aft of the datum.
The loaded center of gravity position is 4.4 m aft.
How much mass must be transferred from the front to the rear hold to bring the out of limit center of gravity position to the foremost limit?

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A

3500 kg

B

62500 kg

C

7500 kg

D

35000 kg

19/30

Question ID: 101504

Determine the maximum fuel load that can be carried in the following conditions?

Dry Operating Mass 2800 kg

Trip Fuel 300 kg

Traffic Load 400 kg

Maximum Take-off Mass 4200 kg

Maximum Landing Mass 3700 kg

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A

500 kg

B

1000 kg

C

700 kg

D

800 kg

20/30

Question ID: 101315

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

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A

To a low total mass with the most aft CG

B

To the maximum allowable mass with the most forward CG

C

To a low total mass with the most forward CG

D

To the maximum allowable mass with the most aft CG

21/30

Question ID: 101353

A container has a base area of 1.44 m2 The container is loaded on two ground supports (of negligible mass), each having floor-contact dimensions of 0.2 m x 1.2 m.

Given that the maximum permissible floor load of the cargo compartment, which is 732 kg/m2, must be respected, what is the maximum mass that can be loaded in the container?

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A

1054 kg

B

175 kg

C

351 kg

D

1525 kg

22/30

Question ID: 101305

The SI units of running (or linear load) are?

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A

N/m², lb/ft

B

kg/m², kg

C

kg/m³, N

D

N/m, kg/m

23/30

Question ID: 101207

What is the principle of the index method?

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A

To determine the CG position by reference to the Mean Aerodynamic Chord

B

To divide high-magnitude moments by a constant and make them more user-friendly

C

To compute the CG position and stabilizer trim setting without completing a load sheet

D

To refer every item of the aircraft to a position called the BA (Balance Arm)

24/30

Question ID: 101272

If an aeroplane lands below its Max Structural Landing Mass, but above its Performance Limited Landing Mass for the arrival airfield
1) It might not have sufficient runway length to stop safely.
2) Tyre temperature limits could be exceeded.
3) It will increase structural fatigue.
4) Physical damage might be suffered as a result of the extra mass.
5) A go-around might not be achievable.
The combination regrouping all the correct statements is?

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A

1,2,4

B

1,2,4,5

C

1,2,3,5

D

1,2,3

25/30

Question ID: 101386

A box weighing 105 kg is loaded into the cargo compartment. Calculate the smallest required floor contact area of this box to avoid exceeding the maximum floor load of 600 kg/m²?

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A

0.571 m²

B

0.157 m²

C

0.155 m²

D

0.175 m²

26/30

Question ID: 101343

By adding to the Basic Empty Mass the mass of crew, crew baggage, catering, and operational equipment for a specific flight, we get the?

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A

Dry Operating Mass

B

Landing Mass

C

Zero Fuel Mass

D

Take-off Mass

27/30

Question ID: 101471

The loaded mass of an aircraft is 12 400 kg. The aft CG limit is 102 inches aft of the datum. If the CG as loaded is 104.5 inches aft of the datum, how many rows forward must two passengers move from the rear seat row (224 inches aft) to bring the CG on to the aft limit, if the seat pitch is 33 inches? Assume a passenger mass of 75 kg each?

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A

5 rows

B

7 rows

C

6 rows

D

8 rows

28/30

Question ID: 101222

Extract the forward and aft center of gravity limit from the given image for a mass of 4300 lb.

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A

Forward CG limit 87.2 in. Aft CG limit 94.0 in

B

Forward CG limit 87.2 in. Aft CG limit 94.6 in

C

Forward CG limit 88.0 in. Aft CG limit 94.6 in

D

Forward CG limit 88.0 in. Aft CG limit 94.0 in

29/30

Question ID: 101490

Given CG is located at station 15 Aeroplane mass is 3650 lbs What is the effect on the CG if you move baggage (total mass 64 lbs) from station 14 to station 20?

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A

It moves AFT by 0.1 units

B

It moves FWD by 0.13 units

C

It moves AFT by 0.31 units

D

It moves AFT by 0.3 units

30/30

Question ID: 101566

Given:
Dry Operating Mass 5320 kg
Zero Fuel Mass 6790 kg
Trip Fuel 770 kg
Take-Off Fuel 1310 kg

The Traffic Load is?

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A

3080 kg

B

2940 kg

C

1470 kg

D

1610 kg

Question ID: 101394

Due to a mistake in the load sheet the aeroplane is 1000 kg heavier than you believe it to be As a consequence?

A

B

C

D

Question ID: 101197

A loaded aircraft has its Centre of Gravity (CG) 48 inches forward of the datum, and its mass is 2966 lb If a last-minute load of 128 lb is added 28 inches aft of the datum. What is the new position of the CG?

A

B

C

D

Question ID: 101419

The Basic Empty Mass (BEM) is 4 800 kg, the Dry Operating Mass (DOM) is 5 050 kg and the Zero Fuel Mass (ZFM) is 6 210 kg. If the Take-off Mass (TOM) is 8 010 kg the Useful Load (UL) is?

A

B

C

D

Question ID: 101190

The moment for an item is?

A

B

C

D

Question ID: 101448

An aeroplane has a Landing Mass of 56 000 kg The range of safe CG positions, as determined from the appropriate graph in the Loading Manual, is?

A

B

C

D

Question ID: 101444

At a given mass the CG position is at 15% MAC. If the leading edge of MAC is at a position 625.6 inches aft of the datum and the MAC is given as 134.5 inches determine the position of the CG in relation to the datum

A

B

C

D

Question ID: 101438

The datum used for balance calculations is?

A

B

C

D

Question ID: 101141

A pilot is taking-off from an airport with a light aircraft which has a maximum structural take-off mass of 3 250 lb and 25 lb of taxi fuel can be added. It is a hot summer day and the maximum all up mass (MAUM) is 3 100 lb. What is the maximum ramp mass in these conditions?

A

B

C

D

Question ID: 101274

Considering only structural limitations, on long distance flights (at the aeroplane maximum range), the Traffic Load is normally limited by?

A

B

C

D

Question ID: 101160

The fuel index?

A

B

C

D

Question ID: 101550

Given Basic Empty Mass 44800 kg Special operational equipment 1240 kg Crew 1060 kg Maximum Zero Fuel Mass 65500 kg The maximum traffic load which could be carried is

A

B

C

D

Question ID: 101496

Given Dry Operating Mass (DOM) 33500 kg Load 7600 kg Maximum Allowable Take-off Mass 66200 kg Standard taxi fuel 200 kg Tank capacity 16100 kg The maximum possible take-off fuel is?

A

B

C

D

Question ID: 101270

The Maximum Structural Take-off Mass is?

A

B

C

D

Question ID: 101325

For the medium range transport aeroplane, from the loading manual, determine the maximum total volume of fuel which can be loaded into the main wing tanks (conversion 1 US-GALLON = 3.785 LITRES)

A loaded aircraft has its Centre of Gravity (CG) 48 inches forward of the datum, and its mass is 2966 lb

If a last-minute load of 128 lb is added 28 inches aft of the datum.

What is the new position of the CG?

An aeroplane weighing schedule indicates that the Basic Empty Mass is 57320 kg.

The Dry Operating Mass is 60120 kg.

The Maximum Zero Fuel Mass is given as 72100 kg.

The Take-off fuel is 18600 kg.

What is the maximum Traffic Load?

Determine the maximum fuel load that can be carried in the following conditions?

Dry Operating Mass 2800 kg

Trip Fuel 300 kg

Traffic Load 400 kg

Maximum Take-off Mass 4200 kg

Maximum Landing Mass 3700 kg