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Which of the following runway contaminants are indicated by a SNOWTAM, according to ICAO Annex 15?1. damp / wet2. hail / showers / haze3. frozen ruts or ridges4. rime covered / ice5. dry / wet snow6. iced / powdered snow

2, 3, 5 and 6

1, 2, 3 and 5

1, 3, 4 and 5

1, 2, 4 and 6

What is the effect of using a stopway on the Accelerate-Stop Distance Required (ASDR)? If all other parameters remain constant, the ASDR...

increases and V₁ increases.

remains the same but V₁ increases.

increases if V₁ remains the same.

remains the same.

A multi-engine piston aircraft suffers an engine failure during the climb. What will happen to the VY and the rate of climb?

Both will decrease.

Both will increase.

VY will decrease and the rate of climb will increase.

VY will increase and the rate of climb will decrease.

A 'Balanced Field Length' is said to exist where...

the take-off run available is equal to the take-off distance available.

the accelerate-stop distance is equal to the take-off distance.

the clearway length does not equal the stopway length.

the accelerate-stop distance available is equal to the take-off distance available.

The speed VS0 is defined as the...

stall speed obtained in a specified configuration.

reference stall speed in the landing configuration.

stall speed in the landing configuration.

reference stall speed in a specific configuration.

At the destination aerodrome the landing distance available is 3000 m. The appropriate weather forecast indicates that the runway at the estimated time of arrival will be wet. For a commercial flight the mass of a turbojet aeroplane at landing must be such that the aeroplane can be landed within...

1800 m.

2070 m.

1565 m.

2609 m.

An aircraft is climbing at a maximum climb angle with constant speed and thrust. Consider for theoretical purposes that the weight of the aircraft suddenly decreases but the flight otherwise continues as normal. For the pilot to maintain the same speed, all factors remaining the same, the angle of climb must be...

Increased, to reduce the backward component of weight in order to be less than the excess thrust.

Reduced, to increase the backward component of weight in order to exceed the excess thrust.

Reduced, to reduce the backward component of weight in order to match the excess thrust.

Increased, to increase the backward component of weight in order to match the excess thrust.

Which of the following options correctly describes the effects on aircraft performance of landing on wet or contaminated runways?

The coefficient of friction is dramatically increased, which reduces the maximum braking energy that can be applied, which increases the landing distance.

The lower effective braking force has a much greater effect on increasing the landing distance than the benefit of higher drag.

Hydroplaning creates more drag on the wheels, which is evenly balanced by less effective brake drag, thus creating a similar deceleration force compared to a dry runway.

The effect of the increased wheel drag through the water is far greater than the loss of friction and reduced braking effect, therefore landing distances decrease.

Assuming an engine failure during take-off. An increase of V1 will (1) _____ TOM limited by TODA and will (2) _____ TOM limited by ASDA.

(1) not be affect; (2) decrease

(1) not be affect; (2) increase

(1) decrease; (2) increase

(1) increase; (2) decrease

Refer to figure or CAP 698 Figure 4.28.Given the following information for a Commercial Air Transport jet aircraft, what is the minimum field length required?Landing mass: 51 000 kgFlaps position: 30°RWY condition: DRYWind component: 10 kt tailwindPressure Altitude: 2000 ftAnti-skid: OPERATIVESpoilers: AUTOMATIC

5350 ft

4700 ft

5725 ft

8200 ft

With regard to the effect of altitude on the speed for maximum endurance for a propeller-driven aeroplane, as altitude increases, the speed for maximum endurance will...

decrease, because the power required decreases with altitude.

decrease, because aeroplane drag decreases with altitude.

increase, because aeroplane drag increases with altitude.

increase, because the power required increases with altitude.

Refer to figure or chart E(LO)2 from the Jeppesen GSPRM 2017. The Lambert chart has its standard parallels at 37°N and 65°N. An aircraft is flying at (N55°00.0', W011°00.0') position and its magnetic heading is 136°. The relative bearing from the aircraft to the Donegal NDB (CFN) (N55°02.6', W008°20.4') is 318°. The true bearing to be plotted from the NDB to the aircraft position is...

272°(T).

268°(T).

266°(T).

270°(T).

Refer to figure or CAP698 file 3.10.Aerodrome Pressure Altitude: 4000 ftOAT: -5°CLanding Mass: 4000 lbHeadwind component: 5 ktRunway condition: dryRunway slope: 2% downGiven the following information for a Performance Class B aeroplane, what is the Landing Distance Required?

2200 ft

3150 ft

2000 ft

2860 ft

Refer to figure or to CAP 698 figure 3.1.Given the following information, calculate the minimum TODA for a multi-engine piston aircraft take-off. Assume an unbalanced field with stopway and clearway.Mass: 4700 lbsPressure Altitude: 6000 ftTemperature: 30°CRunway slope: 2.5% upslopeRunway condition: wet grassTailwind component: 2 kt

3900 ft

5046 ft

3000 ft

4390 ft

To determine the Runway Length Limited Take-Off Mass (RLTOM) for an unbalanced field, what is the TODA to be used given the following data?TORA: 2380 mStopway: 1470 mClearway: 560 m

3850 m

2940 m

4410 m

3570 m

When is a runway considered to be contaminated? When...

Only if the contaminant covers a connected 25% of the runway surface area (patches of contaminants can add up to more than 25% of the surface area without effects).

Less than 25% of the runway surface area (whether in isolated areas or not) is covered with water more than 3 mm deep.

More than 25% of the runway surface area (whether in isolated areas or not) is covered with slush equivalent to 2 mm of water.

More than 25% of the runway surface area (whether in isolated areas or not) is covered with wet ice 1.5 mm thick.

After a new software update, the engineer has changed the crossover data from 250 kt / M0.75 to 250 kt / M0.78. The pilot now must make sure he/she does not exceed...

VNE

MMO

VMO

VNO

For a multi-engine aircraft in the class B performance category, what is the minimum all engine take-off climb gradient?

3.3%

2.5%

4%

2.8%

What is VS1g?

The stall speed or the minimum steady flight speed at which the aeroplane is controllable in 1-g conditions.

The speed at which onset of artificial stall warning occurs with the aeroplane NOT exceeding 1-g conditions.

The 1-g stall speed at which the aeroplane can develop lift equal to its weight.

The speed at which onset of natural stall warning occurs with the aeroplane NOT exceeding 1-g conditions.

What will be the VREF Speed for a class B performance category single-engined piston aeroplane with a maximum take off mass of 1633 kg. Given the following stall speeds?VSO: 60 ktVS1: 63 ktVS: 68 kt

76 kt

88 kt

78 kt

82 kt

Consider a single engined piston Performance Class B aeroplane during cruise and with a power setting for maximum endurance. How does increasing the power setting affect its range and endurance? The range will...

first increase, then decrease, and endurance will decrease.

first decrease, then increase, and endurance will increase.

decrease, and endurance will decrease.

decrease, and endurance will increase.

For performance class A aircraft, V2MIN must be more than which of the following?

1.1 VMC as mentioned in the CS-25.

1.08 VSR for turboprops with 2 engines.

1.13 VSR for turboprops with more than 3 engines.

1.08 VSR for turbojets without provision for obtaining a significant reduction in the one engine inoperative power-on stalling speed.

A Medium-Range Jet Transport aeroplane is planned to depart from a sufficiently long runway and the correct V-speeds have been calculated. The pilot has not flown this variant of the aircraft before, and it has a longer fuselage than the variant they have flown before. As the tail clearance during rotation is reduced on this longer aircraft, the pilot performs their rotation at a slightly slower (but still acceptable) rate than they would normally. What will this change?

It will reduce the climb performance of the aeroplane since the speed will be above V2, which is the speed for maximum climb angle.

It will increase the take-off run, but the take-off distance will be reduced since the aeroplane will attain a climb speed that is slightly faster.

It will increase both the take-off run and the take-off distance and potentially reduce the clearance over low obstacles close to the runway.

It will improve the climb performance of the aeroplane as this procedure is effectively the same as using an increased V2 procedure.

In the drift down for an aeroplane in Performance Class B the net gradient of descent is assumed to be gross gradient of descent... by ...

increased; 0.77%

decreased; 0.77%

increased; 0.5%

decreased; 0.5%

The Cost Index (CI) can be defined as the...

ratio of the actual cost of the fuel to the average price at a reference airport.

fuel flow, expressed as kg/min.

costs incurred by flying the aeroplane over time, divided by the cost of the fuel.

total fuel costs divided by the total flight time.

Which option is correct as regards the effect of meteorological conditions on the obstacle limited Take-Off Mass?

decreases with a contaminated runway due to the greater wheel drag.

increases with a high atmospheric pressure due to the greater thrust available.

decreases with a headwind due to the greater air resistance.

increases with a high outside air temperature due to upward air currents.

According to CS-25, the final take-off speed VFTO...

may not be less than V2 min and VR plus the speed increment to screen height.

may not be less than 1.08 VS1 and must provide the manoeuvring capability.

must be more than 1.1 VMCA and must provide the max climb gradient.

may not be less than 1.18 VSR and must provide at least the minimum climb gradient.

Refer to figure or CAP 698 Figure 4.31.A pilot is instructed to reject their take-off whilst departing from Madrid airport in the MRJT (Medium-Range Jet Transport). Using the data below, when will the brakes have cooled sufficiently for another take-off to be commenced?Actual take-off mass: 56 000 kgAerodrome elevation: 1998 ftOAT: +34°CCAS at rejection: 70 ktGround speed at rejection: 65 kt

Immediately, as no brake cooling is required.

Approximately 10 minutes.

Approximately 15 minutes.

Approximately 23 minutes.

A single-engine class B aeroplane has the following wind limitations: Crosswind: 17 kt, Headwind: 30 kt, Tailwind: 10 kt. Consider a take-off from runway 20 with wind from 260°. Using trigonometry, determine the wind speed which allows to stay below the crosswind limit of 17 kt and take-off (2 decimal places for the calculations).

11 kt

19 kt

18 kt

20 kt

Given the following information, what is the wind velocity (°(T))?TAS: 465 ktGS: 480 ktTrack: 090 (M)Variation: 15° EWind correction angle +13°

360°/110 kt

197°/110 kt

210°/110 kt

015°/110 kt

Requirements for the third segment of climb are...

level acceleration with available min. climb gradient of 1.2%

legal minimum altitude for acceleration is 1500

minimum acceleration altitude for one engine inoperative should be used

there is no climb gradient requirement during acceleration phase

In accordance with CS-25, the take-off safety speed V2MIN for turbo-propeller powered aeroplanes with more than three engines may not be less than...

1.18 VSR.

1.13 VSR.

1.2 VSR.

1.08 VSR.

Performance Class A, Take-Off. The selected V1 is the balanced V1. As a consequence of this the...

Accelerate stop distance is equal to the engine failure take-off distance.

All engine take-off distance is equal to the take-off distance available.

All engine take-off distance is equal to the accelerate-stop distance.

All engine take-off distance is equal to the engine failure take-off distance.

For aircraft with a wingspan of more than 60 m, which formula should be used to calculate obstacle clearance for the initial climb?

90 m + ½ of the wingspan + 1.125 D

60 m + ½ of the wingspan + 0.0125 D

90 m + 0.125 D

60 m + 0.125 D

What is the definition of "wet ice", regarding contaminated runways?

Ice with a layer of water (more than 3 mm) on top of it or ice that is melting.

Ice with a layer of water on top of it more than 3 mm.

Ice with a layer of water (any depth) on top of it or ice that is melting.

Ice that is melting.

What are the consequences of incorrectly inputting 124 kt instead of 142 kt as the V1 speed in the EFB for a take-off, particularly if one engine becomes inoperative?

No significant consequence, as V1 does not directly affect the decision point for rotation.

The aircraft would overrun the runway in case of an engine failure before V1.

Due to the lower V1, the aircraft would rotate and become airborne earlier.

The aircraft would have an increased take-off distance and reduced obstacle clearance.

On a twin engine aeroplane, if an engine failure occurs above the OEI ceiling, the least rate of sink is obtain by flying the aircraft at the...

minimum control speed.

best single engine angle of climb speed.

best single engine rate of climb speed.

stall speed.

A flight crew is trying to minimise a delay. After having fully lined up on the runway, they release the brakes before setting take-off thrust. What will happen to the TOD and ASD?

TOD will decrease and ASD will increase.

Both TOD and ASD will increase.

Both TOD and ASD will decrease.

TOD will increase and ASD will decrease.

Refer to figure or CAP 698 file 4.31.An MRJT aeroplane is landing on runway 25 at an airport which has a long, dry runway with no performance restrictions. The runway has been chosen because of its negligible taxi distance after landing. The planned turnaround time is 25 minutes. Given the following information, is this turnaround time achievable?Landing mass: 51 000 kgVREF: 132 ktSurface Wind: 070°/6 kt (use 50% of headwind component or 150% of tailwind component as applicable)Airfield Elevation: 280 ftQNH: 1013 hPaOAT: +19°C

Yes, provided reverse #2 detent is used with any autobrake setting.

No, reverse thrust cannot be used for credit during landing and most conservative braking must be accounted for, requiring an inspection of the fuse plugs after 30 minutes.

No, reverse thrust cannot be used for credit during landing resulting in a minimum cooling time of approximately 60 minutes for the lowest autobrake settings #1 and #2.

Yes, provided reverse #2 detent is used with autobrake #1 or #2.

Refer to figure. Which of the figures shows the change in the total drag graph when density altitude is increased?

Figure 4

Figure 1

Figure 2

Figure 3

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