During take-offs for a twin engine aircraft with wing mounted engines (both being right hand props), which of the following conditions is the most favourable handling-wise?

Left quartering wind and right engine failure.

Right quartering wind and right engine failure.

Left quartering wind and left engine failure.

Left quartering wind and right engine failure.

Right quartering wind and left engine failure.

What is correct about a balanced field take-off? It is...

Where the OEI TODR = the OEI ASDR.

Where the OEI TODR = the AEO ASDR.

Where the OEI TODR = the OEI ASDR.

Refer to figure or CAP file 4.24. With regard to the drift down performance of the twin jet aeroplane, why does the curve representing 35 000 kg gross mass in the chart for drift down net profiles start at approximately 4 minutes at FL370?

Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

Because at this mass the engines slow down at a slower rate after failure, there is still some thrust left during 4 minutes.

All the curves start at the same point, which is situated outside the chart.

Because at this mass it takes approximately 4 minutes to decelerate to the optimum speed for drift down at the original cruising level.

Due to higher TAS at this mass it takes more time to develop the optimal rate of descent, because of the inertia involved.

What is the best endurance speed on a propeller aircraft?

VMP and it does not change with wind

VMP and it varies with the wind vector

VMP and it does not change with wind

card2brain.ch

A jet aeroplane is flying just below its maximum operating altitude. If the aircraft begins to descend at a constant mach number with no changes to its mass, CG or configuration...

its high-speed buffet margin will decrease because the critical Mach number decreases with reducing altitude.

the low-speed buffet margin will increase because stall speed decreases with reducing altitude.

the low-speed buffet margin will decrease because the critical Mach number decreases with reducing altitude.

its high-speed buffet margin will increase because stall speed decreases with reducing altitude.

its high-speed buffet margin will decrease because the critical Mach number decreases with reducing altitude.

the low-speed buffet margin will increase because stall speed decreases with reducing altitude.

the low-speed buffet margin will decrease because the critical Mach number decreases with reducing altitude.

its high-speed buffet margin will increase because stall speed decreases with reducing altitude.

Consider a fixed-pitch propeller aeroplane at take-off. When the aeroplane accelerates during the take-off run phase, the blade angle of attack will (1) _____ and the thrust produced by the propeller will (2) _____.

(1) decrease; (2) decrease

(1) increase; (2) decrease

(1) increase; (2) increase

(1) decrease; (2) increase

(1) decrease; (2) decrease

(1) increase; (2) decrease

(1) increase; (2) increase

(1) decrease; (2) increase

When should a pilot consider carrying out a step climb during the cruise?

Only when required by ATC to maintain optimum fuel consumption.

Whenever possible to improve best range.

Whenever possible to improve best endurance.

Any time to improve best endurance regardless of flight conditions.

Only when required by ATC to maintain optimum fuel consumption.

Whenever possible to improve best range.

Whenever possible to improve best endurance.

Any time to improve best endurance regardless of flight conditions.

In level flight at a given speed, what happens to the drag if aeroplane mass is increased?

It is NOT affected.

It stays constant.

It decreases.

It increases.

It is NOT affected.

It stays constant.

It decreases.

It increases.

What is true regarding the V2MIN speed for a dual engine turbo-jet aircraft?

It may not be less than 1.3 x VMC.

It's the minimum safe take-off speed with all engines operating.

At low altitudes it's often limited by the minimum control speed.

At low altitudes it's often limited by the stall speed.

It may not be less than 1.3 x VMC.

It's the minimum safe take-off speed with all engines operating.

At low altitudes it's often limited by the minimum control speed.

At low altitudes it's often limited by the stall speed.

Complete the following phrase: Any part of the (1) _____ take-off flight path in which a performance Class A aircraft is banked by more than 15° shall clear all obstacles by a vertical distance of at least (2) _____.

(1) net; (2) 50 ft.

(1) gross; (2) 35 ft.

(1) gross; (2) 50 ft.

(1) net; (2) 35 ft.

(1) net; (2) 50 ft.

(1) gross; (2) 35 ft.

(1) gross; (2) 50 ft.

(1) net; (2) 35 ft.

A multi-engined piston aeroplane is in straight and level flight. As fuel is burnt, the mass of the aeroplane reduces. Consequently, the Specific Range (SR) will (1) _____, and the optimum speed for maximum SR will (2) _____.

(1) increase; (2) increase.

(1) increase; (2) decrease.

(1) decrease; (2) decrease.

(1) decrease; (2) increase.

(1) increase; (2) increase.

(1) increase; (2) decrease.

(1) decrease; (2) decrease.

(1) decrease; (2) increase.

In the cruise, a pilot begins preparing for landing by performing an in-flight landing performance calculation, incorporating the use of autobrakes and spoilers onto a dry runway. The result does NOT satisfy the pilot, who decides to perform the same calculation again, incorporating reverse thrust as well as autobrakes and spoilers. Compared with the first calculation, the newly calculated landing distance will be...

increased, because the use of reverse thrust will cancel the operation of the autobrake system.

nearly the same, because the deceleration due to application of reverse thrust will result in an equivalent reduction in the rate of deceleration provided by the autobrake system.

invalid, because the use of reverse thrust is NOT allowed on dry runways.

considerably reduced, because the deceleration due to application of reverse thrust in combination with the use of autobrakes will result in an increase in the total deceleration rate.

increased, because the use of reverse thrust will cancel the operation of the autobrake system.

nearly the same, because the deceleration due to application of reverse thrust will result in an equivalent reduction in the rate of deceleration provided by the autobrake system.

invalid, because the use of reverse thrust is NOT allowed on dry runways.

considerably reduced, because the deceleration due to application of reverse thrust in combination with the use of autobrakes will result in an increase in the total deceleration rate.

How would you calculate "excess thrust required" in a descent at constant speed?

Drag minus Thrust

Drag minus Lift

Lift minus Weight

Thrust minus Drag

Drag minus Thrust

Drag minus Lift

Lift minus Weight

Thrust minus Drag

Minimum V2 speed (V2MIN) is limited by both the stall speed (VSR) and minimum control speed (VMC). Which statement is correct?

At high density altitudes and high weight, V2MIN is often limited by the stall reference speed (VSR).

At high density altitudes and high weight, V2MIN is often limited by the speed for minimum control (VMC).

V2MIN cannot be lower than the highest of 1.05 times VMC and 1.2 times VSR.

V2MIN is calculated with all engines operating, for flight with one engine inoperative, another safety speed must be used.

At high density altitudes and high weight, V2MIN is often limited by the stall reference speed (VSR).

At high density altitudes and high weight, V2MIN is often limited by the speed for minimum control (VMC).

V2MIN cannot be lower than the highest of 1.05 times VMC and 1.2 times VSR.

V2MIN is calculated with all engines operating, for flight with one engine inoperative, another safety speed must be used.

Which of the equations below defines specific range (SR)?

SR = True Airspeed / Total Fuel Flow

SR = Calibrated Airspeed / Total Fuel Flow

SR = Indicated Airspeed / Total Fuel Flow

SR = Mach number / Total Fuel Flow

SR = True Airspeed / Total Fuel Flow

SR = Calibrated Airspeed / Total Fuel Flow

SR = Indicated Airspeed / Total Fuel Flow

SR = Mach number / Total Fuel Flow

A pilot performs two landings onto the same runway. Both are from 3° approaches, with the same conditions present.Landing 1: The aeroplane passes the runway threshold at a height of almost 100 ft and the correct landing airspeedLanding 2: The aeroplane passes the runway threshold at 50 ft but with an airspeed 5 knots higher than the correct landing airspeed.Choose the correct statement.

Both landings result in a greater landing distance than expected, where landing 2 is less predictable as it depends on how excess energy is dissipated during the flare and subsequent ground roll.

Landing 1 has a greater landing distance due to excess energy while landing 2 achieves the planned landing distance since the aeroplane touches down at the optimum touchdown point.

Landing 1 achieves the planned landing distance since the landing distance starts at 50 ft while landing 2 has a greater landing distance due to excess energy.

Both landings result in the planned landing distance being used since the landing distance allows for small deviations in height above the landing threshold and landing speed.

Both landings result in a greater landing distance than expected, where landing 2 is less predictable as it depends on how excess energy is dissipated during the flare and subsequent ground roll.

Landing 1 has a greater landing distance due to excess energy while landing 2 achieves the planned landing distance since the aeroplane touches down at the optimum touchdown point.

Landing 1 achieves the planned landing distance since the landing distance starts at 50 ft while landing 2 has a greater landing distance due to excess energy.

Both landings result in the planned landing distance being used since the landing distance allows for small deviations in height above the landing threshold and landing speed.

Consider a Class A Medium Range Jet Transport aeroplane that is approved to be operated with increased bank angle limits. The maximum permitted bank angle for the portion of the net take-off flight path between 200 ft and 400 ft is...

none

15°

20°

30°

none

15°

20°

30°

The determination of the maximum mass on brake release, of an aeroplane & certified under CS 25 with 5°, 15° and 25° flaps angles on take-off, leads to the following values with zero wind:Flap angle: 5° / 15° / 25°Runway limitation: 66 000 kg / 69 500 kg / 71 500 kg2nd segment climb limitation: 72 200 kg / 69 000 kg / 61 800 kgWind correction: Head wind: +120 kg / ktTail wind: -360 kg / ktGiven that the tail wind component is equal to 5 kt, the maximum mass on brake release and corresponding flap angle will be...

69 000 kg / 15°

69 700 kg / 25°

72 200 kg / 5°

67 700 kg / 15°

69 000 kg / 15°

69 700 kg / 25°

72 200 kg / 5°

67 700 kg / 15°

You forget to change the MACH setting to the IAS setting while descending at a constant Mach number. What will be the consequence?

The rate of descent increases, and the pitch angle decreases

The rate of descent decreases, and the pitch angle decreases

The rate of descent increases, and the pitch angle remains constant

The rate of descent decreases, and the pitch angle remains constant

The rate of descent increases, and the pitch angle decreases

The rate of descent decreases, and the pitch angle decreases

The rate of descent increases, and the pitch angle remains constant

The rate of descent decreases, and the pitch angle remains constant

An aeroplane executes a steady glide at the speed for minimum glide angle. If the airspeed is kept constant, what is the effect of a lower mass? Rate of descent / Glide angle / CL/CD ratio...

decreases / constant / decreases

increases / increases / constant

increases / increases / decreases

increases / constant / increases

decreases / constant / decreases

increases / increases / constant

increases / increases / decreases

increases / constant / increases

When determining the Maximum Landing Mass of an turbojet powered aeroplane during the planning phase, what factor must be used on the landing distance available (dry runway)?

0.60

115/100

60/115

1.67

0.60

115/100

60/115

1.67

In the event of a planned track change of more than 15° in the NTOFP, what is the maximum bank angle allowed and obstacle clearance height requirement?

Maximum bank angle 25° with a vertical obstacle clearance height of 50 ft with reference to net path.

Maximum bank angle 15° with a vertical obstacle clearance height of 35 ft with reference to net path.

Maximum bank angle 25° with a vertical obstacle clearance height of 35 ft with reference to gross path.

Maximum bank angle 15° with a vertical obstacle clearance height of 50 ft with reference to gross path.

Maximum bank angle 25° with a vertical obstacle clearance height of 50 ft with reference to net path.

Maximum bank angle 15° with a vertical obstacle clearance height of 35 ft with reference to net path.

Maximum bank angle 25° with a vertical obstacle clearance height of 35 ft with reference to gross path.

Maximum bank angle 15° with a vertical obstacle clearance height of 50 ft with reference to gross path.

When performing an increased V2 take-off, our V1 speed will be increased. What related hazards should we pay most attention to?

The stop distance may be compromised.

The climb gradient is reduced, and we may not clear distant obstacles.

The new V1 may be above controllability limits.

The braking efficiency during a rejected take-off will be reduced.

The stop distance may be compromised.

The climb gradient is reduced, and we may not clear distant obstacles.

The new V1 may be above controllability limits.

The braking efficiency during a rejected take-off will be reduced.

For a Performance Class A aircraft, the Net Take-Off Flight Path begins at a height of (1) _____ above the reference zero point and ends at a height of (2) _____ at least.

(1) 35 ft; (2) 400 ft

(1) 35 ft; (2) 1500 ft

(1) 35 ft; (2) 1000 ft

(1) 50 ft; (2) 1000 ft

(1) 35 ft; (2) 400 ft

(1) 35 ft; (2) 1500 ft

(1) 35 ft; (2) 1000 ft

(1) 50 ft; (2) 1000 ft

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

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

(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

Commandes clavier:

= tourner,

= avant/arrière,

= faire défiler

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.

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).

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

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

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

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.

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

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%

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.

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

76 kt

88 kt

78 kt

82 kt