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A jet aircraft is experiencing buffet whilst flying at its aerodynamic ceiling (coffin corner). What is the recommended recovery for this?

Maintain thrust and commence a turn at a 30° bank angle. The drag increase will cause a descent without significantly affecting the manoeuvre margins.

Maintain current thrust setting and descend. Increasing TAS is acceptable, but a decreased TAS will cause a stall.

Reduce thrust, maintain IAS and descend. Any increase or decrease in IAS could increase the buffet.

Reduce thrust, maintain current TAS and descend. Either increasing or decreasing TAS could cause high-speed or low-speed buffet.

The relationship of the reference landing speed (VREF) to the reference stalling speed in the landing configuration (VSR0) is that VREF may not be below...

1.1 VSR0.

VSR0.

1.23 VSR0.

1.32 VSR0.

Refer to figures or CAP 698 figure 4.8. An MRJT aircraft is intending to perform a flight from an airport with the data shown below. Calculate the V1, VR and V2 for this take off. Runway: 01 Pressure Altitude: 328 ft Slope: 1% Upslope OAT: 0° W/V: 190°/10 kt Take off mass: 61 430 kg Flaps 5

V1: 147 kt; VR: 151 kt; V2: 158 kt

V1: 145 kt; VR: 149 kt; V2: 156 kt

V1: 146 kt; VR: 150 kt; V2: 157 kt

V1: 145 kt; VR: 150 kt; V2: 157 kt

Determine the Specific Range (SR), given: Fuel flow: 28 Imp Gal/hr Specific gravity: 0.72 TAS: 154 MPH

2.4 NM air distance / kg.

1.67 NM air distance / kg.

0.68 NM air distance / kg.

1.46 NM air distance / kg.

An aircraft descends from FL410 to FL270 at its cruising Mach and then from FL270 to FL100 at the IAS achieved at FL270 with idle power and in a clean configuration. How does the angle of descent change during the first and second phase?

Decreases then constant

Increases then constant

Constant then decreases

Increases then decreases

Before arriving at your calculated Top of Descent (TOD), you are advised by ATC that you can start your descent at any point with no restrictions in speed or rate of descent. With regard to saving fuel, the speed for the descent should be the speed for...

Minimum power to achieve maximum distance

Minimum drag to achieve maximum distance

Minimum power to achieve minimum rate of descent

Minimum drag to achieve minimum rate of descent

Reference zero is a point 35 ft vertically beneath the aircraft at the end of...

TODR

TORA

ASDA

TODA

Which statement regarding gross performance is true?

Actual flight performance with a safety factor.

Actual flight performance with NO safety factor.

Calculated flight performance with a safety factor.

Margin between the net gradient and gross gradient.

Refer to figure. Which figure represents the effect of flaps on take-off distance with one engine inoperative?

Figure 4

Figure 1

Figure 2

Figure 3

Considering a jet aircraft, specific fuel consumption is measured in...

kg/h.N

kg/W*h

kg/N

NM/kg

An aeroplane is conducting a 6 hour sector flying from North Africa to Europe. The initial cruising altitude is FL340 with the recommended maximum being FL390. Normally the optimum cruising altitude is 500 ft to 2500 ft below the recommended maximum and the recommended maximum altitude increases by 100 ft for every 10 minutes of flight time as the fuel burns off. On this occasion the FMS computes an optimum altitude of FL340 for the entire flight. What could be the reason for it not recommending a step climb to FL370 or higher?

The aeroplane is too heavy for any higher altitudes during the course of the flight to allow for a 2000 ft climb.

The FMS has not been programmed properly with the correct aeroplane weights, thus giving inaccurate information.

Normally it is more efficient to stay at lower altitudes to take advantage of a higher TAS for the same Mach number.

The wind component at higher altitudes is less favourable, offsetting the increased fuel burn at the lower altitude.

The Specific Range (SR) is...

the ground distance that the aircraft would fly per kilogram of fuel.

the air distance that the aircraft would fly per kilogram of fuel.

the air distance that the aircraft would fly per unit of thrust.

the ground distance divided by air distance.

Assuming that the obstacle is 2200 m from the end of TODA, the maximum semi-width of the obstacle domain for an aircraft of wingspan 52 m that can maintain navigational accuracy and is not required to turn more than 15° degrees after take-off is...

600 m

300 m

351 m

365 m

The aerodynamic ceiling...

depends upon thrust setting and increase with increasing thrust.

is the altitude at which the best rate of climb theoretically is zero.

is the altitude where any change in speed results in buffeting.

is the altitude at which the aeroplane reaches 50 ft/min.

An airline wishes to operate a new commercial route on one of their jet aircraft to an airfield with a high field elevation. In summer, the climate of the airfield includes frequent low pressure systems, and the temperatures can get as high as 30°C. In comparison to an airfield at sea level in ISA conditions, what will be the likely effect of this destination on the maximum landing mass?

The MLM will be decreased.

The MLM will remain fairly constant as the pressure difference compensates for the higher temperature.

The MLM will be increased.

The MLM will increase slightly as the temperature difference compensates for the lower pressure.

According to OPS regulations, the runway condition complying with the definition of a "wet runway" is...

More than 25% of the runway surface area is covered by surface water which is more than 3 mm deep.

There is sufficient moisture on the runway surface to cause it to appear reflective, but without significant areas of standing water.

The runway surface is not dry, but the moisture on it does not give it a shiny appearance.

Moisture is present on the runway, but it still has an “effectively dry” braking action.

Consider a constant speed propeller aeroplane in the take-off configuration with full throttle position and forward RPM lever. How does thrust change when the aeroplane accelerates from the brake-release point to VLOF? As speed builds up, the thrust...

Decreases.

Remains constant.

Decrease or increases, depending on the form of the wing.

Increases.

The vertical interval by which a Class A aeroplane must avoid all obstacles in the drift-down path, during the drift-down following an engine failure is...

35 ft

2000 ft

1500 ft

1000 ft

What is the primary advantage of increasing the V2 speed on take-off?

Safety margin of field limited takeoff mass increases.

The obstacle limited takeoff mass can be increased.

Associated screen height with the new V1 speed is situated further down the runway.

The time to reach optimum altitude is reduced.

You are in a multi-engine aircraft equipped with counter-rotating propellers, which rotate away from the cockpit when viewed from behind. In the case of an engine failure, which engine is critical?

Both engines are critical.

There is no critical engine as counter-rotating blades always generate a p-factor closest to the cockpit.

The left engine is critical.

The right engine is critical.

The active runway has a displaced threshold. This decreases the...

LDA, TORA, TODA, ASDA not affected.

TODA only. ASDA, LDA and TORA are the same.

LDA and TODA. TORA, ASDA not affected.

LDA only. ASDA, TODA and TORA are the same.

What is the critical engine of a multi-engined, fixed-wing propeller-driven aeroplane?

The engine installed on the wing where the fuel tank is carrying the least amount of fuel.

The left engine in an aeroplane with two anti-clockwise turning (from the pilot's viewpoint) propellers.

The remaining engine after an engine failure that would produce the largest asymmetric yaw moment.

The engine whose failure would result in the largest asymmetric yaw moment.

Describe the cost index...

Distance travelled divided by cost of fuel.

Cost of fuel divided by distance travelled.

Total cost of flight divided by distance travelled.

Operating costs divided by cost of fuel.

Considering a jet transport aeroplane, Specific Fuel Consumption SFC...

is the nautical miles per unit of fuel flow.

is the nautical miles per unit mass of fuel.

is the fuel flow per unit of thrust.

is the TAS per unit of fuel flow.

The strength of the yawing moment caused by an engine failure on a twin-engine aeroplane...

is independent of the location (fore or aft) of the CG.

will be greater when the CG is located at the aft CG limit.

will be greater when the CG is located at the forward CG limit.

will be greater when the CG is located halfway between the forward and aft CG limits.

A multi-engined performance class B aeroplane has a wingspan of less than 60 metres. What is the semi-width of the obstacle accountability area at a distance of D from the end of the TODA? A semi-width...

at the discretion of the pilot to ensure obstacle avoidance.

of at least 2 x wingspan plus 90 m, plus D x0.125.

of at least 1/2 x wingspan plus 90 m, plus D x0.125.

of at least 1/2 x wingspan plus 60 m, plus D x0.125.

What is correct regarding the vertical obstacle clearance requirement for a Performance Class A aeroplane?If, in the engine-out take-off flight path, the bank angle is more than 15°, all relevant obstacles must be cleared by at least (1) _____, in relation to the (2) _____ take-off flight path.

(1) 35 ft; (2) net

(1) 50 ft; (2) gross

(1) 35 ft; (2) gross

(1) 50 ft; (2) net

The flight path angle is the angle between the...

path of the aircraft relative to the horizon.

path of the aircraft relative to True North.

longitudinal axis and the path of the aircraft.

longitudinal axis and the horizon.

The speed to obtain the maximum Specific Range (SR) of a turbojet aeroplane is...

Minimum power (VMP) speed.

Maximum lift / drag (L/D) ratio speed.

Minimum drag (VMD) speed.

1.32 x minimum drag (VMD) speed.

Refer to figure. Which of the labelled distances represents the TORA?

Distance 4

Distance 1

Distance 3

Distance 2

A multi-engine jet aeroplane is flying at its optimum cruise altitude when an engine fails. To minimise the angle of descent, the crew should descend at...

the speed for L/DMAX maximum lift to drag ratio and reduce weight by jettisoning fuel if possible and required.

the speed for minimum power required, extending flaps to further increase the lift.

VMD minimum drag speed and optimise the angle of descent by increasing lift through the extension of flaps.

1.32 VMD minimum drag speed and reduce weight by jettisoning fuel if possible and required.

Complete the following sentence: Consider two jet aircraft of the same type. The take-off mass of Jet 1 is 75 000 kg, and for Jet 2 it is 67 000 kg. Jet 1 will have a (1) _____ speed for best angle of climb, and a (2) _____ speed for best rate of climb.

(1) higher; (2) lower.

(1) lower; (2) lower.

(1) lower; (2) higher.

(1) higher; (2) higher.

Which of the following expressions accurately represents the rate of climb that would be indicated on a Vertical Speed Indicator (VSI)? Pa = Power Available, Pr = Power Required, Ta = Thrust Available, Tr = Thrust Required, W = Weight.

(Pa - Tr) / W

(Ta - Tr) / W

(Tr - Pr) / W

(Pa - Pr) / W

Before a departure with a Performance Class A twin-jet aeroplane, the pilots calculate the take-off performance. As the Actual Take-off Mass is less than the performance limiting masses for the existing conditions, it is decided to use reduced (FLEX) thrust. An air temperature of 45°C is used for the performance calculation, but the actual OAT is 20°C. Compared to the calculated take-off distance using 45°C, the actual take-off distance will be...

The same. The engines will be producing greater thrust at 20°C, but this will be counteracted by the higher take-off speeds expressed in TAS at that OAT.

Shorter. The engines will produce slightly greater thrust at 20°C, and the take-off speeds expressed in TAS will be lower at that OAT.

Longer. The take-off thrust will be reduced because an assumed temperature 25°C higher than the OAT is used, while the take-off speeds expressed in IAS will be the same in both cases.

The same. The engines will produce the same thrust at 20°C and 45°C, and the take-off speeds expressed in IAS will be the same in both cases.

Compared with still air, the effect a headwind has on the values of the maximum range speed and the maximum gradient climb speed respectively is that...

the maximum range speed increases and the maximum gradient climb speed is not affected.

the maximum range speed decreases and the maximum gradient climb speed increases.

the maximum range speed decreases and the maximum gradient climb speed is not affected.

the maximum range speed decreases and the maximum gradient climb speed decreases.

When determining the accelerate stop distance for a performance class A aeroplane. The available reverse thrust of the operative engine(s) ...

is taken into account on a dry runway.

is taken into account on a wet runway.

is NOT allowed to be used due to the risk of thrust asymmetry.

has NO effect on accelerated stop distance, regardless of the runway conditions.

A jet aeroplane has three configurations available for take-off. T/O 1: 1 stage of slats and flaps. T/O 2: 2 stages of slats and flaps. T/O 3: 3 stages of slats and 3 stages of flaps. The runway is NOT limiting but the given departure requires a climb gradient of 6.8% to 2000 ft. Which T/O configuration will be most appropriate to achieve the best climb gradient?

T/O 1 because it results in greater climb speeds and greater rate of climb than when using T/O2.

T/O 3 because it results in greater climb speeds and greater rate of climb than when using T/O1.

T/O 1 because it results in lower climb speeds, giving a higher angle of climb than when using T/O2.

T/O 2 because it results in lower climb speeds and greater rate of climb than when using T/O3.

A jet aeroplane is descending en route from cruise altitude at idle thrust. If ATC requests the crew to descend to a given flight level by a given point such that it requires a steeper descent gradient, this could be achieved by...

retracting the speed brake.

reducing the airspeed.

increasing the airspeed.

extending the flaps.

Given: VS = Stalling speed, VMCA = Air minimum control speed, VMU = Minimum unstick speed (disregarding engine failure), V1 = take-off decision speed, VR = Rotation speed, V2 min. = Minimum take-off safety speed, VLOF = Lift-off speed. The correct formula is...

VMU <= VMCA < V1

V2MIN. < VMCA > VMU

VS < VMCA < V2 MIN

VR < VMCA < VLOF

An aircraft is in a descent with a constant angle and speed. Which of the following does the aircraft have?

Lift equal to drag

Excess thrust

Excess drag

Excess power available

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