032.01 GENERAL

Question 1

The abbreviation ‘MOPSC’ means (…).

Answer 1

The abbreviation ‘MOPSC’ means (Maximum Operational Passenger Seating Configuration). (excluding crew seats).

Question 2

‘Performance class A aeroplanes’ means multi-engined aeroplanes powered by turbo-propeller engines with an MOPSC of more than (…) or a maximum take-off mass exceeding (…) kg, and all (…) aeroplanes.

Answer 2

‘Performance class A aeroplanes’ means multi-engined aeroplanes powered by turbo-propeller engines with an MOPSC of more than (9) or a maximum take-off mass exceeding (5 700) kg, and all (multi-engined turbo-jet powered) aeroplanes.

Question 3

‘Performance class B aeroplanes’ means aeroplanes powered by propeller engines with an MOPSC of (…) or less and a maximum take-off mass of (…) kg or less.

Answer 3

‘Performance class B aeroplanes’ means aeroplanes powered by propeller engines with an MOPSC of (9) or less and a maximum take-off mass of (5 700) kg or less.

Question 4

Gross performance is determined by (…).

Answer 4

Gross performance is determined by (the average of multiple landings by a regular pilot and aircraft).

Question 5

Measured performance is determined by (…).

Answer 5

Measured performance is determined by (a test pilot with a new aircraft).

Question 6

Gross performance multiplied by a safety factor added is called (…).

Answer 6

Gross performance multiplied by a safety factor added is called (net performance).

Question 7

Net take-off distance is (shorter/longer) than gross take-off distance.

Answer 7

Net take-off distance is (longer) than gross take-off distance.

Question 8

V_X is the speed for best (endurance/range).

Answer 8

V_X is the speed for best (endurance).

Question 9

V_Y is the speed for best (endurance/range).

Answer 9

V_Y is the speed for best (range).

Question 10

V_Y for jet aircraft is equal to (V_MD/1.32 V_MD/V_MP).

Answer 10

V_Y for jet aircraft is equal to (1.32 V_MD).

Question 11

V_Y for propeller aircraft is equal to (V_MD/1.32 V_MD/V_MP).

Answer 11

V_Y for propeller aircraft is equal to (V_MD).

Question 12

V_x for jet aircraft is equal to (V_MD/1.32 V_MD/V_MP).

Answer 12

V_x for jet aircraft is equal to (V_MD).

Question 13

V_x for propeller aircraft is equal to (V_MD/1.32 V_MD/V_MP).

Answer 13

V_x for propeller aircraft is equal to (V_MP).

Question 14

For jet aircraft, V_X is (smaller/greater) than V_MP and (smaller/greater) than V_Y.

Answer 14

For jet aircraft, V_X is (greater) than V_MP and (smaller) than V_Y.

Question 15

A headwind will (increase/decrease/not influence) the flight path angle and (increase/decrease/not influence) the descent angle.

Answer 15

A headwind will (increase) the flight path angle and (not influence) the descent angle.

Question 16

A tailwind will (increase/decrease/not influence) the flight path angle and (increase/decrease/not influence) the descent angle.

Answer 16

A tailwind will (decrease) the flight path angle and (not influence) the descent angle.

Question 17

The tangent from the origin to the power required against the true airspeed curve, for a jet aeroplane, determines teh speed for (critical AoA/min. power/max. endurance/max specific range).

Answer 17

The tangent from the origin to the power required against the true airspeed curve, for a jet aeroplane, determines teh speed for (max. endurance).

Question 18

Specific range is the (ground/still air) distance traveled per unit of (fuel/thrust).

Answer 18

Specific range is the (still air) distance traveled per unit of (fuel).

Question 19

At the absolute ceiling, the achievable rate of climb is (…).

Answer 19

At the absolute ceiling, the achievable rate of climb is (zero).

Question 20

Service ceiling for a piston or propeller aircraft with one engine inoperative is the altitude where the rate of climb reduces to (…) ft/min.

Answer 20

Service ceiling for a piston or propeller aircraft with one engine inoperative is the altitude where the rate of climb reduces to (50) ft/min.

Question 21

Service ceiling for a piston or propeller aircraft is the altitude where the rate of climb reduces to (…) ft/min.

Answer 21

Service ceiling for a piston or propeller aircraft is the altitude where the rate of climb reduces to (100) ft/min.

Question 22

Service ceiling for a jet aircraft is the altitude where the rate of climb reduces to (…) ft/min.

Answer 22

Service ceiling for a jet aircraft is the altitude where the rate of climb reduces to (500) ft/min.

Question 23

When the mass of an aircraft operating at optimum glide speed decreases, the glide angle (increases/decreases/is unchanged) and the rate of descent is (increases/decreases/is unchanged).

Answer 23

When the mass of an aircraft operating at optimum glide speed decreases, the glide angle (is unchanged) and the rate of descent is (decreases)​.

Question 24

An aircraft is descending at a constant TAS and deploys the flaps. The ROD will (increases/decreases/stay unchanged) and the descent gradient (increases/decreases/stay unchanged).

Answer 24

An aircraft is descending at a constant TAS and deploys the flaps. The ROD will (increases) and the descent gradient (increases)​.

- drag increases, so TAS decreases. To keep constant TAS pitch down required -

Question 25

The limit T/O distance is determined by chosing the **(lowest/highest)** value of TORA ÷ **(...)**, ASDA ÷ **(...)** and TODA ÷ **(...)**.

Answer 25

The limit T/O distance is determined by chosing the **(lowest)** value of TORA ÷ **(1)**, ASDA ÷ **(1.3)** and TODA ÷ **(1.15)**.

Question 26

To achieve the maximum range over ground with a tailwind, the airspeed should be **(lower/higher/equal)** compared to the max range speed with no wind.

Answer 26

To achieve the maximum range over ground with a tailwind, the airspeed should be **(lower)** compared to the max range speed with no wind.

Question 27

To achieve the maximum range over ground with a headwind, the airspeed should be **(lower/higher/equal)** compared to the max range speed with no wind.

Answer 27

To achieve the maximum range over ground with a headwind, the airspeed should be **(higher)** compared to the max range speed with no wind.

Question 28

The thrust/drag - speed graph of a jet aircraft is shown by **(graph 1/graph 2)**.

Answer 28

The thrust/drag - speed graph of a jet aircraft is shown by **(graph 1)**.

Question 29

Due to fuel starvation, all engines of a jet aircraft fail. The pilots need to fly the maximum glide endurance regime. The speed used it **(V_MP/V_MD/1.32 V_MD/V_S1g)**.

Answer 29

Due to fuel starvation, all engines of a jet aircraft fail. The pilots need to fly the maximum glide endurance regime. The speed used it **(V_MP)**. ## Footnote *- no difference between prop and jet aircraft -*

Question 30

Due to fuel starvation, all engines of a propeller driven aircraft fail. The pilots need to fly the maximum glide endurance regime. The speed used it **(V_MP/V_MD/1.32 V_MD/V_S1g)**.

Answer 30

Due to fuel starvation, all engines of a propeller driven aircraft fail. The pilots need to fly the maximum glide endurance regime. The speed used it **(V_MP)**. ## Footnote *- no difference between prop and jet aircraft -*

Question 31

Due to fuel starvation, all engines of a propeller driven aircraft fail. The pilots need to fly the maximum glide range regime. The speed used it **(V_MP/V_MD/1.32 V_MD/V_S1g)**.

Answer 31

Due to fuel starvation, all engines of a propeller driven aircraft fail. The pilots need to fly the maximum glide range regime. The speed used it **(V_MD)**. ## Footnote *- no difference between prop and jet aircraft -*

Question 32

Due to fuel starvation, all engines of a jet aircraft fail. The pilots need to fly the maximum glide range regime. The speed used it **(V_MP/V_MD/1.32 V_MD/V_S1g)**.

Answer 32

Due to fuel starvation, all engines of a jet aircraft fail. The pilots need to fly the maximum glide range regime. The speed used it **(V_MD)**. ## Footnote *- no difference between prop and jet aircraft -*

Question 33

On a dry uphill sloped runway compared to a flat runway, the acelelrated stop distance required is **(increased/decreased)**.

Answer 33

On a dry uphill sloped runway compared to a flat runway, the acelelrated stop distance _required_ is **(increased)**. ## Footnote *- because of uphill, distance to reach V₁ is longer -*

Question 34

Maximum excess power = **(V_X/V_Y)** Maximum excess thrust = **(V_X/V_Y)**

Answer 34

Maximum excess power = **(V_Y)** Maximum excess thrust = **(V_X)**

Question 35

Climb/descent angle is **(air mass/ground)** related and flight path angle is **(air mass/ground)**.

Answer 35

Climb/descent angle is **(air mass)** related and flight path angle is **(ground)**.

Question 36

The hourly fuel consumption of a turbojet powered aeroplane in a cruise flight at constant Mach and zero headwind is proportional to **(T / 1÷T / 1÷T²)**. T being outside static air temperature expressed in K.

Answer 36

The hourly fuel consumption of a turbojet powered aeroplane in a cruise flight at constant Mach and zero headwind is proportional to **(T)**. T being outside static air temperature expressed in K. ## Footnote *- Mach = TAS/a, a = LSS, which only depends on temperature -*

Question 37

The thrust of a jet engine at constant RPM is **(proportional/inversily proportional/independent)** to the airspeed.

Answer 37

The thrust of a jet engine at constant RPM is **(proportional)** to the airspeed.

Question 38

Without a stopway or clearway available, TOD • **(...)** should not exceed TORA.

Answer 38

Without a stopway or clearway available, TOD • **(1.25)** should not exceed TORA.

Question 39

V_MD on the power required curve is at the **(lowest point/tangent from the origin)**.

Answer 39

V_MD on the power required curve is at the **(tangent from the origin)**.

Question 40

The minimum width of a clearway is **(...)** ft

Answer 40

The minimum width of a clearway is **(500)** ft (≈ 150 m)

Question 41

Specific fuel consumption is **(NM/fuel flow/TAS)** / unit of **(fuel flow/thrust/mass of fuel)**.

Answer 41

Specific fuel consumption is **(fuel flow)** / unit of **(thrust)**. ## Footnote *SFC is a ratio of mass of fuel required to produce a unit of power or thrust per unit of time (kg per unit of shaft power)*

Question 42

In case of an engine failure with a multi-engine aeroplane, V_XSE is **(lower/higher)** than V_X and V_YSE is **(lower/higher)** than V_Y.

Answer 42

In case of an engine failure with a multi-engine aeroplane, V_XSE is **(higher)** than V_X and V_YSE is **(lower)** than V_Y.