General

Question 1

According Regulation EU 965/2012, “Performance class B aeroplanes” means aeroplanes powered by (1) ___ engines with a maximum operational passenger seating configuration of (2) ___ and a maximum take-off mass of (3) ___.

(1) propeller, (2) 20 or more, (3) more than 5700 kg
(1) jet engine, (2) 9 or more, (3) more than 5700 kg
(1) jet engine, (2) 20 or more, (3) 5700 kg or less
(1) propeller, (2) nine or less, (3) 5700 kg or less

Answer 1

(1) propeller, (2) nine or less, (3) 5700 kg or less

Question 2

With regard to CS-23 and CS-25, the “take-off flight path” (gross flight path) is:

• the actual flight path as demonstrated by the manufacturer reduced by a factor dependent on the number of engines.
• the actual flight path as demonstrated by the manufacturer excluding safety margins.
• the minimum flight path with a gradient an airplane should follow to achieve a minimum obstacle clearance.
• the actual flight path as demonstrated by the manufacturer including safety margins.

Answer 2

• the actual flight path as demonstrated by the manufacturer excluding safety margins.

Question 3

With regard to CS-25 certification requirements for large aeroplanes, which of the following statements is correct?

1. “gross flight path” is the actual flight path demonstrated by the manufacturer with NO safety margins
2. “net flight path” is the actual flight path demonstrated by the manufacturer reduced by safety factor dependent on the number of engines.

1 is incorrect, 2 is incorrect
1 is incorrect, 2 is correct
1 is correct, 2 is correct
1 is correct, 2 is incorrect

Answer 3

1 is correct, 2 is correct

Question 3

According CS-Definitions, an “area beyond the runway under the control of the airport authority (…) extending from the end of the runway with an upward slope not exceeding 1.25%, above which no object or terrain protrudes” is defined as:

Stopway
Brake area
Runaway ramp
Clearway

Answer 3

Clearway

Question 4

According CS-Definitions, an “an area beyond the take-off runway (…) for use in decelerating the aeroplane during an abortive take-off” is defined as:

Stopway
Brake area
Runaway ramp
Clearway

Answer 4

Stopway

Question 5

According Regulation EU 139/2014, the “Take-off distance available” means…

• the length of the take-off run available plus the length of the clearway, if provided.
• the length of the take-off run available plus the length of the stopway, if provided,
• the length of the active runway distance beyond threshold.
• the distance of the active runway plus the distance to an obstacle of 50 ft height.

Answer 5

• the length of the take-off run available plus the length of the clearway, if provided.

Question 6

The pilot of a single engine aeroplane has determined the climb performance.
When carrying an additional passenger in a single-engine aircraft, the climb performance will be…

• unaffected
• decreased or increased, depending on the take-off path
• decreased
• increased

Answer 6

decreased

Question 7

The “screen height” for Performance Class A aeroplanes is a reference height of usually (1) ___ with a dry runway, and is measures overhead (2) ___.

(1) 35 ft, (2) Airport Elevation
(1) 15 ft, (2) Reference Zero (RZ)
(1) 15 ft, (2) Airport Elevation
(1) 35 ft, (2) Reference Zero (RZ)

Answer 7

(1) 35 ft, (2) Reference Zero (RZ)

Question 8

Define “Power Required”:

• The power multiplied by airspeed to maintain unaccelerated straight and level flight.
• The power needed to maintain unaccelerated straight and level flight.
• The thrust force needed to maintain unaccelerated straight and level flight.
• The drag divided by airspeed to maintain unaccelerated straight and level flight.

Answer 8

• The power needed to maintain unaccelerated straight and level flight.

Question 9

If aerodrome pressure altitude decreases, the…

• take-Off Distance Required increases.
• take-Off Distance Required decreases.
• accelerate-Stop Distance increases.
• take-Off Ground Run increases.

Answer 9

take-Off Distance Required decreases.

Question 10

If atmospheric pressure increases, take-off distance [1] ___ and initial climb performance [2] ___.

[1] decreases [2] increases
[1] decreases [2] decreases
[1] increases [2] increases
[1] increases [2] decreases

Answer 10

[1] decreases [2] increases

Question 11

Increasing atmospheric pressure will result in…

• increased landing distance and go-around performance.
• decreased landing distance and go-around performance.
• decreased landing distance, increased go-around performance.
• increased landing distance, decreased go-around performance.

Answer 11

decreased landing distance, increased go-around performance.

Question 12

If the gross mass of a piston engine aeroplane is increased, to keep the angle of attack, configuration and altitude constant…

• an increase in airspeed is required, but power setting should be kept constant.
• a higher drag coefficient is required.
• an increase in power and a decrease in airspeed is required.
• an increase in airspeed and power is required.

Answer 12

• an increase in airspeed and power is required.

Question 12

An aeroplane with reciprocating engines flies at a constant angle of attack, mass and configuration.
Should the altitude increase, the power required will…

• increase and the TAS will increase by the same percentage.
• increase but the TAS will not change.
• decrease and the TAS will also decrease.
• not change but the TAS will increase.

Answer 12

increase and the TAS will increase by the same percentage.

Question 12

When the actual landing mass is higher than planned, the…

• threshold speed will be higher.
• landing distance remains the same.
• landing distance will be longer.
• approach path will be steeper.

Answer 12

landing distance will be longer.

Question 13

When the outside air temperature increases the…

• climb gradient increases and the rate of climb decreases.
• climb performance is not affected.
• the climb gradient and the rate of climb both decrease.
• climb gradient decreases and the rate of climb increases.

Answer 13

the climb gradient and the rate of climb both decrease.

Question 14

If the gross mass of a piston-engine aeroplane increases, to keep the angle of attack, configuration and altitude constant, the…

• airspeed must be increased, but the drag must remain the same.
• airspeed must be increased, resulting in increased drag.
• lift/drag ratio must be increased, but the drag must remain the same.
• airspeed must be decreased, resulting in increased drag.

Answer 14

airspeed must be increased, resulting in increased drag.

Question 15

Take-off and initial climb performance can be adversly affected by [1] ___ temperature and [2] ___ relative humidity.

[1] low [2] low
[1] high [2] low
[1] low [2] high
[1] high [2] high

Answer 15

[1] high [2] high

Question 16

Select the correct definition for Density Altitude:

• The altitude read directly from the altimeter.
• Height above ground.
• Airfield Elevation converted to Pressure Altitude, then corrected for ‘Non-standard’ Temperature.
• The altitude reference to the standard datum plane.

Answer 16

Airfield Elevation converted to Pressure Altitude, then corrected for ‘Non-standard’ Temperature.

Question 17

The Angle of Climb with flaps extended, compared to that with flaps retracted, will be…

increased at a small flap setting, and decreased at a large flap setting.
the same.
smaller.
larger.

Answer 17

smaller.

Question 18

Which of the following parameters decrease the take-off ground run?

1. decreasing take-off mass
2. increasing take-off mass
3. increasing density
4. decreasing density
5. increasing flap tilt angle
6. decreasing flap tilt angle
7. increasing pressure altitude
8. decreasing pressure altitude

• 2, 3, 5 and 7
• 1, 3, 5 and 7
• 2, 4, 6 and 8
• 1, 3, 5 and 8

Answer 18

• 1, 3, 5 and 8

Question 19

The diagram which shows the change of the position of the Power Required curve with Altitude (H2 at a greater altitude than H1), is…

D
A
C
B

Answer 19

D

Question 20

Which sketch correctly illustrates the change in the thrust-required curve with decreasing density altitude?

Sketch A
Sketch B
Sketch D
Sketch C

Answer 20

Sketch B

Question 20

Regarding a propeller-driven aeroplane during climb, the power-required at a given IAS will (1) ___ with (2) ___ density altitude.

(1) decrease, (2) any change in
(1) increase, (2) increasing
(1) not change, (2) changing
(1) decrease, (2) increasing

Answer 20

(1) increase, (2) increasing

Question 21

Which sketch correctly illustrates the change in the thrust-required curve with increasing density altitude? Sketch A Sketch B Sketch C Sketch D

Answer 21

Sketch B

Question 22

When aircraft mass decreases during unaccelerated horizontal flight, the Minimum Drag [1] ___ and the IAS for the Minimum Drag [2] ___. [1] increases [2] decreases [1] increases [2] increases [1] decreases [2] increases [1] decreases [2] decreases

Answer 22

[1] decreases [2] decreases

Question 23

The correct equation about Specific Range over Ground (SRG) is... SR = TAS / Total Fuel Flow SR = GS / Total Fuel Flow SR = CAS / Total Fuel Flow SR = Mach number / Total Fuel Flow

Answer 23

SR = GS / Total Fuel Flow

Question 23

Regarding straight and level flight at a given speed, drag (1) ___ with (2) ___ aeroplane mass. (1) increases, (2) less (1) does not change, (2) any change in (1) decreases, (2) more (1) increases, (2) increasing

Answer 23

(1) increases, (2) increasing

Question 24

To maximize Specific Range (or Specific Air Range), the TAS must be (1) ___ and the Fuel Flow must be (2) ___. (1) high, (2) low. (1) low, (2) low. (1) low, (2) high. (1) high, (2) high.

Answer 24

(1) high, (2) low.

Question 25

The correct equation about Specific Air Range (SAR) is: SAR = TAS / Total Fuel Flow SAR = GS / Total Fuel Flow SAR = Mach number / Total Fuel Flow SAR = CAS / Total Fuel Flow

Answer 25

SAR = TAS / Total Fuel Flow

Question 26

Point (A) in a piston-engine aeroplane at any given mass is the Speed for Maximum ... Lift Endurance Specific Range Thrust

Answer 26

Endurance

Question 27

The term "specific range" can be understood as... - the distance (NM) an airplane multiplied with the average fuel flow (FF). - the ground speed (GS) divided by a given unit mass of fuel (kg). - the distance (NM) an airplane can travel with given unit mass of fuel (kg). - the ground speed (GS) multiplied with the total fuel flow (FF).

Answer 27

- the distance (NM) an airplane can travel with given unit mass of fuel (kg).

Question 28

To fly for maximum time airborne during glide, the speed should be for... maximum lift. critical Mach number. minimum angle of attack. minimum power required.

Answer 28

minimum power required.

Question 29

In a Turbojet, the tangent from the origin of the Power Required against TAS curve, depicts the speed for... minimum power. maximum specific range. maximum endurance. most critical angle of attack.

Answer 29

maximum endurance.

Question 30

In level flight of a piston engine aeroplane without turbo charger the maximum indicated air speed can be reached at the... optimum cruise altitude. lowest possible altitude. aerodynamic ceiling. service ceiling.

Answer 30

lowest possible altitude.

Question 31

Under which conditions can the maximum speed in horizontal flight be reached? When the thrust equals the maximum drag When the thrust equals minimum drag When the maximum thrust equals the total drag When the thrust remains constant with increasing speed

Answer 31

When the maximum thrust equals the total drag

Question 32

When flying at the 'backside of the power curve'... the elevator must be pulled to lower the nose. the aeroplane is not able to stall. the speed is unstable. the altitude cannot be kept constant.

Answer 32

the speed is unstable.

Question 33

On a Thrust Required curve of a jet aeroplane, the lowest point represents... Maximum rate of descent. Minimum Drag. Maximum specific range. Minimum specific range.

Answer 33

Minimum Drag.

Question 34

The point of minimum Drag Coefficient/Lift Coefficient is... on the 'back side' of the drag curve. at the lowest point of the drag curve. at VMO. at the point where a tangent from the origin touches the drag curve.

Answer 34

at the lowest point of the drag curve.

Question 35

On the Power versus TAS graph for level flight, a tangent from the origin touches the power required curve where the... Lift to Drag ratio is a minimum. Maximum Drag Speed is reached. Drag coefficient is a minimum. Lift to Drag ratio is a maximum.

Answer 35

Lift to Drag ratio is a maximum.

Question 36

In straight horizontal steady flight, at speeds below that for minimum drag... the aeroplane can only be controlled in level flight. higher speed, but still below that for minimum drag, requires higher thrust. the aeroplane cannot be flown manually. lower speed requires higher thrust.

Answer 36

lower speed requires higher thrust.

Question 37

The maximum achievable speed (TAS) in level flight with a non-supercharged piston engine (1) ___ with (2) ___ . (1) decreases, (2) increasing density (1) increases, (2) increasing altitude (1) increases, (2) decreasing density (1) decreases, (2) increasing altitude

Answer 37

(1) decreases, (2) increasing altitude

Question 38

Which statement about "maximum endurance" is correct? It can be achieved in unaccelerated level flight with minimum fuel flow. It can be reached when flying at the 'best rate of climb' speed in level flight. It is the same as maximum specific range corrected for the wind component. It can be used in a steady climb only.

Answer 38

It can be achieved in unaccelerated level flight with minimum fuel flow.

Question 39

To achieve maximum range with a headwind, the airspeed should be... equal to the maximum range cruise speed with no wind. lower than the maximum range cruise speed with no wind. reduced to the maximum speed for gust penetration. higher than the maximum range cruise speed with no wind.

Answer 39

higher than the maximum range cruise speed with no wind.

Question 40

For a jet transport aeroplane, the advantage of Maximum Range Speed is... Minimum specific fuel consumption. Longest flight time. Minimum fuel flow. Minimum drag.

Answer 40

Minimum specific fuel consumption.

Question 41

At constant mass and Mach number, for a higher altitude... a higher angle of attack is required. a lower lift coefficient is required. a lower angle of attack is required. a lower drag coefficient is required.

Answer 41

a higher angle of attack is required.

Question 42

With regard to jet-engines, "Specific Fuel Consumption (SFC)" can be understood as: Fuel flow (kg/h) for unit of producible thrust (N). Unit of producible thrust (N) per fuel consumption (kg). Fuel mass (kg) for unit of producible thrust (N). Product of fuel flow (kg/h) and unit of producible thrust (N).

Answer 42

Fuel flow (kg/h) for unit of producible thrust (N).

Question 43

With the Centre of Gravity closer to the aft than the forward limit... The maximum range is increased. The maximum range is decreased. The stalling speed is increased. The longitudinal stability is improved.

Answer 43

The maximum range is increased.

Question 44

Aircraft: Turbojet Speed Regime: Max. Range Cruise Cruise Level: Below Optimum If altitude is increased, the Specific Range will... first increase and then decrease. remain the same. increase only in still-air conditions. decrease.

Answer 44

first increase and then decrease.

Question 45

Regarding a turbojet aeroplane, fuel flow during steady level flight is... proportional to power which directly depends on TAS. proportional to power which directly depends on EAS. proportional to thrust (drag) which directly depends on EAS. proportional to thrust (drag) which directly depends on TAS.

Answer 45

proportional to thrust (drag) which directly depends on EAS.

Question 46

With regard to turbojet aeroplanes, which of the following statements is correct? 1. The speed for maximum endurance increases with increasing head wind component. 2. The (maximum) endurance is not affected by wind. 1 is correct, 2 is íncorrect 1 is incorrect, 2 is incorrect 1 is incorrect, 2 is correct 1 is correct, 2 is correct

Answer 46

1 is incorrect, 2 is correct

Question 46

With regard to a propeller-driven aeroplane, fuel flow (1) ___ with increasing TAS at speeds (2) ____. (1) decreases, (2) below minimum power speed. (1) increases, (2) below minimum power speed. (1) decreases, (2) above minimum power speed. (1) decreases, (2) below the maximum range speed.

Answer 46

(1) decreases, (2) below minimum power speed.

Question 47

With regard to a turbojet aeroplane, speed for maximum endurance corresponds to... the speed for minimum drag. the speed for best specific range. the speed for minimum ratio between drag and speed. the speed for minimum power.

Answer 47

the speed for minimum drag.

Question 48

With regard to turbojet aeroplanes, which of the following statements is correct? 1. Endurance increases with altitude up to the optimum altitude. 2. Endurance decreases with altitude above the optimum altitude. 1 is correct, 2 is íncorrect 1 is incorrect, 2 is incorrect 1 is incorrect, 2 is correct 1 is correct, 2 is correct

Answer 48

1 is correct, 2 is correct

Question 48

With regard to a propeller-driven aeroplane, the speed for maximum endurance (1) ___ with increasing altitude because (2) ___. (1) increases, (2) power required increases. (1) decreases, (2) drag and thrust increase. (1) decreases, (2) power required decreases. (1) increases, (2) drag and thrust decrease.

Answer 48

(1) increases, (2) power required increases.

Question 48

With regard to propeller-driven aeroplanes, which of the following statements is correct? 1. A piston-engine aeroplane will reach its highest endurance at MSL level. 2. Speed for maximum endurance decreases with increasing altitude. 1 is incorrect, 2 is incorrect 1 is correct, 2 is incorrect 1 is incorrect, 2 is correct 1 is correct, 2 is correct

Answer 48

1 is correct, 2 is incorrect

Question 49

With regard to propeller-driven aeroplanes, which of the following statements is correct? 1. Maximum endurance is NOT affected by any wind component. 2. Speed for maximum endurance is reached at minimum power (VMP) 1 is incorrect, 2 is incorrect 1 is correct, 2 is incorrect 1 is correct, 2 is correct 1 is incorrect, 2 is correct

Answer 49

1 is correct, 2 is correct

Question 50

During approach to an airport with a jet transport aeroplane, ATC informs the crew about delays to be expected. If requested to reduce speed, the crew should reduce speed to ___ to maximize endurance. Minimum Power speed (VMP) Long Range Cruise speed (LRC) Reference Speed (VREF) Minimum Drag Speed VMD at clean configuration (Minimum Clean speed)

Answer 50

Minimum Drag Speed VMD at clean configuration (Minimum Clean speed)

Question 50

During approach to an airport with a jet transport aeroplane, ATC informs the crew about delays to be expected. If requested to reduce speed, the crew should reduce speed to ___ to delay arrival at the holding fix as long as possible. - Reference Speed (VREF) - Minimum Power speed (VMP) - Long Range Cruise speed (LRC) - Minimum Drag Speed VMD at clean configuration (Minimum Clean speed)

Answer 50

- Minimum Drag Speed VMD at clean configuration (Minimum Clean speed)

Question 50

The correct statement about unaccelerated climb is... - The thrust is equal to the drag plus the uphill component of the gross weight in the flight path direction. - The thrust is equal to the drag plus the downhill component of the gross weight in the flight path direction. - The lift is higher than the gross weight. - The lift is equal to the weight plus the vertical component of the drag.

Answer 50

- The thrust is equal to the drag plus the downhill component of the gross weight in the flight path direction.

Question 51

The equation applicable to Climb Gradient percentage in unaccelerated flight at small angles is... Climb Gradient = ((Thrust - Drag)/Lift) x 100 Climb Gradient = ((Thrust + Mass)/Lift) x 100 Climb Gradient = (Lift - Weight) x 100 Climb Gradient = ((Thrust - Drag)/Weight) x 100

Answer 51

Climb Gradient = ((Thrust - Drag)/Weight) x 100

Question 51

With all other factors constant, an increase of altitude in a standard atmosphere, will cause [1] VX to ___ and [2] VY to ___ when expressed in TAS. [1] increase [2] decrease [1] decrease [2] decrease [1] decrease [2] increase [1] increase [2] increase

Answer 51

[1] increase [2] increase

Question 52

VX is the speed for best... specific range. angle of climb. angle of flight path. rate of climb.

Answer 52

angle of climb.

Question 52

At an aeroplane with two clockwise-rotating propeller piston engines, the critical engine is... the right engine in case of engine failure during ground roll. the left engine in case of engine failure during idle glide. the left engine in case of engine failure during take-off. the right engine in case of engine failure during taxing.

Answer 52

the left engine in case of engine failure during take-off.

Question 53

Approved take-off flap settings: UP / 5° / 10° / 15°. When performing a take-off with flaps 10° instead of flaps UP, the... take-off distance increases climb performance decreases VLOF increases ground roll distance increases

Answer 53

climb performance decreases

Question 53

With regard to Performance Class B multi-engine aeroplanes, counter-rotating propellers are installed to... increase propeller efficiency during different phases of flight. refresh the boundary layer to enable larger angles of attack. eliminate problems resulting from failure of the critical engine. allow for larger distance of the engines from the longitudinal axis.

Answer 53

eliminate problems resulting from failure of the critical engine.

Question 53

The best rate of climb at a constant gross mass... - Increases with increasing altitude as the drag decreases due to lower air density. - Increases with increasing altitude due to higher TAS. - Decreases with increasing altitude as the thrust available decreases due to lower air density. - Is not affected by changes in altitude.

Answer 53

- Decreases with increasing altitude as the thrust available decreases due to lower air density.

Question 53

With all parameters constant, a change in mass will have the following effect on the best Rate of Climb (ROC) speed: ROC is affected by the mass, but the ROC speed is not. ROC speed increases with increasing mass. ROC speed decreases with increasing mass. ROC speed is independent of the mass.

Answer 53

ROC speed increases with increasing mass.

Question 53

With regard to an aeroplane fitted with different stages of slat- and flap-settings, choosing a lower slat-/flap-setting for take-off would result in a (1) ___ rate of climb (ROC) at a (2) ___ airspeed. (1) lower, (2) lower. (1) lower, (2) higher. (1) higher, (2) higher. (1) higher, (2) lower.

Answer 53

(1) higher, (2) higher.

Question 54

If Gross Mass is increased… VX is increased and VY decreased. VY and VX are decreased. VY and VX are not changed. VY and VX are both increased.

Answer 54

VY and VX are both increased.

Question 55

An obstacle in the flight path segment requires 2.6 % climb gradient for safe clearance. The gradient is 2.8% at 110 000 kg gross weight. With the same power settings and the sine of the angle of climb varying inversely with mass, the maximum mass at which the minimum climb gradient can be maintained is: 118 455 kg 108 430 kg 120 310 kg 102 450 kg

Answer 55

118 455 kg

Question 56

With the information given, calculate the all-engine-operating (AEO) climb gradient for a twin-engine aeroplane (assume g = 10 m/s²): Thrust per engine: 40000 lbs/engine Take-off Mass: 80000 kg Lift-to-drag ratio: 7:1 31.1% 10.8% 6.15% 20.9%

Answer 56

31.1%

Question 57

With the information given, calculate the all-engine-operating (AEO) climb gradient for a twin-engine aeroplane (assume g = 10 m/s²): Thrust per engine: 120000 N Take-off Mass: 55000 kg Lift-to-drag ratio: 8:1 5.35% 9.36% 18.1% 31.1%

Answer 57

31.1%

Question 58

Operation Four-engine Turbojet Mass 150 000 kg Lift-to-Drag ratio 14 Thrust per engine 75 000 N (all operating) g 10 m/s² The Climb Gradient (%) is: 29 1.286 7.94 12.86

Answer 58

12.86 Remember: (10 m/s²) 10+2

Question 59

An aeroplane is in a power-off glide at speed for minimum glide angle. If the pitch attitude is increased, the glide distance... remains constant. increases. decreases. increases or decreases depending on the type of aeroplane.

Answer 59

decreases.

Question 60

An aeroplane is in steady descending flight (descent angle 3°) with T = Thrust, D = Drag and W = Weight. The balance of forces acting on the aeroplane is: T - D = W cos 3° T - W cos 3° = D T - D = W sin 3° T + W sin 3° = D

Answer 60

T + W sin 3° = D

Question 61

The Max. Climb Angle in a Turbojet Aircraft is achieved at a speed corresponding to... 1.1 Vs. Max. CL/CD ratio. 1.3 Vs. Max. CL/CD² ratio.

Answer 61

Max. CL/CD ratio.

Question 62

Descending with Zero Thrust at the best Lift to Drag Ratio speed,... a tailwind will increase the ground distance. a tailwind will reduce the time in the descent. a tailwind will increase the fuel consumption. a headwind will increase the ground distance.

Answer 62

a tailwind will increase the ground distance.

Question 63

When compared to a descent with a given mass at the speed for Minimum Angle of Descent, how will a higher mass affect the Minimum Descent Angle and the corresponding speed? The Minimum Angle of descent will remain constant at the same speed. The Minimum Angle of descent will remain constant at a higher speed. The Minimum Angle of descent will decrease at the same speed. The Minimum Angle of descent will increase with a lower speed.

Answer 63

The Minimum Angle of descent will remain constant at a higher speed.

Question 64

With regard to Minimum Angle of Descent during glide, which of the following statements is correct? 1. A higher mass results in a higher Minimum Angle of Descent. 2. A higher mass allows a higher speed for the same Minimum Angle of Descent. 1 is correct, 2 is incorrect 1 is incorrect, 2 is incorrect 1 is correct, 2 is correct 1 is incorrect, 2 is correct

Answer 64

1 is incorrect, 2 is correct

Question 65

With regard to a Continuous Descent Approach (CDA) to an airport while keeping constant CAS, which of the following statements is correct? 1. An increase in headwind requires a reduction in Rate of Descent. 2. During a turn with sudden increase in headwind, thrust setting will momentarily be reduced. 1 is correct, 2 is correct 1 is correct, 2 is incorrect 1 is incorrect, 2 is correct 1 is incorrect, 2 is incorrect

Answer 65

1 is correct, 2 is correct