Aircraft Performance 445 PJ's 3, 5, & 6

3.53 Which of the following equations below expresses approximately the unaccelerated percentage climb gradient for small climb angles? Climb Gradient= (a) [(Thrust - Drag)/Mass) × 100) (b) [(Thrust + Drag)/Lift) x 100] (c) [(Thrust - Mass)/Lift) x 100] (d) [(Lift/Mass) × 1001

a, (Thrust - Drag)/mass) x 100)

3.27 Given: A three-engined jet aeroplane has 50,000 Newtons of thrust per engine and a total drag of 72,069 Newtons. The gross gradient required with one engine inoperative is 2.75%. The maximum take-off mass is: (a) 101 567 kg (b) 286 781 kg (c) 174 064 kg (d) 209 064 kg

a, 101,567 kg

6.11 Given Pressure Altitude= 18,000 ft; Ambient Temperature -31C. The density altitude is: (a) 16 812 ft (b) 19 188 ft (c) 17 280 ft (d) 18 720 ft

a, 16,812 ft

3.25 Given: TAS= 194 kt; ROC= 1000 fpm. The climb path is: (a) 3° (b) 3% (c) 5° (d) 8%

a, 3 degrees

5.5 If the TAS is 100 kt on a glide slope of 3 degrees, the rate of descent is: (a) 530 fpm (b) 300 fom (c) 250 fpm (d) 1000 fpm

a, 530 fpm

5.25 Two identical aeroplanes at different masses are descending at idle thrust. Which of the following statements correctly describes their descent characteristics? (a) At a given angle of attack, both the vertical and the forward speeds are greater for the heavier aeroplane. (b) There is no difference between the descent characteristics of the two aeroplanes. (c) At a given angle of attack the heavier aeroplane will always will always glide further than the lighter aeroplane. (d) At a given angle of attack, the lighter aeroplane will always glide further than the heavier aeroplane.

a, At a given angle of attack, both the vertical and the forward speeds are greater for the heavier aeroplane

3.21 On an ROC v speed graph, in which direction will the curve move when the flaps are extended from the retracted position? (a) Decrease speed and decrease ROC, down to the left. (b) Decrease speed and ROC constant, horizontally left. (c) Decrease speed and ROC increase, up and to the left. (d) Increase speed and decrease ROC, down and to the left.

a, Decrease speed and decrease ROC, down to the left

6.5 The operational requirements regarding scheduled performance are contained in the following document: (a) JAR-OPS 1 (b) CS 23 (c) CS 25 (d) FAR 25

a, JAR-OPS 1

3.1 absolute ceiling occurs when: (a) the achievable rate of climb is zero (b) for a jet aeroplane when the rate of climb falls to 100 ft per minute (c) at the altitude at which the rate of climb falls to 750 ft per minute (d) at the altitude at which the rate of climb falls to 300 ft per minute

a, The achievable rate of climb is zero

3.43 Which of the following speeds will give the maximum obstacle clearance during a climb? (a) The speed at which the ratio of the rate of climb and the forward speed is maximum (b) V2 + 10 kt (c) VY (d) V2

a, The speed at which the ratio of the rate of climb and the forward speed is maximum

3.13 The effect an increase of mass has on the value of Vx and Vy is: (a) VX increases and Vy increases (b) Vx increases and Vy decreases (c) Vx decreases and Vy increases (d) Vx decreases and Vy decreases.

a, Vx increases and Vy increases

3.19 An aircraft has a climb schedule of 350 KIAS/ 0.8M. If the climbing IAS is increased to 270 KIAS, the MACH limit will be reached at: (a) a lower altitude at all temperatures (b) a higher altitude at all temperatures (c) the same altitude at all temperatures (d) a higher altitude for temperatures above ISA.

a, a lower altitude at all temperatures

5.12 Which of the following combinations of characteristics will affect the glide angle? (a) configuration and angle of attack (b) mass and altitude (c) altitude and configuration (d) configuration and mass

a, configuration and angle of attack

5.1 An aircraft's descent speed schedule is 0.74 M/250 kts. During the descent from 30,000 ft to MSL the angle of attack, will; (a) decrease then remain constant (b) remain constant (c) increase then remain constant (d) decrease

a, decrease then remain constant

3.39 The greatest rate of climb at a constant mass: (a) decreases with increasing altitude because the thrust available decreases due to the decreased air density (b) increases with increasing altitude because drag decreases due to the decreased air density (c) increases with increasing altitude due to the higher TAS (d) is independent of altitude.

a, decreases with increasing altitude because the thrust available decreases due to the decreased air density

3.42 In a constant IAS climb, a headwind component increasing with altitude: (a) has no effect on the rate of climb (b) does not affect the angle of climb (c) increases the angle and rate of climb (d) decreases the angle and rate of climb.

a, has no effect on the rate of climb

3.16 The service ceiling of an aeroplane weighing 3250 lbs is 4000 m. What will the service ceiling be if the mass of the aeroplane is decreased to 3000 lbs? (a) higher (b) lower (c) unchanged (d) cannot be determined without precise calculations.

a, higher

5.6 During a glide descent at a constant Mach number, the nose-down pitch angle will: (a) increase (b) increase initially then decrease (c) remain constant (d) decrease.

a, increase

5.15 In a glide, at minimum glide angle speed, at a lower mass at the same speed (i) the rate of descent will....... (ii) the glide angle will....... (iii) the CL/CD ratio will........ (a) (i) increase; (ii) increase; (ili) decrease (b) (i) decrease; (ii) remain constant; (ili) decrease (c) (i) increase; (ii) increase; (ili) remain constant (d) (i) increase; (ii) remain constant; (ili) increase.

a, increase; increase; decrease

3.54 A constant headwind component: (a) increases the angle of the climb path (b) increases the maximum rate of climb. (c) decreases the angle of the climb path (d) increases the maximum endurance.

a, increases the angle of the climb path

3.44 The effect of a tailwind on the time to climb to a given altitude is: (a) none (b) increases (c) decreases (d) depends on the aeroplane type.

a, none

5.4 During a descent at a constant Mach number and TAT (total air temperature): (a) the IAS increases (b) the IAS decreases (c) the IAS remains constant (d) the IAS increases but only below 20 000 ft.

a, the IAS increases

6.3 Pressure altitude is: (a) the altimeter indication when 1013.2 hPa is set on the sub-scale (b) the altimeter indication when QNE is set on the sub-scale (c) the altimeter indication when QFE is set on the sub-scale (d) the altitude above mean sea level.

a, the altimeter indication when 1013.2 hPa is set on the sub-scale

3.4 Absolute ceiling is defined as: (a) the altitude at which the theoretical rate of climb is zero (b) the altitude at which the rate of climb is 100 fom (c) the altitude at which the gradient of climb is 5 % (d) the altitude at which MO and MMO are equal.

a, the altitude at which the theoretical rate of climb is zero

3.10 For a given power setting in the climb, if the speed is increased: (a) the rate of climb will increase if the speed is below Vy (b) the gradient of climb will increase if the speed is above Vx (c) the rate of climb will decrease if the speed is below Vy (d) the gradient of climb will decrease if the speed is below Vx.

a, the rate of climb will increase if the speed is below Vy

6.8 Given: FL380; Ambient temperature -45C. The ISA deviation is: (a) -11.5°C (b) +11.5°C (c) +16.0 °C (d) -16.0 °C

b, + 11.5 degrees celsius

6.12 Given: FL 360; Ambient temperature -45C. The ISA deviation is: (a) -12.0 °C (b) +12.0 °C (c) +16.0 °C d) -160°C

b, + 12.0 degrees celsius

3.8 Given: The climb gradient of an aeroplane is 10% and an obstruction 900 m high is positioned 10,000 m from the end of the TODR. By what vertical interval will the aircraft clear the obstruction if it is at a height of 15 m at the end of the TODR? (a) 85 m (b) 115 m (c) 100 m (d) It will impact the obstacle.

b, 115 m

6.14 Given: Indicated Altitude 28,000 ft; Ambient Temperature -31C. The true altitude is: (a) 28 430 A (b) 29 120 ft (C) 28 720 ft (d) 27 570 ft

b, 29,120 ft

3.35 Given: Climb gradient= 3.3%; TAS 100 kt; Still-air. The ROC is approximately: (a) 33.0 m/s (b) 330 fpm (c) 3 300 fpm (d) 3.30 m/s

b, 330 fpm

6.7 The factorization of the reported along track wind component required by JAR-OPS 1 when making take-off, climb obstacle clearance or landing performance calculations is: (a) 50 % of any headwind and any tailwind (b) 50 % of any headwind and 150 % of any tailwind (c) 150% of any headwind and 150 % of any tailwind (d) 100 % of any headwind and 150 % of any tailwind.

b, 50% of any headwind and 150% of any tailwind

3.37 In a constant Mach number climb: (a) high speed buffet will occur (b) CL increases (c) To the increased TAS may cause structural damage (d) the IAS remains constant.

b, CL increases

5.24 In a steady descent (descent angle GAMMA) the equilibrium of the forces is given by the formula: (a) T+D= -M sin GAMMA (b) T+ M sin GAMMA = D (c) T - M sin GAMMA = D (d) T -D= M sin GAMMA

b, T + M sin GAMMA = D

5.22 Which of the following statements for a glide descent at the maximum lift to drag ratio speed is correct? (a) The mass of the aeroplane does not have any effect on the sped of descent. (b) The higher the gross mass the greater is the speed for descent. (c) The higher the gross mass the lower is the speed of descent. (d) The higher the average temperature (OAT) the lower is the speed of descent.

b, The higher the gross mass the greater is the speed for descent

5.2 During a constant Mach descent, which one of the following speeds may be exceeded? (a) MMO (b) VMO (c) VD (d) VNE

b, VMO

3.9 At a constant mass, the effect that an increase of altitude has on the value of Vx and Vy is: (a) Vx increases and Vy increases (b) Vx constant and Vy decreases (c) Vx decreases and Vy increases (d) Vx constant and V y constant.

b, Vx constant and Vy decreases

3.32 The maximum angle of climb speed for a jet-engined aeroplane is approximately: (a) 1.1 VS (b) highest CL/CD ratio speed (c) highest CL/CD^2 ratio speed (d) 1.2 VS

b, highest CL/CD ratio speed

5.7 In a glide descent at the optimum speed, the effect that increasing the nose-down pitch angle has on the glide distance is that: (a) it increases (b) it decreases (c) it has no effect (d) it increases but only in a headwind.

b, it decreases

5.8 The effect that increased mass has on a glide descent is: (a) it increases the vertical speed (b) it increases the vertical and the horizontal speeds (c) it increases the distance travelled (d) it decreases the distance travelled.

b, it increases the vertical and the horizontal speeds

3.56 Vx and Vy with take-off flaps will be: (a) higher than that for the clean configuration (b) lower than that for the clean configuration (c) same as that for the clean configuration (d) changed so that Vx increases and Vy decreases compared with the clean configuration.

b, lower than that for the clean configuration

6.1 The scheduled performance target probability factor is: (a) extremely remote -10-0 (b) remote -10^-6 (c) reasonable probable - 10-4 (d) trequent - 10-2

b, remote - 10^-6

3.18 An aircraft is climbing in a standard atmosphere above the tropopause at a constant Mach number: (a) the IAS and the TAS remain constant (b) the IAS decreases and the TAS remains constant (c) the IAS decreases and the TAS decreases (d) the IAS remains constant and the TAS increases

b, the IAS decreases and the TAS remains constant

5.3 To maintain a constant Mach number during a glide descent: (a) the angle of attack must be increased (b) the angle of attack must be decreased (c) the angle of attack must remain constant (d) the angle of attack must be increased on passing 20 000 ft.

b, the angle of attack must be decreased

3.49 In an unaccelerated climb: (a) thrust equals drag plus the uphill componenet of the gross mass in the flight path direction (b) thrust equals drag plus the downhill component of the gross mass in the flight path direction (c) lift is greater than the gross mass (d) lift equals mass plus the vertical component of the drag.

b, thrust equals drag plus the downhill component of the gross mass in the flight path direction

3.57 The maximum rate of climb at the absolute ceiling is: (a) 500 fpm (b) 125 fpm (c) 0 fom (d) 100 fpm.

c, 0 fpm

3.23 Given: Still air climb gradient 4% TAS 400 kt; Wind component 50 kt tail; The ground distance travelled in a climb from 8000 ft to 32,000 ft is: (a) 99 nm (b) 88 nm (c) 111 nm (d) 123 nm

c, 111 nm

3.26 Given: Climb Gradient= 2.8%; Climb Mass = 110,000 kg; Required Climb Gradient = 2.6%. The maximum climb mass to achieve the required gradient is: (a) 121 300 kg (b) 106 425 kg (c) 118 462 kg (d) 102 150 kg

c, 118,462 kg

6.10 Given: Indicated Altitude 18,000 ft; Ambient Temperature -31C. The true altitude is: (a) 18 720 ft (b) 18 360 ft (c) 17 280 ft (d) 17 640 ft

c, 17,280 ft

6.13 Given: Aerodrome Elevation 3200 ft; QNH 1003 hPa. The aerodrome pressure altitude is: (a) 3370 ft (b) 2870 ft (c) 3470 ft (d) 2900 ft

c, 3470 ft

5.21 Which of the following statements for a glide descent at the maximum lift to drag ratio speed is correct? (a) A tailwind component increases the fuel and the time to descend. (b) A tailwind component decreases the ground distance travelled. (c) A tailwind component increases the ground distance travelled. (d) A headwind component increases the ground distance travelled.

c, A tailwind component increases the ground distance travelled

3.58 Climbing at a constant Mach number: (a) the IAS is constant (b) the 1.3 g altitude is exceeded (c) CL increases (d) the TAS increases.

c, CL increases

6.6 The minimum acceptable performance requirements for a Class 'A' aeroplane are contained in the following document: (a) JAR-OPS 1 (b) CS 23 (c) CS 25 (d) FAR 25

c, CS 25

3.22 After take-off, an aircraft just clears a screen height of 50ft and climbs with a 5% gradient. There is an obstacle 1600 m from the end of the TODR which projects 150 m above the runway level. By how much does the aeroplane clear the obstacle? (a) 152.4 ft (b) 102.4 ft (c) It does not clear the obstacle. (d) 50 ft

c, It does not clear the obstacle

3.33 How does the value of Vx vary with wind component? (a) It increases in a headwind. (b) It decreases in a tailwind. (c) It is not affected by the wind component. (d) It decreases in a headwind.

c, It is not affected by the wind component

3.31 In a constant IAS climb, which limiting operational speed is most likely to be exceeded? (a) VMC (b) Mach limit for the Mach trim system (c) MMO (d) VS

c, MMO

5.11 Two identical aeroplanes are descending at idle thrust and the optimum angle of attack but at different masses. Which of the following statements is true? (a) The heavier aeroplane will glide further. (b) The lighter aeroplane will glide further. o The vertical and forward speeds of the heavier acroplane will greater. (d) There is no difference in their glide characteristics.

c, The vertical and forward speeds of the heavier aeroplane will greater

3.40 At the same altitude a higher gross mass decreases the gradient and rate of climb, whereas: (a) Vy and Vx are unaffected (b) VY and VX are decreased (c) Vy and Vx are increased (d) Vx is decreased and Vy is decreased.

c, Vy and Vx are increased

3.59 A higher altitude at a constant mass and Mach number requires: (a) a lower CD (b) a lower angle of attack (c) a higher angle of attack (d) a lower CL.

c, a higher angle of attack

5.14 In a glide descent at the optimum gliding speed, if the pilot increases the pitch attitude the glide distance will: (a) remain the same (b) may increase or decrease dependent on aeroplane type (c) decrease (d) increase.

c, decrease

3.15 The effect a headwind will have on a climb to a specified altitude, compared with still-air, is to: (a) increase the climb time (b) decrease the climb time (c) decrease the ground distance travelled (d) decrease the fuel used.

c, decrease the ground distance travelled

3.46 How do (i) the maximum angle of climb and (ii) the maximum rate of climb vary with increasing altitude? (a) (i) increase (ii) decrease (b) (i) decrease (ii) increase (c) (i) decrease (ii) decrease (d) (i) increase (ii) increase

c, decrease, decrease

3.50 A jet aeroplane is climbing at a constant IAS and maximum climb thrust, how will the (i) climb angle (ii) pitch angle change? (a) (i) remain constant (ii) decrease (b) (i) remain constant (ii) increase (c) (i) decrease (11) decrease (d) (i) decrease (ii) remain constant.

c, decrease, decrease

3.41 A higher ambient temperature: (a) increases the angle of climb but decreases the rate of climb (b) does not affect climb performance (c) decreases the angle of climb and the rate of climb (d) decreases the angle of climb but increases the rate of climb.

c, decreases the angle of climb and the rate of climb

5.9 Which of the following speeds for a jet aeroplane are virtually identical? (a) maximum range, minimum drag, minimum glide angle (b) maximum climb angle, minimum glide angle, maximum range (c) holding, maximum climb angle, minimum glide angle (d) maximum drag, maximum endurance, maximum climb angle.

c, holding, maximum climb angle, minimum glide angle

5.13 During a constant Mach number descent, the margin to the low-speed buffet will: (a) increase, because the lift coefficient increases (b) decrease, because the lift coefficient decreases (c) increase, because the lift coefficient decreases (d) decrease, because the lift coefficient increases.

c, increase, because the lift coefficient decreases

5.16 In a constant Mach number descent followed by a constant IAS descent, the descent angle before the crossover altitude (i)...... and after the crossover altitude (ii)...... (a) (i) will be constant (ii) decreases (b) (i) decreases (ii) will be constant (c) (i) increases (ii) will be constant (d) (i) increases (ii) decreases.

c, increases, will be constant

3.48 If the climb speed schedule is changed from 280/0.74 to 290/0.74 the new crossover altitude is: (a) unchanged (b) only affected by the aeroplane gross mass (c) lower (d) higher

c, lower

6.2 Gross performance is: (a) measured performance diminished by five standard deviations (b) net performance adjusted by safety factorization (c) measured performance adjusted so that all aeroplanes of the type have a 50 % chance of exceeding it (d) measured performance diminished to allow for manoeuvring, piloting technique and tempo. rary below average performance

c, measured performance adjusted so that all aeroplanes of the type have a 50% chance of exceeding it

3.20 An aircraft is climbing at a constant IAS, below the Mach limit. As altitude increases drag: (a) decreases because density decreases (b) increases because TAS increases (c) remains constant but the climb gradient decreases (d) remains constant and the climb gradient remains constant.

c, remains constant but the climb gradient decreases

5.23 The lift coefficient decreases during a glide descent at a constant Mach number because: (a) the TAS decreases (b) the glide angle decreases (c) the IAS increases (d) the aircraft mass decreases.

c, the IAS increases

3.2 The conditions that determine the aerodynamic ceiling are: (a) when thrust available is equal to the thrust required (b) when the power available is equal to the power required (c) when the high-speed buffet and the low-speed buffet are equal (d) all three of the above

c, when the high-speed buffet and the low-speed buffet are equal

6.4 The minimum range of runway slopes required to be included in the Flight Manual for a Class 'A' aeroplane is: (a) 11% to -2% (b) 1 % to - 1% (c) +1% to -2 % (d) +2% to -2%.

d, +2% to -2%

6.15 Given Pressure Altitude 28,000 ft; Ambient Temperature -31C. The density altitude is: (a) 26 812 ft (b) 29 120 ft (c) 28 720 ft (d) 29 188 ft

d, 29,188 ft

3.5 An aircraft has a thrust: mass ratio of 1:4 at take-off. If the lift: drag ratio in the climb is 12:1 the climb gradient will be: (a) 3.0% (b) 8.3% (c) 33.0% (d) 16.7%.

d, 3.0%

6.9 Given: Aerodrome Elevation 4200 ft; QNH 1023 hPa. The aerodrome pressure altitude is: (a) 4470 1t (b) 3830 ft (c) 4370 ft (d) 3930 ft

d, 3930 ft

3.30 Given: TAS= 194 kt; ROC= 1000 fpm. The climb gradient is: (a) 3 degrees (b) 3% (c) 5 degrees (d) 5%

d, 5 %

3.24 Given: A four-engined jet aeroplane weighing 37,500 kg has a lift: drag ratio of 14:1 and a total thrust of 75,000 Newtons. g= 10m/s/s. The climb gradient is: (a) 1.286 % (b) 27% (c) 7.86% (d) 12.86 %

d, 7.86 %

3.29 For a piston/propeller aeroplane if VIMD= 125 kt and the holding speed= 95 kt. What speed is Vy? (a) less than 95 kt (b) between 95 kt and 125 kt (c) 125 kt (d) 95 kt

d, 95 kt

5.10 In a constant Mach number descent, which of the following speeds is likely to be exceeded first? (a) VNE (b) high speed buffet limit (c) MMO (d) Maximum Operating Speed

d, Maximum Operating Speed

3.12 The effect an increase of mass has on the values of the ROC and the climb speeds is: (a) ROC decreases and the climb speeds remain the same (b) ROC is unchanged and the climb speeds are unchanged (c) ROC increases and the climb speeds increase (d) ROC decreases and the climb speeds increase

d, ROC decreases and the climb speeds increase

3.11 The wind effective climb gradient is equal to: (a) ROC in fpm ÷ TAS in kt (b) ROC in {pm ÷ ground distance in nm (c) TAS in kt. ÷ horizontal distance in nm (d) ROC in fpm. ÷ Groundspeed in kt.

d, ROC in fpm. / groundspeed in kt.

3.36 The speed to fly to obtain the maximum obstacle clearance in the climb is: (a) 1.2 Vs (b) VY (c) V2 (d) Vx

d, Vx

3.6 What is the effect of extending flap on the value of Vx and Vy? (a) Vx increases and Vy increases (b) Vx increases and Vy decreases (c) Vx decreases and Vy increases (d) Vx decreases and Vy decreases.

d, Vx decreases and Vy decreases

3.38 While in a positive climb: (a) Vx is sometimes greater and sometimes less than Vy (b) Vx is always greater than Vy (c) Vr is always greater than VMO (d) Vx is always less than Vy.

d, Vx is always less than Vy

5.17 Which of the following will increase the glide distance? (a) increased aeroplane mass (b) decreased aeroplane mass (c) a headwind (d) a tailwind

d, a tailwind

3.3 The absolute ceiling is determined by: (a) aircraft mass, altitude and speed (b) aircraft mass, speed and CG position (c) aircraft speed, altitude and CG position (d) aircraft mass and CG position

d, aircraft mass and CG position

3.47 On a twin-engined piston aeroplane with variable pitch propellers, for a given mass and altitude, VIMD is 125 kt and the holding speed (minimum fuel flow) is 95 kt. The maximum rate of climb speed is: (a) less than 95 kt (b) between 95 kt and 125 kt (c) at 125 kt (d) at 95 kt

d, at 95 kt

3.17 An aircraft is climbing at a constant power setting and a speed of Vx. If the speed is reduced and the power setting maintained the climb gradient will (i)....... In addition, the rate of climb will (ii)..... (a) (i) decrease; (ii) increase (b) (i) increase; (ii) increase (c) (i) increase; (li) decrease (d) (i) decrease; (ii) decrease.

d, decrease; decrease

5.18 Which of the following factors will increase the glide time? (a) increased aeroplane mass (b) a headwind (c) a tailwind (d) decreased aeroplane mass

d, decreased aeroplane mass

3.52 How does the thrust of a fixed pitch propeller vary during take-off run? the thrust: (a) increases slightly while the aeroplane builds up speed (b) only varies with mass changes (c) is constant during the take-off and climb (d) decreases slightly while the aeroplane builds up speed.

d, decreases slightly while the aeroplane builds up speed

3.60 Acceleration in a climb with a constant power setting: (a) improves the climb gradient if the airspeed is below Vx (b) improves the rate of climb if the airspeed is below Vy (c) decreases the rate of climb and increases the angle of climb (d) decreases the rate of climb and the angle of climb.

d, decreases the rate of climb and the angle of climb

3.34 Increased mass will cause the climb performance to: (a) improve (b) be unchanged (c) be unchanged if the short-field technique is used (d) degrade.

d, degrade

3.28 The wind effective climb gradient is defined as the ratio of: (a) TAS to ROC (b) ROC to TAS (c) increase of altitude to horizontal air distance as a percentage (d) increase of altitude to horizontal ground distance as a percentage.

d, increase of altitude to horizontal ground distance as a percentage

3.55 The maximum operating altitude for an aeroplane with a pressurized cabin: (a) is dependent on the aerodynamic ceiling (b) is dependent on the OAT (c) is only certified for four-engined aeroplanes (d) is the highest pressure altitude certified for normal operation

d, is the highest pressure altitude certified for normal operation

3.45 Apart from lift, the forces that determine the angle of climb are: (a) mass and drag only (b) thrust and drag only (c) mass and thrust only (d) mass, drag and thrust.

d, mass, drag and thrust

3.14 The speed of Vy is flown to obtain: (a) maximum range for a piston-engined aeroplane (b) maximum endurance for a piston-engined aeroplane (c) maximum gradient of climb (d) maximum rate of climb.

d, maximum rate of climb

3.7 What is the effect of an increased flap setting on the gradient and rate of climb? (a) the gradient of climb increases and the rate of climb increases (b) the gradient of climb increases and the rate of climb decreases (c) the gradient of climb decreases and the rate of climb increases. (d) the gradient of climb decreases and the rate of climb decreases.

d, the gradient of climb decreases and the rate of climb decreases

5.19 In a glide descent, to fly for the maximum endurance the speed should be that for: (a) maximum lift (b) minimum drag (c) critical Mach number (d) the minimum angle of descent.

d, the minimum angle of descent

5.20 What effect does increased aeroplane mass have on a glide descent? a) none (b) glide angle decreases (c) the lift/drag ratio decreases (d) the speed for the best angle of descent increases.

d, the speed for the best angle of descent increases

3.51 Which of the following provides the maximum obstacle clearance during a climb? (a) 1.2 VS (b) the speed for the maximum rate of climb (c) the speed at which the flaps may be selected UP one notch (d) the speed for the maximum climb angle VX.

d, the speed for the maximum climb angle Vx