Arunaksha Nandy (Technical General questions)

AIRCRAFT TECHNICAL AND GENERAL QUESTIONS (Part 1)


AIRCRAFT TECHNICAL GENERAL QUESTIONS (Part 1)

TECHNICAL GENERAL QUESTIONS

 

  1. Using counter-rotation propellers has the effect of:
  • Cancelling out the gyroscopic and torque effect.
  • Cancelling out the gyroscopic effect and increasing the torque.
  • Increasing the gyroscopic effect and the torque.
  1. With an increase in temperature, the service ceiling would:
  • Increase
  • Decrease
  • Remain unaffected.
  1. In the choke tube area of the fuel nozzle an area of:
  • High pressure is found.
  • Low pressure is found.
  • There is no difference in pressure.
  1. As air density decreases, density altitude will:
  • Increase
  • Decrease
  • Remain unaffected.
  1. If the atmospheric pressure and temperature remain the same, how would an increase in humidity affect take-off performance?
  • Shorter take-off distance, the air is less dense.
  • Longer take-off distance, the air is dense.
  • Longer take-off distance, the air is less dense.
  1. Which airspeed would a pilot be unable to identify by the colour coding of an ASI?
  • The maximum flap operating speed.
  • The maximum landing gear extended speed.
  • The never exceed speed.
  1. If the landing gear on an aircraft moves forward during retraction the:
  • Total moments will decrease.
  • Total moments will remain the same.
  • Total moments will increase.

8.    The tendency of an aircraft to develop forces which restore it to its original condition, when disturbed from a condition of steady flight, is known as:

  • Controllability
  • Manoeuvrability
  • Stability

 

  1. When carburettor heating is used, it:
  • Riches the mixture.
  • Leans the mixture.
  • Puts more air into the mixture.
  1. Differential ailerons are installed to:
  • Improve lateral stability.
  • Prevent spiral instability.
  • Reduce adverse aileron yaw.
  1. The “blow-out” process on turbine engines is:
  • To get rid of excess fuel after an aborted start.
  • When the turbine section explodes after overspeeding.
  • Timing the run-down to check for structural failure.
  1. Why is the angle of attack increased during a turn?
  • To compensate for increased aeroplane drag.
  • To compensate for the reduced horizontal lift component.
  • To compensate for the reduced vertical lift component.
  1. Where does a magneto get its current from?
  • Battery
  • E.M.F. (generators).
  • Magnets
  1. Aircraft A has a span of 50 ft and a chord of 5 ft.

Aircraft B has a span of 80 ft and a chord of 10 ft.

Aircraft C has a span of 48 ft and a chord of 4 ft.

Which aircraft has the highest aspect ratio and which aircraft has the lowest aspect ratio?

  • A & B.
  • B & C.
  • C & B.
  1. Refer to question 14. Which of the aircraft mentioned has the highest stalling angle?
  • A
  • B
  • C

 

  1. A tail-dragger aircraft with a propeller turning clockwise as viewed from the cockpit, tends to turn the aircraft:
  • Left around the vertical axis and left around the longitudinal axis.
  • Right around the vertical axis and left around the longitudinal axis.
  • Left around the vertical axis and right around the longitudinal axis.
  1. At sea level, the Manifold gauge will read?
  • 29.92”.
  • 1013.25 hPa.
  • Static pressure.
  1. The correct way to increase power on piston prop is:
  • Throttle, RPM, Mixture.
  • RPM, Mixture, Throttle.
  • Mixture, RPM, Throttle.
  1. When the weight of the aircraft is increased the stalling speed will:
  • Increase
  • Decrease
  • Remain the same.
  1. What power supply is used to supply an aircraft instrument that operates on alternating current?
  • An alternator that is mechanically driven by the engine.
  • An inverter.
  • A transformer.
  1. A crankshaft with counter balance can be damaged by:
  • Carburettor icing.
  • Closing and opening the throttle in rapid succession.
  • Operating the engine with too rich a mixture.
  1. When flying for endurance an aircraft must be flown at:
  • Minimum power speed.
  • Full throttle height.
  • Minimum drag speed.
  1. What is the reason for the twist in the propeller?
  • To keep the propeller flying at the most efficient angle at all sections.
  • To cancel out the effect of the high speed near the tips.
  • Design requirement to keep the centrifugal twist axis in the centre.
  1. Electrical power of a battery is measured by:
  • Amp/hr.
  • The number of cells in the battery.
  • The voltage.
  1. Pneumatic boots that are used for de-icing are:
  • Fitted on the leading edge of the wing.
  • Fitted around the propeller intakes.
  • Fitted on the leading edge of the wing and stabilisers.
  1. The use of fuel with an incorrect octane rating may lead to:
  • Detonation
  • Pre-ignition.
  • A higher manifold pressure.
  1. Propeller efficiency is defined as:
  • The ratio of shaft horsepower to brake horsepower.
  • The ratio of brake horsepower to thrust horsepower.
  • The ratio of thrust horsepower to brake horsepower.
  1. When the aircraft exhaust smoke is blue, it means the aircraft:
  • Has a too rich a mixture.
  • Is burning oil.
  • Has incorrect timing.
  1. Carburettor icing occurs at:
  • The engine air intake.
  • The venturi, butterfly valve and manifold.
  • The intake manifold only.
  1. What is the purpose of the breather pipe on an engine?
  • To blow excess oil.
  • To vent excess temperature.
  • To relieve excess sump pressure.
  1. What is the purpose of the reverse current cut-out switch in the electrical system?
  • To prevent the battery from losing its charge by driving the generator.
  • To switch off the generator.
  • To prevent the battery from being overcharge.
  1. For what purpose are CBs (circuit breakers) installed in aircraft?
  • To switch systems on and off.
  • To prevent overloading of a system.
  • To see how much power a system requires.
  1. The SG of AVGAS is 0.7. How much does 100 Gallonss of fuel weigh?
  • 700 lbs.
  • 70 lbs.
  • 7 000 lbs.
  1. The load capacity of a battery is measured in:
  • Volts
  • Amps/hr.
  • Ohms
  1. Which generator supplies more power?
  • AC generator.
  • DC generator.
  • AC/DC generator with TR unit.
  1. Carb icing on an engine a variable pitch propeller can be noticed by:
  • Drop in RPM.
  • Drop in Manifold Pressure.
  • Drop in RPM and Manifold Pressure.
  1. On an EGT gauge (fixed pitch propeller) the mixture is set at lean when:
  • The temperature and RPM peaks.
  • The temperature and RPM have peaked & then 2 units richer.
  • The temperature only peaks.
  1. A suction pump supplies vacuum to:
  • ASI, T&S, DI.
  • ASI, Turn indicator and DI.
  • AH, DI and Turn indicator.
  1. On the power available/required versus TAS graph, the lowest value would be:
  • Minimum drag.
  • Speed for endurance.
  • Speed for range.
  1. The absolute ceiling is:
  • The level beyond which the aircraft cannot climb.
  • The level at which the aircraft can only climb at 100 ft/min.
  • The maximum level aircraft can attain full throttle.
  1. At the absolute ceiling the:
  • Minimum speed is less than the maximum speed.
  • Minimum speed is more than the maximum speed.
  • Minimum speed is equal to the maximum speed.
  1. Too low an octane rating (anti-knock value) can cause:
  • Pre-ignition.
  • Detonation
  • overheating
  1. In level flight the following affects the balance of forces:
  • Mass of the aircraft.
  • Height of the aircraft.
  • Fuel burn rate.
  1. On a turbocharged aircraft the supercharger is powered by:
  • The engine.
  • An electrical motor.
  • Exhaust gases.
  1. With reference to aircraft fitted with constant speed propellers, when the MP is reduced:
  • The blade angle decreases.
  • The blade angle increases.
  • The blade angle remains the same.
  1. A battery rated for 40 amps/hr it will operate for:
  • At 40 amps for 10 hours.
  • At 10 amps for 40 hours.
  • At 4 amps for 10 hours.
  1. Conditions favourable for the formation of icing:
  • High temperature and low humidity.
  • High temperature and high humidity.
  • High humidity and low temperature.
  1. Choose the correct statement:
  • An increase in temperature will cause an increase in density.
  • An increase in humidity will cause a decrease in density.
  • An increase in humidity will cause an increase in density.
  1. Density is measured in:
  • Kgs/cu metre.
  • Pounds per square metre.
  • Millibars
  1. The main load carrying part of the wing structure is:
  • The leading edge.
  • The spar.
  • The rib.
  1. The strength of the wing structure will have to be greater:
  • With large variations of the position of the centre of pressure.
  • The centre of pressure has no effect on wngh strength.
  • With small movements of the centre of pressure.
  1. A twenty-four volt lead acid battery would have:
  • Six cells.
  • Twelve cells.
  • Twenty-four cells.
  1. A twenty-four volt Nicad battery would probably have:
  • Twelve cells.
  • Twenty-four cells.
  • Nineteen cells.
  1. Combustion in a gas turbine engine occurs at:
  • Constant volume.
  • Constant pressure.
  • Constant velocity.
  1. The velocity of the gases through the turbine can be very high:
  • Because of the high temperature and speed of sound.
  • Because they are supersonic.
  • Because of the speed of sound being low.
  1. In relation to a generator, an alternator will:
  • Provide less electrical power.
  • Provide more power at lower RPM.
  • Weigh more and be bigger.
  1. An aircraft magneto depends on the following to generate electrical power.
  • The battery.
  • The generator.
  • Magnets
  1. An oleo leg relies on the following for its operation:
  • Torque link and shimmy damper.
  • Rubber blocks or bunjees.
  • Oil and air.
  1. Absorption of water into aviation fuel is more likely:
  • With cold fuel.
  • In hot fuel.
  • The temperature of the fuel has no effect.
  1. To eliminate the risk of fire when refuelling:
  • You should use plastic containers.
  • Bond the aircraft to the fuel nozzle.
  • Have an earth lead between ground, fuel truck, fuel nozzle and the aircraft.
  1. Operation of the mixture control to the lean position controls:
  • The amount of fuel entering the inlet manifold is reduced.
  • The amount of air entering the inlet manifold is increased.
  • The amount of air entering the inlet manifold is reduced.
  1. A breakage or disconnection of the magneto earth wire will have the effect of:
  • Stopping the engine.
  • Causing the engine to run roughly.
  • Make it impossible to stop the engine by switching off ignition.
  1. An ignition system in which the spark can be lethal is used on:
  • Piston engines and turbine engines.
  • Turbine engines only.
  • Piston engines only.
  1. With a fixed pitch propeller during climb after take-off, what should be your actions if you suspect detonation is occurring:
  • Increase rate of climb.
  • Reduce power.
  • Reduce speed.
  1. To obtain best efficiency and effective fuel consumption with a constant speed propeller the best setting would be:
  • Low RPM (high pitch) when cruising.
  • High RPM (coarse pitch) for take-off.
  • Low RPM (fine pitch) for take-off.
  1. When establishing climb power after take-off the sequence should be:
  • Throttle, Mixture, RPM.
  • Throttle, RPM, Mixture.
  • Mixture, RPM, Throttle.
  1. Entering a climb from cruise flight the sequence should be:
  • Throttle, RPM, Mixture.
  • RPM, Throttle, Mixture.
  • Mixture, RPM, Throttle.
  1. If the cylinder head temperature and oil temperature are usually high, the probable causes would be:
  • Using fuel of too low an octane value.
  • Using fuel of too high an octane rating.
  • Using too rich a mixture.
  1. After about 20 minutes flight with full tanks the engine stops but restarts after selection of another tank:
  • The possible cause was a blocked fuel tank vent.
  • Detonation
  • Pre-ignition.
  1. During operation of a reciprocating engine the piston is travelling up:
  • During the induction stroke.
  • During the power stroke.
  • During the exhaust stroke.
  1. In a piston engine ignition occurs during:
  • The power stroke.
  • The compression stroke.
  • The exhaust stroke.
  1. Valve overlap occurs between:
  • The induction stroke and the power stroke.
  • The compression stroke and the power stroke.
  • The exhaust stroke and induction stroke.
  1. High pressure oil is required in a piston engine:
  • For lubricating the accessory gearbox.
  • For lubricating the cylinder walls.
  • For lubricating the big end and main bearings.
  1. Which oil pump has greater capacity?
  • The Scavenge pump.
  • The Pressure pump.
  • The Scavenge and Pressure pumps must have the same capacity.
  1. The flow of fuel from the tank to the carburettor is controlled by:
  • The float and diffuser.
  • The needle valve and float.
  • The accelerate pump.
  1. Mass balance on an aileron is used:
  • To assist the pilot in moving the controls.
  • To eliminate flutter.
  • To prevent aileron drag.
  1. Aileron reversal is most likely to occur:
  • At very low speeds.
  • At large angles of attack.
  • At very high speeds.
  1. The speed at which full deflection of the flight controls can be made is:
  • Va
  • Vmd
  • Vso
  1. In a pressurised aircraft you are cruising at Flight Level 290 and are at Maximum Differential. You wish to climb to Flight Level 330. You must:
  • Decrease the cabin altitude by at least 4 000 ft.
  • Increase the cabin altitude by at least 4 000 ft.
  • Increase the cabin altitude.
  1. The type of reciprocating aero-engine that would use a wet sump would be:
  • A horizontally opposed engine.
  • A radial engine.
  • An inverted in-line engine.
  1. The part of the valve gear which absorbs the wear from the cam is:
  • The tappet.
  • The push rod.
  • The rocker arm.
  1. In a piston engine the spark would occur:
  • About 20° before TDC.
  • About 20° after TDC.
  • 20° after BDC.
  1. To avoid wake turbulence when taking off behind a heavy aircraft it is best to:
  • Lift off before his rotate point and stay upwind of his flight path.
  • Lift off before his lift off point and stay downwind of his flight path.
  • Lift off after his lift off point and stay below his flight path.
  1. A loss of power when opening the throttle from idle to 1 500 RPM would be prevented by:
  • The enrichment jet.
  • The main jet.
  • A rich idling mixture.
  1. Comparing a carburettor engine to a fuel injection engine:
  • Only the fuel injection engine is affected by impact icing.
  • Both are affected by impact icing.
  • Only the injection engine is affected by fuel evaporation icing.
  1. Aircraft ignition systems have the following characteristics:
  • The HT system requires only a light harness.
  • The LT system uses a light harness and a transformer coil.
  • The LT system requires suppressors and is more likely to cause radio interference.
  1. The jet engine compressor which provides the biggest frontal area is:
  • The axial flow.
  • An axial flow first stage and a centrifugal second stage.
  • A centrifugal first stage and an axial flow second stage.
  1. When a jet engine starts normally but fails to accelerate above 30% RPM it is:
  • A hung start.
  • A hot start.
  • A wet start.
  1. The most suitable property for a metal used to construct fairings would be:
  • Its toughness.
  • Its malleability.
  • Its brittleness.
  1. The lubricating system of a piston engine normally uses the following type of pump:
  • A diaphragm type pump.
  • A vane of pump.
  • A gear type of pump.
  1. The hydraulic service usually provided by the accumulator is:
  • Emergency brakes.
  • Emergency gear operation.
  • Emergency flap operation.
  1. The unit which is usually used in a hydraulic system to operate the various services is called:
  • A hydraulic jack.
  • An accumulator.
  • A reservoir.
  1. The best way to determine the pre-charge pressure in an hydraulic accumulator is to operate the following service until the pressure drops:
  • The toe brakes.
  • The undercarriage.
  • The flaps.
  1. When operating the wheel brake system when stopping distance is important, the best way to use the brakes would be:
  • Wait until the speed has dropped to below 100 kts and then use maximum braking.
  • Pump the brakes to allow cooling periods.
  • Use maximum braking as soon as possible after touch down.
  1. The most modern fire detection system uses:
  • A bi-metallic type switch.
  • A fire wire or live wire system.
  • A thermo-couple warning system.
  1. Fires originating in electrically powered equipment are classified as:
  • Class A fires.
  • Class B fires.
  • Class C fires.
  1. The main longitudinal member in a Truss type of fuselage construction would be:
  • A stringer.
  • A longeron.
  • A former.
  1. Manual reversion is possible on:
  • A hydraulically assisted control system.
  • A hydraulically operated control system.
  • A cable operated control system.
  1. In a modern automatic pilot system if one of the modes were inoperative, the pilot would be prevented from engaging by:
  • The rate-rate system.
  • The manual reversion system.
  • The interlock system.
  1. During flight, if a change is made in pitch attitude, an aircraft will rotate around its:
  • Centre of pressure.
  • Centre of lift.
  • Centre of gravity.

TECHNICAL GENERAL QUESTIONS

  1. During a change in pitch attitude, an aircraft will rotate around its:
  • Gravity and longitudinal axis.
  • Pressure and lateral axis.
  • Gravity and lateral axis.
  1. Rotation about the lateral axis is known as:
  • Yawing and is controlled with the rudder.
  • Rolling and is controlled with the ailerons.
  • Pitching and is controlled with the elevator.
  1. During a change in bank, an aircraft will rotate around its:
  • Centre of gravity and longitudinal axis.
  • Centre of gravity and lateral axis.
  • Centre of pressure and longitudinal axis.
  1. Rotation about the longitudinal axis is known as:
  • Yawing and is controlled with the rudder.
  • Rolling and is controlled with the ailerons.
  • Rolling and is controlled with the rudder.
  1. The three axis of an aircraft intersect at the:
  • Centre of pressure.
  • Centre of gravity.
  • Midpoint of the datum line.
  1. Aspect ratio of the wing is defined as:
  • Wingspan to the wingroot.
  • Square of the chord to the wingspan
  • Wingspan to the mean aerodynamic chord.
  1. The angle between the chord line of a wing and the longitudinal axis of the aircraft is known as the angle of:
  • Dihedral
  • Incidence
  • Attack
  1. The acute angle between the chord of an airfoil and its direction of motion relative to the air is known as:
  • Dihedral angle.
  • Angle of attack.
  • Angle of incidence.
  1. The angle between the chord line of an airfoil and the relative airflow is known as the angle of:
  • Attack
  • Incidence
  • Longitudinal dihedral.
  1. Lift on wing is most properly defined as the:
  • Force produced perpendicular to the longitudinal axis.
  • Reduced pressure resulting from a smooth flow of air over a curved surface and acting perpendicular to the mean surface.
  • Force produced perpendicular to the relative airflow.
  1. The lift produced by an airfoil is the force produced:
  • Halfway between the chord line and the relative airflow.
  • Opposite to the relative airflow.
  • Perpendicular to the relative airflow.
  1. During flight with zero angle of attack, the pressure along the upper surface of the wing should be:
  • Less than atmospheric pressure.
  • Equal to atmospheric pressure.
  • Greater than atmospheric pressure.
  1. Choose the correct statement re. angle of attack:
  • An increase in angle of attack will increase impact pressure below the wing, and decrease drag.
  • An increase in angle of attack will increase impact pressure below the wing, and increase drag.
  • A decrease in angle of attack will increase impact pressure below the wing, and increase drag.
  1. What changes in aircraft control must be made to maintain altitude while the airspeed is being decreased:
  • Increase the angle of attack to compensate for decreasing lift.
  • Maintain a constant angle of attack until the desired airspeed is reached, then increase the angle of attack.
  • Increase the angle of attack to produce more lift than weight.
  1. The point of an airfoil through which lift acts, is the:
  • Centre of pressure.
  • Centre of gravity.
  • Centre of rotation.
  1. When the angle of attack of an airfoil is increased from 1° to 8° the centre of pressure will:
  • Remain unaffected.
  • Move forward.
  • Move aft.
  1. Both lift and drag of an airfoil are:
  • Proportional to the square of the velocity (V2) of the relative airflow.
  • Proportional to the increases in the velocity of the relative airflow.
  • Inversely proportional to the area of the wing.
  1. If the airspeed of an aircraft is double while the angle of attack is held constant, the parasite drag will:
  • Remain the same.
  • Be four times greater.
  • Double
  1. Assume an aircraft cruising at 100 mph and creating 1 000 lbs of drag, if the angle of attack remains the same but the airspeed is doubled, the total drag would be increased to:
  • 4 000 lbs.
  • 3 000 lbs.
  • 2 000 lbs.
  1. Which of the following statements generally describes the relationship of the forces acting on an aircraft that is climbing at a constant airspeed and at constant power:
  • Thrust is greater than drag; lift is greater than weight.
  • Thrust is greater than drag and lift is equal to weight.
  • Total thrust is equal to total drag; total lift is equal to total weight.
  1. The reason a light general aviation aeroplane tends to nose down during power reductions, is that the:
  • Thrust line acts horizontally and above the force of drag.
  • Centre of gravity is located forward of the centre of pressure.
  • Centre of pressure is located forward of the centre of gravity.
  1. How is an aircraft’s performance affected by frost on the wings:
  • Lift is decreased; drag is decreased.
  • Lift is increased; drag is decreased.
  • Lift is decreased; drag is increased.
  1. Frost covering the upper surface of an airfoil (wing) will usually cause:
  • The aircraft to stall at an angle of attack that is lower than normal.
  • The aircraft to stall at an angle of attack that is higher than normal.
  • No problem for pilots of light aircraft.
  1. What determines the angle of attack at which an aircraft stalls?
  • Design of the wing.
  • Load factor.
  • True airspeed.
  1. In all aircraft, stalls are caused by:
  • A loss of airspeed.
  • Exceeding the critical angle of pitch.
  • Exceeding the critical angle of attack.
  1. For a given airfoil, the angle of attack which results in a stall:
  • Varies directly with the degree of bank.
  • Remains constant regardless of bank, load factor or airspeed.
  • Varies with the speed on airflow around the airfoil.
  1. The angle of attack at which an aircraft stalls:
  • Is dependant upon the speed of the airflow over the wings.
  • Is a function of speed and density altitude.
  • Will remain constant regardless of gross weight.
  1. Which statement is true relating to factors which produce stalls:
  • The stalling angle of attack depends upon the speed of the airflow over the wings.
  • The critical angle of attack is a function of the degree of bank.
  • The stalling angle of attack is independent of the speed of airflow over the wings.
  1. Indicated stall speed is affected by:
  • Angle of attack, weight and air density.
  • Weight, load factor and power.
  • Load factor, angle of attack and power.
  1. An aircraft in a steep-banked turn stalls at a higher IAS than it does with the wings level, because in the turn:
  • The critical angle of attack has decreased.
  • The critical angle of attack is reached at a higher IAS.
  • Total lift has decreased.
  1. Why can turbulent air cause an increase in stall speed:
  • The TAS is abruptly increased.
  • The load factor is suddenly decreased.
  • The angle of attack is increased.
  1. To produce the desired effect, trim tabs must be adjusted:
  • In such a direction as to remain flush with the primary control surfaces they affect.
  • In the same direction as the primary control surfaces they affect.
  • In the opposite direction to the primary control surfaces they affect.
  1. Choose the correct statement re. the use of rudder in conventional aircraft to compensate for the effects of torque:
  • If airspeed is decreased (power constant), right rudder pressure must be added.
  • If power is reduced (airspeed constant), right rudder pressure must be added.
  • If power is increased (airspeed constant), left rudder pressure must be added.
  1. The primary function of rudder, while entering a turn from straight-and-level flight, is to:
  • Overcome the yaw caused by the lowered aileron on the higher wing.
  • Overcome the yaw caused by the lowered aileron on the lower wing.
  • Overcome the yaw caused by the raised aileron on the higher wing.
  1. When entering a turn, the primary function of rudder is to:
  • Control yawing about the vertical axis.
  • Allow the aircraft to pitch about its lateral axis.
  • Prevent the aircraft from rolling about the longitudinal axis.
  1. The hazardous vortex turbulence that might be encountered behind large aircraft is created only when that aircraft is:
  • Using high power settings.
  • Operating at high airspeeds.
  • Developing lift.
  1. Choose the correct statement regarding wake turbulence:
  • The primary hazard is loss of control because of induced roll.
  • Vortex operation begins with the initiation of the take off roll.
  • Vortices tend to remain level for a period of time.
  1. If wake turbulence is encountered, the probability of induced roll increases when the encountering aircraft’s:
  • Airspeed is slower than that of the generating aircraft.
  • Altitude is higher than that of the generating aircraft.
  • Heading is aligned with the flight path of the generating aircraft.
  1. Aerodynamically, propeller thrust is the result of the:
  • Angle of incidence of the blade.
  • Decreased pressure on the flat side of the blade and increased pressure on the curved side.
  • Shape and angle of attack of the blade.
  1. Air deflection produced by a rotating propeller cause dynamic pressure on the engine side of the propeller to be greater than atmospheric pressure, thus generating:
  • Torque
  • Drag
  • Thrust
  1. During take-off, when maximum power and thrust are required, the constant speed propeller should be set at a propeller blade angle which:
  • Will produce a low slipstream velocity.
  • Will produce a small angle of attack with respect to its relative airflow.
  • Will produce a large angle of attack with respect to its relative airflow.
  1. To develop maximum power and thrust, a constant speed propeller should be set to a blade angle which will produce:
  • Large angle of attack and low RPM.
  • Small angle of attack and high RPM.
  • Large angle of attack and high RPM.
  1. To establish a climb after take-off in an aircraft equipped with a constant speed propeller, the output of the engine is reduced to climb power by decreasing manifold pressure and:
  • Increasing RPM by increasing propeller blade angle.
  • Decreasing RPM by decreasing propeller blade angle.
  • Decreasing RPM by increasing propeller blade angle.
  1. In relation to an aerofoil the propeller provides:
  • More thrust and less torque than lift and drag.
  • Less thrust and more torque than lift and drag.
  • More torque than lift and less thrust than drag.
  1. Which is correct for the following statements:
  • Blade angle consists of helix angle and angle of attack.
  • Helix angle consists of blade angle and angle of attack.
  • Angle of attack equals helix angle.
  1. The blade angle of a propeller will:
  • Be greatest at the tip.
  • Be greatest at 7° radius.
  • Be greatest at the root.
  1. The force tending to twist a propeller blade of a constant speed propeller to fine pitch is:
  • Torque
  • Centrifugal twisting moment.
  • Aerodynamic twisting moment.
  1. The use of flaps will produce:
  • Increased lift and decreased drag.
  • Increased lift and increased drag.
  • Decreased lift and increased drag.
  1. The primary function of flap is to:
  • Provide a steeper gliding angle.
  • Increase control-effectiveness at slow airspeeds.
  • Permit a safer take-off over high obstructions.
  1. Lowering the flap during a landing approach will:
  • Increase the angle of descent with increasing airspeed.
  • Decrease the angle of descent with increasing power.
  • Permits approaches in aircraft with a good L/D ratio.
  1. Which statement is true regarding the use of flaps during turns:
  • The addition of flaps decreases the stall speed.
  • The addition of flaps increases the stall speed.
  • Using a constant flap setting and varying the bank has no affect on the stall speed.
  1. The lowering of flaps decreases the stalling angle except with:
  • Fowler flaps.
  • Slotted flaps.
  • Split flaps.
  1. The effect of flaps is to:
  • Improve the L/D ratio.
  • Improve the L/D ratio at small flap settings.
  • Spoil the L/D ratio.
  1. The ratio between the total air load imposed on the wing and the gross weight in flight is known as:
  • Power loading.
  • Load factor.
  • Yield load.
  1. Assume an aircraft is certificated with a maximum gross weight of 2 500 lbs and a load factor of 3.8. If this aircraft were loaded to a gross weight of 2650 lbs and flown in turbulence creating a 3.8 load factor, what air load would be imposed upon its structure?
  • 2 650 lbs and this aircraft should not be flown with this gross weight.
  • 570 lbs above maximum permissible, this aircraft should not be flown at this gross weight.
  • 150 lbs above maximum permissible and this aircraft should not be flown at this gross weight.
  1. Wing loading of an aircraft is determined by a value which is the:
  • Gross weight of the aircraft divided by the wing area.
  • Ratio of the wing area to the horsepower.
  • Gross weight divided by the span.
  1. Load factor is the actual weight supported by the wings at any given moment:
  • Divided by the normal weight of the aircraft.
  • Multiplied by the total weight of the aircraft.
  • Added to the total weight of the aircraft.
  1. If the angle of bank were held constant and the airspeed varied, the load factor would:
  • Vary depending on the rate of turn.
  • Decrease when the airspeed decreases.
  • Remain constant.
  1. The additional load imposed on the wings during a level co-ordinated turn in smooth air is dependent on the:
  • Angle of bank.
  • Rate of turn.
  • True airspeed.
  1. For a given angle of bank, the load factor imposed on both the aircraft and pilot in a co-ordinated constant altitude turn:
  • Varies with the rate of turn.
  • Is directly related to the aircraft’s gross weight.
  • Is constant.
  1. In a constant altitude co-ordinated turn, the load factor imposed on an aircraft is the result of:
  • Rate of turn and airspeed.
  • Angle of attack and airspeed.
  • Centrifugal force and gravity.
  1. If, while holding the angle of bank constant, the rate of turn is varied, the load factor would:
  • Remain constant.
  • Vary depending upon airspeed.
  • Increase if the speed were increased.
  1. What increase in load factor would take place if the angle of bank were increased for 60 to 70 degrees?
  • 5 G.
  • 0 G.
  • 5 G.
  1. What is the stall speed of an aircraft under a load factor of 2 if the unaccelerated stall speed is 60 knots?
  • 66 knots.
  • 74 knots.
  • 84 knots.
  1. What is the stall speed of an aircraft under a load factor of 2 if the unaccelerated stall speed is 80 knots?
  • 90 knots.
  • 112 knots.
  • 120 knots.
  1. At a constant power setting the rate of climb of an aircraft is greater when the wings are level than when in a climbing turn because, when level, the:
  • Wing loading is greater.
  • Centre of lift is nearer the trailing edge.
  • Vertical lift component is greater.
  1. Which statement is correct with respect to rate and radius of turn for an aircraft in a co-ordinated turn at a constant altitude:
  • For a specific angle of bank and airspeed, the rate and radius of turn will not vary.
  • For any specific angle of bank and airspeed, the lighter the aircraft, the faster the rate and the smaller the radius of turn.
  • The lower the airspeed the less the rate of turn for a specific bank angle.
  1. Which statement is true if, during a level co-ordinated turn, the load factor was kept constant:
  • A decrease in airspeed results in an increase in radius.
  • An increase in airspeed results in an increase in radius.
  • An increase in airspeed results in a decrease in radius.
  1. Increasing the airspeed while maintaining a constant load factor during a level co-ordinated turn would result in:
  • The same radius of turn.
  • A decrease in the radius of turn.
  • An increase in the radius of turn.
  1. If, during a level turn, the rate of turn is kept constant, an increase in airspeed will result in:
  • Constant load factor regardless of changes in angle of bank.
  • Need to decrease the angle of bank to maintain the same rate of turn.
  • Need to increase the angle of bank to maintain the same rate of turn.
  1. The type of drag which decreases with increase in speed is:
  • Form drag.
  • Interference drag.
  • Induced drag.
  1. It is not necessary to hold off bank in:
  • A gliding turn.
  • A climbing turn.
  • A level turn.
  1. Aileron drag, or adverse yaw, is most likely at:
  • High speed.
  • High angle of attack.
  • Low angle of attack.
  1. To be suitable for supersonic flight an aerofoil should have:
  • A well rounded leading edge.
  • A laminar flow section.
  • A very sharp leading edge.
  1. The first shock wave on an aerofoil approaching the speed of sound occurs:
  • At the trailing edge.
  • On the top surface.
  • Under the bottom surface.
  1. The characteristics which would improve lateral stability are:
  • High keel surface, Low centre of gravity, Dihedral.
  • Longitudinal dihedral, Low centre of gravity, Large keel surface.
  • Sweepback and High centre of gravity, Anhedral.
  1. The effect of inertia moment would be increased with:
  • Forward centre of gravity.
  • Centre of pressure well aft.
  • Centre of gravity well aft.
  1. The type of control balance used to oppose flutter is:
  • Inset hinge balance.
  • Servo tab balance.
  • Mass balance.
  1. A wing would by called polymorphic if fitted with:
  • Split flaps.
  • Vortex generators.
  • Fowler flaps.
  1. An aircraft is in a state of equilibrium in:
  • A steady rate 1 turn.
  • In a steady climb.
  • During take-off.
  1. A heavy aircraft in relation to a lighter aircraft of the same type will glide:
  • Further in a tail wind.
  • The same distance in still air conditions.
  • More slowly in a head wind.
  1. When taking off with an obstacle ahead, the best speed to use for the initial climb would be:
  • Vx.
  • Va.
  • Vy.
  1. The vectors shown below indicate:

H.C.L.                 C.F.

 

  • A slipping right turn.
  • A skidding left turn.
  • A skidding right turn.
  1. To achieve the correct Vref at maximum landing weight you would approach at:
  • 3 times the speed at the bottom of the ASI green arc.
  • 3 times the speed at the bottom of the ASI white arc.
  • 3 times the speed at the top of the ASI white arc.
  1. Contra-rotating propellers have the effect of:
  • Eliminating both gyroscopic and torque effects.
  • Reducing gyroscopic effects but increasing torque effects.
  • Increasing gyroscopic but reducing torque effects.
  1. The effect of size when considering aerodynamic forces is allowed for by:
  • Joules Law.
  • Bernoulli’s Theorem.
  • Reynolds Number.
  1. The dividing line between laminar flow and turbulent flow around an aerofoil is known as:
  • Separation point.
  • Transition point
  • Line of Mean camber.
  1. The effect of induced drag can be reduced by:
  • Wash out.
  • Low aspect ratio.
  • Increasing the angle of incidence at the tip.
  1. Apart from warning devices the aerodynamic warning of the approaching stall is:
  • The attitude of the aircraft.
  • Buffet of the tail surfaces.
  • A sharp dropping of the nose.
  1. The possibility of a spin developing into a flat spin is greatest with:
  • A forward centre of gravity.
  • A small inertia moment.
  • An aft centre of gravity.
  1. The density of the air at sea level is ISA is:
  • 1 225 Kgs/Cubic metre.
  • 1 225 gms/sq.metre.
  • 1225 gms/cubic metre.
  1. The difference between RAS and EAS is:
  • Compressibility
  • Position error.
  • Position error and instrument error.
  1. The sum of Form drag, Skin Friction drag and Interference drag is:
  • Total drag.
  • Induced drag.
  • Profile drag.
  1. Aileron reversal is most likely to occur at:
  • Large angles of attack.
  • Very high speed.
  • Very low speed.
  1. If the humidity is high you would expect the take-off run:
  • To be unaffected because it is not given in the chart.
  • To be longer because of the lower density.
  • To be shorter because of the higher density.
  1. The rate of climb of an aircraft is determined by:
  • Power available over power required.
  • Lift available over lift required.
  • The lift/drag ratio.
  1. Ignoring the effect of Mach Number, the stalling speed (IAS):
  • Reduces with increasing height.
  • Remains the same with increasing weight.
  • Increases with reduced density.
  1. If, while holding the angle of bank constant, the rate of turn is increased, the load factor would:
  • Remain the same.
  • Vary depending on speed.
  • Vary depending on weight.
  1. Down movement of the elevator trimming tab will:
  • Overcome a tendency to fly nose heavy.
  • Overcome a tendency to fly tail heavy.
  • Make the aircraft nose heavy.
  1. To correct for nose heaviness on an aircraft fitted with a variable incidence tailplane, the incidence of the tailplane would have to be:
  • Increased and this can be done by a mechanism which lowers the leading edge.
  • Decreased and this can be done by a mechanism which lowers the trailing edge.
  • Decreased and this can be done by a mechanism which lowers the leading edge.

TECHNICAL GENERAL QUESTIONS

  1. You have adjusted the elevator trim tab to correct for nose heavy, what was the direction of travel of the trim tab:
  • The elevator trim has moved up.
  • The port elevator tab has moved up and starboard moved down.
  • The elevator trim tab has moved down.
  1. When an aileron trim control in the cockpit is moved to counteract a tendency to fly left wing low, an aileron trim tab fitted to the port aileron will:
  • Move up and cause the left aileron to move down and the right aileron to move down to a lesser degree.
  • Move up and cause the left aileron to move down but the right aileron will remain neutral.
  • Move up and this will cause the left aileron to move down and the right aileron to move up.
  1. The purpose of a trim tab is:
  • To provide “feel” when flying at high airspeeds.
  • To assist the pilot in initiating movement of the controls in both directions.
  • To zero the loads on the pilot’s control in the flight attitude required.
  1. A free servo tab is operated:
  • Automatically and moves in the same direction as the main control surface.
  • Directly by the pilot to produce forces which in turn move the main control surfaces.
  • By a trimmer wheel, and moves in the opposite direction to the main control surface when moved.
  1. If the control column is moved to the right, a balance tab on the port aileron should:
  • Move up relative to the aileron.
  • Move down relative to the aileron.
  • Not move unless the aileron trim control is operated.
  1. On an aircraft with a variable incidence trimming tailplane, the tailplane incidence changes:
  • Automatically if the elevator moves.
  • If the control column is moved back or forward.
  • If the trim wheel is turned back or forward.
  1. With the aircraft standing on the ground, if the control column is pulled back, a spring tab on the elevator:
  • Will remain in the neutral position relative to the elevator.
  • Will move down relative to the elevator.
  • Will move up relative to the elevator.
  1. A stall warning must be set to operate:
  • At a speed just below stalling speed.
  • At a speed above stalling speed.
  • At a stalling speed.
  1. In a steady turn an aircraft experiences 3g, the stalling speed will be:
  • Above the normal stalling speed.
  • Below the normal stalling speed.
  • The same as the normal stalling speed.
  1. At altitudes above sea level the IAS stalling speed will be:
  • The same as at sea level.
  • Less than at sea level
  • Greater than at sea level.
  1. A typical stalling angle of attack is:
  • 30
  • 15
  • 5
  1. With engine power on, an aircraft will stall:
  • At the same speed as with power off.
  • At a lower speed than with power off.
  • At a higher speed than with power off.
  1. If the aircraft weight changes by 6% the stalling speed will change by approximately.
  • 3%.
  • 12%.
  • 6%
  1. A fixed spoiler on the leading edge of the wing at the root will:
  • Prevent a root stall.
  • Induce a root stall.
  • Give a shorter landing run.
  1. At angles of attack above the stalling angle:
  • The lift decreases and the drag decreases.
  • The lift decreases and the drag increases.
  • The lift increases and the drag increases.
  1. A wing is stalled when:
  • The lift produced is less than the weight.
  • The airflow has separated from most of the upper surface.
  • The lift is zero.
  1. A leading edge slat is a device for:
  • Increasing the stalling angle of the wing.
  • Decreasing the drag of the wing.
  • Decreasing the stalling angle of the wing.
  1. The purpose of a leading edge droop is:
  • To give a more cambered section for high-speed flight.
  • To increase wing camber, and prevent separation of the airflow when trailing edge flaps are lowered.
  • To increase the wing area for take-off and landing.
  1. The type of flap which increases wing area is:
  • A fowler flap.
  • A split flap.
  • A plain flap.
  1. Lowering a flap to its landing setting will:
  • Give a large increase in drag and a lower stalling speed.
  • Give a large increase in drag but a higher stalling speed.
  • Give a smaller increase in drag but a lower stalling speed.
  1. A stick shaker is:
  • A high Mach Number warning device.
  • An artificial stability device.
  • A device to vibrate the control column to give a stall warning.
  1. The stalling speed is determined by:
  • The CL for zero lift.
  • The maximum value of CL.
  • The CL for maximum L/D ratio.
  1. A stick pusher is a device for:
  • Assisting the pilot to move the control against high air loads.
  • Preventing the aircraft from getting into a stall.
  • Automatically compensating pitch changes at high speeds.
  1. If the control column is moved forward and to the right:
  • The left aileron will move down and the right aileron up, elevator up.
  • The left aileron will move up, and the right aileron down, elevator up.
  • The right aileron will move up, and the left aileron down, elevator down.
  1. The purpose of a turnbuckle in a flying control system, is:
  • To enable the control cables to be cross-connected.
  • To enable the range of movement of the control surface to be adjusted.
  • To enable the cable tension to be adjusted.
  1. With a differential aileron control systems:
  • The aileron moves further down than up.
  • The leading edge projects beneath the wing when the aileron is raised.
  • The aileron moves further up than down.
  1. A duplicate inspection is required:
  • On both flying control and engine control systems.
  • On flying systems only.
  • On engine control systems only.
  1. Locking of a turnbuckle in a flying control run is normally achieved by:
  • Locking wire through the turnbuckle and the end fittings.
  • Slotted nuts and split pins at each end.
  • Self-locking stop nuts in the end fittings.
  1. Over tension cables of a flying control system could result in:
  • Excessive friction in the system.
  • Insufficient friction in the system.
  • Insufficient range of movement of the control surface.
  1. The purpose of control locks on a flying control system is:
  • To prevent structural damage to the controls in gusty conditions.
  • The enable any free movement in the control system to be detected.
  • To keep the control surface rigid for ground handling.
  1. A control surface is mass balanced by:
  • The attachment of weights acting on the hinge line.
  • Fitting a balance tab.
  • The attachment of weights acting forward of the hinge line.
  1. A frise aileron is one on which:
  • Upward movement is greater than downward movement.
  • The leading edge protrudes above the wing when the aileron is lowered.
  • The leading edge protrudes below the wing when the aileron is raised.
  1. To limit the range of control surface movement:
  • Cables are tensioned correctly.
  • Control cables are left a little slack.
  • Control stops are provided.
  1. When left rudder is applied:
  • The left side of the rudder bar is moved forward and the rudder moves to the starboard.
  • The left side of the rudder bar moves forward and the rudder moves to port.
  • The right side of the rudder bar moves forward and the rudder moves to port.
  1. Controls are mass balanced in order to:
  • Aerodynamically assist the pilot in moving the controls.
  • Eliminate control flutter.
  • Provide equal control forces on all three controls.
  1. A duplicate inspection of flying controls by a pilot or flight engineer must cover the checking of several different aspects of the appropriate flying control system. Amongst these are checks to verify:
  • The operation of the controls in flight produces the intended effect on the flight path of the aircraft.
  • That full movement is in accordance with figures stated in the Certificate of Airworthiness.
  • That full, free and correct movement of control surfaces relative to the movement of their controls is obtained.
  1. The airflow over the top surface of an aerofoil produces:
  • A smaller proportion of the total lift than the airflow past the lower surface.
  • An equal proportion of the total to that produced by the airflow past the lower surface.
  • A greater proportion of the total lift than the airflow past the lower surface.
  1. The optimum angle of attack of an aerofoil is the angle at which:
  • The highest lift/drag ratio is produced.
  • The aerofoil produces zero lift.
  • The aerofoil produces maximum lift.
  1. The factors which affect lift produced by an aerofoil are:
  • Angle of attack, air density, velocity, and wing area.
  • Angle of attack, air temperature, velocity, and wing area.
  • Angle of attack, velocity, wing area, aerofoil shape, and air density.
  1. If the density of air is increased, the lift will:
  • Remain the same.
  • Decrease
  • Increase
  1. A cambered aerofoil section set at zero angle of attack in an airstream will:
  • Produce negative lift.
  • Produce lift.
  • Produce no lift.
  1. The stalling angle of attack of a typical aerofoil is approximately:
  • 15°
  • –1°
  1. If the airspeed over a wing at a constant angle of attack is doubled:
  • The lift will be double.
  • The lift will increase four times.
  • The lift will increase eight times.
  1. A high speed and high aspect ratio wing:
  • Decreases skin friction drag.
  • Decreases induced drag.
  • Increases induced drag.
  1. The boundary layer of a body in a moving airstreams is:
  • A thin layer of air over the surface where the air is stationary.
  • A layer of separated flow where the air is turbulent.
  • A layer of air over the surface where the airspeed is changing from free stream to zero speed.
  1. As the speed of an aircraft increases the profile drag:
  • Decreases
  • Decreases at first then increases.
  • Increases
  1. Minimum total drag of an aircraft occurs:
  • When induced drag is least.
  • At the stalling speed.
  • When profile drag equals induced drag.
  1. The induced drag of an aircraft:
  • Increases with increasing speed.
  • Increases as aspect ratio is increased.
  • Decreases with increasing speed.
  1. Two geometrically similar streamlined bodies A and B have the same fineness ratio, but A is larger than B:
  • A would have a lower drag Coefficient than B.
  • A would have a higher drag Coefficient than B.
  • A would have the same drag Coefficient at B.
  1. If the weight of an aircraft is increased, the profile drag at a given speed:
  • Will remain the same.
  • Will increase.
  • Will decrease.
  1. A symmetrical aerofoil section set at zero angle of attack in an airstream will produce:
  • Drag but no lift.
  • No lift or drag.
  • Lift and drag.
  1. A high wing position on an a/c gives:
  • The same lateral stability as a low wing.
  • Less lateral stability than a low wing.
  • More lateral stability than a low wing.
  1. Increasing the size of the fin will:
  • Increase lateral stability.
  • Decrease lateral stability.
  • Not affect lateral stability.
  1. After a disturbance in pitch an aircraft oscillates with increasing amplitude. It is:
  • Dynamically neutral.
  • Dynamically stable but statically unstable.
  • Dynamically unstable longitudinally.
  1. To ensure longitudinally stability in flight, the position of the C of G:
  • Should not be forward of the neutral point.
  • Should not be aft of the neutral point.
  • Should coincide with the neutral point.
  1. Moving the centre of gravity aft will:
  • Increase longitudinal stability.
  • Reduce longitudinal stability.
  • Have no effect on longitudinal stability.
  1. After a disturbance in pitch, an aircraft continues to oscillate at a constant amplitude. It is:
  • Laterally unstable.
  • Longitudinally neutrally stable.
  • Longitudinally unstable.
  1. Sweepback of the wing will:
  • Not affect the lateral stability.
  • Decrease lateral stability.
  • Increase lateral stability.
  1. Longitudinal stability is given by:
  • The horizontal tailplane.
  • The wing dihedral.
  • The fin.
  1. Lateral stability is given by:
  • The ailerons.
  • The wing dihedral.
  • The horizontal tailplane.
  1. The static margin is equal to the distance between:
  • The C of G and the neutral point.
  • The C of P and the neutral point.
  • The C of G and the C of P.
  1. An aircraft is constructed with dihedral to provide:
  • Longitudinal stability about the lateral axis.
  • Lateral stability about the longitudinal axis.
  • Lateral stability about the normal axis.
  1. The fin gives:
  • Directional stability about the longitudinal axis.
  • Directional stability about the normal axis.
  • Longitudinal stability about the lateral axis.
  1. The lift/drag ratio of a wing section at its stalling angle of attack is:
  • Of a negative quantity.
  • Low
  • High
  1. For the same angle of attack a cambered wing will:
  • Give less lift than one with no camber.
  • Give the same lift as one with no camber.
  • Give more lift than one with no camber.
  1. The Centre of Pressure is:
  • The centre of gravity of the wing.
  • The point on the chord line at which the resultant lift force may be said to act.
  • The point of maximum pressure on the under surface of the wing.
  1. For a cambered wing section the zero lift angle will be:
  • Positive
  • Negative
  • Zero
  1. The type of drag which increases with increasing angle of attack:
  • Interference drag.
  • Induced drag.
  • Profile drag.
  1. If an aircraft is flying 0° angle of attack, the pressure over the top surface of an aerofoil would be:
  • Above atmospheric pressure.
  • Below atmospheric pressure.
  • The same as atmospheric pressure.
  1. In the narrow section of a Venturi Tube:
  • The velocity is minimum; pressure is decreasing.
  • The velocity is maximum; pressure is minimum.
  • The velocity is decreasing; pressure is minimum.
  1. If kinetic energy increases in a Venturi Tube there will be a decrease in:
  • Potential energy.
  • Energy due to position.
  • Pressure energy.
  1. Regarding angle of attack it is true to say that:
  • An increase in angle of attack will increase impact pressure below the wing and decrease drag.
  • An increase in angle of attack will increase impact pressure below the wing and increase drag.
  • A decrease in angle of attack will increase impact pressure below the wing and increase drag.
  1. The lift produced by an aerofoil is the force produced:
  • Halfway between the chord line and the relative wind.
  • Opposite to the relative wind.
  • Perpendicular to the relative wind.
  1. In an engine fitted with a convergent-divergent exhaust duct, the airflow:
  • In the convergent section reaches sonic velocities.
  • In the divergent section reaches sonic velocities.
  • In the divergent section undergoes a decrease in pressure.
  1. In a carburettor engine which is running at high power, the fuel level in the diffuser is:
  • Lower than that in the carburettor bowl.
  • The same as that in the carburettor bowl.
  • Higher than that in the carburettor bowl.
  1. The purpose of suppressors as close as possible to the generator is:
  • To prevent the switching of high voltage to low voltage within the cockpit.
  • To control the generator voltage output within close limits.
  • To suppress generator produced interferences, which are detrimental to the efficient operation of radio and radar services.
  1. In a climb the resultant forces which combine to support the aircraft are:
  • Total reaction and lift.
  • Thrust and drag.
  • Lift and thrust.
  1. The four flight fundamentals involved in manoeuvring an aircraft are:
  • Straight and level flight, turns, climbs and descents.
  • Starting, taxiing, take-off, landing.
  • Aircraft power, pitch, bank and trim.
  1. Torsional flutter is a condition during which:
  • The wing twists in rapidly alternating directions at high IAS because of the attachment of poorly balanced control surfaces.
  • The control surfaces flutter, but not the wings to which they are attached.
  • The aircraft is stalled resulting in the rapid longitudinal movement in the centre of pressure.
  1. Lift on a wing is most properly defined as the:
  • Force produced parallel to the relative wind.
  • Reduced pressure resulting from a smooth flow of air over a curved surface and acting perpendicular to the longitudinal axis.
  • Differential pressure acting perpendicular to the chord of the wing.
  1. Lateral stability will be improved with:
  • Dihedral
  • Anhedral
  • Longitudinal dihedral.
  1. The tendency for an aircraft to return to a previous trimmed flight condition is know as:
  • Controllability
  • Stability
  • Manoeuvrability
  1. As aircraft weight is reduced by fuel consumption, the stalling speed will:
  • Decrease
  • Remain the same.
  • Increase
  1. Density of the air will increase with:
  • An increase in temperature.
  • An increase in pressure.
  • An increase in humidity.
  1. It is unwise to operate an aeroplane in excess of its maximum certificated gross weight primarily because:
  • Of the significant increase in fuel consumption.
  • An overload aeroplane is excessively stable in flight.
  • Excessive loads may be imposed on some parts of the structure.
  1. Factors for lateral stability are:
  • Dihedral, large fin and low C of G.
  • Dihedral, high wing and low C of G.
  • Sweepback, large tail area.
  1. Volumetric efficiency in a piston engine fitted with a constant speed propeller will be better at:
  • High engine RPM, and high manifold pressure.
  • High engine RPM, and low manifold pressure.
  • High manifold pressure and low engine RPM.
  1. The main longitudinal members in a truss type fuselage construction are:
  • Longerons
  • Formers
  • The empennage.
  1. The section of a piston engine requiring the highest oil pressure is:
  • The camshaft.
  • The main bearings.
  • The cylinder.
  1. The valves are opened by:
  • A spring.
  • The camshaft.
  • The gudgeon pin.
  1. Apart from lubrication, an advantage obtained from oil is that it:
  • Prevents detonation.
  • Prevents pre-ignition.
  • Assists with cooling.
  1. Hazardous vortex turbulence that might be encountered behind large aircraft is created only when the aircraft is:
  • Heavily loaded.
  • Developing lift.
  • Operating at high speeds.
  1. The loss of aircraft control which may occur if a light aeroplane is flown into the wake of a large aeroplane is caused principally by:
  • The tornado-like vortices produced by the wingtips of the large aeroplane.
  • Meteorological conditions which create wind-shear.
  • Turbulence created by the propellers of jet engine of the large aeroplane.
  1. The first indication of carburettor icing in aeroplane equipped with a fixed pitch propeller would most likely be a:
  • Decrease in manifold pressure.
  • Increase in oil pressure.
  • Rough running engine and a decrease in RPM.
  1. If fuel-air mixture adjustments are not made during operation at high altitudes, engine performance will be affected because of:
  • A constant volume of air and an increase in the amount of fuel metered by the carburettor.
  • A decrease in the weight of air while approximately the same amount of fuel is delivered by the carburettor.
  • A decrease in the amount of fuel and a decrease in the amount of air delivered by the carburettor.
  1. In the choke tube area of the carburettor an area of:
  • High pressure is found.
  • Low pressure in found.
  • No difference in pressure in found.
  1. Operating with too lean a mixture is likely to lead to:
  • More power.
  • Pre-ignition.
  • A very cool running engine.
  1. The fuel system which is not susceptible to icing from fuel evaporation is:
  • Gravity feed.
  • Pump driven carburettor feed.
  • Fuel injection.
  1. The compressor air into the can annular which is not used in the combustion process in a turbo-jet engine is used to:
  • Reduce the noise level in the exhaust gasses.
  • Reduce the temperature of the gasses at the turbine blades.
  • Provide power to the rear turbine.
  1. If atmospheric pressure and temperature remain the same, an increase in humidity would affect take-off performance by:
  • A shorter take-off distance (the air is less dense).
  • A longer take-off distance (the air is more dense).
  • A longer take-off distance (the air is less dense).

TECHNICAL GENERAL QUESTIONS

  1. With reference to starting aeroplane engines, “hydraulicing” refers to:
  • An excessive build-up of oil pressure in the oil pump due to cold oil and consequent overloading of the starter.
  • Possible damage due to excessive amounts of liquid in some engine cylinders.
  • Possible damage to bearings to hydraulic locks in the oil system because of cold oil.
  1. With reference to aeroplane operating manual, the Vle refers to:
  • The maximum speed at which the undercarriage may be lowered.
  • The maximum speed at which the aeroplane may be flown with the undercarriage extended.
  • The maximum speed of the aeroplane in the landing configuration.
  1. Propeller efficiency relates to:
  • The theoretical distance the propeller advances in one revolution.
  • The ratio of useful work produced by the propeller to the work put into the propeller by the engine.
  • The effect that slippage has on the propeller.
  1. An aircraft loaded with the C of G too far aft is:
  • Nose heavy and less stable.
  • Tail heavy and less stable.
  • Tail heavy and more stable.
  1. Cabin differential is:
  • The difference between cabin altitude and aircraft altitude and is usually negative.
  • The difference between cabin pressure and ambient pressure and is usually positive.
  • The difference between cabin pressure and ambient pressure is negative.
  1. The capacity of a battery is given in:
  • Volts
  • Amp/hour.
  • Amps
  1. Warning of an electrical overload would be given by:
  • Low amps.
  • Generator warning light.
  • High amps.
  1. If while starting a jet engine there is no indication of a rise in EGT, it indicates:
  • A huge start.
  • A wet start.
  • A hot start.
  1. The advantage of the centrifugal compressor in relation to the axial flow compressor is that:
  • It gives a greater pressure rise in one stage.
  • It has a smaller frontal area.
  • The flow of the gases into the combustion chambers is straighter.
  1. Flexural aileron flutter would by reduced by:
  • Horn balance.
  • Insert hinge balance.
  • Mass balance.
  1. The pilot’s movement of the controls will be made easier by:
  • Mass balance.
  • Servo tab.
  • Anti-servo tab.
  1. The strokes in a four stroke engine are:
  • Induction, power, exhaust, compression.
  • Power, exhaust, induction, compression.
  • Compression, power, induction, exhaust.
  1. In four stroke reciprocating engine the:
  • Camshaft turns at twice the speed of the crankshaft.
  • Crankshaft turns at twice the speed of the camshaft.
  • The crankshaft and the camshaft turn at the same speed.
  1. In an engine fitted with a carburettor, a worn needle and seat will cause difficulty in starting because of:
  • An excessively rich mixture.
  • Too lean a mixture.
  • A fuel blockage to the carburettor bowl.
  1. An aircraft engine fitted with a dry sump system has a scavenge pump which pumps at:
  • A lower capacity than the pressure pump.
  • A greater capacity than the pressure pump.
  • The same capacity as the pressure pump.
  1. A high by-pass fan engine, compared with a low by-pass fan engine:
  • Produces less thrust at a specific fuel flow, but is much quieter.
  • Has reduced take-off performance, but enjoys improved cruise fuel efficiency.
  • Produces more thrust for a specific fuel flow and has a reduced noise level.
  1. At the critical Mach number of the aircraft:
  • Local airflows may reach Mach 1.
  • All the local airflows are less than Mach 1.
  • The aircraft has reached the local speed of sound.
  1. The load factor experienced by an aircraft is a function of:
  • The speed and rate of turn.
  • The rate of turn.
  • Neither by the above is correct, as the load factor is purely a function of the bank angle.
  1. Two aircraft are of the same type but are loaded to different weights. The heavier aircraft will:
  • Not be able to glide as far as the lighter aircraft.
  • Be able to glide further than the lighter aircraft provided that the heavier aircraft is flown at a lower IAS.
  • Will be able to glide at the same glide angle as the lighter aircraft
  1. When flying for range, the aircraft should be flown at a speed which provides the:
  • Lowest safe TAS, at an altitude which requires full throttle to achieve that TAS.
  • Lowest value of thrust required.
  • Lowest value of thrust horsepower required by the airframe.
  1. Autorotation will result at or near the stalling angle of attack when:
  • The wing producing the greater lift is producing the least drag.
  • The wing producing the least lift is producing the least drag.
  • The wing experiencing the smaller angle of attack produces the greater drag value.
  1. During a climbing turn in an aircraft powered by a clockwise rotating propeller as viewed from the rear, the required bank angle is maintained by sustained:
  • Out of turn aileron.
  • Into turn aileron.
  • Neutral aileron.
  1. When flying for maximum endurance, the aircraft must be flown:
  • As high as possible, at a speed which provides for minimum drag.
  • As high as possible, at a speed which provides for minimum THP.
  • At the recommended endurance speed, which usually approximates the speed recommended for best angle of climb.
  1. During a climb, the thrust is:
  • Equal to the aerodynamic drag.
  • Equal to the weight apparent drag.
  • Neither of the above statements is correct.
  1. When gliding into a head wind the best glide angle will be achieved at:
  • An IAS, which produces the best lift/drag ratio.
  • An IAS, which is higher than that for best lift/drag ratio.
  • An IAS which is lower than that for best lift/drag ratio, but which is higher than that required for best endurance speed.
  1. An aircraft in level flight has a stalling speed of 107 kts at 1.8g. The stalling speed in straight and level flight will be:
  • 143 kts.
  • 59 kts.
  • 80 kts.
  1. Application of aileron alone when rolling into a turn will result in unbalanced flight for the duration of the aileron input and will result in:
  • Sideslip
  • Skid
  • Either of the above may be correct depending on the direction of the turn.
  1. Experimental mean pitch is the advance per revolution when the propeller:
  • Produces zero thrust.
  • At zero angle of attack.
  • Is feathered and may be taken at two thirds of the blade length.
  1. In forward flight:
  • The thrust developed by a propeller is greater than the torque reaction.
  • A propeller’s torque reaction is greater than the thrust.
  • The trust from a propeller is greater than the lift to ensure propeller efficiency.
  1. A reciprocating piston engine which is fitted with an oil cooler will have a relief bypass valve fitted between:
  • The engine and the oil cooler.
  • The oil cooler and the oil tank.
  • The oil temperature gauge and the engine.
  1. If ambient conditions determine that carburettor heat should be sustained during flight, it will be necessary to:
  • Enrich the mixture to adjust for the changing density.
  • Lean the mixture further to adjust for changing density.
  • Enrich the mixture and throttle back slightly to prevent detonation.
  1. On engine shut down, the manifold pressure gauge in an engine fitted with this gauge will read:
  • Sea level pressure.
  • Ambient air pressure.
  • Zero
  1. Normally aspirated engines are designed to run on fuels with a specific anti-knock capability. However, when need to:
  • A fuel with a higher anti-knock rating may be used for limited periods.
  • A fuel with a lower anti-knock rating may be used for limited periods.
  • None of the above statements is correct, as damage will result if the design anti-knock rated fuel is not used.
  1. A transformer which halves the voltage will have:
  • Half as many turns on the secondary coil as on the primary coil.
  • Twice as many turns on the secondary as on the primary.
  • Four times as many turns on the secondary as on the primary.
  1. The moving part of the AC generator is:
  • The rotor.
  • The stator.
  • The exciter.
  1. Output from an AC generator is taken from:
  • The exciter.
  • The stator windings.
  • The rotor windings.
  1. The voltage of an AC generator:
  • Rises to a maximum in one direction, falls to zero, and then rises in the same direction to a maximum and falls to zero.
  • Rises to a maximum in one direction and then remains constant.
  • Rises to a maximum in one direction, falls to zero and then rises to a maximum in the opposite direction and falls to zero.
  1. An alternator is:
  • A static inverter.
  • A rotary switch for a de-icing system.
  • An AC generator.
  1. Impedance is:
  • Volts/ Watts
  • Volts/Amps
  • Volts/Frequency
  1. If the frequency is increased in an inductive circuit:
  • Impedance will decrease.
  • Impedance will increase.
  • Impedance will remain constant.
  1. In an AC circuit which is mainly inductive:
  • Current will lead voltage.
  • Current and voltage will be in phase.
  • Current will lag voltage.
  1. If frequency increases, capacitive reactance will:
  • Increase,
  • Not change.
  • Decrease
  1. Power factor is:
  • Real load/Apparent load
  • Apparent load/Real load
  • Real load/Wattless load
  1. In a non-paralleled constant frequency AC system the generator loadmeters will normally measure:
  • KVA or Amps.
  • KVA and power factor.
  • KVA and KW.
  1. A 400 Hz supply has:
  • A capacity of 400 000 watts.
  • An impedance of 400 ohms.
  • A frequency of 400 cycles per second.
  1. One advantage of a main AC supply system is:
  • Easy, and almost losses stepping up or down of voltage.
  • Voltage does not need to be changed.
  • Batteries are not needed.
  1. One of the advantages of three phases generation over single phase generation is:
  • That most aircrafts services required three phase supply.
  • That there is more efficient conversation of mechanical energy to electrical energy.
  • That it gives lower cable weights and more compact generators.
  1. In a typical aircraft constant frequency paralleled AC system the line voltage is:
  • 115 Volts.
  • 208 Volts.
  • 200 Volts.
  1. In an AC generator, voltage regulation:
  • Is by varying the drive RPM.
  • Is by varying the excitation current.
  • Is by the insertion of variable resistors into the circuit.
  1. In a constant speed AC generation system which is paralleled:
  • All engines are run at the same RPM.
  • All generators are run off the same engine.
  • A generator has its own constant speed drive.
  1. A low reactive load on one generator is compensated for in paralleled system:
  • Through the excitation circuit of the generator.
  • By altering the rotor speed.
  • By increasing the real load on the other generators.
  1. To increase the real load taken by a paralleled AC generator, the:
  • Generator drive torque is increased.
  • Generator excitation is increased.
  • Generator drive torque and excitation are increased.
  1. The frequency of aircraft constant frequency systems is maintained:
  • Between 380 and 420 Hz.
  • Between 350 and 450 Hz.
  • Between 395 and 495 Hz.
  1. Frequency is controlled by:
  • Excitation voltage.
  • Speed of rotation.
  • Excitation current.
  1. Load sharing circuits are necessary:
  • Whenever generators are operating in series.
  • Whenever generators are operating independently.
  • Whenever generators are operating in parallel.
  1. Paralleled AC generators will have:
  • One load meter to measure total system load.
  • One volt meter for each generator.
  • One load meter for each generator.
  1. If an AC generator control relay tripped, the:
  • Generator circuit breaker for that generator will have opened.
  • Generator circuit breaker for that generator will close.
  • Generator circuit breaker for that generator trips and busbar tiebreaker will also trip.
  1. On an aircraft AC generator, the output is usually taken from:
  • The stator windings.
  • The rotor.
  • The exciter.
  1. The CSD function is:
  • To maintain a constant ratio between engine speed and generator speed.
  • To vary the generator speed in proportion to load.
  • To maintain constant generator speed.
  1. If the CSD disconnect switch is used, the drive can be:
  • Only reinstated when the aircraft is on the ground.
  • Re-instated in flight from the electrical supply compartment.
  • Re-instated in flight from the flight deck.
  1. In the event of a mechanical failure occurring in the generator the CSD is protected by:
  • A hydraulic clutch.
  • A universal joint.
  • Quill drive.
  1. An APU is driven:
  • By its own dedicated gas turbine.
  • By a hydraulic motor.
  • By a ram air turbine.
  1. An auto-transformer:
  • Varies the turns ratio automatically to maintain a constant output voltage with varying input voltage.
  • Has only one coil, which is used as both primary and secondary.
  • Will maintain a constant output frequency with a varying supply frequency.
  1. As the torque load increases on an induction motor, it will:
  • Slow down.
  • Maintain RPM.
  • Speed up.
  1. The valves of a four stroke piston engine will each:
  • Open twice during the normal “Otto” cycle.
  • Open once during the normal “Otto” cycle.
  • Open four times during the normal “Otto” cycle.
  1. Tappet and rocker arm clearance is essential:
  • To allow lubrication between the contact surface.
  • To allow for valve operation by the cam.
  • To allow for expansion throughout the working temperature range of the engine.
  1. Valve “Dwell” is:
  • The period a valve remains open.
  • The period a valve remains closed.
  • The period taken by the rocker to take up the clearance gap before operating the valve.
  1. Valve overlap occurs:
  • At the end of the power stroke.
  • At the end of the exhaust stroke.
  • At the end of the induction stroke.
  1. The weight of charge induced into a piston engine cylinder during normal operation:
  • Is increased by closing the exhaust valve before TDC.
  • Is reduced by closing the inlet valve after BDC.
  • Is increased by delaying the closing of the inlet valve.
  1. The exhaust valve of a piston engine:
  • Normally has a hollow stem partially filled with sodium.
  • Is normally manufactured from metallic sodium to assist with cooling.
  • Normally has a hollow head filled with sodium.
  1. Valve springs are primarily duplicated:
  • To ensure a gas tight seal when the valve is closed.
  • To prevent the valve dropping into the cylinder in the event a spring breaks.
  • To reduce valve bounce.
  1. When the piston of a four stroke piston engine is towards the end of the power stroke:
  • The gas temperature will be at its highest.
  • The gas temperature will be reducing.
  • The gas temperature will remain constant until BDC.
  1. The compression ratio of a piston engine is the:
  • Ratio of the cylinder volume when the piston is at BDC to the cylinder volume when at TDC.
  • Difference in pressure generated when the piston is at BDC to that generated at TDC.
  • Variation between the volume of the combustion chamber and the swept volume.
  1. The majority of aircraft piston engine lubrication systems are of the:
  • Self-lubricating type.
  • Wet sump type.
  • Dry sump type.
  1. A dry sump lubrication system:
  • Maintains a reserve of oil in a separate tank.
  • Maintains a reserve of oil in the sump.
  • Requires no reserve of oil.
  1. The pressure pump of a dry sump lubrication system:
  • Has a greater capacity than the scavenge pump.
  • Has less capacity than the scavenge pump.
  • Is driven on a common shaft and has the same capacity as the scavenge pump.
  1. The pressure filter in a dry sump lubrication system is:
  • Located between the pressure pump and tank.
  • Located after the pressure pump.
  • Located between the scavenge pump and the tank.
  1. The by-pass valve of a dry sump lubrication system is:
  • Normally activated during low temperature engine starting.
  • Normally activated during high temperature engine stating.
  • Is a relief valve for excess oil pressure.
  1. Normally on most piston engines the lubrication oil of a dry sump system is cooled:
  • On leaving the pressure pump.
  • Before returning to the oil tank.
  • Before returning to the sump.
  1. The reserve of lubricating oil of a wet sump piston engine is stored in:
  • The sump.
  • A separate tank.
  • The pipe system.
  1. The oil tank of a dry sump lubrication system has a space above the oil to provide for:
  • Jack ram displacement.
  • Pressurisation
  • Expansion of the oil and frothing.
  1. The oil tank of a dry sump lubrication system is normally cooled by:
  • Water
  • Compressor oil.
  • Ram air.
  1. Excessive arcing across the contact breaker points of a magneto when the point are open is prevented by:
  • A diode being fitted.
  • A condense being fitted.
  • Insulation of the contacts.
  1. On a four stroke engine the ignition spark will occur:
  • Once each revolution of the engine.
  • Once every forth revolution of the engine.
  • Once every two revolutions of the engine.
  1. On engine start up, the generator warning light fails to extinguish, this will result in:
  • The engine stopping when the battery is totally discharged.
  • Failure of the initial excitation of the magneto.
  • The engine continuing to run normally.
  1. The distributor rotor on a four stroke engine rotates at:
  • The same speed as the engine.
  • Twice the speed of the engine.
  • Half the speed of the engine.
  1. With increase of engine speed, ignition timing:
  • Will advance.
  • Will retard.
  • Will remain constant.
  1. Fuel pumps:
  • Should not be run when the fuel system is dry.
  • Of all types are lubricated by the fuel that passes through them.
  • Are normally electrically operated.
  1. Booster pumps are:
  • Normally driven by the engine.
  • Electrically operated.
  • Normally used for priming the engine only.
  1. If the fuel pressure warning light comes on in flight the:
  • Booster pump must be isolated.
  • Main fuel pump must be isolated.
  • Booster pumps must be switched on.
  1. In the event of booster pump failure, the:
  • Fuel will continue to be drawn through the booster pump bypass by the engine driven pump.
  • Pump must be isolated and the remaining fuel in the tank transferred by the transfer pumps.
  • Fuel will be isolated in the tank.
  1. Fuel pump delivery is normally:
  • Supplied at a constant flow rate to the engine.
  • Supplied at a constant pressure, controlled by a pressure relief valve.
  • Supplied at a constant volume.
  1. In an air-cooled piston engine:
  • Fins are incorporated to increase the cylinder and head surface area.
  • Air is ducted through drillings in the cylinder head walls.
  • Air is used to cool the cooling oil.
  1. Air is directed over the cylinder wall fins by:
  • Cowl gills.
  • Baffles
  • Air deflection plates.
  1. Cooling air is normally provided by:
  • Airflow from a supercharger.
  • Airflow from a compressor bleed.
  • Ram air.
  1. In a liquid cooled engine cooling system:
  • Temperature is controlled by a thermostat.
  • Temperature is controlled by a master pump.
  • Fuel is used to cool the coolant.
  1. An alternative name sometimes given to the choke is the:
  • Butterfly
  • Venturi
  • Intake controller.
  1. To prevent fuel starvation due to sudden opening of the throttle:
  • The enrichment jet is fitted.
  • The pressure balance duct is fitted.
  • The accelerator pump is fitted.
Technical General Question Bank

Airbus 380

 

 

 

 

 

 

 

 

 

 

TECHNICAL GENERAL QUESTIONS (Answers)

 

1 A 48 B 95 B
2 B 49 A 96 C
3 B 50 B 97 B
4 A 51 A 98 A
5 C 52 B 99 C
6 A 53 C 100 C
7 A 54 B 101 C
8 C 55 A 102 C
9 A 56 B 103 A
10 C 57 C 104 B
11 A 58 C 105 B
12 C 59 B 106 C
13 C 60 C 107 B
14 C 61 A 108 B
15 B 62 C 109 A
16 A 63 B 110 C
17 C 64 B 111 C
18 C 65 A 112 A
19 A 66 B 113 B
20 B 67 C 114 A
21 B 68 A 115 A
22 A 69 A 116 B
23 A 70 C 117 A
24 A 71 B 118 B
25 C 72 C 119 A
26 A 73 C 120 C
27 C 74 A 121 B
28 B 75 B 122 C
29 B 76 B 123 A
30 C 77 C 124 A
31 A 78 A 125 C
32 B 79 C 126 A
33 A 80 A 127 C
34 B 81 A 128 C
35 A 82 B 129 B
36 B 83 A 130 B
37 B 84 C 131 C
38 C 85 B 132 C
39 B 86 B 133 A
40 A 87 C 134 A
41 C 88 A 135 A
42 B 89 B 136 C
43 C 90 C 137 A
44 C 91 B 138 C
45 B 92 A 139 C
46 C 93 A 140 C
47 C 94 C 141 B

 

142 B 190 C 238 A
143 C 191 C 239 C
144 B 192 A 240 C
145 A 193 C 241 B
146 C 194 B 242 B
147 B 195 B 243 B
148 B 196 A 244 B
149 A 197 C 245 C
150 C 198 A 246 C
151 A 199 A 247 C
152 B 200 C 248 C
153 C 201 C 249 C
154 B 202 C 250 A
155 B 203 C 251 A
156 A 204 B 252 C
157 A 205 A 253 A
158 C 206 C 254 C
159 A 207 A 255 B
160 C 208 B 256 B
161 A 209 A 257 A
162 A 210 A 258 C
163 B 211 B 259 B
164 C 212 B 260 C
165 B 213 A 261 A
166 C 214 B 262 B
167 B 215 B 263 B
168 B 216 B 264 B
169 C 217 A 265 C
170 C 218 B 266 B
171 C 219 B 267 B
172 A 220 A 268 B
173 B 221 C 269 B
174 C 222 A 270 B
175 B 223 B 271 C
176 A 224 C 272 B
177 C 225 C 273 C
178 C 226 C 274 A
179 C 227 A 275 A
180 B 228 A 276 C
181 B 229 A 277 C
182 A 230 A 278 A
183 A 231 C 279 A
184 B 232 C 280 C
185 A 233 C 281 A
186 C 234 B 282 B
187 B 235 A 283 A
188 A 236 C 284 B
189 A 237 C 285 C

 

286 B 334 A
287 C 335 A
288 A 336 B
289 B 337 C
290 B 338 C
291 C 339 B
292 B 340 B
293 A 341 C
294 C 342 C
295 B 343 A
296 B 344 A
297 B 345 C
298 C 346 A
299 B 347 C
300 C 348 C
301 B 349 B
302 B 350 C
303 A 351 A
304 B 352 A
305 B 353 A
306 B 354 B
307 C 355 C
308 A 356 C
309 A 357 A
310 C 358 A
311 B 359 C
312 B 360 A
313 B 361 C
314 A 362 A
315 B 363 B
316 C 364 A
317 A 365 B
318 A 366 C
319 C 367 B
320 B 368 B
321 A 369 C
322 A 370 A
323 C 371 C
324 C 372 B
325 B 373 A
326 C 374 C
327 A 375 A
328 A 376 B
329 B 377 A
330 A 378 A
331 B 379 B
332 B 380 A
333 A 381 C

 

382 C
383 B
384 C
385 C
386 C
387 A
388 A
389 B
390 C
391 A
392 B
393 A
394 A
395 C
396 A
397 B
398 C
Technical General Questions

Arunaksha Nandy

 

 

 

 

 

 

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